Solid fuel-gel oxidant rocket engine with continuously adjustable thrust

Abstract

The invention discloses a solid fuel-gel oxidant rocket engine capable of continuously adjusting thrust. The solid fuel-gel oxidant rocket engine comprises a gas flow adjusting mechanism, a front sealing head, a solid fuel with a shell, a spraying pipe, a submerged staged combustion injector and a flexible ignition layer. The flexible ignition layer is adhered to the solid fuel with the shell; the gas flow adjusting mechanism comprises a base and a heat insulation throat liner, and the gas flow adjusting mechanism can axially move along the center face of the front end socket and a cylindrical inlet in the submerged staged combustion injector. The submerged staged combustion inspirator comprises an inspirator main body, an outer wall heat insulation layer, a heat insulation material, an axial connecting section heat insulation layer and a radial connecting section heat insulation layer, wherein the heat insulation material is positioned at a streaming section of the inspirator main body. The solid fuel-gel oxidant rocket engine capable of continuously adjusting the thrust is an effective way for continuously adjusting the thrust of a power system, and the problems that an engine is low in combustion efficiency and large thrust is difficult to output can be solved.

Description

Technical Field

[0001] The invention belongs to the field of aerospace propulsion technology, and in particular relates to a solid fuel-gel oxidizer rocket engine with continuously adjustable thrust. Background Art

[0002] The thrust adjustment capability of the power system is of great significance for missile weapons to achieve efficient maneuverability and precision strike. Solid fuel has the advantages of a wide range of choices, high energy density, and low cost, while liquid oxidizer has the advantages of high oxygen content, high density, and adjustable flow. The combination of the two provides a technical approach to achieve thrust adjustment and efficient energy output of the power system. In recent years, with the development of small molecule gel oxidant technology, it has provided technical support for the realization of solid-state storage and liquid use of oxidizers, and the construction of a solid power system with continuously adjustable thrust.

[0003] The thrust continuous adjustment of existing solid propulsion systems is generally achieved through a throat-type adjustment mechanism, which has the problems of large size and weight of the adjustment mechanism, prominent structural ablation problems, and complex systems. In the existing solid fuel-liquid oxidizer power system, the liquid oxidizer is sprayed into the engine head, and the combustion gas generated by the combustion of the solid fuel inner hole is mixed with the oxidizer injected from the head to burn. In this combustion mode, the oxidizer is highly concentrated in the head and gradually decreases toward the nozzle, resulting in uneven retreat of the solid fuel combustion surface and low engine combustion efficiency, which has become a major difficulty restricting the development of solid fuel and liquid oxidizer mixed combustion engine technology. At the same time, the burning rate of the solid fuel is passively adjusted by the change of the oxidizer flow rate, and the combustion process is diffusion combustion, which makes it difficult to increase the fuel burning rate and achieve high engine thrust output. Summary of the invention

[0004] The technical problem solved by the present invention is: in view of the problems in the background technology that the thrust regulating mechanism is large in size and weight, the structural ablation problem is prominent, the system is complex, the solid fuel-liquid oxidizer power system has low combustion efficiency, and it is difficult to output large thrust. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust is provided, which can not only ensure the accuracy and reliability of each test result, but also reasonably protect each participating measurement and control equipment and reduce the test system error caused by the independent operation of each system.

[0005] In order to solve the above technical problems, the present invention discloses a solid fuel-gel oxidizer rocket engine with continuously adjustable thrust, comprising a gas flow regulating mechanism, a front head, a solid fuel with a shell, a nozzle, a submersible staged combustion injector, and a flexible ignition layer;

[0006] The flexible ignition layer is adhered to the solid fuel with shell;

[0007] The gas flow regulating mechanism comprises a base and a heat-insulating throat liner, and the gas flow regulating mechanism can move axially along the center plane of the front head and the cylindrical inlet on the submersible staged combustion injector;

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

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

[0010] Furthermore, the injection holes are distributed along the axial direction of the engine, and each axial hole is evenly distributed in the circumferential direction, so as to realize graded injection of the oxidant.

[0011] Furthermore, a gas throat with an adjustable flow area is formed between the gas flow regulating mechanism and the submerged staged combustion injector for regulating the gas flow.

[0012] Furthermore, the solid fuel with shell includes a metal shell, a shell insulation layer and a high-pressure index solid fuel.

[0013] Furthermore, the head of the metal shell has a protrusion, and the protrusion overlaps with the radial connecting section of the injector body.

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

[0015] Furthermore, when the high pressure index solid fuel burns, it burns self-sustainingly from the end surface near the front end cover to generate fuel-rich combustion gas.

[0016] Furthermore, a flexible ignition layer is pasted on the end surface of the high pressure strength index solid fuel.

[0017] Furthermore, the lead of the flexible ignition layer passes through the gas flow hole and then leads out from the nozzle.

[0018] The present invention has the following advantages:

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

[0020] (2) The change in the gas flow channel area formed by the gas flow regulating mechanism and the submerged staged combustion injector, as well as the precise regulation of the flow of the liquefied gel oxidizer, can achieve continuous regulation of the engine thrust while the combustion process is at the optimal oxygen-fuel ratio. The only moving part is the gas flow regulating mechanism, and its movement and thermal protection technology are easy to implement, effectively reducing the volume and weight of the regulating mechanism;

[0021] (3) Solid fuel can sustain combustion, and the combustion rate can be adjusted over a wide range by changing the pressure, making it easy to achieve high thrust output of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the prior art descriptions. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. It should be noted that for the sake of clarity and ease of description, the drawings are not necessarily drawn to scale.

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

[0024] Figure 2 It is a schematic diagram of the main body of the submersible staged combustion injector of the solid fuel-gel oxidizer rocket engine with continuously adjustable thrust of the present invention;

[0025] Markings in the figure: 1. base; 2. outer sealing ring of base; 3. front head shell; 4. front head insulation layer; 5. gas flow hole; 6. inner sealing ring of base; 7. injector body; 8. insulation throat liner; 9. insulation material; 10. solid fuel; 11. metal shell; 12. insulation layer; 13. outer insulation layer of injector body; 14. rear insulation layer of shell; 15. rear insulation layer of injector body; 16. front insulation layer of injector body; 101. gas flow regulating mechanism; 102. front head; 103. solid fuel with shell; 104. nozzle; 105. submersible staged combustion injector; 106. flexible ignition layer.

[0026] Specific implementation methods

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

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

[0029] The heat-insulating layer 12 and the shell rear heat-insulating layer 14 are pasted on the inner surface of the metal shell 11 to form a shell with a heat-insulating layer;

[0030] The shell with the heat insulation layer is assembled with the submersible staged combustion injector 105, so that the radial connection section of the submersible staged combustion injector 105 overlaps with the protrusion 13, and the solid fuel 10 is poured and charged in the cavity formed by the shell with the heat insulation layer and the submersible staged combustion injector 105, and solidified and shaped to obtain the solid fuel 103 with the shell;

[0031] The inner surface of the solid fuel with shell 103 is pasted with a flexible ignition layer 106, and the lead wire passes through the gas flow hole 5 and then leads out from the nozzle;

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

[0033] The inner surface of the base 1 is bonded with an insulating throat liner 8 to form a gas flow regulating mechanism 101. The base inner sealing ring 6 and the base outer sealing ring 2 are sealed and installed in the inner and outer sealing grooves of the gas flow regulating mechanism 101, and grease is applied to the inner and outer surfaces of the axial movement of the gas flow regulating mechanism 101. The gas flow regulating mechanism 101 is sleeved on the cylindrical inlet of the submerged staged combustion injector 105 and installed into the corresponding center surface of the front head 102;

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

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

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

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

[0038] Although the present invention has been disclosed as a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed methods and technical contents without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention. The contents not described in detail in the specification of the present invention belong to the known technology of professional and technical personnel in this field.

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 solid fuel with a shell, a nozzle, a submersible staged combustion injector, and a flexible ignition layer; The flexible ignition layer is adhered to the solid fuel with shell; The gas flow regulating mechanism comprises a base and an insulating throat liner, and the gas flow regulating mechanism can move axially along the center surface of the front head and the cylindrical inlet on the submersible staged combustion injector; The submerged staged combustion injector includes an injector body, an outer wall insulation layer, an insulation material, an axial connecting section insulation layer, and a radial connecting section insulation layer. The outer wall insulation layer is located on the outer surface of the injector body, the axial connecting section insulation layer is located on the inner surface of the axial connecting section, the radial connecting section insulation layer is located on the inner surface of the radial connecting section, and the insulation material is located in the flow section of the injector body.

2. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 1, characterized in that: The injector body is provided with an oxidant chamber, which is a double-layer structure of inner and outer walls. The inner wall of the injector body is provided with injection holes. The oxidant flows in the oxidant chamber and is sprayed into the central flow channel from the injection holes on the inner wall.

3. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 2, characterized in that: The injection holes are distributed along the axial direction of the engine, and each axial hole is evenly distributed in the circumferential direction, so as to realize the graded injection of the oxidant.

4. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 1, characterized in that: A gas throat with an adjustable flow area is formed between the gas flow regulating mechanism and the submerged staged combustion injector, which is used to regulate the gas flow.

5. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 1, characterized in that: The solid fuel with shell comprises a metal shell, a shell insulation layer and a high-pressure index solid fuel.

6. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 5, characterized in that: The metal shell has a protrusion, and the protrusion overlaps with the radial connecting section of the injector body.

7. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 5, characterized in that: The pressure index of the high pressure index solid fuel is between 0.55 and 0.

67.

8. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 5, characterized in that: When the high pressure strength index solid fuel burns, it burns self-sustainingly from the end surface near the front end cover to generate fuel-rich combustion gas.

9. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 5, characterized in that: A flexible ignition layer is pasted on the end surface of the high pressure strength index solid fuel.

10. A solid fuel-gel oxidizer rocket engine with continuously adjustable thrust as claimed in claim 1, characterized in that: The lead wire of the flexible ignition layer passes through the gas flow through hole and then leads out from the nozzle.

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