Solid fuel-gel oxidizer rocket engine with continuously adjustable thrust

Abstract

The application discloses a solid fuel-gel oxidizer rocket engine with continuously adjustable thrust, which comprises a gas flow adjusting mechanism, a front head, a shell-carrying solid fuel, a nozzle, a submerged staged combustion injector and a flexible ignition layer; the flexible ignition layer is pasted to the shell-carrying solid fuel; the gas flow adjusting mechanism comprises a base and a heat-insulating throat lining, and the gas flow adjusting mechanism can be axially moved along the center surface of the front head and a cylindrical inlet on the submerged staged combustion injector; the submerged staged combustion injector comprises an injector main body, an outer wall heat-insulating layer, heat-insulating material, an axial connecting section heat-insulating layer and a radial connecting section heat-insulating layer, and the heat-insulating material is arranged on the flow section of the injector main body. The solid fuel-gel oxidizer rocket engine with continuously adjustable thrust provided by the application is an effective way to realize continuous adjustment of the thrust of a power system, and can solve the problems of low combustion efficiency and difficulty in outputting large thrust of the engine.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace propulsion, and particularly relates to a solid fuel-gel oxidizer rocket engine with continuous adjustable thrust. BACKGROUND

[0002] Solid fuel has the advantages of wide selection range, high energy density and low cost, while liquid oxidizer has the advantages of high oxygen content, large density and adjustable flow, and the combination of the two provides a technical approach for realizing thrust regulation and efficient energy output of a power system. In recent years, with the development of small molecule gel oxidizer technology, it provides a technical guarantee for realizing solid-state storage and liquid-state use of oxidizer and constructing a solid power system with continuously adjustable thrust.

[0003] The existing solid power system with continuously adjustable thrust is generally realized through a plug-type regulation mechanism, and has problems of large volume and weight of the regulation mechanism, prominent structure ablation, complex system and the like; and the existing solid fuel-liquid oxidizer power system sprays liquid oxidizer from the head of the engine, and the gas generated by the combustion of the solid fuel in the hole is mixed with the oxidizer sprayed from the head and combusted, and in this combustion mode, the oxidizer is highly concentrated in the head and gradually decreases towards the nozzle, causing uneven retreat of the solid fuel combustion surface and low combustion efficiency of the engine, which is a major difficulty in the development of the solid fuel-liquid oxidizer hybrid combustion engine technology, and at the same time, the fuel burning rate is passively regulated by the change of the oxidizer flow, and the combustion process belongs to diffusion combustion, causing difficulty in increasing the fuel burning rate and difficulty in realizing high thrust output of the engine. SUMMARY

[0004] The application solves the problems of large volume and weight of the thrust regulation mechanism, prominent structure ablation, complex system, low combustion efficiency of the solid fuel-liquid oxidizer power system and difficulty in high thrust output, and provides a solid fuel-gel oxidizer rocket engine with continuously adjustable thrust, which can ensure the accuracy and reliability of test results, reasonably protect test control equipment and reduce test system errors caused by independent work of each system.

[0005] In order to solve the above technical problems, the application discloses a solid fuel-gel oxidizer rocket engine with continuously adjustable thrust, which comprises a gas flow regulation mechanism, a front head, a shell-equipped solid fuel, a nozzle, a submerged staged combustion injector and a flexible ignition layer.

[0006] The flexible ignition layer is pasted to the shell-equipped solid fuel.

[0007] The gas flow regulation mechanism comprises a base and a heat-insulating throat liner, and the gas flow regulation mechanism can move axially along the center surface of the front head and the cylindrical inlet of the submerged staged combustion injector.

[0008] The submerged staged combustion injector comprises an injector body, an outer wall thermal insulation layer, a thermal insulation material, an axial connecting section thermal insulation layer, a radial connecting section thermal insulation layer, the outer wall thermal insulation layer is located on the outer surface of the injector body, the axial connecting section thermal insulation layer is located on the inner surface of the axial connecting section, the radial connecting section thermal insulation layer is located on the inner surface of the radial connecting section, and the thermal insulation material is located in the flow section of the injector body.

[0009] Further, the injector body has an annular oxidant chamber in a double-layer structure of inner and outer walls, the inner wall of the injector body is provided with injection holes, and the oxidant flows in the oxidant chamber and is injected into the central flow channel from the inner wall injection holes.

[0010] Further, the injection holes are distributed along the engine axis, and each axial hole is uniformly distributed in a ring shape to realize staged injection of the oxidant.

[0011] Further, the fuel gas flow adjusting mechanism and the submerged staged combustion injector form a fuel gas throat with adjustable flow area for adjusting the fuel gas flow.

[0012] Further, the solid fuel with a shell comprises a metal shell, a shell thermal insulation layer and a high-pressure index solid fuel.

[0013] Further, the metal shell head is provided with a protrusion which overlaps the radial connecting section of the injector body.

[0014] Further, the pressure index of the high-pressure index solid fuel is between 0.55 and 0.67.

[0015] Further, the high-pressure index solid fuel burns in an end face self-sustaining manner from the vicinity of the front head to generate fuel-rich fuel gas.

[0016] Further, the high-pressure index solid fuel is pasted with a flexible ignition layer on the end face.

[0017] Further, the lead wire of the flexible ignition layer passes through the fuel gas flow hole and is led out from the nozzle.

[0018] The present application has the following advantages:

[0019] (1) The submerged staged combustion injector can deeply inject the oxidant into the engine combustion chamber, and the staged injection can provide favorable conditions for efficient combustion of fuel-rich fuel gas and oxidant, thereby improving the energy release efficiency of the engine.

[0020] (2) The area of the gas flow passage formed by the gas flow regulating mechanism and the submerged staged combustion injector, and the precise regulation of the liquefied gel oxidizer flow, can realize the continuous regulation of the engine thrust, while the combustion process is in the best oxygen-fuel ratio. The moving parts are only the gas flow regulating mechanism, and the movement and thermal protection technology is easy to realize, effectively reducing the volume and weight of the regulating mechanism;

[0021] (3) The solid fuel can self-sustain combustion, and the combustion rate can be regulated in a wide range by changing the pressure, which is easy to realize the large thrust output of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creating labor. It should be noted that the drawings are not necessarily drawn to scale for clarity and ease of illustration.

[0023] Figure 1 A sectional view and a partial enlarged view of the solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to the present application;

[0024] Figure 2 A schematic diagram of the main body of the submerged staged combustion injector of the solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to the present application;

[0025] Marked in the figure: 1. Base; 2. Outer seal ring of base; 3. Front head shell; 4. Front head thermal insulation layer; 5. Gas flow through hole; 6. Inner seal ring of base; 7. Injector body; 8. Throat insulation; 9. Insulation material; 10. Solid fuel; 11. Metal shell; 12. Front shell thermal insulation layer; 13. Outer wall thermal insulation layer of injector body; 14. Axial connecting section thermal insulation layer; 15. Rear thermal insulation layer of injector body; 16. Radial connecting section thermal insulation layer; 17. Metal shell protrusion; 18. Rear shell thermal insulation layer; 101. Gas flow regulating mechanism; 102. Front head; 103. Shell solid fuel; 104. Nozzle; 105. Submerged staged combustion injector; 106. Flexible ignition layer.

[0026] Specific implementation

[0027] The present application will be further described below in conjunction with the drawings.

[0028] In this embodiment, the sectional view and the partial enlarged view of the solid fuel-gel oxidizer rocket engine with adjustable thrust are shown in Figure 1 The schematic diagram of the main body of the submerged staged combustion injector is shown in Figure 2The shown gas flow regulating mechanism 101, front head 102, shell solid fuel 103, nozzle 104, submerged staged combustion injector 105 and flexible ignition layer 106;

[0029] The shell front heat insulation layer 12 and shell rear heat insulation layer 18 are pasted on the inner surface of the metal shell 11 to form a shell with heat insulation layer;

[0030] The shell with heat insulation layer is assembled with the submerged staged combustion injector 105 so that the radial connecting section of the submerged staged combustion injector 105 is overlapped with the protrusion 17, the solid fuel 10 is poured into the cavity formed by the shell with heat insulation layer and the submerged staged combustion injector 105, and the shell solid fuel 103 is obtained after solidification and shaping;

[0031] The flexible ignition layer 106 is pasted on the inner surface of the shell solid fuel 103, and the lead wire is drawn out from the nozzle after passing through the gas flow hole 5;

[0032] The front head heat insulation layer 4 is pasted on the inner surface of the front head shell 3 to form the front head 102;

[0033] The heat insulation throat liner 8 is pasted on the inner surface of the base 1 to form the gas flow regulating mechanism 101, the base inner sealing ring 6 and the base outer sealing ring 2 are sealingly installed in the inner and outer sealing grooves of the gas flow regulating mechanism 101, and the gas flow regulating mechanism 101 is sleeved on the cylindrical inlet of the submerged staged combustion injector 105 and fitted into the corresponding center surface of the front head 102 by coating grease on the inner and outer surfaces of the gas flow regulating mechanism 101 which moves axially;

[0034] The nozzle 104 is connected with the shell solid fuel 103, the cylindrical inlet of the submerged staged combustion injector 105 is connected with the oxidant supply system, and the gas flow regulating mechanism 101 is connected with the driving motor.

[0035] During operation, the cylindrical inlet of the submerged staged combustion injector 105 is first connected with the oxidant supply system, and the gas flow regulating mechanism 101 is connected with the driving motor;

[0036] According to the test procedure, the main control electromagnetic valve of the oxidant supply system is opened, the flexible ignition layer 106 is ignited, the fuel-rich gas generated after the solid fuel 10 is ignited passes through the gas flow regulating mechanism 101 and the throat of the submerged staged combustion injector 105, enters the central flow passage of the submerged staged combustion injector 105 through the gas flow hole 5, and is mixed and burned with the liquefied gel oxidant sprayed from the injection hole;

[0037] According to the thrust output demand, the axial position of the gas flow regulating mechanism 101 and the oxidant flow are adjusted to realize continuous thrust adjustment and optimal fuel-oxidant ratio combustion.

[0038] Although the present application has been disclosed with reference to the preferred embodiments thereof, it is not intended to limit the present application thereto, for it will be apparent that those skilled in the art can make modifications or alterations to the present application without departing from the spirit and scope thereof. Any simple modifications, equivalent changes and modifications made to the above embodiments according to the technical essence of the present application, without departing from the technical solutions of the present application, shall fall within the protection scope of the present application. The contents not described in detail in the present application specification are the known technology of the skilled in the art.

Claims

1. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust, characterized in that: The engine comprises a gas flow regulating mechanism, a front head, a shell-contained solid fuel, a nozzle, a submerged staged combustion injector, and a flexible ignition layer; The flexible ignition layer is attached to the shell-contained solid fuel; The gas flow regulating mechanism comprises a base and an adiabatic throat insert, and is axially movable along the center surface of the front head and the cylindrical inlet of the submerged staged combustion injector; The submerged staged combustion injector comprises a flow-around section, an injection section, an axial connecting section, and a radial connecting section in sequence along the axial direction, and comprises an injector body, an outer wall adiabatic layer, a heat insulation material, an axial connecting section adiabatic layer, and a radial connecting section adiabatic layer, wherein the outer wall adiabatic layer is located on the outer surface of the injector body, the axial connecting section adiabatic layer is located on the inner surface of the axial connecting section, the radial connecting section adiabatic layer is located on the inner surface of the radial connecting section, and the heat insulation material is located in the flow-around section of the injector body; The injector body is provided with an oxidant chamber in a double-layer structure of inner and outer walls, and the inner wall of the injector body is provided with injection holes, through which the oxidant in the oxidant chamber flows into the central flow passage; The gas flow regulating mechanism and the submerged staged combustion injector form a gas throat with adjustable flow area for regulating the gas flow.

2. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to claim 1, characterized in that: The injection holes are distributed along the axial direction of the engine, and each axial hole is uniformly distributed in a ring shape to realize staged injection of the oxidant.

3. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to claim 1, characterized in that: The shell-contained solid fuel comprises a metal shell, a shell adiabatic layer, and a high-pressure exponent solid fuel.

4. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to claim 3, characterized in that: The metal shell is provided with a protrusion which overlaps the radial connecting section of the injector body.

5. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to claim 3, characterized in that: The high-pressure exponent solid fuel has a pressure exponent between 0.55 and 0.

67.

6. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust according to claim 3, characterized in that: The high-pressure exponent solid fuel burns in an end-face self-sustaining manner from the position close to the front head to generate fuel-rich gas.

7. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 3 wherein: The high-pressure exponent solid fuel is attached with the flexible ignition layer on the end face.

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