RU2422336C1 - Method for creation of heat channel for spacecraft injection into earth orbit using "gun" start - Google Patents

Abstract

FIELD: transport. ^ SUBSTANCE: invention concerns aerospace vehicle (ASV) start form planet surfaces. The method includes ASV start from electromagnetic or gas-dynamic gun with simultaneous creation of heat channel to reduce drag force while ASV passes dense atmosphere. In this process, at the moment before ASV launching, the main laser beam of superthreshold intensity is generated by means of ground complex. This beam is directed along gun axis through a mirror located on gun diaphragm. Additionally, initiating laser beam is directed so that at the place of the main and initiating beams superimposition there would be area where laser emission intensity is enough for air breakthrough. Thereby the conditions arise to start laser-supported detonation mode of the main beam laser radiation absorption along gun axis. Laser-supported detonation wave creating the mentioned heat channel should come to the mirror (on diaphragm, at barrel edge) just at the moment when ASV exits gun. ^ EFFECT: simplification of ASV drag force reducing heat channel creation facilities by means of avoiding usage in atmosphere or near-Earth space of high-level facilities for remirroring the main beam creating heat channel. ^ 5 dwg

Description

The invention relates to rocket and space technology and can be used to launch from the Earth both unmanned and manned aerospace vehicles.

At present, one of the promising directions for bringing payloads to near-earth orbit is considered to be a “cannon” launch, i.e. Conclusion of the payload into near-Earth orbit using an electromagnetic or gas-dynamic gun. In this case, the payload apparatus is accelerated to a speed of about 10 km / s. However, when flying out of the gun, an intensive decrease in the speed of the aircraft occurs due to the high density of the atmosphere near the surface of the Earth. (RU 2343091 2009.01.10; RU 2239586 C3 2002.11.27; IEEE Transaction on Magnetics, vol. MAG-20. No 2. Mach 1984, pp.227-228; US 5950543 A, 09/14/1999; US 4795113 A, 03.01 .1989; US 4881446 A, 11/21/1989; Anatoly Shibanov. Concerns of the space architect. - M.: Children's Literature, 1982, pp. 14-16, 28, 29).

When developing promising samples of rocket and space technology, it becomes necessary to provide the required aerodynamic characteristics, namely a low drag coefficient and a given aerodynamic quality. In traditional ways, for example, by improving the geometry of the aircraft, this is impossible to achieve.

A known method of launching an aerospace vehicle into near-Earth orbit (RU 2343091 2009.01.10), in which to reduce the drag force of an aerospace vehicle when flying in dense layers of the atmosphere, a heat channel is used that is created in the atmosphere at the time the spacecraft leaves the gun ( (1) FIG. 1) using a ground-based laser complex ((2) of FIG. 1) through a mirror ((3) of FIG. 1), by means of a light-detonation regime for absorbing laser radiation ((4) of FIG. 1) in atmospheric air located within the beam.

The disadvantage of this prototype is that the laser beam ((4) of FIG. 1) is directed through a mirror ((3) of FIG. 1) located in the atmosphere or near-Earth outer space, while the solutions to the problems of orientation and keeping it stationary are not considered mirrors for a period of time until a heat channel of the required length is created (RU 2343091 2009.01.10).

The objective of the invention is to simplify the system for creating a heat channel due to the rejection of the presence in the atmosphere or near-Earth space of technical devices for transmitting the main laser beam.

This technical result is achieved in that two laser beams are used to simplify the system for creating the heat channel needed to reduce high drag when flying in dense layers of the atmosphere of an aerospace vehicle.

The invention is illustrated in figure 2, 3, 4 and 5.

Figure 2 shows the moment before the launch of the aerospace vehicle. The main laser beam above the threshold intensity (4), created using the ground-based laser complex (2), through the mirror ((6) of figure 3) located on the membrane of the gun ((7) of figure 3), is directed coaxially to the barrel of the gun (1) . The initiating laser beam (5) is guided in such a way that at the boundary of the realizability of the light-detonation regime at a height H, a region ((8) of FIG. 4) is formed where the laser radiation intensity is sufficient for air breakdown. In the region where two laser beams coincide ((8) of Fig. 4), an air breakdown occurs and conditions arise for the start of the light-detonation regime of absorption of the laser radiation of the main beam above the threshold intensity (Polonsky L.Ya., Pyatnitsky L.N. Continuous extended laser sparks in air . / Atmospheric Optics. No. 7 1988, p. 86-92).

Figure 5 shows the motion scheme of the light-detonation wave (9) towards the laser radiation of the main beam (4). Light detonation wave propagates at a speed of the order of 100 km / s. A thermal channel (10) with a high temperature and low density is formed in the wave trace. At the time of the release of the aerospace vehicle from the gun, the light-detonation wave (9) reached the mirror. Thus, along the axis of the gun to a height H (FIG. 2), a heat channel (10) was formed with high temperature and low density.

A comparative analysis of the proposed method with prototypes shows that the creation of a heat channel by means of a light-detonation regime for absorbing laser radiation in atmospheric air using two laser beams (the main and the initiating) can not only achieve a significant reduction in drag when the aircraft passes through dense layers of the atmosphere until while the controls of the device keep it in the heat channel (RU 2343091 2009.01.10), but it also allows you to simplify the system for creating heat channel due to non-use of atmospheric or near space engineering devices for the transmission of the main laser beam.

The proposed method allows to abandon the use in the atmosphere or near-Earth space of technical devices for transmitting the main laser beam.

Claims (1)

A method of launching an aerospace apparatus into near-Earth orbit using a heat channel to reduce drag and to reduce speed losses when the aircraft passes dense layers of the atmosphere based on a launch from an electromagnetic or gas-dynamic gun installed at an angle to the horizon, providing the required predetermined initial trajectory apparatus, characterized in that at the time before starting the apparatus, the main laser beam above the threshold intensity generated by by means of the ground-based laser complex, through a mirror located on the membrane of the gun, they are directed coaxially to the barrel of the gun, and the initiating laser beam is directed so that in the region where the main and initiating beams coincide, a region is formed where the laser radiation intensity is sufficient for air breakdown and conditions to start detonation mode of absorption of laser radiation of the main beam, and at the time of the exit of the aerospace apparatus from the gun, the detonation wave reached the specified mirror At the same time, a thermal channel was formed, which made it possible to abandon the presence in the atmosphere or near-Earth space of technical devices for transmitting laser radiation from the main laser beam.

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