RU2478535C1 - Carrier rocket tail compartment bottom protection - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and may be used in carrier rocket tail compartments for protection against gas dynamic effects caused by operating rocket engines. Proposed protection comprises four moving spherical circular shields arranged at engine rotary combustion chambers, fixed shield with openings for combustion chambers mounted on engine frame, flexible plate arranged between said moving and said fixed shields. Said flexible plate is composed of thin shaped-cross-section resilient ring from titanium alloy with taper part angle in initial position exceeding similar angle in engine. Resilient ring has radial slots and gets in contact with spherical shield by outer side of its folding in spring loaded state.

EFFECT: better vibration and heat protection.

3 cl, 12 dwg

Description

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

Known bottom protection of the tail compartment of the launch vehicle block (patent No. 2347725, figure 2, IPC B64G 1/52, B64G 1/40, 2008), containing a movable annular screen with a spherical surface mounted on a rotary combustion chamber using an annular flange. The bottom protection also contains a fixed screen, made in the form of the end surface of the tail compartment. Between the mating spherical surfaces of the movable annular screen and the fixed screen, a gap is made according to the type of labyrinth seal, and the spherical surface of the fixed screen is formed by a radius (R) from the center of rotation of the rotary part of the engine.

A disadvantage of the known technical solution is the lack of sealing elements on the camera and the tail compartment, compensating for deviations of the slot gap with angular and radial displacements of the geometric axis of the camera relative to the axis of the compartment, as well as due to technological errors in their manufacture (displacement of the axes of the screens, deviation of their profile from sphericity, deviations from the flatness of the flange on the camera, etc.), i.e. for constancy of the gap gap requires high precision manufacturing and installation of movable and fixed parts of thermal protection.

In addition, the considered technical solution increases the mass of bottom protection if a four-chamber engine is installed in the compartment. When mounting a bundle of four engines in the compartment of the launch vehicle block, the technical result is not achieved and is practically unrealizable.

Known bottom protection block of the third stage of the launch vehicle "Soyuz-2" (patent No. 2347725, figure 1, IPC B64G 1/52, B64G 1/40, 2008, prototype), containing the fixed part of the device in the form of a flat circular screen 1 with a frame 2, mounted on the engine frame 3 using fastening elements 4, in which holes are made for the passage of four chambers 5. On the rotary chamber 5, a movable part of the bottom protection device is installed, which is made in the form of an annular screen 6 with a spherical surface (see figure 1) with a radius R passing through the axis of swing of the cameras s 5 (see figure 2).

A structural joint of the spherical surface of the movable annular screen 6 with the surface of the stationary flat screen 1 along the contour of the hole for the passage of the rotary chamber 5 is made with an annular slotted gap (see figure 2). The articulation of the fixed part of a flat circular screen 1 with annular screens 6 with a spherical surface is achieved using a set of flat adjusting plates 7 and profiled flexible plates 8 and 9, made with a flange located along the generatrix of the angle β of the nominal (zero) location of the chambers 5, which can swing in one plane in the range of angles βmin ÷ βmax. The articulation of the screen 1 with the shell of the tail compartment is carried out using a flexible element 10 and fastening elements 11 mounted on the end of the tail compartment 12.

The disadvantage of this technical solution is the difficulty of providing the gap required between the movable and stationary parts of the thermal protection required by the design documentation due to the influence of a large number of deviations in the relative position of the thermal protection elements and the engine:

- non-flatness of the fixed screen 1 (undulation) that occurs when forming its parts in dies and other devices;

- non-flatness of the frame 2, because it is made of a sufficiently large diameter and there are structural elements on it that cause welding;

- angular deviation of the geometric axis of the chamber 5 relative to the nominal position;

- non-perpendicularity of the location of the flange on the nozzle of the chamber 5 of its geometric axis;

- radial displacement of the axes of the chambers relative to the axis of the block and other factors.

In addition, the o-ring faces the spherical annular screen 6 with a sharp flanging edge, which can cause increased resistance to camera swing, tearing on the screen and jamming.

The non-flatness (waviness) of the fixed screen causes non-uniformity of the gap gap l around the joint of the profiled ring 8 with a spherical annular screen 6, which is in the range from l = 0 to l = l _max . This circumstance requires the introduction of stiffeners (ribs), to which it is necessary to attach a fixed screen 1.

The fastening of the fixed screen 1 to the stiffeners with screws and nuts due to their different flexibility (elasticity) causes the formation of cracks and even the destruction of the fixed screen in the places where the screw heads are pressed against vibration loads when the engine is running.

In addition, the tight fit of the fixed screen over the entire surface to the stiffeners leads to increased heat transfer from the heated screen to the stiffeners, which, in turn, weakens their strength characteristics and increases heat transfer to the tail section of the block.

Despite the presence of adjusting profiled rings in the axial and radial direction in the thermal protection design, it is not possible to achieve the required crevice gap during engine assembly and completely eliminate gas breakthrough from the engine jets, which reduces the reliability of the articulation of the movable and fixed parts of thermal protection.

The objective of the proposed technical solutions are:

1. Ensuring the necessary tightness in the joint of the movable and stationary parts of thermal protection by eliminating the gap gap, increasing the reliability of its operation and reducing weight by replacing the sealing and adjusting rings with one ring;

2. Increasing the vibration resistance of the fixed screen during engine operation;

3. Reducing heat transfer from the side of the cuts of the nozzles of the running engine in the tail compartment of the block.

The problem is achieved in that in the known technical solution containing bottom protection of the tail section of the launch vehicle block, containing four movable spherical annular screens mounted on rotary combustion chambers of the launch vehicle engine, a fixed screen with holes for passage of combustion chambers, mounted on the frame engine, a flexible plate mounted between movable spherical and flat fixed screens, according to the invention:

1. The flexible plate is made in the form of a thin elastic ring made of titanium alloy with a profiled cross section with an angle of the conical part, in the initial state, larger than a similar angle in the composition of the engine in contact with the spherical annular screen with the outer side of its flanging in a spring-loaded state, on which radial cuts are made.

2. Between the power frame and the conical casing fixed on the central ring, frames and channels of rigidity are fixed with screws and nuts, to which a fixed screen is attached with screws, and damping washers are installed between the frames, channels and a fixed screen.

3. Damping washers made of heat insulating material, such as asbestos-laminate.

Figure 3 shows the bottom protection of the tail section of the launch vehicle block; Fig. 4 shows a section through the junction of the spherical annular screen 6 and the stationary screen 1; Fig. 5 shows a view of the elastic ring 7 from the cut side of the nozzle of the chamber; Fig. Fig. 6 shows a radial section of the elastic ring 7 (lining 13 is not shown on the left), Fig. 7 shows thermal protection (top view), Fig. 8 shows a section of the central part of thermal protection on the engine, Fig. 9 shows a cross section of the junction of frames, stiffener channels with power frame 2, figure 10 p the cross-section of the junction of the frames, channels with a conical casing on the Central ring of heat protection is shown, in Fig.11 shows a cross section of the frame 13 and channel 14, Fig.12 shows a longitudinal section of the frame 13 and channel 14, where:

1 - stationary flat screen;

2 - frame;

3 - frame;

4 - stretch marks;

5 - cameras;

6 - spherical ring screens;

7 - an elastic ring;

8 - flexible element HO;

9 - fastening elements of a flexible element;

10 - tail compartment;

11 - overlays;

12 - screw;

13 - frame stiffness;

14 - channel stiffness;

15 - the central ring of protection;

16 - damping washers;

17 - screw;

18 - a nut;

19 - conical protection casing;

20 - two-nut nut;

21 - rivet.

α is the angle of the conical part of the flexible ring 7 in the initial state (before installation on the engine);

α ₁ - the angle of the conical part of the flexible ring 7 mounted on the engine;

β is the angle between the axis of the chamber and the junction of the spherical annular screen 6 with a flexible ring 7 in the zero position of the chamber;

β _min , β _max - the angles of swing of the camera in one plane;

h - radial cuts of the elastic ring 7;

δ is a section of the elastic ring 7 into two parts;

l is the gap gap.

The bottom protection comprises a stationary flat screen 1 with a frame 2, mounted on the frame 3 using stretch marks 4. The nozzles of their chambers 5 pass through the holes of the fixed screen (see Fig. 3).

Movable spherical annular screens 6 are installed and fixed on the flanges 13 of the nozzle part of the chambers 5 (see figure 4). Between the movable annular screens 6 and the stationary screen 1, profiled flexible plates are installed, made in the form of elastic rings 7, on which radial cuts h are made to facilitate their circumferential flexibility and which are flanged to the spherical screen 6 (“inverted” compared to the prototype) and pre-made with an angle α (see FIGS. 5 and 6) of the profile inclination greater than angle α ₁ (see FIG. 4) of the rings already mounted on the engine. This design feature of the ring ensures its spring-loaded fit with its flanging along the entire circumference to the spherical annular screen 6 on the rotary chamber 5, thereby compensating for the above-mentioned deviations made in the manufacture of thermal protection and motor components and their relative position after mounting on the engine. Cuts δ mm of the ring 7 overlap the local lining 13 (2 pcs.), Fixed with screws 14.

Due to the insignificant contact area of the flanging of the flexible ring 7 with the surface of the annular spherical screen 6, the thermal protection resistance to swing of the rotary chamber is minimal, and the jamming of the flexible ring 7 is completely excluded, which ensures the reliability of the components of thermal protection.

The geometric parameters of the spherical annular screen 6 and the flexible ring 7 are selected in such a way that when swinging along the radius R of the pivoting chamber in one plane around the axis of swing on both sides of its nominal position at an angle β _min ÷ β _{max, the} deformation of the ring petals ensures a smooth and tight fit the latter around the entire circumference, excluding the gap between the spherical annular screen 6 and the elastic ring 7.

Since the stationary screen 1, after molding, distorts its surface and becomes wave-like, in order to ensure its flatness between the power frame 2 and the conical casing 19 (see Fig. 8), frames 13, channels of rigidity 14 are installed on the central ring 15 (see Fig. .7) connected by screws 17 and nuts 18.

Between the frames 13, channels 14 stiffness and a fixed screen 1 placed damping washers 16 (see Fig.9, 10), made of heat-insulating material, such as asbestos laminate. Such mechanical fastening is resistant to vibration and dynamic loads acting on thermal protection from a running engine, therefore, cracking, tearing and other defects do not occur at the installation sites and nuts on thermal protection.

Due to the use of heat-insulating material for washers, for example asbestos-laminate, heat transfer from the side of the fixed screen to the frames 13, stiffeners 14, power frame 2, the central ring 15 is reduced, which ultimately has a beneficial effect on lowering the temperature in the tail section of the launch vehicle block .

For a symmetrical perception of the action of the load from vibrations, the cross section of the frame 13 and the channel 14 is made with two stiffeners (see Fig. 11), i.e. with a channel profile.

Double-eye nuts 20 are connected to the frame 13 and the channel 14 using rivets 21.

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

The movable spherical screen 6, rotating together with the camera 5, contacts its outer mirror-polished surface with the flanging of the mirror-polished flexible ring 7, which is in a spring-loaded state, which eliminates the breakthrough of gases from the working engine into the compartment of the launch vehicle block.

Thus, the proposed technical solution will allow:

1. To increase the tightness of the junction of the movable and fixed parts of the bottom thermal protection of the tail section of the launch vehicle block by eliminating the gap gap, to increase the reliability of thermal protection by eliminating the possibility of jamming of the flexible ring 7 with a spherical screen 6 during temperature deformations and to reduce the mass of the bottom thermal protection due to the replacement of several types of adjusting and sealing rings pos. 7, 8, 9 of FIG. 2 to one flexible ring 7 (FIG. 4), mounted between the spherical annular screen 6 and the stationary screen 1;

2. To increase the vibration resistance of the fixed screen due to the installation between the power frame 2 and the conical casing 19, mounted on the Central ring 15 of protection, frames 13 and channels 14 stiffness, to which the fixed screen 1 is attached, as well as damping washers 16 between the fixed screen 1 and channels 13 and frames 14;

3. To reduce the transfer of heat fluxes from the nozzles of the chambers of the working engine to the power frame 2, frames 13, channels 14 and to the tail section of the launch vehicle block.

Claims (3)

1. The bottom protection of the tail section of the launch vehicle block, comprising four movable spherical annular screens mounted on rotary combustion chambers of the launch vehicle engine, a fixed screen with holes for passage of combustion chambers, mounted on the engine frame, a flexible plate mounted between the movable spherical and flat fixed screens, characterized in that the flexible plate is made in the form of a thin elastic ring on which radial cuts are made of a titanium alloy of profiled section with an angle of the conical part in the initial state greater than a similar angle in the composition of the engine in contact with the spherical annular screen with the outer side of its flanging in the spring state. 2. The bottom protection of the tail compartment of the launch vehicle block according to claim 1, characterized in that in it between the power frame and the conical casing mounted on the central ring, frames and stiffener channels are fixed to which a fixed screen is attached with screws, and between frames, channels and a fixed screen mounted damping washers. 3. The bottom protection of the tail section of the launch vehicle block according to claim 2, characterized in that the damping washers in it are made of heat-insulating material, for example asbestos-laminate.

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