text:
EPFLx: EE585x Space Mission Design and Operations
English | mp4 | H264 1280x720 | AAC 2 ch | Sub: English | 3.06 GB
English | mp4 | H264 1280x720 | AAC 2 ch | Sub: English | 3.06 GB
Welcome to the course Space Mission Design and Operations!
Space exploration is truly fascinating. From the Sputnik mission to the assembly and exploitation of the International Space Station or the Apollo program, we are just beginning to uncover the many mysteries of our universe!
This course may help you decide if you really want to become an aerospace engineer or, why not, an astronaut.
This course builds on university-level mechanics to introduce and illustrate orbital dynamics as they are applied in the design of space missions. You will learn from the experiences of Claude Nicollier, one of the first ESA astronauts, specifically, his role in the maintenance of the Hubble Space Telescope with NASA.
The course will start with a brief history (and mainly human) of space exploration , an introduction to main space missions before reviewing the fundamental laws of newtonian mechanics and conservation laws. It will present some basic concepts on space environment, robotic and human spacecraft and will introduce operational aspects of such vehicles, including maneuvers and propulsion.
The list of concepts that will be explained during the course is also available here
Learners will gain knowledge of the challenges related to the use of the space environment as a scientific and commercial platform.
We hope that you will enjoy the course!
Concepts explained in this course:
C1 - Newton's laws of motion
First law: In the absence of a force, a body either is at rest or moves in a straight line with constant speed.
Second law: A body experiencing a force will be subject to an acceleration such that the force is equal to the product of the mass of the body and the acceleration.
Third law: Whenever a first body exerts a force on a second body, the second body exerts a force equal in magnitude and opposite in direction on the first body.
This concept is explained in the following video: 1.2.1.
C2 - Inertial Frame
The inertial frame is a frame with respect to which the laws of Newton are valid.
The direction of the axes of an inertial frame can be imagined as being fixed with respect to distant stars.
The center of the inertial frame, which is an orthogonal coordinate system, will depend on the application.
This concept is explained in the following video: 1.2.1.
C3 - Newton's law of gravitation
Newton's law of gravitation states that any two bodies in the universe attract each other with a force that is directly proportional to the product of their masses and inversely proportional to the square of the distance between them.
This concept is explained in the following video: 1.2.2.
C4 - Laws of motion of a solid body and in rotation
This concept is based on the Newton's second law of motion applied for a rotation: the torque is equal to the time derivative of the angular momentum.
This concept is explained in the following video: 1.2.2.
C5 - Conservation Laws
Conservation of momentum in an isolated system (absence of forces).
Conservation of angular momentum in an isolated system (absence of torques).
Conservation of mechanical energy, potential and kinetic, in an isolated system, in a conservative force field (for instance a gravitational force field in the absence of dissipative forces).
This concept is explained in the following video: 1.2.3.
C6 - Structure and composition oF the Earth's atmosphere
Chemical composition: 78 % of nitrogen, 21 % of oxygen, 1 % of argon, < 0.1 % others.
Layers: Troposphere, stratosphere, mesosphere, thermosphere. Tropopause: limit of the troposphere, 9 to 17 km altitude, depending on the latitude. Stratopause: limit of stratosphere, around 50 km altitude.
The limit of the atmosphere and the beginning of space is considered to be at 100 km altitude.
This concept is explained in the following video: 1.3.1.
C7 - Microgravity
Microgravity is the term used to characterize the very low acceleration level encountered inside a spacecraft in LEO (typically
g at 300 km altitude).
This concept is explained in the following video: 1.3.1.
C8 - Transparency of the atmosphere
The atmosphere is opaque to electromagnetic radiation except in the visible part of the spectrum and in the radio part between about 3 cm to 10 m wavelength. It has limited transparency in the infrared, between 1 and 10 microns wavelength.
This concept is explained in the following video: 1.3.2.
C9 - Light Effects
Airglow: emission of light by the atmosphere due to the photoionization of oxygen atoms and de-excitation which produces a luminescence, mainly due to the oxygen, somewhat also to nitrogen and the radical OH.
This concept is explained in the following video: 1.3.2.
C10 - Magnetic Field
Close to the Earth's surface, the geomagnetic field is essentially a bipolar field slightly offset from the center of the Earth. The expression of the amplitude of the magnetic field is a function of the distance to the center of the Earth and the magnetic latitude.
Radiation or Van Allen belts: High energy protons and electrons trapped in two regions of the magnetosphere, Protons and electrons in the inner RB, electrons only in the outer RB.
The Earth's magnetic field is significantly distorted away from the surface of Earth toward the Sun (5, up to 10 Earth radii) and in the anti-Sun direction due to solar wind, made of charged particles flowing in all directions from the Sun.
This concept is explained in the following videos: 1.4.1.
C11 - Northern/Southern lights
Northern and Southern Lights are produced from the excitation of nitrogen and oxygen atoms, by the electrons flowing from the solar wind.
This concept is explained in the following videos: 1.4.1.
C12 -Solar cycle - influence on the Earth's atmosphere
A solar cycle is a period of approximately 11 years, based on the sunspot number, which is changing over time with an increase of sunspot during 5 years until the solar maxima followed by 6 years of decrease until the solar minima.
A better determination of the phase of the solar cycle is the solar radio flux. The solar radiation flux at a wavelength of 10.7 cm varies along the solar cycle and is often used as a measure of the level of the solar activity along the cycle.
The Sun has also a significant effect on the thickness of the atmosphere; respectively on the density of the Earth's atmosphere at a given altitude.
This concept is explained in the following videos: 1.4.2.
C13 - Sun activity
The Sun is an active star. Its surface is granular with prominences: flares and coronal mass ejections.
A solar prominence is a large, bright feature extending outward from the Sun's surface, often in a loop shape. While the corona consists of extremely hot ionised gases, which do not emit much visible light, prominences contain much cooler plasma, similar in composition to that of the chromosphere.
This concept is explained in the following video: 1.4.3.
C14 - Particle flux
Following Coronal Mass Ejections or CMEs, there is an enormous amount of charged particles that flow through the Solar System all the way to the Earth and beyond.
This concept is explained in the following video: 1.5.1.
C15 - South Atlantic Anomaly
The South Atlantic Anomaly or SAA is an area where the Earth's inner Van Allen radiation belt comes closest to the Earth's surface.
This concept is explained in the following video: 1.5.1.
C16 - Solar radiation, outside the Earth's atmosphere and on the surface
Cosmic particles of galactic origin: high-energy charged particles, usually protons, electrons and fully ionized nuclei of light elements.
Radiation are expressed in RAD - Radiation Absorbed Dose - which is the amount of energy absorbed or REM (Roentgen Equivalent Man); or Sievert (Sv = 100 REM).
Astronauts have to stay way below 100 REM, or one Sievert, which is the vomiting effective threshold. Medical problems start over 100 REM and become significant above 500 REM.
This concept is explained in the following video: 1.5.1.
C17 - Solar irradiance
The total irradiance of the Sun is the total energy that it sends every unit of time or every second on a square meter surface outside of the Earth's atmosphere, in the form of electromagnetic radiation.
The solar constant is a conventional measure of the mean total solar irradiance at a distance of one Astronomical Unit.
Solar irradiance in the Solar system decreases with the distance to the Sun.
This concept is explained in the following video: 1.5.2.
C18 - Albedo
Albedo is the diffuse reflectivity or reflecting power of a surface measured from zero for no reflecting power of a perfectly black surface, to 1 for perfect reflection.
This concept is explained in the following video: 1.5.3.
C19 - Earth's energy budget
The solar constant is approximately 1368 watts per square meter. This value has been slowly decreasing over the past few years and in April 2015, the value was 1361 watts per square meter.
About 30% of this radiation is reflected back in space by the atmosphere (6%), clouds (20%) and the Earth's surface (4%). The rest is absorbed by land and oceans and re-radiated out in space in the form of infrared radiation.
From the Earth, there are two sources of radiation: the albedo, which is the solar spectrum reflected from the high layers of the Earth atmosphere, and the infrared radiation from the Earth itself.
This concept is explained in the following video: 1.5.3.
C20 - Radiation balance for a spacecraft on orbit around the Earth
If we consider a spacecraft in the vicinity of the Earth, the dominant source of radiation it receives comes from the Sun. 30% of the radiation of the Sun impacting the Earth is coming back towards space (Albedo). The other source of radiation is the Earth infrared radiation, which is a rather dim source.
The total absorbed radiation by the spacecraft is equal to the emitted radiation in a balanced situation.
The Stefan-Boltzmann law gives the value of the emitted radiation per unit surface in the case of a black body.
The spacecraft is not a black body and its emitted radiation depends of its total surface and its IR emissivity.
The equation expressing the radiation balance can be used to determine the average temperature of a spacecraft, knowing its emissivity and absorptivity.
This concept is explained in the following video: 1.5.4.
C21 - Orbit decay - ballistic coefficient
The orbit decay is the reduction in the altitude of a satellite's orbit. The major cause is the drag of the Earth's atmosphere, which is more important during the solar maxima at a given altitude. Positive Feedback effect: The more the orbit decays, the lower the altitude, the faster the decay.
The drag equation expresses the force experienced by an object moving through a fluid or a gas at a velocity V.
The ballistic coefficient is the measure of the resistance to orbit decay caused by atmospheric drag and is inversely proportional to the drag coefficient and the frontal surface of the spacecraft.
This concept is explained in the following video: 1.6.1.
C22 - Space debris
Space debris is an object in space that is no longer functional and useful. There is a huge amount of space debris in LEO and GEO causing high risk of collision with active spacecraft.
Several rules have been put in place to regulate satellites allocation in certain areas and the end of missions: when a communication satellite in the geostationary orbit are is longer functional, it shall be moved to a graveyard orbit. Measures are in place to limit satellites lifetime in Low Earth Orbit to 25 years.
Two break-up: Iridium-Cosmos in 2009 and Fengyun-1C in 2007 caused a very high density of space debris around 800 km altitude.
This concept is explained in the following video: 1.6.2.
C23 - asteroid collision threat
Several asteroids collisions happened on Earth but also in other planets in the Solar System.
A major event was the Cretaceous-Paleogene extinction, 65 million years ago, large scale extinction of most of life on Earth, including dinosaurs from the impact of large meteorite Earth, probably in the region of the Yucatan peninsula, Mexico.
Different techniques to improve early detection of dangerous asteroids, and to modify their trajectories to avoid collision with earth are currently being looked at.
This concept is explained in the following video: 1.6.3.
C24 - Gravitational Profile of the Earth
Inside the Earth, considered homogeneous, the gravitational acceleration varies linearly from zero at the center to 9.81 meters per second square at the surface. From the surface on, it varies as 1/r2, r being the distance to the center of the Earth.
This concept is explained in the following video: 2.2.1.
C25 - Gravitational well, Work and Depth
A gravitational well is a conceptual model of the gravitational field surrounding a body in space.
The work necessary to lift a unit mass from the surface of a spherical object such as Earth, to infinity, is equal to the work necessary to lift the same mass from the surface of the sphere over a distance equal to the object's radius, with a constant force equal to the force at the surface.
The object's radius is the depth of the object's gravitational well. The profile of the gravitational well is in 1/r
This concept is explained in the following videos: 2.2.1. and 2.2.2.
C26 - Normalized gravitational well
The depth of gravitational well of any spherical objects in the solar system or elsewhere, is always normalized to the gravitational acceleration of the Earth for comparison purposes.
This concept is explained in the following video: 2.2.2.
C27 - Escape Velocity
Escape velocity from the Earth's surface is the velocity at which a spacecraft has to leave this surface in order to go to infinity with a zero velocity. The escape velocity is independent of the direction of the initial impulse (as long as escape really takes place).
For Earth, the escape velocity from the surface is equal to 11.2 km/second. For higher altitudes, it varies as
This concept is explained in the following video: 2.2.3.
C28 - Circular Velocity
The circular velocity is the velocity of a spacecraft on a circular orbit around an object such as the Earth. For a spacecraft in orbit around the Earth, its circular velocity is equal to
This concept is explained in the following video: 2.2.3
C29 - GRavitational well in term of transfer velocity
The transfer velocity, for a given planet, is the velocity that has to be added to the planet's circular velocity for a transfer to infinity from this location in the Sun's gravitational well, i.e. as if to leave the solar system.
This concept is explained in the following video: 2.2.3.
C30 - Two-Body Problem
The two-body problem is to determine the motion of the two bodies that interact only with each other.
This concept is explained in the following video: 2.3.1.
C31 - Kepler's Laws
First law: The orbit of every planet is an ellipse with the Sun at one of the two foci.
Second law: A line is joining a planet and the Sun sweeps out equal areas during equal intervals of time.
Third law: The square of the orbital period of a planet is proportional to the cube of the semi-major axis of the orbit.
This concept is explained in the following video: 2.3.1.
C32 - Generalisation of the first Kepler's Law
The first Kepler's law can be generalized in the case of a two-body problem: the orbit of the small body versus the large body is, generally speaking, a conic, i.e. an ellipse, a circle, a parabola or hyperbola.
This concept is explained in the following video: 2.3.1.
C33 - Important elliptical parameters: Periapsis, apoapsis, eccentricity, true anomaly
Periapsis and apoapsis are general terms. Periastris and apoastris are sometimes used for a star as central body. If the Earth is the central body, we talk about perigee and apogee; if it is the Sun, perihelion and aphelion.
If the eccentricity is equal to 0 the orbit is circular, if the distance of the focus from the center of the orbit increases, the eccentricity becomes closer to 1. If the eccentricity is equal to 1, the orbit is parabolic.
The True anomaly is the angle between the direction of the periapsis from the central body to the radius vector to the spacecraft or the planet.
This concept is explained in the following video: 2.4.1.
C34 - Mechanical Energy of the orbital motion
The total mechanical energy of a body in a gravitational field is the sum of its kinetic energy and its potential energy.
In the limit case of a very elongated ellipse, the total mechanical energy of the orbital motion is close to zero.
In the limit case of a parabolic orbit, the total mechanical energy is equal to zero.
If V < escape velocity, which is the case for a closed orbit, elliptical or circular, the total mechanical energy is negative.
If the orbit is hyperbolic (velocity > 0 at infinity), the total mechanical energy is positive.
This concept is explained in the following video: 2.4.1.
C35 - Orbital Velocity
The orbital velocity for an elliptical orbit is
The orbital velocity for a circular orbit is
This concept is explained in the following video: 2.4.1.
C36 - Flight Path Angle
The flight path angle is the angle between the direction of the velocity vector and the perpendicular to the radius vector at the point where the spacecraft is.
The variation of the flight path angle on an elliptical orbit as a function of position:
This concept is explained in the following video: 2.4.1.
C37 - Circular and elliptical orbits – fundamental relationshis
Several formulas express fundamental relationships between elliptical parameters.
Some of the most used formulas are the expression of the mean motion and the Kepler's equation.
The mean motion is the average angular speed required for a body to complete one orbit, it is expressed in radians per second.
E, the eccentric anomaly, is an angular parameter that defines the position of a body that is moving along an elliptic Kepler orbit.
The Kepler's equation is a transcendental equation that cannot be solved for E but expresses the time evolution of E, the eccentric anomaly.
This concept is explained in the following video: 2.4.2.
C38 - Reference Frames
The geographic coordinate system is used for describing positions on the surface of planet Earth.
The geocentric-inertial coordinate system is an orthogonal reference frame centered at the center of the Earth. The plane of reference is the plane of the Equator, where the direction of X is the direction of the vernal equinox for a given year, nowadays chosen to be the year 2000. Y is also in the equator, and Z in the rotation axis of the Earth pointing to the North
The heliocentric-inertial coordinate system has the same directions of axes as the geocentric-inertial coordinate system, but it is centered at the center of the Sun.
This concept is explained in the following video: 2.5.1.
C39 - AXial Precession
Axial precession is the displacement of the rotational axis of an astronomical body.
The Earth is not a perfect sphere, but has an equatorial bulge, and the gravitational force from the Sun and the Moon, on a non-spherical body, causes the precession. The Earth goes through one such complete precessional cycle in about 26000 years.
This concept is explained in the following video: 2.5.1.
C40 - Classical orbital parameters and spacecraft state vector
There are 6 orbital parameters used to describe an orbit: the eccentricity, the semi-major axis, the inclination, the longitude or Right Ascension of the Ascending Node (RAAN, in the plane of reference), the argument of periapsis (in the orbital plane), the time of periapsis transit.
With the addition of the time t, we can have a determination of the exact position of the celestial body or satellite.
The spacecraft's state vector is functionally equivalent to the six orbital parameters plus the time t.
This concept is explained in the following video: 2.5.2.
C41 - Mean solar day and sidereal day
The sidereal day, is the time it takes for the Earth to make one full rotation with respect to the stars.
The mean solar day is the time it takes for the Earth to make one full rotation with respect to the Sun.
The duration of the mean solar day is 24 hours, but the duration of the sidereal day, is 23h 56' 04''.
This concept is explained in the following video: 2.5.2.
C42 - Calendars
Julian day is used in the Julian date (JD) system of time measurement for scientific use by the astronomy community, presenting the interval of time in days and fractions of a day since January 1st, 4713 BC Greenwich noon. Julian date is recomended for astronomical use by the International Astronomical Union.
This concept is explained in the following video: 2.5.2.
C43 -Maneuvers in Orbit
A maneuver on orbit is the modification of the orbit of a satellite by adding a velocity (ΔV) on the initial orbit.
This concept is explained in the following video: 3.2.1.
C44 - Hohmann Transfer
The Hohmann transfer is a transfer between one circular orbit to another circular orbit around the same central body.
This concept is explained in the following video: 3.2.1.
C45 - Hohmann transfer for small increments in speed or distance to the central body
This Hohmann transfer is often used for rendezvous at Low Earth Orbit.
For LEO:
This concept is explained in the following video: 3.2.2.
C46 - Orbital change plane
The orbital plane change or orbital inclination change is an orbital maneuver aimed at changing the inclination of an orbiting body's orbit.
This concept is explained in the following video: 3.2.3.
C47 - Geosynchronous and Geostationary orbits
If the rotation period of a satellite is equal to a sidereal day, the satellite will rotate around the Earth at the same pace as the Earth rotates around itself: this is called geosynchronous orbit.
A Geostationary orbit is a geosynchronous circular orbit on the equatorial plane (e = 0 and i = 0).
This concept is explained in the following video: 3.3.1.
C48 - strategy for reaching such an orbit, and changing spacecraft longitude
To reach the geostationary orbit, a Hohmann transfer is necessary followed by a plane change of the orbit from the initial plane to the Equatorial condition. The apogee shall be at the geostationary altitude, 36,000 km above the Earth's surface.
There are two options to reach the geostationary orbit:
a plane change and then an acceleration to the circular condition at that orbit.
a combined maneuver of the plane change and acceleration to the circular condition
This concept is explained in the following video: 3.3.1.
C49 -Geometry of a launch from the Earth's surface
A satellite has a certain inclination versus the Equator which is equal to the latitude of the launch site. Typically, seven degrees for a launch from French Guiana, in Kourou, the European launch site, 28.5 degrees if the launch takes place from Kennedy Space Center, Florida.
This concept is explained in the following video: 3.3.1.
C50 - Nodal regression (or progression) of an orbit around the Earth
One consequence of the Earth's equatorial bulge is the nodal regression, for orbits with an inclination of more than 0 and less than 90, the line of nodes is moving to the west.
For inclinations larger than 90 degrees, the line of node will be drifting to the east: this is the nodal progression.
This concept is explained in the following video: 3.3.2.
C51 - Sun synchronous orbits
Sun-synchronous orbit is an orbit that keeps the same orientation versus the Sun as the Earth is going around the Sun in a full year.
This concept is explained in the following video: 3.3.2.
C52 -Restricted three-body problem
The restricted three-body problem is applied to two relatively large bodies and a smaller body, the spacecraft. The two main bodies are on circular orbits around the center of mass of the system. The mass of the third body (satellite) is very small compared to the mass of the two main bodies. The third body is in an orbit contained in the plane of the orbits of the two main bodies.
This concept is explained in the following video: 3.3.3.
C53 -Lagrange points
The Lagrange points are five positions where the small body keeps the same position with respect to the other two bodies which are revolving around each other.
This concept is explained in the following video: 3.3.3.
C54 -Catch up rate for nearby orbits
In general, for circular and close elliptical orbits:
For circular orbits:
This concept is explained in the following video: 3.4.1.
C55 - Maneuvers and Burns
As orbital altitude increases, orbital period increases and orbital velocity decreases. Velocity is greatest at perigee and least at apogee.
Posigrade burns increase altitude 180° from the burn point. Retrograde burns decrease altitude 180° from the burn point. Radial burns shift the semi-major axis without significantly altering other orbital parameters.
Plane change must be performed at junction of two orbits: nodal crossing.
This concept is explained in the following video: 3.4.2.
C56 -Rendezvous in Earth's Orbit - General Strategy
The rendezvous is the action of bringing together two spacecraft. Most of the time there is a spacecraft on the ground, called chaser, which is active and another spacecraft on orbit, the target, passive.
In the initial conditions, the orbit inclination is larger than the latitude of the launch site for the chaser.
The final conditions are chaser and target at the same location in space with the same vectorial velocity.
Example of the the Space Shuttle and HST, Space Shuttle and ISS, HTV and ISS, ATV and ISS.
This concept is explained in the following videos: 3.4.3. and 3.5.1.
C57 -Phase Angle and Phasing Rate
Phase angle is the angle between the chaser and target, measured from the center of the Earth. Phasing rate or catch-up rate is the rate at which phase angle changes. Phasing rate is a function of differential altitude.
This concept is explained in the following videos: 3.4.4.
C58 -Rendezvous profile
The profile of the orbit of the chaser versus a target is represented in a one-dimensional plane which is a plane of the orbit of the target, at least a plane of the orbit of the target at the end of the rendezvous
This concept is explained in the following videos: 3.4.4.
C59 - RENDEZVOUS Control
Rendezvous sensors are used to update the relative state vector of a chaser versus target using sensor data, to control the rotation and translation and to perform manually the end portion of the rendezvous.
3 sensors on the Space Shuttle : Star Tracker (S TRK), Rendezvous Radar (RR) and Crew Optical Alignment Sight (COAS).
Rotation hand controller (RHC): 3 degrees of freedom rotation: pitch, roll and yaw.
Translation hand controller (THC): translation on X or Z axis.
This concept is explained in the following videos: 3.4.5.
C60 - Relative motion of the chaser vs. the target in a rendezvous
A posigrade burn of the Shuttle with respect to the Station implies a higher and slower orbit with a longer period.
A retrograde burn brings the Shuttle on an orbit with lower altitude behind the Station.
A radial burn is a burn perpendicular to the velocity vector. The amplitude of the velocity vector, the energy and the period will be unchanged.
This concept is explained in the following videos: 3.4.6.
C61 -Case of the ATV
The ATV brings resupply equipment, fuel, water, payloads and food for the crew. It can also reboost the ISS, firing thrusters with the proper attitude, to the nominal altitude.
The ATV performs automatic rendezvous and automatic re-entry after de-docking. Its re-entry is destructive.
This concept is explained in the following video: 3.5.1.
C62 - Astronomical unit
Astronomical unit is the average distance between the Sun and the Earth
1 AU = 149.5978707 x 106 km
This concept is explained in the following video: 4.2.1.
C63 -Interplanetary Trajectories
In order to plan for and execute a mission to another planet, we consider the Sun, the planet of departure (the Earth), the planet of destination and the spacecraft.
When the spacecraft leaves the sphere of influence of the Earth, it occurs to be on a heliocentric elliptical trajectory, from the departure orbit, which is the orbit of the Earth, until the destination orbit which is a semi-circular orbit, either inside the orbit of the Earth or outside for Mars, Jupiter or Saturn, etc.
This concept is explained in the following video: 4.2.1.
C64 -Patched conics approximation
The spacecraft is on orbit around the Earth, on a parking orbit, and is accelerated to leave the area of the Earth, the sphere of influence.
As long as the spacecraft is within this sphere of influence, its motion with respect to the Earth is a two-body problem with the Earth as a central body and the spacecraft having a very small mass compared to the mass of the Earth.
At the end its heliocentric elliptic trajectory, in the vicinity of the destination planet, the spacecraft enters the sphere of influence of the destination planet (two-body problem).
This concept is explained in the following video: 4.2.1.
Sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian.
The radius of the sphere of influence RS has been determined by Laplace as:
R is the average distance between Sun and the planet.
This concept is explained in the following video: 4.2.1.
C66 -Symbol Convention for Position and Velocity
P for planet, S for Spacecraft, Capital letters for heliocentric movements, small letters for planetocentric movements.
The heliocentric movement of the spacecraft is equal to the planetocentric motion of the spacecraft added to the heliocentric movement of the planet when the spacecraft leaves the sphere of influence.
If the spacecraft enters a sphere of influence, the planetocentric movement of the planet is equal to the difference between the heliocentric movement of the spacecraft and the planets.
This concept is explained in the following video: 4.2.2.
C67 -Departure from a planet
A journey to a destination in the solar system always starts with a parking orbit. Then the orbital velocity in increased to reach the departure velocity.
The departure velocity amplitude influences the orbit of the spacecraft: if the departure velocity is smaller than the escape velocity, the spacecraft will be on an elliptical orbit, if it is equal, the spacecraft will be on a parabola, if it is higher, the spacecraft will be on a hyperbolic orbit.
This concept is explained in the following video: 4.2.2. and 4.2.5.
C68 -Hyperbolic excess velocity & reaching the Sphere of Influence
On a hyperbolic orbit, at a large distance from the Earth, the spacecraft comes to a certain constant velocity
This concept is explained in the following videos: 4.2.2. and 4.2.3.
C69 -Vis-viva equation - elliptical and Hyperbolic velocities
Ellipse :
This concept is explained in the following video: 4.2.3. and 4.2.5.
C70 -Arrival at a planet
The spacecraft is on a heliocentric trajectory, elliptical orbit around the Sun, until it is close enough to the destination planet. Then only the motion of the spacecraft with respect to the destination planet is considered as hyperbolic trajectory inside the sphere of influence of the destination planet.
Flight controllers in the control room control the motion of the spacecraft and select the value of d∞, the impact parameter, and θ in order to accomplish either a flyby or landing.
ΔVi indicates how much the spacecraft needs to brake in km per second in order to insert itself in an elliptical orbit around the destination planet.
This concept is explained in the following videos: 4.2.4. and 4.2.5.
C71 -Aerobraking, Aerocapture, Aeroentry
The idea is to generate changes of the velocity.
It could be done by using the atmosphere of a planet (Mars, Venus) or the satellite of a planet like Titan, which will minimize the use of propellant or by thrusters.
Aerocapture : Transfers the spacecraft from a hyperbolic approach trajectory to an elliptical orbit around the target planet. Further loss of energy will occur at every subsequent crossing of the periapsis.
Aerobraking : Transfers the spacecraft from an initial elliptical orbit to a less energetic (i.e. lower apoapsis) elliptical orbit. Involves small ΔV.
Aeroentry : Transfers the spacecraft from either a hyperbolic, parabolic or elliptical approach orbit to the planet surface
This concept is explained in the following video: 4.3.1.
C72 -Gravity assist or slingshot maneuver
When a spacecraft on an orbit around the Sun approaches another planet and comes in close proximity to it, the gravity of that planet takes over, pulling the spacecraft in and altering its speed.
The amount by which the spacecraft speeds up or slows down is determined by the geometry of the approach, passing behind or in front of the planet.
When the spacecraft leaves the sphere of influence of the planet, it again follows an orbit around the Sun, but a different one from before, either on course for the original target or heading for another fly-by.
This concept is explained in the following video: 4.3.2
C73 -Tsiolkovsky Equation
ΔV = change of velocity; ve = exhaust velocity of the gas in the propulsion system; mi, mf = initial and final mass
Valid in free space – Gravitational field-induced and drag-induced ΔVs will be added to the propulsion-induced ΔVs.
This concept is explained in the following video: 4.4.1.
C74 -Specific Impulse
Isp, the specific impulse, is a measure of the propulsion system efficiency, it is its thrust (kg-force) divided by the mass flow of propellants (fuel and oxidizer, kg/s).
This concept is explained in the following video: 4.4.1.
C75 -Chemical propulsion
Chemical propulsion is used for all of the stages until orbit insertion. Two main types of chemical propulsion systems: monopropellant or bipropellant.
The fuel and the oxidizers are being fed in the combustion chamber in liquid form or the solid propellant contains the oxidizer and the fuel in solid form
An igniter system is needed if there is no hypergolic propellant and oxidizer. A hot gas is produced under high pressure, expanded in a nozzle in order to increase the velocity of the exhaust.
This concept is explained in the following video: 4.4.1. and 4.4.2
C76 -Nuclear Propulsion
Heating of the propellant with a nuclear reactor with the control of the flux of neutrons with a reflector.
The velocity that can be reached is higher than with a chemical rocket.
This concept is explained in the following video: 4.4.3.
C77 -Electric or ion Propulsion
Ionization of propellants and acceleration with the electric field.
Higher velocities than with a liquid-fueled or solid propellant rocket engine can be reached.
There is high efficiency or very high ejection velocity, but relatively low thrust, of the order of a fraction of a newton.
It can be used for propulsion in space, but not for leaving the Earth's surface and t bring a spacecraft to orbital conditions.
This concept is explained in the following video: 4.4.3
C78 -Strategies for ascent into orbit, and reentry in the Earth's atmosphere
The idea is to shape the ascent trajectory to minimize gravity and drag losses.
Orbit insertion consists in bringing a spacecraft to a desired stable orbit after a launch from the Earth surface.
Direct insertion into orbit: initial launch at the vertical, powered ascent, using the propulsion system of either one, two or three stages until orbit insertion.
For Earth launch, the ascent trajectory shall be lofted because of the atmosphere. On a planet with thinner atmosphere like Mars, loft is less necessary.
Braking maneuver such as deorbit burn are realized for the re-entry of the Space Shuttle.
● Entry requirements and constraints applicable for any re-entry vehicle, which does not have a destructive re-entry: Deceleration: Human limit is about 12g's for short duration.
● Heating: Must withstand both total heat load and peak heating rate.
● Accuracy of landing or impact: Function primarily of trajectory and vehicle design.
● Size of the entry corridor: The size of the corridor depends on three constraints (deceleration, heating and accuracy).
This concept is explained in the following video: 4.5.1.
C79 -Attitude Measurement and control system (AMCS)
Man-made spacecraft or natural objects like asteroid or comet nucleus, are very slowly rotating subject to possibly gravity gradient forces, if located in the vicinity of a large body, to sun radiation, solar wind, atmospheric effect of a near planet or magnetic effect.
AMCS consists in measuring and maintaining, or changing in a controlled manner, the orientation of a coordinate system attached to the spacecraft with respect to an inertial or any other reference system. Attitude within a specified deadband.
This concept is explained in the following video: 5.2.1.
C80 - Euler sequence
Rotations around axis X, Y, and Z are non commutative. Normally Euler sequence: Yaw Pitch Roll. For the Space Shuttle, ISS, including associated robotic system: Pitch Yaw Roll.
This concept is explained in the following video: 5.2.1.
C81 -types of attitude control
Gravity gradient, Magnetic torquers, Spinning spacecraft, Momentum devices: reaction wheels or Control Momentum Gyros, Thrusters. Passive and active methods.
This concept is explained in the following video: 5.2.2.
C82 -Gravity Gradient
An elongated object will take an orientation in orbit around the Earth such that its long axis will be along the local vertical, with some swinging motion, or attitude changes around the local vertical gravity gradients.
This concept is explained in the following video: 5.2.2.
C83 -Magnetic torquers
A magnetic torquer is an elongated bar with a wire coil wrapped around it and an external protection.
A current through the coil will produce a magnetic field which will try to align itself along the geomagnetic field with a torque expressed by:
Torques on the spacecraft induced by variations of the wheel's rotational speed. Requires thrusters or magnetic torque generators to get out of wheels saturation.
Magnetic torquers are used if the orientation to space track doesn't need to be extremely precise and as a system to desaturate momentum gyros (HST example).
This concept is explained in the following video: 5.2.2. and 5.2.3.
C84 -Stabilization by rotation
The inertial orientation is maintained by spinning the spacecraft with the sun vector perpendicular to the axis of rotation.
Advantages: cheap, propellant flow from tanks provided by inertial forces
Disadvantages: low accuracy in controlled attitude (0.3-1°), translations only possible along rotation axis, pointing of antennas and other devices impossible except in the direction of spin
This concept is explained in the following video: 5.2.2. and 5.2.3.
C85 -Three-axis stabilization with thrusters
Advantages: Any orientation possible, high pointing accuracy (better than 0.001°), efficient use of solar arrays.
Disadvantages: complexity and price, complex redundancy architecture, need to insure propellant supply from the tanks by other means than using the inertial forces.
This concept is explained in the following videos: 5.2.2., 5.2.3. and 5.2.4.
C86 - Reaction wheel, Control Momentum Gyros or CMGs
Constant angular velocity. Mounted on gimbals. A torque along the input axis produces a corresponding torque reaction along the output axis.
If the angular rotation speed of the reaction wheel is increased, the angular rotation speed of the spacecraft will increase in the opposite direction.
This concept is explained in the following videos: 5.2.3. and 5.2.5.
C87 - Electrical power generation and distribution, basic principles
Fuel cells, solar arrays, primary batteries, nuclear reactors, radioisotopic thermal generators.
Fuel cells convert chemical energy from reactants into electricity through a chemical reaction of positively charged hydrogen ions with oxygen (or other oxidizing agent). They require continuous source of reactants to sustain the chemical reaction. The by-products of this reaction are water and heat.
Rechargeable batteries: NiCd (Nickel Cadmium) currently replaced by Li-Ion (Lithium Ion) and NiH2 (Nickel Hydrogen)
A Radioisotope Thermoelectric Generator (RTG), uses the fact that radioactive materials (such as plutonium 238) generate heat as they decay into non-radioactive materials. The heat is converted into electricity by an array of thermocouples which then power the spacecraft.
This concept is explained in the following video: 5.3.1.
C88 -Solar Cells
An electrical energy storage system must be provided and must be sized as a function of the eclipse duration and electrical power requirements.
Upper layer: N doped semiconductor, Lower layer: P doped semiconductor, PN junction which, when irradiated by a photon flow, will displace electrons form N to P, holes from P to N from which voltage and current are resulting.
Cell types: Silicium or Gallium arsenide.
This concept is explained in the following video: 5.3.1.
C89 - Tethered satellite – concept and utilization (mechanical and electrodynamical)
Applications: Electrical power generation, Orbit transfers, Ionospheric studies, Variable gravity research, Space debris removal, Provision of artificial gravity for long journeys in the Solar System, Earth-Moon payload transfer, Space Elevator.
This concept is explained in the following videos: 5.3.2., 5.3.3. and 5.3.4.
C90 - Reliability and redundancy of space systems
Reliability R(t) is the probability that the system will not fail in the interval (0, t). MTTF = Mean Time To Failure, average time duration until first failure. MTBF = Mean Time Between Failures, average time duration between two consecutive failures.
This concept is explained in the following video: 5.4.1.
C91 -Space Shuttle conception and first tests
The conception of the Space Shuttle started in the 70s. The idea was to have a reusable spacecraft for access to low Earth orbit to launch commercial payloads, to use it for the needs of the Department of Defense and to do space exploration and utilization.
A fully reusable spacecraft would have induced quite high development cost for a relatively low operation cost, because everything was going to be reusable.
Due to budget limitations, NASA and the US government had to cut it off at the lower point of the horizontal axis, meaning less development costs but a higher cost per flights as the final configuration chosen was only partially reusable.
Approach and Landing Tests (ALT) in 1977, with different tail cone configuration and the Space Shuttle Enterprise.
This concept is explained in the following video: 6.2.1.
C92 -Space Shuttle final configuration
External tank, 2 solid rocket boosters, Orbiter with 3 main engines, protection tiles, large payload bay, cabin for up to 7 crewmembers. Protection tiles are able to resist high temperature during the re-entry. The heating was mainly in the nose of the Orbiter, the leading edge of the wings and the bottom of the Orbiter (black tiles). The white areas were also covered with thermal protection tiles, but not with the same capabilities that the black ones.
This concept is explained in the following video: 6.2.1.
C93 -Space Shuttle program
OFTs (Orbital Flight Tests): Tests of the system, STS-1, the first flight, in April, 1981, until STS-4 in 1982. Operational phase: STS-5, in 1982, through STS-135, in 2011.
John Young and Robert Crippen the two crewmembers of STS-1.
Major achievements: Hubble Program, Assembly of the ISS, 355 astronauts to go in space, 135 flights total.
Two major accidents in this program: Challenger in 1986, and Columbia in 2003
6 orbiters were used: Enterprise (Test vehicle), Columbia (28 missions), Challenger (10 missions), Atlantis (39 missions), Discovery (33 missions), Endeavour (25 missions).
This concept is explained in the following videos: 6.2.2. and 6.3.1.
C94 -Space Shuttle Habitable compartments
Forward portion: the flight deck, the mid-deck and the airlock.
Seats for ascent to orbit and re-entry: four in the flight deck, the commander, the pilot and two mission specialists and up to three in the mid deck.
Instrument panels, windows, lockers with personal items, tools and food, food preparation station to hydrate and heat the food, waste collection system.
The airlock was inhabited when there was space walking in order to go out and come back in the Space Shuttle.
This concept is explained in the following video: 6.2.3.
C95 -Space Shuttle from countdown to orbit
Access to the cabin with an elevator and a bridge giving access to the White Room, where the crew with the help of technicians was making the last preparations before getting into the Space Shuttle orbiter cabin.
Orange Launch and Entry Suit and helmet, there was a possibility of pressurizing the suit in case there was any problem with the cabin pressure during the ascent. There was also a possibility to technically explode the side hatch for rapid escape in case there was a launch abort and the crew had to escape rapidly before liftoff of the orbiter.
Solid Rocket Booster ignition at T-zero Initial vertical lift off then shortly after roll maneuver in order to come into the proper plane of the planned orbit which could be between 28.5 degrees (latitude of Kennedy Space Center) to 52 degrees (inclination of the International Space Station) Ascent until Solid Rocket Booster separation few seconds later, which fall down into the Pacific ocean and recovered for later flights. Then the ascent to orbit continues for 6.5 extra minutes, for 8.5 total minutes. And at the end of this ascent phase, there is an acceleration of the velocity of 20,000 km/hour or about Mach 76. Then, main engine cutoff and the Shuttle goes from 3 G to 0 G within a very short time - about a second and a half.
This concept is explained in the following video: 6.2.4.
C96 -Space Shuttle: From orbit to post landing
During very hot phase of the re-entry between about 80 km altitude and 50 km, there was about 10 minutes of generation of heat because of the friction of the orbiter coming in the atmosphere
The orbiter had a high angle of attack: about 40 degrees angle of attack to brake in the higher layers of the atmosphere and to enter the lower layers of the atmosphere at a lower speed to control the heating and the trajectory of the spaceship.
After touchdown there was a deployment of the brake chute, a slow slap-down, the nose of the orbiter was coming down until nose wheel touch down.
OPF: Orbiter Processing Facility - Maintenance during several months stacking in the vehicle assembly building. Complexity of hardware around the orbiter for the maintenance between flights, especially concerning the thermal protection system.
This concept is explained in the following video: 6.2.5.
C97 - Space Shuttle selected missions
Utilization of the Shuttle: Satellites deployment including Hubble Space Telescope, Return to Earth of broken satellites, Space science with mainly Spacelab - 22 missions from STS-9 in 1983 until 1998, Interventions on satellites or telescope, Repair work, Assembly of large structures (ISS).
Space Shuttle-MIR program. Roscosmos and NASA technical and human cooperation: design and engineering of mating system between the Shuttle and Mir, opportunity for US astronauts to work with Russian cosmonauts. The idea was to prepare the assembly and utilization of the International Space Station.
This concept is explained in the following video: 6.3.1.
C98 - Space Shuttle Challenger accident
STS 51L in January 1986: explosion of the Space Shuttle happened 73 seconds after lift off.
The cause of the accident was the faulty design of the field joint and the low temperature preventing the O-ring to perform its expected task.
The Rogers Commission recommended to add another O-ring and a heater system to maintain a relatively high temperature in the area of every field joint of the Solid Rocket Booster.
After the Challenger accident, it was decided to use the Shuttle only for research and development, science and not for commercial missions or Department of Defense missions.
The crew had to wear the Launch and Entry Suit to protect itself against possible failures during the ascent, like a loss of cabin pressure.
NASA took advantage on the basis of the recommendations of the Rogers Commission to improve the safety of the Space Shuttle and of the organization.
This concept is explained in the following video: 6.3.2.
C99 - Space Shuttle Columbia accident
Lift off in January 2003, the accident happened during the re-entry of the spaceship, two weeks later.
A piece of thermal protection of the external tank detached from the tank and hit the wing.
The main recommendations were to fix the problem of detachment of thermal protection from the external tank, and give a possibility to the crew to do inspections of the thermal protection system while on orbit to make sure that there were no fatal damage of this thermal protection, and to do repair by space walking with necessary tools and materials.
This concept is explained in the following video: 6.3.3
C100 - Space Shuttle Hubble servicing missions
5 servicing missions: SM1 in December 1993, SM2 – February 1997, SM3A – December 1999, SM3B – March 2002, SM4 – May 2009. All servicing missions served the purpose of repair or improvements of the telescope.
Intervention on orbit could be done in the instrument section or on the surface of the telescope (addition of thermal protection for magnetometers). The solar arrays were replaced several times
This concept is explained in the following video: 6.3.4.
C101 - International Space Station
Signature of ISS Agreements in 1998 by 15 countries: US, Russian Federation, Japan, Canada and 11 ESA member states.
The idea was to make available a world-class laboratory in space for life science, materials science, Earth observations, solar physics, technology development and support of long-duration spaceflight in the Solar System in the future.
Mating of the first two elements: Zarya Russian module and Unity node or Node 1, 1st US element, followed by another Russian module, Zvezda.
Two years after the beginning of the assembly of the Station, the first crew arrived by Soyuz.
The ISS has been permanently inhabited from that time on until now. Astronauts and cosmonauts stay five to six months missions on board.
This concept is explained in the following video: 6.4.1.
C102 - Soyuz: human access to ISS
Since the Shuttle was retired in the summer of 2011, the only way to get to the International Space Station for astronauts and cosmonauts is using the Russian Soyuz, launched from Baikonur with a Soyuz rocket.
The "escape tower", on top of the Soyuz capsule, allows the crew to escape in case there is any problem during launch. Rockets on this escape tower can be fired and take the Soyuz capsule, with the three crew members on board, to some distance and then come down with parachutes to the ground.
The nominal approach and docking of the Soyuz capsule to ISS is automatic, with various sensors, antennas and cameras that are used to guide and control the displacement of Soyuz in the vicinity of its target, ISS.
There are always several Soyuz attached to the ISS to rescue crewmembers in case of emergency and bring them back to Earth.
Re-entry: braking maneuver that initiate the descent, with fiery re-entry in the atmosphere, and large parachute opening. For the last portion of the descent, before touch down, there is a retrorocket firing at the last moment in order to reduce the shock of the contact of the descent module with the ground.
This concept is explained in the following video: 6.4.2.
C103 - US future human access to space
3 commercial companies have been chosen by NASA to develop a manned system to and from ISS from US soil.
Space X is developing the Manned Dragon, human version of the Dragon capsule used to deliver freight to the ISS and return trash to Earth for 6 or 7 crewmembers
SpaceX has recently done an evaluation of the pad abort system of the manned dragon capsule, to be used in case there is a problem with a Falcon-9 rocket.
CST-100 capsule, developed by Boeing, will be able to take six to seven crew members to Station.
Sierra Nevada Corporation develops the Dream Chaser, a mini Shuttle that will be able from 2017-2018 to take crews to ISS.
This concept is explained in the following video: 6.4.2.
C104 - Chinese human access to space
Shenzou 10, the last version of the ascent and descent vehicle, has three modules: on-orbit module; descent module, where the crew takes place for the ascent and the entry, and the service module with solar arrays on both sides.
China is developing right the successor to Tiangong 1 Space Station, Tiangong 2, and a new vehicle for ascent and re-entry, Shenzhou 11.
This concept is explained in the following video: 6.4.2.
C105 - Logistics supply to ISS
Progress – HTV – Dragon – ATV – Cygnus (2 versions)
NASA's Commercial Crew and Cargo Program Office (C3PO): Commercial Orbital Transportion Services (COTS); Commercial Crew Development (CCDev) with Space X, Boeing and Sierra Nevada Corporation; Commercial Resupply Services (CRS): Phase 1: Space X and Orbital Sciences and Phase 2: Space X, Orbital ATK, Sierra Nevada Corporation
Delivery and return of 14-17 t of pressurized cargo in 4 or 5 trips per year. Delivery and disposal of 1.5-4 t of unpressuried cargo per year. Various ground support services for ISS resupply.
This concept is explained in the following video: 6.4.3.
C106 -Extravehicular Activities (EVA)
Extravehicular activity (EVA) is any activity done by an astronaut or cosmonaut outside a spacecraft beyond the Earth's appreciable atmosphere.
The first spacewalk was realised by Alexei Leonov in May 1965.
EVA can aborted because of problem threating the life of the astronaut such as a water leak inside helmet.
EVA have been used in Hubble servicing missions, ISS assembly, ISS repairs. Spacewalks have been mostly done from the Space Shuttle and the ISS.
This concept is explained in the following video: 7.2.1. and 7.2.3.
C107 - EVA space suits
Different type of Spacesuits exist depending of their utilization: High altitude pilot suit, Launch and Entry Suit, NASA Extravehicular Mobility Unit (EMU), NASA Manned Maneuvering Unit design (MMU), Orlan spacesuit.
MMU is a small spacecraft attached to the spacesuits that allowed astronauts to move around in translation rotation and to get toward the satellites without being attached to the robot arm, or without having a safety tether.
This concept is explained in the following video: 7.2.2.
C108 -Robotics arms for ISS and Space Shuttle
Shuttle Remote Manipulator System (SRMS) or Canadarm was used to rendezvous with Hubble and as a support to EVA.
Space Station Remote Manipulator System (SSRMS) or Canadarm 2.
Both RMS have been manufactured by Canada.
This concept is explained in the following video: 7.3.1.
C109 - Astronaut training
Centrifuge that creates the condition of ascent and re-entry, zero-g to experience microgravity, survival trainings, flight trainings, training of missions in simulators, mockups and pools, using virtual reality.
This concept is explained in the following video: 7.4.1.
C110 - Commercial space suborbital
A suborbital spaceflight is a flight in which the spacecraft reaches space (>100 km altitude in the case of the Earth), but its trajectory intersects the atmosphere or surface of the body from which it was launched, so that it does not even complete one orbit.
The first suborbital spaceflight was realized with Mercury-Redstone 3 and 4 in 1961.
The current actors of suborbital flights are: Virgin Galactic, XCOR Aerospace, Blue Origin and Airbus defense and Space.
This concept is explained in the following video: 7.5.1.
C110 - Commercial space suborbital
A suborbital spaceflight is a flight in which the spacecraft reaches space (>100 km altitude in the case of the Earth), but its trajectory intersects the atmosphere or surface of the body from which it was launched, so that it does not even complete one orbit.
The first suborbital spaceflight was realized with Mercury-Redstone 3 and 4 in 1961.
The current actors of suborbital flights are: Virgin Galactic, XCOR Aerospace, Blue Origin and Airbus defense and Space.
This concept is explained in the following video: 7.5.1.
c111 - Future of space utilization and exploration
Earth and atmosphere science and monitoring, Space applications (Galileo navigation system, GPS, etc…, communications), Space Solar Power concept, James Webb Space Telescope (JWST), Orion, rise of commercial space.
This concept is explained in the following video: 7.6.1.
C112 - Future human solar system exploration
Moon: ESA's Moon village, exploiting the resources; Manned missions to asteroids; Mars: human settlement; Europa and Saturn moons.
This concept is explained in the following video: 7.6.2.
C113 - Orion and Space Launch System
Orion Multi-Purpose Crew Vehicle has been in development since 2005, in collaboration with ESA since 2013. It consists of a launch abort system tower, the crew module and the service module. Crew from 2 to 6 astronauts. Launched by Space Launch System (SLS), first crewed flight planned for 2021.
This concept is explained in the following video: 7.6.3.
Please note that the links to the videos do not work if the unit is not yet released.


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We received a thank you note from the Head Start facility for the Christmas Gifts donated by the Trenton Flyers. I'll post it and some individual thank you cards in the club house.
Blog >
Blog >
GLEAMNS Christmas Giftsposted Jan 19, 2010, 7:26 AM by Unknown user [ updated Jan 19, 2010, 7:37 AM by Benjamin Richardson ]

subset: commoncrawl


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Get Free TRUSS Hair Care Sample!
TRUSS has an impressive presence in more than 9 countries and offers a high-end complete hair care line to professional stylists and can be found in the finest hair salons of the world. Request a free sample of TRUSS Professional Hair Care today. Since the beginning of March, TRUSS will be fulfilling all of the entrees for consumer samples, not only professionals' so you can go ahead and claim one.
Just follow this link to get the freebie:


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Bantams a Complete Pet Owners ManualItem No. BANT1
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Descriptions on many breeds of Modern Game, Old English, and American Game, feather-legged, clean-legged, rose-comb...$12.50
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We host several Open Houses throughout the year. Prospective students are welcome, although we hold separate tours and Orientation Days for new students that give them a deeper understanding and experience of life at VIS.
Open Houses for 2017/2018 and 2018/2019 Enrollment
Open Houses for 2017/2018 and 2018/2019 applicants are scheduled on the following dates:
Thursday, October 5th, 2017, 1:30 – 3:30pm
Thursday, November 9th, 2017, 10:00 -12:00 noon
Thursday, January 11th, 2018, 10:00 – 12:00 noon
Thursday, March 1st, 2018, 10:00 – 12:00 noon
We appreciate your interest in Voice Integrative School. Do not hesitate to contact the school regarding the current status of admissions or further information regarding these Open Houses. Please inquire with Jamie Milroy, Principal: (416) 691 4639 or email@example.com for more information. Thank you.
Kids Informing Kids: A Student –Led Tour for Potential VIS Applicants
Our Open Houses are dedicated to the families of potential students and provide parents and guardians with an opportunity to gain a deeper understanding of our philosophy, to take a tour while classes are in progress and to get answers to any questions they might have. Beginning this year, we have decided to hold a second Open House event- Kids Informing Kids: A Student-Led Tour. This hour long tour is geared toward kids and is led almost entirely by student leaders from our primary, junior and intermediate divisions. It is available to students interested in enrolling in all grades. These tours are available to any student interested in VIS, regardless of if their families have previously attended an Open House.
We ask that parents drop off students at the main office by 10:00 am and return for pick up by 11:00 am.
Upcoming Tours
Monday January 15 from 10:00am to 11:00am
Monday, March 5th from 10:00am to 11:00am
Please note: The Kids Informing Kids Tour is not to be confused with our formal Student Orientation Days which take place following an official application.
Your Application package must include the following:
- Application form ( Please click here to download )
- $100.00 non-refundable application fee payable to VIS or Voice Intermediate School or Voice Integrative School
- Recent photograph of your child
- A photocopy of the student's most recent progress report
- A graded sample of the student's writing (i.e. poem, short story, or essay)
You will be contacted with a date and details on the aspects pertaining to your child's Orientation Day:
- Meeting students and participating in classes
- Interviews with the Principal and Student Council
- Math and Language Assessment
PLEASE NOTE: Enrollment is closed for the summer and will resume in September 2018.
There is a wait-list for certain grades; however, a few spaces are available for the 2018/2019 academic year. Should you be interested in applying for the upcoming school year; please contact firstname.lastname@example.com. Please check our website at that time for upcoming Open Houses and admissions updates.


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Product Description
This beautiful scene imagined as life in an aquarium is created on a stretched canvas. This piece of art is ready for your wall or you can frame it as a shadow box.
I have used many die cuts and two different rubber stamps. The base is two different tissue papers representing the different colors of sea water. The angelfish have been stamped on watercolor paper, embossed, and painted with Twinkling H2Os watercolors. Shells have been added to the bottom of the aquarium and Prills added for sand.
This mixed media fine art is a finished size of 5" x 7"6" square. Most of my mixed media pieces are ready for wall hanging or ready for you to frame as you like. All will be wrapped for safe shipping and mailed USPS First Class in the United States and Canada. I use rubber and/or digital images in most of my designs. I work in a smoke-free environment and in the company of my dog Gypsy. My business stamp, along with my signature and date, are on the back of most of my pieces.
Thanks for stopping by! Contact me if you have any questions.
"Art washes away from the soul the dust of everyday life."—Pablo Picasso
Welcome to my shop "AJ's Desigsns," and Zibbet! The talented artisans that Zibbet has attracted will keep you in one spot for a while. Get a refreshment, come as you are, sit down, and have a browse.
If you have any questions, please contact me. Happy shopping and thanks for stopping by.


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Great piece of /sw Havent had a chance to use the API in much detail.But to have a java library that allows snmp querieswrapped such that the implementation is abstracted is simply awesome.
AdventNet SNMP API - Free Edition. It is providing many useful functions. And is very easy to use.
Embedded Problems It worked well in my desktop tests but caused my embeeded app to fail to load on its device. I suspect memory requirements, which are somewhat tight.
SNMP API I want to know different SNMP API
A good Java library for working with SNMP I have been searching for a Java library that used SNMP. I've tried netsnmpj, a binding of net-snmp but couldn't get to work correctly on fedora 5, with problems with old libraries (besides, it seems to be a dead binding for a few years now).AdventNet SNMP worked with no problems... just unzip and update the classpath and pronto... no need for external .so files and no digging arround. The only digging i had to do was searching for the stuff i wanted inside the library, but the examples are a great help.
Audio & Multimedia
Games & Entertainment
Graphic Apps
Home & Hobby
Network & Internet
Security & Privacy
System Utilities
Web Development
Java Snmp Response
System Oid Adventnet Linux Mib
Snmp Response Java
Snmp Response In Java
Simulate Snmp Response
Rfc3416 Agent
Loriotpro Uac
How To Send Snmp Response Message With Java
Get Snmp Response From Network Pc
Free "mib Browser" Linux
Cant Get Snmp Response Windows 2008 Server


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Field Tested: Foundry Overland
From Bicycle Times Issue #36
Reviewer: Gary Boulanger
"Foundry is aiming for old-school 'cross riders who might pin on a race number now and then with the Overland."
Foundry entered the market with carbon models a few years ago, providing bike shops an alternative to the bigger brands. So it came as a surprise when they introduced titanium models like the Overland. But should this be a surprise with steel making a strong comeback recently? Titanium has always been viewed as an upscale metal to its ferrous cousin, so Foundry obviously did its homework.
The Frame
The Foundry Overland is a titanium bike designed with drop bars for cyclocross or gravel riding and racing, a nice alternative to all the carbon and aluminum models on the scene. Foundry was aiming for the highest strength-to-weight ratio, and Ti-3Al- 2.5v titanium made the cut. Expensive, but no worries about rust over the long haul.
Where the Overland differs from dedicated "gravel" bikes is in the shorter 42.5 cm chainstays, with cyclocross racing in mind. Our test sample arrived with narrow Clement 33 tires, but Foundry says 40s will fit fine. This is a quicker-handling machine compared to longer wheelbase bikes made for Dirty Kanza-type events, like the Salsa Warbird.
Foundry chose thru-axles for the Overland; 142×12 on the rear and 100×15 mm on Whisky's No. 9 carbon fork up front. These axles provide a stiffer ride than a traditional quick release and I like the extra assurance that my wheels are secure when riding hard off road. The fork tracks well, and I appreciate the fender mounts. Alas, there are no rear fender or rack braze-ons.
The Ride
I prefer riding to my off-road destinations, and the Overland is comfortable on the asphalt as well as the dirt. It feels equally smooth once I jump on the trail, and despite its 'cross-racing geometry, handled switchbacks and descents like a champ.
For me, versatility is most important for riding a drop-bar bike on the dirt. Our test sample arrived with narrow 'cross tires, but that didn't stop the Overland and I from having a blast on the gravel trails of Arastradero Preserve in Palo Alto. I'd certainly replace the 33mm tires with 38s if I chose to just ride the Foundry instead of race it. I'm a seated climber, and the wheelbase made getting to the top of each riser a rather simple task.
Parting Shot
You'll notice that old-school top-tube cable routing has been chosen, which requires a pulley mounted on a threaded seat tube boss. This is to keep as many cables away from the mud that's sure to build up when riding the Foundry where intended, in the muck and mire.
Several of my newer riding buddies come from a mountain bike background and feel a bit overwhelmed riding on the road. A smart 'cross bike like the Overland may help them and others overcome their fears, stealing away onto some singletrack or a Jeep trail when the opportunity presents itself. Foundry is aiming for old-school 'cross riders who might pin on a race number now and then with the Overland, and I found it to be fun and responsive just ripping around on my local trails.
Not in the market for a new complete bike? Foundry is offering the Overland frameset for $2,495, and with several major manufacturers offering stout 700c wheels with thru-axles and disc brakes, one could put together a unique and fun mud puppy.
- Price: $4,695
- Weight: 20.3 pounds
- Sizes: 52, 54, 56, 58 (tested) and 60 cm
- foundrycycles.com
- Additional photos from our Overland preview


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WOW What a cool site, and free with no hassle sign up, Glorious! Using above desktop PC WIN 8 beats audio, IDT audio codec, Using a YAMAHA V373 RECIEVER, I have been all thru speaker IDT configure, I can get a 6 speaker 5:1 set up display but when I hit test it only tests 2 speakers in stereo It is set to 5:1 and shows it but again only stereo sound is tested, Beats audio is set for 5:1 but if I shut down PC beats audio goes to stereo and I have to manually reset it to 5:1 again, Also beats audio wont test in 5:1 even though it displays 6 speakers and 5:1 I only hear stereo 2 speakers in test, so I am stumped, I am on other sites regularly so I will refer back and check for any replies, please excuse any delay in responding if this occurs, Thanks for any and all replies
message edited by karmachemeleon
Yes, this is a cool site.
I am curious as to why you did not use the System scan tool mentioned on the first screen. That tool would tell us what hardware you are running. Now I need to ask you for that information in order to actually help with the posted issue.
List the full computer model of HP Pavillion.
Thank you OtheHill, Thais is very kind of you, I am unfamiliar with the scan tool you mention unless I have used it but under another name IDK, The PC Is a HP P 7 1414 6 Months old, with factory beats audio, I already had to replace the hard drive due to 60+ bad sectors, I don't know how the hell that happened but what else can I tell you?, I wish I could be more thorough but I have had PC's for 10 years and it baffles me how much learning curve is required every other time windows releases a "new' OS, Seems like with win 8 I have to re learn damn near everything, What is wrong with continually user friendly?, With my former win XP I could do anything, then this monstrosity win 8 appears in my life, What else can you run me through? I want to be co operative as possible, The Best Buy Geek squad wants $125.00 to come and do what? I believe I am close but not the proverbial cigar just yet, I went to win sound etc configurations and got it to make sound test through all 6 speakers just once then it went back to stereo only, It doesn't sound THAT bad but I am a lifelong musician/singer and the sound is muddy if you know what I mean, Common term for ,,,well, for a muddy sound, the bass (sub) is either overwhelming, I can hear the cone rattle ,or the bass is underwhelming, Weird, just wierd.I could run the scan tool you mention if you can guide me as to where it's at? Again thank you for replying
message edited by karmachemeleon
The scan tool is HERE at Computing.net. Click on "My Home" in the upper right of this screen. You should see a message at the bottom of that screen about scan your system.
See the link below for some help with your sound. According to the HP site, your IDT audio chip is compatible with Intel HD sound. Sometimes 2 drivers are required. You may only have AC97 sound now.
Have you checked in Device Manager to see if the sound is working?
I am not familiar with your exact sound chip but most HD sound chips have programmable ports. You MUST select the output port to the receiver even if it appears you are already using it try clicking on the port icon.
If your speakers are connected to the receiver then you should select LINE OUT to the receiver and then use the receiver settings to control the speakers. Hope this helps.
If drivers are needed go to the link below to download them.
message edited by OtheHill


text:
November 22, 2011
Thanksgiving Wonder Guests
Top 10 Authors I Want At My Thanksgiving Dinner
So even though this weekend isn't Thanksgiving for me (we celebrated Thanksgiving over a month ago here in Canada), this seemed like a super fun topic. Here are my choices:
1) Ally Condie (Matched series) - Invited specifically for her great taste in poetry. She'd give a reading and would not be above admonishing guests to 'not go gently' into their respective turkey comas, but to 'rage, rage' against it and the pull of the sofa.
2) J. K. Rowling (Harry Potter series) - She'd bring butterbeer, pumpkin pasties, and lumpy hand knit jumpers for the whole gang. Oh, and promises that she'll write stories about the Potter and Weasley offspring's adventures at Hogwarts.
3) Veronica Roth (Divergent) - She's here because she's awesome but also so she can carve the turkey. Why? Because she's DAUNTLESS! and knives scare the crap out of me.
4) Stephanie Perkins (Anna & Lola)
5) Laini Taylor (Daughter of Smoke & Bone)
They can trade super sweet/funky hair-dying tips and share them with the group. Also, they can sit on either side of me and tell me what it's like to write such awesome books (hope it rubs off).
6) Jane Austen (Persuasion, Pride & Prejudice...) - Who else would be eager to 'take a turn about the room' to burn off turkey and discuss her hot book boys? I'm Team Wentworth, though I know this will make Team Darcy want my head on a stake. Jane is Team Mum's the Word.
7) C. S. Lewis (The Chronicles of Narnia) - He's a great author, and because Tolkien - if invited - would probably spend the whole meal speaking in Elvish or Entish (which nobody wants, believe me). Turkey coma + Entish = bad combination.
8) Tyra Banks (Modelland) - She can bring this dinner party up several notches in the WTF-ery department. Who wouldn't want to hear how this steaming pile made it to publication?! Oh, and she'd treat us all to Tookie De La Crème Brûlée for dessert. Also, the guests get really good at fake 'smizing' when they tell her how much they l♥ved her book.
9) Stephenie Meyer (Twilight Saga)
10) Stephen King (On Writing, among others)
Since no Thanksgiving feast would be complete without its fair share of squabbling, these two honored guests get places at the kiddie table. As a centerpiece, there will be stacked copies of Twilight and On Writing to promote awkward and scintillating discussion. Too mean? Maybe, but definitely entertaining (at some point during dinner, King also manages to slip a copy of On Writing into Ms. Banks oversized tote on the sly *hint, hint, hint*).
12 comments:
Fantastic list! Several of these are on my list too. Incredible authors that seem like equally incredible people. Love how you posted their pics, really neat.ReplyDelete
My TTT!
Happy (early) Thanksgiving!
Can I join your table? I'll bring some pie!ReplyDelete
Austen and Lewis made my list. I wish I would have thought to put Condie. I'd beg for some spoilers on what happens next. ;)ReplyDelete
We have lots of the same authors! Really awesome list. :)ReplyDelete
- AnonymousNovember 22, 2011 at 12:18 PM
I love your list! I almost put Laini Taylor on mine because I LOVED Daughter of Smoke and Bone soo hard. I hope that these lists don't make my actual Thanksgiving a letdown!ReplyDelete
My favorites would be Nora Roberts, JK Rawlings, Stephen King, Jane Austen and Tolkien.ReplyDelete
Here's My Post
I would love to have many of your authors at my Thanksgiving dinner too!ReplyDelete
stopping by to see who's at your turkey dinner.ReplyDelete
@trippingbooks I just finished Daughter of Smoke and Bone and really liked it. It was the perfect vacation book.ReplyDelete
I was sacred for a sec when I saw Tyra on the list but the reasoning is hilarious. I read the first chapter online of Modelland - wow. Just wow. Also: smizing (!!!)
Stephenie Meyer gets a bad rap for her writing quality, but I have to admit, it would be quite a sight to see her and King discuss writing. I can see him reading a selection about Edward's jaw clenching or something and saying, "who farted?" (that's actually from On Writing, I swear)
I want to come too!ReplyDelete
Love your choices, and love your reasons for selecting each person. Sounds like a dinner party full of fun conversation. :)
Hah! Awesome. That would be one for the ages. (I kind of wonder what Ms. Austen would have to say to Ms. Meyer. Yeesh.)ReplyDelete
I ADORE this list. It was cracking me up! Especially the Stephanie Meyer Stephen King bit. This would definitely be a dinner party I would love to attend.ReplyDelete


text:
Great Counseling Services
A Guideline In Spotting The Perfect Therapist For You
Life may not be always easy and there are times when we find ourselves in hard situations that give us a feeling of self-doubt. These situations can happen anywhere, be it at work, at home, or in our relationships. But don't fret for we are here to help you out with this article that shows one way for you to handle such hard times.
The option we are talking about is through a professional therapist. These are the people who have made a career out of helping other people sort out their bad feelings about the things going on with their lives. Often times, people have a negative outlook in life because they do not understand things fully or they cannot see the big picture. The job of the professional therapist is to try to enlighten these people so that they can feel better about themselves. Many people are skeptical about the idea of telling a total stranger about all the issues that go through your head, but therapy has long been proven and tested to work quite well.
So how are you going to assess the skills of a therapist? Well, a good therapist from northern kentucky marriage counseling would be able to handle whatever issues you are going through with your life. It does not matter is the issue is about you not being happy with your job, your family not being supportive enough, you relationship is falling apart, or you are simply confused and do not have any idea on how to be happy about life. An experience therapist can talk about anything under the sun.
The thing about therapists is that it does not mean that he or she is good, then you will be able to get along. Therapy is where you talk to a total stranger about your issues and so you need to find a therapist that you feel comfortable talking to. Recommendations are good but the thing here is that the issues your going through might be different from the issues the person you asked for recommendations has gone through. You two might have different preferences when it comes to the person you want to talk to so when you do get recommendations, just take it into consideration but do not base your decision solely on it.
It is also important for you to take into account the amount of experience the therapist from cincinnati counseling has. Keep in mind that experience is the best teacher and therefore those who have been in the business for a long time, tend to be better.


text:
|TAKE ACTION: Protect Farm Bill Conservation Programs
Right now, the House and Senate are behind closed doors, negotiating a new Farm Bill. Bay restoration relies heavily on key conservation programs within the bill that protect our local water quality. Please make sure your representatives preserve this vital funding to Bay state farmers. TAKE ACTION NOW!
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|How Is Virginia Doing?
CBF's Hampton Roads Director Christy Everett updates us on how Virginia is faring in Bay restoration. "[Virginia] needs to make changes if it wants to stay on track to meet its Bay clean-up commitments." Learn what exactly needs to be done. Plus, read other updates on our local Bay-saving efforts in Maryland and Pennsylvania.
|Keeping Bay Restoration on Track
The news is out! Our latest assessment report evaluates what progress the Bay states are���or are not���making toward clean water restoration. It celebrates the areas where states are exceeding the Chesapeake Bay restoration goals, but also shines a light on areas needing improvement. So, how did your state measure up? Read on to find out!
Download the latest issue of Tidelines,
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Roasted Red Grape, Brie and Rosemary Flatbread
This red grape, brie and rosemary flatbread is studded with juicy red grapes, bubbling brie cheese, sprinkled with fresh rosemary and sea salt.
Today is a very special day.
A bunch, and by bunch I mean THIRTY SEVEN bloggers teamed up to virtually bring some amazing food to our friend Bev, for one of the biggest surprise virtual baby showers I've ever seen. This party is slammin' with a ton of delicious food from pear, cranberry and arugula salad to sweet potato crème brulée. I mean Bev's pregnant with twins, so she's eating for two and all, right?
Bev is a riot. {Did that just make me sound reeeeally old??} No really, she's probably one of the funniest writers I've ever read. I can't read a blog post of hers and not chuckle if not a full-on belly laugh and most times it's out loud and sometimes it involves a snort. But all this funny business aside… she's also a great cook, photographer, she's caring two babies and is still a size negative zero, OH and she sings. What can't this girl do? No, really Bev… what can't you do???
So when the email popped into my inbox for Bev's virtual shower, I instantly started thinking of Bev. No, nothing creepy like… but what I wanted to bring to Bev's shower. Instantly I thought of flatbread. Bev LOVES her pizza so I knew that I was going to throw together a Bev-worthy flatbread and I was going to serve it on a wood cutting board, in true Bev style.
So first things first, I made some flatbread dough. It's SUPER easy yo's! I spared you all the step-by-step's of this part and plugged the directions into the printable below the post.
Then I used a Y vegetable peeler and peeled off as much of the waxy rind I could from the {8 oz.} brie wheel. If you can find those brie logs, those probably would work better. That's what I was looking for actually, but my grocery store was all out. Wah-wah.
So I awkwardly sliced it pretty thin, so I could then tear it into pieces.
Then I just wash some pretty red grapes… pretty hard stuff right here.
You'll need about a heaping cup… and some fresh rosemary.
Next I drizzled a rimmed sheet pan with two tablespoons of olive oil, don't skimp, and just rub it around with your hands.
Don't even bother washing the olive oil off your hands before you punch the risen dough down and stretch it out almost to the sides of the pan. Now, go wash. 😉
Then I scattered the torn pieces of brie over the dough.
Then with two tablespoons of chopped rosemary leaves.
Press the grapes into the flatbread dough…
…and lastly sprinkle with the two teaspoons of flaked sea salt.
Cover and let rise for 20 more minutes. Bake in a 400 degree oven for 20 minutes or until the grapes start bursting, the brie is bubbly and the flatbread is perfectly golden and crispy.
Bubbles are a good sign. It means the grapes plumped up until they burst and leave a sweet trail of bubbly juice. Yeah. That's right.
This recipe is perfect for a gathering. It serves 15 or more depending how you slice it and it's sure to be gone in no time.
The crust is crispy, chewy and undeniably addicting. The grapes add a burst of sweetness and baking them along with brie, rosemary and a sprinkle of flaked sea salt really elevates this flatbread to a whole new level.
I'm now considering having a baby, so I can have an excuse to throw myself a shower and eat this entire Red Grape, Brie and Rosemary Flatbread. Amen.
Be sure to check out more amazing dishes that were brought by some crazy-talented bloggers to Bev's Shower:
Bacon Cotija Guacamole from Gaby Dalkin
Gruyère Gougères from Shaina Olmanson
Lemon Risotto Tarts from Kelly Salemi
Goat Cheese Crostini with Pesto and Roasted Red Peppers from Liz Della Croce
Spinach and Feta Quinoa Bites from Aggie Goodman
Roasted Red Grape, Brie and Rosemary Flatbread from Laurie McNamara
The Fastest Appetizer Ever from Brooke McLay
Apple Pear Tart – Two Ways from Sarah Glyer
Chocolate Chai Frappe from Brandy O'Neill
Cherry Chocolate Kiss Smoothie from Amy Flanigan
Cranberry Sorbet Bellini – Non-Alcoholic and Alcoholic from Megan Keno
Peppermint Mocha Affogato from Christina Lane
toasted marshmallow cream hot chocolate from Jessica Merchant
Pomegranate Lemonade Punch from Heather Christo
Kale Salad with Pomegranate, Orange and Pine Nuts from Rachel Gurk
Pear Cranberry Arugula Salad from Tracy Benjamin
Brussels Sprout Salad + maple roasted cranberry dressing from Katie Unger
Gluten-Free Pasta Salad from Lisa Thiele
Hearty Roasted Winter Vegetable Salad with Honey Ginger Dressing from Heather Disarro
Winter Citrus Salad from Catherine McCord
Creamy Roasted Red Pepper and Chicken Sausage Pasta from Heidi Larsen
Eggplant Parmesan Lasagna from Joanne Ozug
cheesy chicken enchilada 'double' stacks from Lauren Grier
Jalapeno Popper Chicken Soup from Kevin Lynch
Thai Spiced Chicken with Coconut Cream Swiss Chard from Brandi Evans
Sausage and Red Pepper Quiche from Tasty Kitchen
Roasted Red Pepper Pasta with Goat Cheese from Julie Deily
Soft and Chewy Oatmeal Coconut Chocolate Chip Cookies from Averie Sunshine
Glazed Dulce de Leche Pound Cake from Meagan Micozzi
Mississippi Mud Pie Brownie Ice Cream from Megan DeKok
Buttermint Frosted Sugar Cookie Cups from Shelly Jaronsky
4-Ingredient Peanut Butter Chocolate Cookies from Ali Ebright
Sweet Potato Creme Brulee from Brian Samuels
Whole Wheat Double Chocolate Mint Cookies from Aimée Wimbush-Bourque
Mini Chocolate Stout Cheesecake with Salted Beer Caramel Sauce from Jackie Dodd
Red Velvet Hi Hat Cookies from Kristan Roland
Double Chocolate Panini from Kathy Strahs
Enjoy! And if you give this Red Grape, Brie and Rosemary Flatbread recipe a try, let me know! Snap a photo and tag me on twitter or instagram!
My cookbook Simply Scratch : 120 Wholesome Homemade Recipes Made Easy is now available! CLICK HERE for details and THANK YOU in advance!
Roasted Red Grape, Brie and Rosemary Flatbread
Crispy flatbread studded with juicy red grapes, bubbling brie cheese, sprinkled with fresh rosemary and sea salt. The perfect savory-sweet-and-salty snackitzer.
Yield: 15 pieces
Prep Time: 20 minutes plus 1 hour for the dough to rise
Cook Time: 20 minutes
Total Time: 1 hour 40 minutes
1 cup warm water (110-115 degrees)
1 envelope (or 1-1/4 teaspoon) active dry yeast
2 cups unbleached bread flour
1/2 teaspoon kosher salt
3 tablespoon olive oil, divided
brie cheese, rind removed, sliced and torn into pieces
2 tablespoons chopped fresh rosemary
1 heaping cup firm red grapes, washed
2 teaspoons flaked sea salt
FOR THE FLATBREAD: In the bowl of your stand mixer fitted with the dough hook; measure in the two cups of bread flour and the 1/2 teaspoon kosher salt. Turn the mixer on low to combine for a few turns.
In a one cup liquid measuring cup, measure out a cup of warm {110-115 degrees} water. Sprinkle in the package of active dry yeast and wait for it to bloom. {about 5 minutes}
Turn the mixer on low and slowly pour in the yeast/water mixture. Turn up the speed a bit and continue to "knead" the dough until the dough pulls away from the bowl and starts to climb up the dough hook.
Lightly flour a clean surface and knead the dough into a ball for a minute or two.
Add the tablespoon of olive oil into a clean bowl and roll the dough ball in the oil and up the sides of the bowl to coat. Cover with a clean towel and set in a warm place to rise for one hour or until it doubles in size.
Drizzle two tablespoons of oil onto a rimmed sheet pan and spread it around with your fingers. Punch the dough down and stretch out onto the oiled pan until it almost touches the sides.
Scatter pieces of brie cheese over top evenly and sprinkle with the chopped fresh rosemary. Press the grapes slightly into the flatbread dough and sprinkle with flaked sea salt. Cover again with a clean towel and let it rise for the second time for 20 minutes.
Pop the flatbread into a preheated 400 degree oven and bake for 20 minutes, rotating the pan halfway through for even baking.
Remove once the grapes have started to burst, the brie is bubbling and the crust is golden and crispy.
Slide the flatbread onto a wood cutting board and slice into 15 pieces.
[this post contains affiliate links.]


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Download EBOOK GMAT Verbal Strategy Guide Set PDF for free
Category: Business, Finance & Law
The author of the book: Manhattan Prep
Format files: PDF, EPUB, TXT, DOCX
The size of the: 247 KB
Language: English
Edition: Manhattan Prep Publishing
Date of issue: 2 December 2014
Description of the book "GMAT Verbal Strategy Guide Set":Adapting to the ever-changing GMAT exam, Manhattan Prep's 6th Edition GMAT Strategy Guides offer the latest approaches for students looking to score in the top percentiles. Written by active instructors with 99th-percentile scores, these books are designed with the student in mind. Acing the GMAT requires more than tricks and tips--you've got to master the material. Students looking to boost their GMAT verbal score can now turn to a name known for high quality instruction. Manhattan Prep's GMAT Verbal Strategy Guide Set includes our 3 books devoted to this section's major content areas, providing PDF detailed and specialized instruction on Sentence Correction, Critical Reasoning, and Reading Comprehension. Developed by the best teachers in the business, these guides are the backbone of Manhattan Prep's GMAT verbal curriculum and the most in-depth, comprehensive materials available. The GMAT Verbal Strategy Guide Set is aligned to both the 2015 and the 13th edition GMAC Official Guide and includes: The Sentence Correction Guide (ISBN: 9781941234075) The Reading Comprehension Guide (ISBN: 9781941234068) The Critical Reasoning Guide (ISBN: 9781941234013 Purchase of this set includes one year of access to Manhattan Prep's online computer-adaptive GMAT practice exams and 3 Verbal Question Banks.
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text:
Welcome to Devizes RFC Under 15s
Players must be aged 14 on 31st August
We are friendly group of players who are learning different skills through our rugby journey. We run fun training sessions on a Sunday from 10 am and Wednesday from 6.30 pm at Devizes Rugby Club where we are supported and coached by DBS cleared and RFU trained coaches. We play matches with other teams from the local area which are both inclusive and fun.
We play a full 15 a side game.
We learn our rugby in accordance with the Age Grade Regulations to learn more about this you can read more here. This means we are player centred, development driven and competition supported.
To join us please contact:
Stevie Sheppard
Tel: 07971 290354


text: Ok. My 1 year old dog has SO much energy. Seperation anxiety is what the vet calls it. She must be touching you every minute you are home. Checked into the Doggie Daycare. Friend brings her dog there. Thought I would try this one day a week, maybe it will help her "seperate". As the day was coming (a non work day) I was feeling guilty about bringing and leaving her there. Was thinking maybe 1/2 day for the first day. THEN...I had a pound of hamburger frozen, thawing out on the counter. Brought difficult child to school and when I got home I saw the tin foil, the shredded saran wrap...and the entire pound of hamburger gone! She has gotten other things like a sandwich, even a steak that was on the counter. This was it. I was GLAD she was going the next day. We didn't quite know how she was getting these things, thought she was jumping up and knocking it down. (she is a jumper. All four paws right off the ground like she is on a trampoline) Then, that very same night I brought easy child to work. difficult child heard a noise in the kitchen and SHE...Kenzie...was ON the counter. All four paws. Took her to daycare the following morning. Hung around and viewed her on the "doggie Cam" Went home and viewed her one time on the "doggie cam". When we went back to get her we noticed she was in an isolated area, the kennel area and all other dogs were out. They told me she was "rude" so she was given a time out. I asked how long she had been in there. They said they rotated throughout the day. I asked what it was she did. They said she was nipping at the legs of the other dogs. Not viciously (sp?) playfully. I see her do that at home with Chloe. When she is playing. They both do it. When we got home I opened the car door and she ran to the door of the house scratching the door. (usually tries to visit the neighbor dog). Opened the door and she went and drank about 1/2 bowl of water!! I am wondering if they gave her any water?? She did not eat her dinner that night, she did not eat her breakfast the next day. That food sat a good 24 hours. Do you think she should continue? Did she deserve the isolation? Does she need to learn? I am really hesitant about returning. And, yes, I called the vet about the pound of frozen hamburger. I was told to watch both dogs for vomiting and poops. I would WANT to see that happen. If it did not happen then I need to bring them a stool sample from each dog in 5 days to check for parasites. Friend said not to do that. Would you?


text:
I have been building an instrument since January. It's finally more or less done. It's not a guitar and not exactly a go-to instrument for blues, but I guess you could play blues on it
Here it is all finished. It is a mandocello, which is an instrument in the mandolin family.
The scale is 25.5". The top is western red cedar, the back/sides/neck are african mahogany. Both top and back are carved. The neck and tail stripes are wenge, as is the tailpiece. The fretboard is macassar ebony and the nut and bridge are some other ebony (gaboon? can't remember). The top is X-braced. The finish is quite amateurly french polished with garnet-colored shellac.
Here is an audio recording.
And here are a bunch of gigantic pictures: