RU2553402C1 - Reusable return stage step of carrier rocket - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: reusable return stage of a carrier rocket contains a direct rotary wing with the inclined heat-insulated wall and a tip from heat resisting material designed as separate sections with a possibility of free deformation during heating, return engines, fuel system with fuel for return engines placed in the wing front part, in the wing tip along its whole span in compartments, the central compartment in front part of the centre wing section with the function of feed tank.

EFFECT: increase of reliability and decrease of temperature deformations and tension, structure weight.

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Description

The invention relates to rocket and space technology and can be used to create returnable reusable winged stages of launch vehicles.

From the patent literature there is known a technical solution chosen 'as a prototype, where the reusable return stage of the launch vehicle contains a direct rotary wing mounted on the body with the possibility of fixing it in position along the axis of the stage at the launching stage and rotated 90 ° at the stage of return flight, with the fuel system located in it with fuel, which ensures the operation of return engines (see RF patent No. 2148536, class B64G, 1/14 dated 10.26.1999).

The disadvantages of this technical solution are.

When flying an aircraft with a direct wing, the occurrence of self-excited oscillations in the wing (flutter).

During descent - braking, the windward surface of the wing, and especially its nose, undergoes intense unsteady heating with large temperature gradients both in depth and on the outer surface of the wing structure. Heating reduces the strength characteristics of construction materials, and uneven heating leads to additional temperature stresses and warpage of the structure.

Also, at the removal stage, when the wing is in a position along the axis of the stage, the wing structure is subject to high pressure (determined by the length of the tank, the wing span and overload along the axis of the stage, reaching four or more units) of the fuel in it, which makes the structure heavier wings.

The problem to which this invention is directed is the creation of a reusable return stage in which the above disadvantages are eliminated.

The technical result of this invention is to improve the anti-flatter characteristics of the wing, reducing the temperature, temperature deformations and temperature stresses in the wing structure, increasing reliability, reducing the weight and manufacturing cost of the structure.

This technical result is achieved in that in a reusable return stage of the launch vehicle containing a direct rotary wing mounted on the body with the possibility of fixing it in a position along the axis of the stage at the launching stage and rotated 90 ° at the stage of the return flight, the fuel system with fuel, ensuring the operation of return engines, where the fuel system with fuel for return engines is located in the front part of the wing, in the nose of the wing, over its entire span in the compartments formed by separate from each other partitions along the ribs, with the central compartment located in the front of the center wing with the function of a supply tank, while in the zone of the most intense heating of the surface of the wing toe there is an inclined heat-insulated wall separating the fuel from the wing of the wing, and the toe in this zone is made of heat-resistant material in the form of separate sections, pivotally attached to power panels at their ends, with the possibility of free deformation when heated.

The proposed device is explained in more detail using circuit diagrams, where:

- FIG. 1 shows a general view of a reusable return stage of a launch vehicle;

- FIG. 2 shows a diagram of a wing with an arrangement of fuel zones;

- FIG. 3 shows a diagram of a wing toe section.

The reusable return stage of the launch vehicle 1 comprises a direct rotary wing 2 mounted on the body with the possibility of fixing it in position along the axis of the stage at the launching stage 3 and rotated 90 ° at the stage of the return flight 4, the fuel system 5 with fuel 6, which ensures the operation of the engines return 7. Fuel for return engines is located in the front part of the wing, including in the nose of the wing 8, over the whole range in the compartments formed by solid partitions 9 separated from each other by ribs, with the central position a compartment in the front of the center section with the function of a supply tank 10, while in the zone of the most intense heating of the surface of the wing tip 11, the fuel is separated from the wing tip by an inclined heat-insulated wall 12 13, and the toe in this zone is made of heat-resistant material in the form of separate sections 14, pivotally 15 attached to the power panels 16 at their ends, with the possibility of free deformation when heated.

The reusable return stage of the launch vehicle with a direct rotary wing mounted on the hull at the stage of launch, descent and return flight is exposed to various loads (aerodynamic, thermal, vibrational, acoustic, etc.).

During the return flight of a step with a direct wing, self-excited oscillations in the wing (flutter) may occur.

During descent - braking, the windward surface of the wing, and especially its nose, undergoes intense non-uniform non-stationary heating. Heating reduces the strength characteristics of construction materials, and uneven heating leads to additional temperature stresses and warpage of the structure.

At the withdrawal stage, when the wing is in a position along the axis of the stage, the wing structure is affected by the high pressure of the fuel in it (pressure is determined by the length of the tank, the wing span, and overload along the axis of the stage, reaching four or more units).

The present invention reduces the negative effects of these factors. Placement of fuel for return engines in the front of the wing, including in the socks of the wing throughout the whole range:

- shifts forward the line of centers of gravity of the wing sections, bringing it closer to the line of its centers of stiffness and the line of its centers of pressure (focus), which significantly improves the antiflatter characteristics of the wing. When combining the centers of gravity with the centers of rigidity or with the foci of the wing, flutter is impossible;

- reduces the temperature of the structure of the most heated front of the wing, due to the large heat capacity of the fuel located in it, which reduces thermal deformation and temperature stresses in the structure and, therefore, reduces the mass of the structure,

- allows you to use high-strength technological aluminum alloys for the panels of the front of the wing and even the socks of the wing, which reduce the weight of the structure and the cost of its manufacture.

When placing fuel in the compartments formed by solid partitions separated from each other by ribs, the fuel pressure in the compartments decreases, which reduces the mass of the structure.

The location of the central compartment in front of the center section with the function of the supply tank reduces the misalignment of the centering of the stage when generating fuel.

Separation of fuel from the nose by an inclined heat-insulated wall in the local zone of the most intense heating of the wing nose surface (the zone of impact on the wing of the shock wave from the nose fairing of the stage body, the heat fluxes to the nose in this zone increase by two or more times):

- prevents overheating of the fuel adjacent directly to the surface of the sock, with the formation of the vapor phase and resinous substances (a decrease in heat removal from the wall of the sock by the vapor phase of the fuel can lead to burnout of the wing sock, and the formation of resinous substances can disrupt the fuel system);

- the inclination of the wall with thermal insulation minimizes the size of the hot toe and the temperature difference on its surface, which reduces its mass, thermal deformation and temperature stresses in it.

The implementation of the sock of heat-resistant material in the form of separate sections, pivotally attached to the power panels at their ends, allows the design of the sock to freely deform when this zone is heated and reduces thermal deformation and temperature stresses in it.

Thanks to such a reusable return stage, the desired technical result is achieved, namely:

- improvement of anti-flutter characteristics of the wing;

- reduction of temperature, temperature deformation and temperature stresses in the wing structure;

- increased reliability;

- reduction in the mass of the structure;

- reducing the cost of manufacturing the structure.

Claims (1)

A reusable return stage of the launch vehicle, comprising a direct rotary wing mounted on the body with the possibility of fixing it in position along the axis of the stage at the stage of launching and turned 90 ° at the stage of return flight, a fuel system with fuel providing operation of return engines, characterized in that that the fuel system with fuel for return engines is located in the front of the wing, in the nose of the wing, along its entire span in the compartments formed by solid partitions separated from each other along the rib , with the central compartment located in the front of the center wing with the function of a supply tank, while in the zone of the most intense heating of the surface of the wing nose, an inclined heat-insulated wall separating the fuel from the wing nose is installed in it, and the sock in this zone is made of heat-resistant material in the form of separate sections pivotally attached to power panels at their ends, with the possibility of free deformation when heated.

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