Patent ID: 6508435
Filing Date: 2003-01-21
Classification: B64D,B64G

Abstract:
A method for controlling an aerospace system to put a payload into an orbit, comprising the steps of starting a carrier aircraft 1 with a launch vehicle 2 and the payload 3 on board from a base aerodrome 4, flying it to a launch area 5 of the launch vehicle, separating the launch vehicle from the lagging the launch vehicle 2 behind the carrier aircraft 1 with subsequent launch of the launch vehicle 2 to a predetermined trajectory point and separation of the payload 3 from the launch vehicle 2, wherein the carrier aircraft 1 at a maximum cruising speed mode 6 in the launch area 5 of the launch vehicle 2 performs a dive 7 to gain a maximum permissible horizontal flight speed, at a moment that speed is reached by the carrier aircraft, a pitchup 8 is effected at a maximum permissible angle of attack, terminating with a transition 9 to an angle of attack ensuring a near-zero normal g-loading, wherein said pitchup parameters are chosen so as to be adequate to the achievement, at a preset time tp, of a flight trajectory point where a design flight speed VD, a flight altitude HD and trajectory pitch angle &phgr;D provide a maximum launch vehicle 2 payload 3, as well as to ensure subsequent flight to the carrier aircraft 1 with allowable parameters both after separating the launch vehicle 2 and in the case of emergency non-separating the launch vehicle 2, after the carrier aircraft 1 reaches at the preset time tp a flight path point with VD, HD, &phgr;D parameters and with the near-zero normal g-loading, the launch vehicle 2 is separated from the carrier aircraft 1 and imparted with a speed relative to the carrier aircraft 1 equal to a design speed 10 at which the launch vehicle 2 lags behind the carrier aircraft 1 at a safe distance at a moment the launch vehicle 2 sustainers are ignited, and before the launch of the launch vehicle 2 to a scheduled trajectory point, the launch vehicle 2 mated with the payload 3 is turned 11 to a position differing from the vertical by an angle of 10-30Â° in a vertical plane in the launch direction.