RU80221U1 - STARTING COMPLEX FOR SPACE MISSILE Rocket - Google Patents

Abstract

A launch complex is proposed, consisting of a missile with a diameter d _p , a launch channel, a multi-slope gas-reflecting device, flume-type gas ducts and an overlap in which a launch channel is made expanding from the inlet d on the outer surface of the complex to the outlet outlet D of the overlap at an air flow rate at the exit of the launch channel Vp> 150 m / s, the ratio of the areas of the inlet and outlet openings is: S _D / S _d > 3, where S _d = 0.25π (d ² -d ² _p ) is the area of the inlet of the start channel; S _D = 0.25π (D ² -d ² _p ) is the area of the outlet of the launch channel. 1 ill.

Description

The utility model relates to the field of rocket and space technology and can be used for ground launch of space rockets.

Missile systems are known [Afanasyev E.V., Baloban V.I., Bobyshev S.V., Dobroserdov I.L. / Structural-element modeling of gas-dynamic processes at rocket launch. - Ball. state technical un-t SPb., 2004, pp. 1-9, (416 pp.)], Consisting of a rocket, a multi-rolled gas-reflecting device, flume-type waste gas and the ceiling in which the rocket is mounted. When the rocket starts, the expiring jets act on the multi-slope gas-reflection device. The flow resulting from this, propagating through the flues of the chute type, is divided into a direct flow and an annular reverse flow directed to the rocket body. With certain parameters of the rocket propulsion system and its position relative to the gas deflector, the annular reverse flow can cause heating of the rocket body, which is strictly limited or not at all acceptable [G. Biryukov. B. Grankin, V. Kozlov, V. N. Soloviev ./ Fundamentals of the design of space rocket complexes). - St. Petersburg: Alphabet, 2002, S. 264-265].

The objective of the utility model is to reduce the overall dimensions of the launch complex, provided that there is no ring backflow effect on the space rocket body.

This problem is solved in that in a launch complex consisting of a rocket with a diameter d _p , a launch channel, a multi-slope gas deflector, flume-type ducts and a ceiling, the launch channel is made in the ceiling expanding from the inlet d on the outer surface of the complex to the outlet D of the overlap.

The maximum velocity in the jet mixing layer is established experimentally and is 2500 m / s. The transverse velocity at the boundary of a circular jet is 2%, that is, 50 m / s [Theory of turbulent jets / Abramovich GN, Girshovich TA, Krasheninnikov S.Yu. and etc.; under the editorship of G.N. Abramovich. - 2nd ed., Revised. and add. - M .: Nauka, 1984. p. 56-57]. To obtain the air flow velocity at the exit to the start channel Vп> 150 m / s, from the continuity equation, the ratio of the areas of the inlet and outlet openings has the form:

S _D / S _d > 3, where

S _d = 0.25π (d ² -d ² _p ) is the area of the inlet of the launch channel;

S _D = 0.25π (D ² -d ² _p ) is the area of the outlet of the launch channel.

Figure 1 shows a longitudinal section of a launch complex for space rockets.

The launch complex contains a rocket 1 (d _p ) located in the launch channel 2, made in the ceiling, expanding from the inlet (d) on the outer surface of the complex to the outlet (D) of the ceiling 3. In addition, the launch complex contains flume ducts 4 and gas reflective device 5.

The launch complex works as follows. When the jets of the rocket 1 engines are exposed to the multi-slope gas-reflecting device 5, the direct flow propagates through the flues of the tray type 4, the formation of an annular reverse flow directed to the rocket 1, and the appearance of the air flow in the launch channel 2 due to ejection by flowing air jets. The ratio of the areas S _{d of the} inlet d on the outer surface of the complex and S _D of the outlet D of the start channel 2, made expanding in the floor 3, should be selected more than 3 so that the air flow velocity Vп at the entrance to the start channel 2 is at least 150 m / C., this condition allows you to get the resulting flow around the rocket over the complex, directed into the channel, thereby significantly

prevent or reduce the thermal effect of the annular reverse flow on the spacecraft’s hull.

The launch complex has a number of significant advantages compared to the known ones. One of them is the reduction of costs for the construction and operation of complexes due to their smaller dimensions. In addition, relatively inexpensive modernization is possible, i.e. the use of existing systems to launch missiles of greater power. Due to the fact that the proposed complex provides for the removal of hot gases of the reverse annular flow from the space rocket body, its launch is more reliable, and the lower part of its body can be made thinner, which makes it possible to put a payload into orbit with the same fuel costs more weight.

Claims (1)

A launch complex comprising a missile with a diameter of d _p , a launch channel, a multi-slope gas deflector device, flume-type ducts, an overlap, characterized in that the launch channel is made expanding from an inlet d located on the outer surface of the complex to an exit opening D of the overlap, wherein the ratio of the area of the inlet and outlet is S _D / S _d > 3, where S _d = 0.25π (d ² -d ² _p ) is the area of the inlet of the launch channel; S _D = 0.25π (D ² -d ² _p ) - the area of the outlet opening of the launch channel, to obtain the air flow rate at the exit to the launch channel Vп> 150 m / s.