FIELD: aviation rocketry, in particular, methods for injection of payloads to low and medium near-earth orbits according to the air-start pattern of launch vehicle from the carrier aeroplane. SUBSTANCE: after arrival at the maximum cruising flight to the launching area a dive of the carrier aeroplane is accomplished, and at the instant of gain of the maximum flight speed by it a maximum flight speed by it a pitch-up with a maximum allowable angle of attack is accomplished. Then transition to the angle of attack creating a g-load close to zero-G is effected. The pitching parameters are such that the aeroplane at the instant of separation of the rocket with the payload from it has a speed, flight altitude and trajectory giving the maximum injected payload, and a normal acceleration close to zero-G. At separation the velocity lag from the aeroplane to a safe distance is imparted to the rocket by the moment of starting of cruise engines. With the aid of these engines, or before their starting (by auxiliary engines) the rocket with the payload is turned through an angle of 10 to 30 deg. to the vertical in the direction of injection. At rocket separation the carrier aeroplane is stabilized in the inertial coordinate system. EFFECT: enhanced reliability and economical efficiency of delivery of payload with a maximum capacity to the orbit or pre-set area of the Earth or Universe ocean. 4 cl, 1 dwg
