A ring cluster plug engine layout scheme fusing multi-unit solid-liquid combustion chamber

Abstract

The patent is a kind of ring cluster plug engine layout scheme fusing multiple unit solid-liquid combustion chamber, which uses liquid propellant supply system to adjust the flow of multiple unit combustion chamber, has thrust regulation, thrust vector and multiple starting ability, and comprises liquid propellant, storage tank, storage tank valve, storage tank pipeline, electric pump, power supply and control module, plug cone, post-pump pipeline, flange, inner nozzle, combustion chamber, solid charge, injector, ignition device, combustion chamber pipeline, combustion chamber pipeline valve and liquid collecting ring. The electric pump, post-pump valve and combustion chamber pipeline valve work cooperatively to adjust the valve opening, change the liquid propellant flow into the combustion chamber, and realize the nozzle thrust regulation; the inner nozzles are uniformly arranged along the plug cone in a ring direction, each inner nozzle corresponds to a combustion chamber and a combustion chamber pipeline, the combustion chamber pipeline valve controls the opening, adjusts the combustion chamber pipeline valve to change the flow field of the plug nozzle engine, generates lateral force, and realizes the engine thrust vector; the liquid propellant is injected into the combustion chamber multiple times, the mixed solid-liquid propellant is ignited by the ignition device, and the nozzle realizes multiple start.

Description

Technical Field

[0001] This invention provides a layout scheme for an annular cluster plug engine that integrates a multi-unit solid-liquid combustion chamber, belonging to the field of aerospace technology. Background Technology

[0002] Among existing aerospace propulsion technologies, liquid rocket engines have advantages such as adjustable thrust and strong re-start capability. However, their system structure is complex, including numerous pipelines, pumps, valves, and tank pressurization systems, resulting in high manufacturing costs, difficult maintenance, and long launch preparation cycles. In contrast, solid rocket engines have advantages such as simple structure, good storage stability, fast response speed, and low maintenance costs. However, they have inherent drawbacks such as non-adjustable thrust, the inability to stop the operation once started, and high safety risks (such as accidental ignition or abnormal combustion), making it difficult to meet the thrust requirements of complex flight missions and limiting their application flexibility.

[0003] In recent years, hybrid rocket engines, as a technological approach between liquid and solid engines, have gradually become a research hotspot in the propulsion field due to their combination of the high density, low volatility, and good storage properties of solid fuels with the controllable flow rate of liquid oxidizers. Typical hybrid engines employ a combined combustion method of solid propellant grains and liquid oxidizers (such as liquid oxygen and hydrogen peroxide). Thrust is continuously adjusted by regulating the supply flow rate of the liquid oxidizer, resulting in high operational safety and mission adaptability. Simultaneously, it avoids the complex piping systems of liquid engines and the uncontrollable combustion problems of solid engines, demonstrating excellent overall performance potential.

[0004] However, traditional solid-liquid hybrid engines mostly employ fixed-geometry nozzle structures. This structure only achieves optimal performance at the design point and struggles to adapt to varying external pressures across a wide range of flight altitudes. At low altitudes, overexpansion can lead to flow separation and increased structural loads, while at high altitudes, underexpansion results in insufficient release of combustion gas energy, significantly reducing propulsion efficiency and limiting performance in cross-altitude, high-Mach-number flight missions. Therefore, the plug nozzle, as an advanced adaptive aerodynamic nozzle structure, has received widespread attention in recent years. This nozzle uses a plug cone and an outer bell-shaped inner nozzle to form a ring-cluster layout, allowing high-temperature combustion gas to expand freely along the surface of the plug cone. It can automatically adjust the effective expansion ratio according to the external environmental pressure, achieving high efficiency across a wide altitude range and significantly improving engine performance under variable-altitude flight conditions.

[0005] Currently, thrust regulation technology has been implemented in various ways across different engine types: liquid engines primarily achieve thrust control by adjusting the oxidizer / fuel flow rate through the main valve; solid engines rely on throat adjustment or special propellant design to achieve limited thrust regulation; while hybrid engines typically control combustion chamber pressure by adjusting the opening of the liquid oxidizer valve, thereby achieving thrust regulation. Regarding thrust vector control, common solutions include secondary injection, secondary jet, and gas vane deflection. The secondary jet solution requires introducing lateral injection into the plug cone region, but this exacerbates local heat loads, placing higher demands on the thermal protection and sealing design of the plug cone structure; the gas vane solution requires additional high-temperature actuation mechanisms and high-strength materials, increasing system complexity and weight. Therefore, achieving efficient and reliable thrust vector control without significantly increasing structural complexity remains a key challenge for plug-type solid-liquid engines.

[0006] Furthermore, the plug cone structure at the bottom of plug-type nozzles is typically a solid or hollow support design, resulting in inefficient use of internal space, leading to structural redundancy and wasted layout. Since hybrid engines inherently require liquid oxidizer storage, the liquid oxidizer tank or delivery pipeline can be integrated into the multi-unit combined structure and the cavity inside the plug cone, improving the overall space utilization and structural compactness of the engine, and contributing to weight reduction.

[0007] Therefore, it is necessary to provide a layout scheme for a ring-cluster plug engine that integrates multiple solid-liquid combustion chambers. This scheme aims to achieve high-precision, wide-range thrust regulation by integrating an electrically driven pump-type supply system and valves to control the flow and pressure of the liquid propellant; simultaneously, it utilizes the aerodynamic characteristics of the ring-cluster plug nozzle to achieve altitude compensation; and employs a structure where one combustion chamber corresponds to one internal nozzle to control engine thrust magnitude, thrust direction, and multiple start-ups. This invention aims to overcome the technical bottlenecks of limited control capabilities and low structural utilization in traditional solid-liquid engines, improving the engine's adaptability, safety, and overall performance in wide-range flight missions. Summary of the Invention

[0008] The purpose of this invention is to provide a multi-unit solid-liquid combustion chamber annular cluster plug nozzle layout scheme to achieve nozzle height compensation, thrust adjustment, and thrust vectoring.

[0009] The technical solution adopted by this invention to achieve its objective is as follows:

[0010] This solid-liquid propellant annular cluster plug nozzle engine comprises a liquid propellant, a tank, tank valves, tank piping, an electric pump, a power supply and control module, a plug cone, post-pump piping, a flange, an internal nozzle, a combustion chamber, a solid charge, an injector, an ignition device, combustion chamber piping, combustion chamber piping valves, and a liquid collection ring. The liquid tank is located inside the multi-unit combined structure and within the cavity of the plug cone. The bottom of the tank is connected to the tank piping, which is then connected to the electric pump system. The electric pump system is connected to the post-pump piping, which is connected to the liquid collection ring. The liquid collection ring is connected to the combustion chamber via the combustion chamber piping. The injector and igniter are located at the head of the combustion chamber, which contains a solid propellant grain connected to the internal nozzle. The internal nozzle is embedded in an annular flange. The plug cone is a truncated plug cone, with the length from the lower edge of the internal nozzle outlet to the bottom end face of the truncated plug cone being 30% of the total length of the plug cone.

[0011] The internal nozzles are uniformly arranged circumferentially along the plug cone. Each internal nozzle corresponds to one combustion chamber and one combustion chamber pipeline. The opening degree of the combustion chamber pipeline valves is controlled individually, thereby controlling the injection amount of liquid propellant. When all combustion chamber pipeline valves are at the same opening degree, the nozzles operate normally and do not generate lateral force. Adjusting the combustion chamber pipeline valves changes the flow field of the nozzles, thereby generating lateral force and achieving thrust vectoring.

[0012] The electric pump, post-pump valve, and combustion chamber pipeline valve work together to adjust the valve opening, thereby changing the flow rate of liquid propellant entering the combustion chamber and adjusting the nozzle thrust. Furthermore, switching the combustion chamber pipeline valves on and off, thus changing the combustion chamber's on / off state, can also adjust the thrust of the plug-type nozzle engine.

[0013] The liquid propellant is injected into the combustion chamber multiple times, and the mixed solid-liquid propellant is ignited by an ignition device, allowing the nozzle to be started multiple times.

[0014] The inner nozzle and the plug cone form a solid wall for the gas flow. The gas is generated in the combustion chamber and discharged through the inner nozzle. The aerodynamic boundary of the gas is constrained by the ambient pressure and the plug cone wall, allowing the gas to expand freely within it. As the flight altitude changes, the ambient pressure changes, and the aerodynamic boundary of the gas changes accordingly, achieving an altitude compensation effect.

[0015] Compared with the prior art, the advantages of the present invention are as follows:

[0016] This invention provides a layout scheme for a ring-cluster plug engine that integrates multiple solid-liquid combustion chambers. It adopts a plug nozzle configuration to achieve height compensation; through an electric pump-pressurized supply system and multiple valves, the amount of liquid propellant injected into the combustion chamber is adjusted to achieve thrust regulation; by controlling the thrust of the circumferentially distributed inner nozzles, thrust vector control is achieved by using thrust differential, eliminating the need for traditional complex mechanical vector nozzle mechanisms; and the liquid propellant tank is integrated into the multi-unit combined structure and the plug cone, improving the engine's structural compactness. Attached Figure Description

[0017] Figure 1 This is a cross-sectional view of a layout scheme for an annular cluster piston engine integrating a multi-unit solid-liquid combustion chamber according to the present invention.

[0018] 1-Liquid propellant, 2-Tank, 3-Tank valve, 4-Tank piping, 5-Electric pump, 6-Power supply and control module, 7-Plug cone, 8-Post-pump piping, 9-Flange, 10-Inner nozzle, 11-Combustion chamber, 12-Charging, 13-Injector, 14-Ignition device, 15-Combustion chamber piping, 16-Combustion chamber piping valve, 17-Collecting ring Detailed Implementation

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and implementation guidelines.

[0020] Figure 1 As shown, one specific embodiment of the present invention discloses a layout scheme for a ring-cluster plug engine integrating a multi-unit solid-liquid combustion chamber, including 1-liquid propellant, 2-tank, 3-tank valve, 4-tank pipeline, 5-electric pump, 6-power supply and control module, 7-plug cone, 8-post-pump pipeline, 9-flange, 10-inner nozzle, 11-combustion chamber, 12-solid charge, 13-injector, 14-ignition device, 15-combustion chamber pipeline, 16-combustion chamber pipeline valve, and 17-liquid collecting ring. The 2-inner nozzle and the 7-plug cone constitute a plug-type nozzle engine. The profile of the 2-inner nozzle and the profile of the 7-plug cone together form the aerodynamic profile of the plug nozzle. The 7-plug cone is a truncated plug cone, and the length from the lower edge of the 2-inner nozzle outlet to the bottom end face of the 7-plug cone is 30% of the original plug cone's total length.

[0021] 1. Liquid propellant is controlled by valve 3 (reservoir valve). When the plug nozzle engine is running, valve 3 (reservoir valve) is opened, and liquid propellant 1 (1) enters pump 5 (electric pump) through pipeline 4 (reservoir). Pump 5 (electric pump), under the control of power supply and control module 6 (power supply and control module), pumps liquid propellant 1 (1) into pipeline 8 (post-pump pipeline). After being collected by liquid collection ring 17 (collector ring), it enters combustion chamber pipeline 15 (combustion chamber pipeline). Valve 16 (combustion chamber pipeline valve) controls the flow rate of liquid propellant 1 (1) entering combustion chamber 11 (combustion chamber). When liquid propellant 1 (1) enters combustion chamber 11 (combustion chamber), it is diffused into combustion chamber 11 (combustion chamber) by injector 13 (injector). Under the action of ignition device 14 (ignition device), it is ignited together with solid charge 12 (12). The resulting combustion gas is discharged after passing through inner nozzle 10 (inner nozzle) and continues to expand on the surface of plug cone 7 (7), thereby generating thrust. The opening degree of combustion chamber pipeline valve 16 (16) controls the flow rate of liquid propellant 1 (1) and adjusts nozzle thrust. Pump 5 (electric pump) adjusts flow rate by adjusting speed, and can also adjust nozzle thrust. When the 12-solid charge and 1-liquid propellant are mixed and ignited, the 2-inner nozzle begins to operate; when the supply of 1-liquid propellant is stopped, the 2-inner nozzle ceases to operate. The 2-inner nozzle can be restarted multiple times provided that the 12-solid charge and 1-liquid propellant are not completely consumed.

Claims

1. This patent proposes a layout scheme for an annular cluster piston engine that integrates a multi-unit solid-liquid combustion chamber. Its characteristics are: This is a multi-unit solid-liquid combustion chamber annular cluster type piston engine, comprising liquid propellant, tank, tank valves, tank piping, electric pump, power supply and control module, plug cone, post-pump piping, flange, internal nozzle, combustion chamber, solid charge, injector, ignition device, combustion chamber piping, combustion chamber piping valves, and a liquid collection ring. Based on the annular cluster piston engine mechanism, height compensation is achieved. The plug cone is a truncated type, with the length from the lower edge of the internal nozzle outlet to the bottom end face of the truncated plug cone being 30% of the total length of the plug cone. The liquid tank is located inside the multi-unit combustion chamber assembly structure, achieving a compact spatial layout. The electric pump system delivers liquid propellant to each combustion chamber through post-pump piping, the liquid collection ring, combustion chamber piping, and the injector. Each combustion chamber contains a solid propellant grain connected to the internal nozzle, which is embedded in the annular flange, realizing a distributed ignition and unit-combined propulsion scheme.

2. The layout scheme of an annular cluster piston engine integrating a multi-unit solid-liquid combustion chamber according to claim 1, characterized in that: The electric pump, the downstream valve, and the combustion chamber pipeline valve work together to adjust the electric pump speed, the opening of the downstream valve, and the opening of the combustion chamber pipeline valve, thereby controlling the flow rate of liquid propellant in the combustion chamber and changing the thrust of the multi-unit solid-liquid combustion chamber annular cluster plug nozzle to achieve thrust regulation.

3. The layout scheme of an annular cluster piston engine integrating a multi-unit solid-liquid combustion chamber according to claim 1, characterized in that: The electric pump, the valve after the pump, and the combustion chamber pipeline valve work together to switch the on / off state of the combustion chamber by opening and closing the combustion chamber pipeline valve, thereby enabling the engine to start multiple times.

4. The layout scheme of an annular cluster piston engine integrating a multi-unit solid-liquid combustion chamber according to claim 1, characterized in that: The internal nozzles are uniformly arranged circumferentially along the plug cone, with each nozzle corresponding to a combustion chamber and a combustion chamber pipeline. The injection amount of liquid propellant is controlled by the opening degree of the combustion chamber pipeline valves. When the combustion chamber pipeline valves are at the same opening degree, the multi-unit solid-liquid combustion chamber annular plug engine operates normally without generating lateral force. Adjusting the combustion chamber pipeline valves changes the nozzle flow field, generating lateral force and achieving thrust vectoring.

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