Specified Finite Series Control for Three-Dimensional, Multi-Phase, Optimal Reentry.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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An optimal, three-dimensional, multi-phase reentry problem is based on NASAs Mission 1 with a vehicle like the Nr-ATP delta-wing vehicles equations of motion include Earth rotation but are developed for relative velocity and express the vehicles position relative to a reference trajectory plane which is fixed to the Earth. The reentry trajectory is divided into two phases. An entry phase from reentry at 400,000 ft to first pullup is optimized with respect to pullup heat rate by maintaining 0 degree roll angle. An equilibrium-glide phase from pullup to termination at 143,000 ft is optimized by varying roll angle to minimize terminal errors, total heat absorbed, and functions of heat rate and flight path angle rate. The roll control function is formulated as a specified finite series of terms, with each term being a function of system states and having a constant coefficient. Modified author abstract
- Spacecraft Trajectories and Reentry