RU2347725C2 - Rocket-carrier rocket tail compartment bottom protection - Google Patents

Abstract

FIELD: transport, space engineering.

SUBSTANCE: invention can be used for protection of rocket-carrier against gasdynamic effects of working engine jets. Proposed protection, according to this invention, contains the mobile ring screen with the spherical surface, fitted on the rotary combustion chamber of the carrier engine, the motionless screen and a slot-like gap between the said screens. Note here that the motionless screen represents an end face spherical surface of the tail compartment casing, formed by the radius from the centre of rotation of a rotary part of the engine. The mobile ring screen overlaps the motionless screen over its spherical surface. The said slot-like gap is located in the zone of overlapping of said spherical surfaces of screens to allow changing the direction of gas flows affecting the aforesaid compartment.

EFFECT: decreased weight of bottom protection, higher reliability and efficiency.

2 dwg

Description

The invention relates to rocket and space technology and can be used in the construction of the tail blocks of launch vehicles to protect them from the gas-dynamic effects of a working engine.

The bottom protection of the block of the third stage of the Soyuz-2 carrier rocket is known (working drawings No. 14D23.00-00.000GCH developed by JSC KBHA Voronezh), containing the fixed part of the device in the form of a flat circular screen 1, mounted on the engine frame 2 using elements fastening 3, in which a hole is made for the passage of the combustion chamber 4. On the rotary combustion chamber 4, a movable part of the bottom protection device is installed, which is made in the form of an annular screen 5 with a spherical surface (Fig. 1, prototype).

Constructive coupling of the spherical surface of the movable annular screen 5 with the surface of the stationary flat screen 1 along the contour of the hole for the passage of the rotary combustion chamber 4 is made with an annular gap gap. The articulation of the fixed part of the flat circular screen 1 with the engine is provided using profiled flexible plates 6 and fastening elements 7 mounted on the end of the tail compartment 8.

The disadvantages of the known technical solutions are the large weight of the bottom protection due to the presence of structural elements that make up the tail section and the engine itself, ensuring the articulation of the tail section and the engine, as well as the low reliability of its operation due to the possible spell of the movable and fixed parts due to gas dynamic and temperature deformations during engine operation.

The objective of the proposed technical solution is to reduce the weight of bottom protection, as well as improving the reliability and efficiency of its functioning.

The task is achieved in that the bottom protection of the tail section of the launch vehicle block comprises a movable annular screen with a spherical surface mounted on a rotary combustion chamber of the launch vehicle engine, a fixed screen, and has a gap gap, while the fixed screen is made in the form of an end spherical surface the body of the tail compartment, formed by a radius from the center of rotation of the rotary part of the engine, and the movable annular screen is configured to overlap the stationary screen in its sphere surface-symmetric, and the slit gap is located in the overlap zone sferecheskih surfaces, changing the direction of movement of the working gas acting engine.

Figure 2 presents the bottom protection of the tail section of the launch vehicle block, which contains a movable annular screen 1 with a spherical surface mounted on a rotary combustion chamber 2 using an annular flange 3. The bottom protection also contains a fixed screen 4, made in the form of the end surface of the tail compartment 5. Between the mating spherical surfaces of the movable annular screen 1 and the stationary screen 4, a slotted gap 6 is made as a labyrinth seal, and the spherical surface of the stationary crane 4 is formed by a radius (R) of the center of rotation of the rotary part of the engine 7.

The geometric parameters of the screens 1, 4 are selected in such a way that they provide a certain area of overlapping of their surfaces when the movable screen 1 is rotated together with the combustion chamber 2 by a certain angle relative to the longitudinal axis of the tail compartment 5.

The bottom protection of the tail section of the launch vehicle works as follows.

The movable screen 1, rotating together with the combustion chamber 2, constantly overlaps the fixed part of the bottom protection without contact of their parts due to slotted gap 6 according to the type of labyrinth seal, which changes the direction of movement of the acting gases from the working engine.

Thus, the proposed technical solution will reduce the weight of the bottom protection of the tail section of the launch vehicle block due to the exclusion from the structure of its structural elements 6, 7, designed to articulate the tail section with a fixed engine crane, as well as a fixed screen with elements of cremation 1, 3 to the engine frame, and to increase the reliability and efficiency of the bottom protection by increasing the gap gap, made as a labyrinth seal, which eliminates jamming on moving and stationary parts due to temperature and gas-dynamic deformations during engine operation.

Claims (1)

The bottom protection of the tail section of the launch vehicle block, comprising a movable annular screen with a spherical surface mounted on a rotary combustion chamber of the launch vehicle engine, a fixed screen and a gap between the screens, characterized in that the fixed screen is made in the form of an end spherical surface of the tail compartment body formed by the radius from the center of rotation of the rotary part of the engine, while the movable annular screen is made with the overlapping of the stationary screen on its spherical surface so that the specified gap is located in the zone of the specified overlap, providing a change in the direction of movement of the acting gases from the working engine.

Images