Download e-book for kindle: An Introduction to Mission Design for Geostationary by J.J. Pocha

By J.J. Pocha

` The publication is a good written and is acceptable for a vast diversity of readers from scholars to managers drawn to studying in regards to the undertaking layout challenge and research suggestions for the geo-synchronous orbit. '
Canadian Aeronautics and house magazine, March 1988

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Extra info for An Introduction to Mission Design for Geostationary Satellites

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Once this has been achieved, the next step is taken. It was mentioned above that each sub-range had associated with it an optimal apogee motor size. The spacecraft can have but a single apogee motor. Of the optimal sizes, the one that is selected is that which is associated with the lowest BOL mass. The motor size is then kept fixed, and the sub-ranges re-optimised using the same procedure as before. This results in a set of optimal transfer orbits for the node-shift sub-ranges considered. 2 Orbit Optimisation for Spacecraft with Solid Propellant Apogee Motors 37 The 01Jtimisation Procedure for the Shuttle Let us now consider the optimisation for the Shuttle.

R",mJaR. I. 7 Launch Window Due to Solar Aspect Angle and Eclipse Constraints i I -I i --~~ ! So\ft<. )

The activity consists of determining the spacecraft's spin rate through examination of its sensor output. The manoeuvre to achieve the required spin rate is determined on the ground and appropriate commands are sent to the spacecraft. After the manoeuvre, the ground station determines the new spin rate. If it is within acceptable limits the manoeuvre is complete; if not, further manoeuvres are executed until the desired spin rate is obtained. 4 Ground Station Coverage 43 For example, the first ECS spacecraft was injected into transfer orbit by the Ariane 1 vehicle with a spin rate of 10 rpm.

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