RU2159727C1 - Method of injection of payload into orbit in space - Google Patents

Abstract

FIELD: space engineering; air start of launch vehicles. SUBSTANCE: preparation and take-off multi-mode accelerating aircraft are performed at aerodrome at sufficient distance from launch area and safe route of flight. Flight to this area is performed at mode of maximum flying range. At approach to zone, accelerating aircraft gains altitude and supersonic flying speed. Then, zoom is performed and launch vehicle is separated after required pitch angle has been achieved. It is good practice to ensure zero angle of attack of launch vehicle at moment of launch. Then, accelerating aircraft is brought to mode of command measuring station for tracking the payload before it is put in preset orbit, after which accelerating aircraft is returned to landing aerodrome. EFFECT: increased mass of payload injected into near-earth orbit of preset inclination. 3 cl, 1 dwg

Description

 The invention relates to aerospace engineering, and in particular to methods for launching a payload (object) into space using an aerospace rocket and space system (ARKS).

 A known method of launching an aerospace aircraft into orbit (RU N 2000257 C, B 64 G 1/14 of 10/15/91 [1]), including refueling the fuel tanks of an aerospace aircraft (VKS) and its docking with a carrier aircraft, joint start, set-up of a given height and flight to a given area of the carrier aircraft and the VKS docked with it, separation of the VKS from the carrier and its acceleration to space speed, the fuel tanks of the VKS are partially filled, and before the separation of the VKS they are refueling from an additional tanker aircraft into tanks which is run by nedos ayuschuyu portion of the fuel is performed while rise and outputting the tanker aircraft in the area following the carrier aircraft with videoconferencing. At the same time, refueling of the HVS is carried out using refueling lines located on the carrier aircraft. A significant drawback of this technical solution is the high unit cost of putting the payload into orbit into space [2]. This is primarily due to the fact that such a method, in principle, does not allow to reduce the cost of rocket fuel for the withdrawal of the aerospace forces after starting the flight path, and also requires an increase in the number of staff units serving the flight of the aerospace forces.

 The well-known technical solution for launching a payload into space using an An-124 transport aircraft and the Polet carrier rocket allows to reduce specific launch performance by no more than 30% compared to a traditional launch [3]. The complex process of separation of the launch vehicle and strong alternating loads at the same time led to a significant increase in the mass of the design of the launch vehicle. The implementation of the vertical launch of the launch vehicle after separation from the carrier aircraft does not allow the kinetic energy of the carrier aircraft, reported to her during separation. For this reason, this method does not allow us to bring payloads weighing about 1000 kg into high orbits, while reducing unit costs.

 The closest technical solution is a launch vehicle dropped from a carrier aircraft, the method of its launch in the air and flight control (RU N 2026798 C1, 6 B 64 D 5/00, F 42 B 15/00 - [4], [5 ] is the prototype). However, such a technical solution does not provide the launch into space in high orbits of payloads weighing more than 500 kg.

 The aim of the invention is to develop a method of putting the payload into orbit into space, which ensures the lowest unit cost of achieving a technical result: putting the greatest payload into space into a given orbit with a given inclination.

 The essence of the invention is a method of launching a payload into orbit into space, including preparation for flight and take-off of a multi-mode launch vehicle with a launch vehicle from an aerodrome, flight to the launch area of a launch vehicle with or without refueling, acceleration and climb when approaching to the launch zone of the launch vehicle, maneuver of the launch vehicle, separation and launch of the launch vehicle, transfer of the launch vehicle to the mode of the command and measurement point, tracking of the displayed object until it enters orbit from refueling oh in the air or without it and return to the landing aerodrome.

The specified technical result is achieved in that a multi-mode accelerator aircraft with one or more launch vehicles is used to derive the payload. Preparation of the booster aircraft and launch vehicles for flight and take-off is carried out from the aerodrome, which is at the shortest distance to the launch zone of the launch vehicle at the safest flight route. After takeoff, in order to reduce kilometer fuel consumption, the accelerator aircraft flies to the launch zone of the launch vehicle at the longest flight range mode 1 (see drawing). If necessary, in order to increase the flight range, the accelerator aircraft performs an intermediate landing with refueling or refueling in the air. When approaching a predetermined intermediate point of the route (MRP) 2, it accelerates to a predetermined or ultimate supersonic speed with a climb in a predetermined direction to the separation point of the launch vehicle 3. After reaching the specified flight speed, altitude and geographical coordinates, the accelerator aircraft performs a hill maneuver "4. The maneuver parameters of the booster aircraft and the moment of separation of the launch vehicle are determined on the basis of the condition of ensuring a zero angle of attack of the launch vehicle at the time of launch and the minimum overload and in implementing it as a plane-overclockers maneuver, and for all time-to a predetermined trajectory. When the booster plane reaches the required pitch angle, the carrier rocket is separated. Moreover, at the time of separation of the launch vehicle, the accelerator aircraft provides normal overload n _{y of} at least 1.2. The propulsion system of the launch vehicle is launched when the launch vehicle reaches a predetermined pitch angle with free movement along a ballistic trajectory after separation from the accelerator aircraft. Thus, the specified order of events when launching the launch vehicle provides it with minimal kinetic energy losses due to the necessary time delay for starting the propulsion system and the required angular rotation to enter the flight path. After turning on the propulsion system, the launch vehicle is independently displayed along the optimal trajectory (optimality criterion: orbit height H = H _max for a given payload mass) to a given orbit. After separation of the launch vehicle, the booster aircraft is automatically switched to the command-and-measurement point mode to accompany the payload being discharged until it reaches a given orbit and at the same time exits the maneuver. In this mode, the course, altitude and flight speed of the accelerator aircraft are determined taking into account the trajectory of the payload launch into space. Combining the functions of a booster aircraft and an aircraft command and control point within one aircraft allows reducing the number of staff units in the ARKS and simplifying the process of launching a payload into space. If necessary, after the end of the maneuver, without interrupting the tracking of the object, the booster aircraft is refueled in the air to ensure the required duration of the remaining part of the flight, return to the airfield and land.

 Thus, the specified method of launching the payload into space allows you to achieve the above technical result. In this case, the total effect of reducing the unit cost of putting the payload into space is achieved by reducing costs at each stage and reducing the number of staff units in the ARKS.

Sources of information
1. RU N 2000257 C, B 64 G 1/14 dated 10.15.91.

 2. News of foreign science and technology. Series: Aviation and rocket technology. Status of work on promising aerospace aircraft abroad. TsAGI named prof. NOT. Zhukovsky, N 13, 1988, p. 1-3.

 3. Flying spaceport. "Science and Life", N 11, 1999, p. 49.

 4. RU N 2026798 C1, 6 N 64 D 5/00, F 42 V 15/00.

 5. News of foreign science and technology. Series: Aviation and rocket technology. Pegasus cruise carrier rocket. TsAGI named prof. NOT. Zhukovsky, N 20, 1989, p. 22-29.

Claims (3)

 1. A method of launching a payload into orbit into space, including preparation for flight and take-off of a multi-mode launch vehicle with a launch vehicle from an aerodrome, flight to the launch area of a launch vehicle with or without refueling, acceleration and climb when approaching launch vehicle launch zone, booster aircraft maneuver, launch vehicle booster separation and launch, transfer of the booster aircraft to the command and control point mode, escort of the displayed object until its launch into orbit, with refueling of the booster aircraft or it, and return to the landing aerodrome, characterized in that preparation for flight and take-off is carried out from the aerodrome, which provides the smallest distance to the launch zone of the launch vehicle with the safest flight route, flight to the specified launch zone is carried out in the longest flight range mode, and when approaching a predetermined intermediate point of the route, accelerate to a predetermined or ultimate supersonic speed with a climb in a given direction to the separation point of the launch vehicle, after reaching the specified speed the flight, altitude and geographical coordinates perform the “hill” maneuver by the booster plane and, upon reaching the required pitch angle, launch the carrier rocket, launch its propulsion system and move along the optimal trajectory, and the booster plane is put into the command and measurement point mode to accompany the displayed payload before it enters a given orbit.  2. The method of launching a payload into orbit into space according to claim 1, characterized in that the parameters of the maneuver "hill" and the moment of separation of the launch vehicle are determined on the basis of the conditions for ensuring a zero angle of attack of the launch vehicle at the time of launch and the minimum overload on it during the implementation of the maneuver and during the entire time of reaching the given trajectory.  3. The method of putting the payload into orbit into space according to claim 1, characterized in that the transfer of the booster to the mode of the command and measurement point to accompany the displayed payload is carried out automatically during separation of the launch vehicle, with the course, altitude and flight speed the booster aircraft is determined taking into account the trajectory of launching the payload into space.