ATTITUDE CONTROL SYSTEM FOR REENTRY VEHICLE

摘要

PURPOSE:To aim at the relief of a large elevation attitude and the increase of weathercock stability by receiving turning force to two turbine blades at bilateral symmetric position by air out of an air intake at time of taking a flight at the atmosphere, and changing a pitch of the blade with a drag control means. CONSTITUTION:Two turbines 1a, 1b as an attitude control system are attached to respective spots separated at the same distance right and left from a fuselage axis. Compressors 2a, 2b are operated by these turbines 1a, 1b, whereby compressed air is stored, sprayed out of each of nozzles 4a- 6a, 4b- 6b, thus a body attitude is controlled. At time of taking a flight at the atmosphere, air from air intakes 7a, 7b hits on each blade of the turbines 1a, 1b and thereby turning force is received. A pitch of each blade is changed according to a yaw-axis control signal and drag is controlled by a drag controller. With this constitution, body elevation can be made smaller, and symmetric pitches are changed whereby motion around a yaw-axis is controllable, so that weathercock stability is increased.