RU2534464C1 - Carrier rocket tail compartment bottom protection - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention can be used for carrier rocket tail compartment bottom protection against gas-dynamic effects caused by liquid-propellant engine jets. Proposed protection comprises moving circular shield with flange and spherical surface mounted at rotary combustion chamber of carrier rocket engine, fixed spherical shield with flange and mid spherical shield with flange. Mid shield overlaps the clearance between said moving and fixed shields at chamber turn. Spherical surfaces of all said shields have one centre of spheres aligned with that of chambers oscillation.

EFFECT: higher efficiency, decreased weight and overall dimensions.

2 cl, 1 dwg

Description

The invention relates to rocket and space technology and can be used to protect the tail compartments of launch vehicles from the gas-dynamic effects of jets of working liquid rocket engines (LRE).

Known bottom protection of the tail section of the launch vehicle (RF application with a positive decision No. 20111146508 dated 11/16/2011, IPC B64G 1/52, B64G 1/40) containing a fixed part in the form of a flat screen and an elastic ring with radial cuts mounted on the frame engine, and the moving part in the form of a spherical annular screen mounted on a rotary combustion chamber (KS).

A disadvantage of the known technical solution is the insufficient thermal protection of the units of the tail section of the launch vehicle due to the possibility of formation of a gap gap with a radial displacement of the axis of the CS relative to the axis of the elastic ring, since these axes are not interconnected, as well as significant weight and size characteristics of the device due to the large diameter a movable spherical annular screen, necessary to close the gap between the CS and the stationary elastic ring in the zero position of the CS and when it is deflected by predetermined angle of control of the thrust vector of the launch vehicle.

Known bottom protection of the tail section of the carrier rocket (patent No. 2347725 from 11/20/2006, IPC B64G 1/40, IPC B64G 1/52, prototype) containing fixed and movable spherical annular screens with an annular target gap between them.

A disadvantage of the known technical solution is the lack of thermal protection of the units of the tail section of the launch vehicle due to the presence of an annular slotted gap with significant weight and size characteristics of the device due to the large diameter of the movable ring screen, which is necessary to ensure that the gap between the CS and the stationary screen in the zero position of the CS and when it is rejected by a given angle of control of the thrust vector of the launch vehicle.

The task to which the proposed technical solution is directed is to increase the efficiency of thermal protection of the units of the tail section of the launch vehicle during the operation of the rocket engine and reduce the overall dimensions of the bottom protection.

This problem is solved in that in the bottom protection of the tail section of the launch vehicle containing a movable annular screen with a spherical surface mounted on a rotary CS of the engine of the launch vehicle and a fixed spherical screen, according to the invention, at least between the movable and fixed screens one intermediate spherical screen so that it overlaps the gap between the movable and fixed screens when the CS is rotated, and the spherical surfaces of the movable, fixed and intermediate screens are They have one center of spheres, which coincides with the center of swing of the camera. In addition, the movable, fixed, intermediate screens have a persistent shoulder.

The specified set of features exhibits new properties, namely, due to the introduction of an intermediate screen, the overall dimensions of the device are reduced by reducing the external diameters of the movable and fixed screens while maintaining a given angle of deflection of the CS. At the same time, the introduction of a larger number of intermediate screens allows these diameters to be reduced more. The presence of thrust flanges on the movable, fixed and intermediate screens allows the gap to be closed between the CS and the fixed bottom protection screen for any deviations of the CC within the specified angle of the CC deviation, since the contact flanges do not allow the intermediate screen to deviate from the zero position more than the gap between the CS and a fixed bottom protection screen.

In addition, the implementation of the movable, fixed and intermediate screens spherical with a common center of spheres coinciding with the center of swing of the compressor, will improve the thermal protection of the units of the tail section of the launch vehicle during the operation of the rocket engine due to the fact that the screens are jointly installed on the control panel and installed together with the control panel in the compartment with respect to the bottom protection, which allows them to freely slide relative to each other without the presence of an annular gap between them.

The presence of persistent collar of the screens increases their rigidity, which will allow them to move relative to each other without jamming and jamming.

The schematic diagram of the invention is presented in figure 1, where

1 - bottom protection;

2 - a tail compartment;

3 - movable annular screen;

4 - combustion chamber;

5 - fixed spherical screen;

6 - intermediate spherical screen;

7 - persistent shoulder.

The bottom protection 1 of the tail section 2 of the launch vehicle contains a movable annular screen 3 with a spherical surface that is mounted on the COP 4. A fixed spherical screen 5 is installed on the bottom protection 1. An intermediate spherical screen 6 is installed between the movable 3 and the stationary 5 screens, which has the ability move between them. All three screens have one center of their spherical surfaces, which are in contact with each other, and this center coincides with the center of swing of the CS. All three screens have persistent beads 7.

The bottom protection 1 of the tail compartment 2 of the launch vehicle operates as follows. When the COP 4 is rejected, the movable screen 3 mounted on the combustion chamber slides along the intermediate screen 6. The stop collar 7 of the movable screen 3, having reached the contact collar 7 of the intermediate screen 6, will begin to shift the intermediate screen 6. In this case, the intermediate screen 6 will begin to slide on the fixed screen 5 until it touches its thrust shoulder with the thrust shoulder of the stationary screen 5, which is mounted on the bottom protection 1 of the tail section 2 of the launch vehicle. When the thrust collars of the three screens touch, KS 4 will reach its extreme position. In this case, on the other hand, the intermediate screen 6 overlaps the increased gap between the movable 3 and the stationary 5 screens.

Thus, the intermediate screen 6 can be displaced between the movable 3 and the stationary 5 screens until it contacts their thrust shoulders 7 and the gap between them will always be covered by the intermediate screen 6.

Thus, the proposed technical solution will improve the thermal protection of the units installed in the tail compartment of the launch vehicle and on the KS itself, due to the absence of gaps between the screens, which, due to the common center of their spherical surfaces, coinciding with the center of swing of the KS, can slide freely relative to each other, and reduce the weight and size characteristics of the bottom protection by reducing the outer diameters of the movable and fixed screens while maintaining a given angle of deviation of the COP.

Claims (2)

1. The bottom protection of the tail section of the launch vehicle, comprising a movable annular screen with a spherical surface mounted on a rotary combustion chamber of the engine of the launch vehicle, and a fixed spherical screen, characterized in that at least one intermediate is installed between the movable and stationary screens the spherical screen so that it covers the gap between the movable and fixed screens when the camera is rotated, in addition, the spherical surfaces of the movable, fixed and intermediate screens have one price p spheres, which coincides with the center oscillation chamber. 2. The device according to claim 1, characterized in that the movable, stationary, intermediate screens have a thrust shoulder.