Abstract: The invention relates to the aerospace engineering and can be used for jettisoning boost rockets from an aircraft. The inventive device comprises a landing container (3) with an open end (4) provided with a high-pressure source (5). The freight to be jettisoned (2) is arranged in two sections inside the container (3) on mounting elements (10), one of which is embodied in the form of a calibrated support (9). The values of maximum efforts and acceptable lateral movements (13) of the supports (9) are chosen in such a way that a minimum positive allowance (12) between the container (3) and the freight (2) is provided. The supports (9) are provided with dampers. The aim of the invention is to reduce a transverse load affecting the freight to be jettisoned landing.

Abstract: A method for determining a position of reference axes in an inertial navigation system of an object with respect to a basic coordinate system is provided. The method includes measuring coordinates and/or speed in a basic coordinate system and an inertial coordinate system at moments of time. The method measures an acceleration vector in the inertial coordinate system at a trajectory portion of the moments of time which allows measuring of the coordinates and/or the speed. The coordinates and speed are determined by similarities in the coordinate systems at the moments of time in a portion not parallel to the trajectory portion where measurements have been made. Vectors corresponding to displacements and/or to an increase of speed of the object in the coordinate systems are determined for at least two portions of the trajectory. The vectors are used to determine a matrix of transfer between the coordinate systems.

Abstract: An aerospace system, which comprises a carrier aircraft, a launch vehicle and a payload.

Abstract: Aerospace technology, in particular, 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 Od ensuring a maximum PL 3 and a near-zero normal g-load 9.