| 摘要 |
The invention relates to aerospace technology, in particular, to methods for orbital injection of payloads (communication satellites, monitoring satellites, etc.) into low and medium earth orbits with the aid of aerospace systems comprising a carrier aircraft (CA) and a launch vehicle (LV) with a payload (PL). In the present method, after the CA 1 takeoff from the base aerodrome, its flight in the maximum cruising speed mode to the LV 2 launch area, pitchdown 7 of the CA 1 is effected to gain the maximum permissible horizontal flight speed, and at the moment that speed is attained, CA 1 pitchup 8 with the maximum allowable angle of attack is executed, culminating in transition to an angle of attack with a near-zero g-load (zero-gravity condition), with the pitchup parameters chosen so that at the LV 2 with PL 3 point of separation from the CA 1, the CA 1 has attained a speed VD, flight altitude HD and a trajectory pitch angle &thetas;D ensuring a maximum PL 3 and a near-zero normal g-load 9. Separation of the LV 2 from the CA 1 is executed, imparting the LV 2 with a CA 1 related speed assuring that the LV 2 lags behind the CA 1 at a safe distance 10, then the LV 2 sustainers are fired, and, either prior to the sustainers' ignition (by extra power units), or after the ignition (by sustainers), the launch vehicle with the PL 3 is turned into a position differing from the vertical by an angle of 10 - 30 DEG in the vertical plane in the launch direction 11. At the LV 2 - PL 3 separation point 22, the CA 1 position is stabilized in an inertial coordinate system. The present invention makes it possible to safely, efficiently and with maximum payload capacity, place payloads into designated orbits and deliver payloads to given terrestrial and oceanic areas. <IMAGE> |
