By J.J. Pocha
` The ebook is a good written and is appropriate for a large variety of readers from scholars to managers drawn to studying in regards to the undertaking layout challenge and research strategies for the geo-synchronous orbit. '
Canadian Aeronautics and house magazine, March 1988
Read or Download An Introduction to Mission Design for Geostationary Satellites PDF
Similar repair & maintenance books
Ventiltriebsysteme steuern den Ladungswechsel beim Verbrennungsmotor und sind somit ein maßgeblicher Stellhebel für den optimalen Verbrennungsprozess. Ihre Energie beziehen sie aus der Kurbelwelle, ein effizienter Ventiltrieb trägt dadurch zusätzlich erheblich zur Verbesserung des Gesamtwirkungsgrads bei.
This booklet should be of significant curiosity to any expert engineer or automobile engineering scholar engaged on off-road automobiles. Reflecting the rise in off-road automobile creation and development―recreational, agricultural, building, military―this e-book equips readers with all the beneficial wisdom to effectively layout and version off-road motor vehicle structures, and gives a finished advent to terramechanics, the mechanics of vehicle/terrain interplay.
Extra info for An Introduction to Mission Design for Geostationary Satellites
Now target the apogee manoeuvre to achieve a post-burn orbit in the equatorial plane, with the opposite apse at geostationary height (the manoeuvre is itself made at an apse which is lower than synchronous height). This manoeuvre requires somewhat less energy than the nominal manoeuvre, and hence requires less propellant. After the burn, the spacecraft will be in a slightly lower orbit than geostationary orbit, and an Easterly drift rate will automatically be established. This saves further manoeuvre propellant compared to the nominal case.
Active separation can be achieved by actuation of satellite on-board thrusters, while passive separation is achieved through differential drag effects. Passive separation can be achieved also by timing the deployment from the Orbiter's cargo bay. 3 The Launch Event Sequence for MARECS on Ariane Event First Stage Ignition Lift Off Umbilical Eject Start of Pitch Program First Stage Burn Out First Stage Separation Second Stage Full Thrust Fairing Jettison Second Stage Burn Out Second Stage Separation Third Stage Full Thrust Third Stage Cut-Off by Guidance Computer Start of Payload Re-orientation to Nominal AMF Attitude Slow Spin-Up to 10 rpm.
We take into account the variation in the launcher's payload performance with apogee height, and calculate the mass of the spacecraft into transfer orbit. Finally, we select the apogee height that yields the maximum spacecraft mass into drift orbit. Thus the optimal transfer orbit is fully defined. An exercise such as the above was carried out for the OLYMPUS spacecraft, and it was found that the apogee height had to be lowered by about 200 km to yield optimal results. We consider now the case of the multi-burn apogee engine firing (AEF) strategy.