Optimal trajectories for the Aeroassisted Flight Experiment. Part 1: Equations of motion in an Earthfixed system
Abstract
The determination of optimal trajectories for the aeroassisted flight experiment (AFE) is discussed. The AFE refers to the study of the free flight of an autonomous spacecraft, shuttlelaunched and shuttlerecovered. Its purpose is to gather atmospheric entry environmental data for use in designing aeroassisted orbital transfer vehicles (AOTV). It is assumed that: (1) the spacecraft is a particle of constant mass; (2) the Earth is rotating with constant angular velocity; (3) the Earth is an oblate planet, and the gravitational potential depends on both the radial distance and the latitude (harmonics of order higher than four are ignored); and (4) the atmosphere is at rest with respect to the Earth. Under these assumptions, the equations of motion for hypervelocity atmospheric flight (which can be used not only for AFE problems, but also for AOT problems and space shuttle problems) are derived in an Earthfixed system. Transformation relations are supplied which allow one to pass from quantities computed in an Earthfixed system to quantities computed in an inertial system, and vice versa.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 1989
 Bibcode:
 1989STIN...9013441M
 Keywords:

 Atmospheric Entry;
 Equations Of Motion;
 Flight Mechanics;
 Orbit Transfer Vehicles;
 Trajectory Optimization;
 Transfer Orbits;
 Aeromaneuvering;
 Angular Velocity;
 Hypersonic Speed;
 Orbital Velocity;
 Spacecraft Control;
 Spacecraft Reentry;
 Astrodynamics