New PDF release: An Introduction to Mission Design for Geostationary

By J.J. Pocha

ISBN-10: 9400938578

ISBN-13: 9789400938571

ISBN-10: 9401082154

ISBN-13: 9789401082150

` The publication is a good written and is appropriate for a wide variety of readers from scholars to managers drawn to studying in regards to the challenge layout challenge and research thoughts for the geo-synchronous orbit. '
Canadian Aeronautics and area magazine, March 1988

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Additional resources for An Introduction to Mission Design for Geostationary Satellites

Example text

Only then will the orbit inclination first reduce, pass through a minimum, and then increase again. This implies that the initial value of the right ascension of the orbit's ascending node must be in the region of 270 0 . 11), if the launch window is to be rendered sufficiently open as to allow a launch on most days of the year, some node shifting must be carried out as part of the apogee manoeuvre. To transfer between two orbits of different inclinations, such as the transfer orbit and the geosynchronous orbit, a manoeuvre is carried out at their point of intersection.

If, however, this brief launch slot is precluded due to the violation of anyone of the several other launch window constraints, it becomes evident that launch opportunities will be severely restricted. To open the launch window we need to expand the range of allowed positions in inertial space of either the transfer orbit or drift orbit ascending nodes. As the drift orbit node is moved away from its optimum position, the period of on-station free-drift within the inclination limit reduces, and eventually results in the need for some North-South station-keeping.

The consequences of this can be two-fold. The apogee is rapidly lowered due to the effect of aerodynamic drag, and the spacecraft suffers abnormally high heat input owing to friction with the upper layers of the atmosphere. To avoid both, the perigee must be raised before the spacecraft passes through it again. The most efficient point in the orbit at which to perform the perigee raising manoeuvre is at apogee. Half the period of the transfer orbit (about 5~ hours) is, therefore, available to identify the need for such a manoeuvre, plan the manoeuvre, achieve the correct spacecraft attitude to perform the manoeuvre, and then to command its execution.

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An Introduction to Mission Design for Geostationary Satellites by J.J. Pocha

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