Compact single-component liquid power device capable of working in one-time steady state and control method of compact single-component liquid power device

Abstract

The invention discloses a compact single-component liquid power device capable of working stably at a time and a control method of the compact single-component liquid power device. The compact single-component liquid power device comprises an upper isolating valve, a storage box, a lower isolating valve, a cavitation pipe, a single-component thrust chamber and a controller. The single-component thrust chamber is positioned below the storage tank; the upper isolating valve is arranged at a gas path inlet of the storage tank, and the lower isolating valve is arranged at a liquid path outlet of the storage tank; an inner runner is integrated at the bottom of the storage box; one end of the inner runner is communicated with the lower isolating valve, and the other end of the inner runner is communicated with an inlet of the single-component thrust chamber through a cavitation pipe; and the controller is respectively connected with the upper isolating valve and the lower isolating valve through cables. According to the scheme, the method can adapt to application occasions where the axial space length of the spacecraft is limited and an orbit control engine needs to work in a one-time steady state, and is suitable for orbit control power devices of the spacecrafts such as satellites and detectors.

Description

Technical Field

[0001] This invention belongs to the field of liquid rocket engine technology, and particularly relates to a compact single-component liquid propulsion device and its control method for single-phase steady-state operation. Background Technology

[0002] Monocomponent liquid propulsion systems are widely used in the field of spacecraft. They typically consist of components such as tanks, isolation valves, control valves, and monocomponent thrust chambers. These components are connected by pipelines. The monocomponent thrust chamber is composed of structures such as a heat insulation frame, capillary tubes, and a thrust chamber body. The thrust level generally ranges from a few Newtons to hundreds of Newtons, and it has both steady-state and pulsed operating modes.

[0003] Traditional monocomponent fluid power units have numerous components, are spatially dispersed, and have low space utilization. For some applications with only one steady-state operating mode and limited axial space envelope, traditional monocomponent fluid power units are difficult to adapt. Summary of the Invention

[0004] The technical problem solved by the present invention is to overcome the shortcomings of the prior art and provide a compact single-component liquid propulsion device and its control method for single steady-state operation. It can be adapted to applications where the axial space length of spacecraft is limited and the orbital control engine needs to operate in a single steady-state state. It is applicable to orbital control propulsion devices for spacecraft such as satellites and probes.

[0005] To address the aforementioned technical problems, this invention discloses a compact monocomponent liquid propulsion device operating in a single steady state, comprising: an upper isolation valve, a storage tank, a lower isolation valve, a cavitation pipe, a monocomponent thrust chamber, and a controller; wherein, the monocomponent thrust chamber is located below the storage tank; the upper isolation valve is located at the gas inlet of the storage tank, and the lower isolation valve is located at the liquid outlet of the storage tank; an internal flow channel is integrated at the bottom of the storage tank; one end of the internal flow channel is connected to the lower isolation valve, and the other end is connected to the inlet of the monocomponent thrust chamber through the cavitation pipe; the controller is connected to the upper isolation valve and the lower isolation valve respectively via cables.

[0006] The compact monocomponent liquid propulsion device described above, which operates in a single steady state, also includes a heat insulation pad. The heat insulation pad is fitted onto the cavitation pipe and located between the contact surface between the tank and the monocomponent thrust chamber. It is used to reduce the heat backflow from the monocomponent thrust chamber to the tank after the tank has finished operating, and to prevent thermal explosion of the propellant that has not been discharged from the tank.

[0007] In the aforementioned compact single-component hydraulic power unit operating in a single steady state, the storage tank is either a metal diaphragm tank or a non-metallic diaphragm tank.

[0008] In the aforementioned compact monocomponent liquid propulsion device operating in a single steady state, the monocomponent thrust chamber includes: a thrust chamber head, a thrust chamber body, and a Laval nozzle connected in sequence; wherein, the thrust chamber body is filled with a catalyst.

[0009] In the aforementioned compact single-component fluid power unit operating in a single steady state, the thrust chamber head has a lotus-shaped structure.

[0010] In the aforementioned compact monocomponent liquid power unit operating in a single steady state, the cavitation tube is used to control the starting flow rate of the monocomponent thrust chamber, thereby controlling the cold start pressure peak.

[0011] In the aforementioned compact single-component liquid power unit operating in a single steady state, a nitrogen constant-pressure extrusion system or a gas booster system is used to provide a constant-pressure gas source, which enters the storage tank via the upper isolation valve.

[0012] In the aforementioned compact monocomponent hydrodynamic device operating in a single steady state, the monocomponent thrust chamber operates in a single steady state.

[0013] In the aforementioned compact monocomponent liquid propulsion unit operating under steady-state conditions, the working process is as follows: When the compact monocomponent liquid propulsion unit needs to operate, the controller sends commands to the upper and lower isolation valves, which then open. The propellant in the reservoir's liquid chamber flows sequentially through the inner flow channel and cavitation pipe under the pressure of the pressurized gas, entering the thrust chamber head. After being evenly distributed at the thrust chamber head, it enters the catalyst bed in the thrust chamber body. Under the action of the catalyst, the propellant decomposes into high-temperature, high-pressure gas, which expands and accelerates through the Laval nozzle of the monocomponent thrust chamber to generate thrust. After the propellant is completely exhausted, the monocomponent thrust chamber shuts down.

[0014] Accordingly, the present invention also discloses a control method for a compact single-component hydrodynamic device operating in a single steady state, comprising:

[0015] During operation, the controller sends commands to the upper and lower isolation valves, which then open. The propellant in the reservoir liquid chamber flows sequentially through the inner flow channel, cavitation pipe, and into the head of the single-component thrust chamber under the pressure of the pressurized gas.

[0016] After the propellant is evenly distributed at the head of the single-component thrust chamber, it enters the catalyst bed in the body of the single-component thrust chamber. Under the action of the catalyst, the propellant decomposes into high-temperature and high-pressure gas, which expands and accelerates through the Laval nozzle of the single-component thrust chamber to generate thrust.

[0017] Once the propellant is completely depleted, the single-component thrust chamber is shut down.

[0018] The present invention has the following advantages:

[0019] (1) This invention discloses a compact single-component liquid power device with one steady-state operation. The storage tank integrates an isolation valve and an internal flow channel. The single-component thrust chamber eliminates the heat insulation frame and control valve, which greatly reduces the axial length of the liquid power device. It is particularly suitable for applications with limited axial space.

[0020] (2) The present invention discloses a compact single-component liquid power device that operates in a single steady state. By opening the isolation valve and depleting the propellant, the opening and closing control of the single-component thrust chamber can be directly realized, reducing the number of components and improving the reliability of the device.

[0021] (3) The present invention discloses a compact single-component liquid power device with single steady-state operation. By setting a cavitation pipe at the tank outlet and adding a heat insulation pad between the tank and the single-component thrust chamber, the cold start pressure peak of the single-component thrust chamber and the heat back-immersion to the tank after the single-component thrust chamber finishes working are suppressed, thereby further improving the reliability of the device operation.

[0022] (4) This invention discloses a compact single-component liquid propulsion device with a single steady-state operation, which has the advantages of simple structure, compact spatial layout and high reliability, improves the space utilization and operational reliability of the spacecraft, and is suitable for the orbital control propulsion system of spacecraft. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the structure of a compact single-component liquid power device operating in a single steady state according to an embodiment of the present invention. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0025] Reference Figure 1 In this embodiment, the compact monocomponent liquid propulsion device with single-phase steady-state operation includes: an upper isolation valve 1, a tank 2, a lower isolation valve 3, a cavitation pipe 5, a heat insulation pad 6, a monocomponent thrust chamber 7, and a controller 8. The monocomponent thrust chamber 7 is located below the tank 2; the upper isolation valve 1 is located at the gas inlet of the tank 2, and the lower isolation valve 3 is located at the liquid outlet of the tank 2; an internal flow channel 4 is integrated at the bottom of the tank 2; one end of the internal flow channel 4 is connected to the lower isolation valve 3, and the other end is connected to the inlet of the monocomponent thrust chamber 7 via the cavitation pipe 5; the controller 8 is connected to the upper isolation valve 1 and the lower isolation valve 3 via cables; the heat insulation pad 6 is fitted onto the cavitation pipe 5 and located between the contact surfaces of the tank 2 and the monocomponent thrust chamber 7, used to reduce the heat backflow into the tank 2 after the monocomponent thrust chamber 7 finishes operating, preventing thermal explosion of undischarged propellant within the tank 2.

[0026] In this embodiment, the storage tank 2 is a metal diaphragm storage tank or a non-metal diaphragm storage tank.

[0027] In this embodiment, the single-component thrust chamber 7 eliminates the traditional control valve and heat insulation frame, and mainly includes: a thrust chamber head 71, a thrust chamber body 72, and a Laval nozzle 73 connected in sequence. The thrust chamber body 72 is filled with a catalyst; the thrust chamber head 71 has a lotus-shaped structure: the outlet of the thrust chamber head 71 has several evenly distributed holes, which can achieve uniform flow distribution.

[0028] In this embodiment, the cavitation pipe 5 is used to control the starting flow of the unit thrust chamber 7, thereby controlling the cold start pressure peak.

[0029] In this embodiment, a nitrogen constant pressure extrusion system or a gas booster system can be used to provide a constant pressure gas source, which enters the storage tank 2 through the upper isolation valve 1.

[0030] In this embodiment, the single-component thrust chamber 7 operates in a steady-state mode.

[0031] In this embodiment, the working process of the compact single-component liquid propulsion device is as follows: When the compact single-component liquid propulsion device needs to work, the controller 8 sends a command to the upper isolation valve 1 and the lower isolation valve 3, and the upper isolation valve 1 and the lower isolation valve 3 open; the propellant in the liquid chamber of the tank 2 flows sequentially through the inner flow channel 4, the cavitation pipe 5, and enters the thrust chamber head 71 under the squeezing action of the pressurized gas. After the flow rate is evenly distributed by the thrust chamber head 71, it enters the catalyst bed in the thrust chamber body 72. Under the action of the catalyst, the propellant decomposes into high-temperature and high-pressure gas, which expands and accelerates through the Laval nozzle 73 to generate thrust; after the propellant is completely exhausted, the single-component thrust chamber 7 shuts down.

[0032] Based on the above embodiments, a detailed explanation will be provided below with reference to a specific example.

[0033] A compact, single-component liquid propulsion device for steady-state operation mainly includes: an upper isolation valve 1, a reservoir 2, a lower isolation valve 3, a cavitation pipe 5, a single-component thrust chamber 7, and a controller 8. The reservoir 2 can be a metal diaphragm reservoir or a non-metallic diaphragm reservoir; the upper isolation valve 1 is located at the gas inlet of the reservoir 2, and the lower isolation valve 3 is located at the liquid outlet of the reservoir 2; an internal flow channel 4 is integrated at the bottom of the reservoir 2; one end of the internal flow channel 4 is connected to the lower isolation valve 3, and the other end is connected to the inlet of the single-component thrust chamber 7 through the cavitation pipe 5; a heat insulation pad 6 is fitted onto the cavitation pipe 5 and located between the contact surfaces of the reservoir 2 and the single-component thrust chamber 7. The single-component thrust chamber 7 eliminates the traditional control valve and heat insulation frame design, and consists of a lotus-shaped thrust chamber head 71 and a thrust chamber body 72, with the thrust chamber body 72 filled with a catalyst. The cavitation pipe 5 is used to control the starting flow of the unit thrust chamber 7, thereby controlling the cold start pressure peak. A heat insulation pad 6 is installed between the unit thrust chamber 7 and the tank 2 to reduce the heat backflow from the unit thrust chamber 7 to the tank 2 after the unit thrust chamber 7 has finished working, and to prevent thermal explosion caused by undischarged propellant in the tank 2.

[0034] The inlet of this compact, single-component hydraulic propulsion unit, operating in a single steady state, is connected to a constant-pressure extrusion system or a gas pressurization system, forming a complete attitude and orbit control propulsion system. The thrust level of the single-component thrust chamber 7 is 300N–600N, used for spacecraft orbit adjustment. When the spacecraft needs to perform a single orbit change, the workflow of this attitude and orbit control propulsion system is as follows:

[0035] The controller 8 sends commands to the upper isolation valve 1 and the lower isolation valve 3, which open the upper isolation valve 1 and the lower isolation valve 3. Under the pressure of the pressurized gas, the propellant in the liquid chamber of the tank 2 flows sequentially through the inner flow channel 4, the cavitation pipe 5, and enters the thrust chamber head 71. After the flow rate is evenly distributed by the thrust chamber head 71, it enters the catalyst bed in the thrust chamber body 72. Under the action of the catalyst, the propellant decomposes into high-temperature and high-pressure gas, which expands and accelerates through the Laval nozzle 73 to generate thrust. After the propellant is completely exhausted, the single-component thrust chamber 7 shuts down.

[0036] Based on the above embodiments, the present invention also discloses a control method for a compact single-component liquid propulsion device operating in a single steady state, comprising: during operation, the controller 8 sends a command to the upper isolation valve 1 and the lower isolation valve 3, and the upper isolation valve 1 and the lower isolation valve 3 open; the propellant in the liquid chamber of the tank 2 flows sequentially through the inner flow channel 4, the cavitation pipe 5, and enters the thrust chamber head 71 under the compression of the pressurized gas; after the propellant is evenly distributed in the flow rate by the thrust chamber head 71, it enters the catalyst bed in the thrust chamber body 72, and the propellant decomposes into high-temperature and high-pressure gas under the action of the catalyst, which expands and accelerates through the Laval nozzle 73 to generate thrust; after the propellant is completely exhausted, the single-component thrust chamber 7 is shut down.

[0037] As the method embodiments correspond to the device embodiments, the description is relatively simple, and relevant details can be found in the description of the device embodiments section.

[0038] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

[0039] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A compact, single-component hydrodynamic device operating in a single steady state, characterized in that, include: The tank consists of an upper isolation valve (1), a storage tank (2), a lower isolation valve (3), a cavitation pipe (5), a single-component thrust chamber (7), and a controller (8). The single-component thrust chamber (7) is located below the storage tank (2). The upper isolation valve (1) is located at the gas inlet of the storage tank (2), and the lower isolation valve (3) is located at the liquid outlet of the storage tank (2). The bottom of the storage tank (2) is integrated with an internal flow channel (4). One end of the internal flow channel (4) is connected to the lower isolation valve (3), and the other end is connected to the inlet of the single-component thrust chamber (7) through the cavitation pipe (5). The controller (8) is connected to the upper isolation valve (1) and the lower isolation valve (3) respectively via cables.

2. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, Also includes: Heat insulation pad (6); wherein, the heat insulation pad (6) is fitted on the cavitation pipe (5) and located between the contact surface of the tank (2) and the single-component thrust chamber (7), and is used to reduce the heat back-immersion to the tank (2) after the single-component thrust chamber (7) finishes working, and to prevent thermal explosion of the propellant that has not been discharged from the tank (2).

3. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, The storage tank (2) is a metal diaphragm storage tank or a non-metal diaphragm storage tank.

4. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, The single-component thrust chamber (7) includes: a thrust chamber head (71), a thrust chamber body (72), and a Laval nozzle (73) connected in sequence; wherein the thrust chamber body (72) is filled with a catalyst.

5. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 4, characterized in that, The thrust chamber head (71) has a lotus-shaped structure.

6. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, Cavitation tube (5) is used to control the starting flow of the single-component thrust chamber (7), thereby controlling the cold start pressure peak.

7. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, A constant pressure gas source is provided by a nitrogen constant pressure extrusion system or a gas booster system. The constant pressure gas source enters the storage tank (2) through the upper isolation valve (1).

8. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 1, characterized in that, The working mode of the single-component thrust chamber (7) is a single steady-state operation.

9. The compact single-component hydrodynamic device with single-phase steady-state operation according to claim 4, characterized in that, The working process of the compact single-component liquid propulsion unit is as follows: When the compact single-component liquid propulsion unit needs to work, the controller (8) sends a command to the upper isolation valve (1) and the lower isolation valve (3), and the upper isolation valve (1) and the lower isolation valve (3) open; the propellant in the liquid chamber of the tank (2) flows through the inner flow channel (4), the cavitation pipe (5) and enters the thrust chamber head (71) in sequence under the pressure of the pressurized gas. After the flow is evenly distributed by the thrust chamber head (71), it enters the catalyst bed in the thrust chamber body (72). The propellant is decomposed into high temperature and high pressure gas under the action of the catalyst. It expands and accelerates through the Laval nozzle (73) of the single-component thrust chamber (7) to generate thrust; after the propellant is completely exhausted, the single-component thrust chamber (7) shuts down.

10. A control method for a compact single-component hydrodynamic device operating in a single steady state, characterized in that, include: During operation, the controller (8) sends commands to the upper isolation valve (1) and the lower isolation valve (3), and the upper isolation valve (1) and the lower isolation valve (3) open; the propellant in the liquid chamber of the tank (2) flows through the inner flow channel (4), the cavitation pipe (5) and enters the head of the single-component thrust chamber (7) in sequence under the squeezing action of the pressurized gas; After the propellant is evenly distributed in flow through the head of the single-component thrust chamber (7), it enters the catalyst bed in the body of the single-component thrust chamber (7). Under the action of the catalyst, the propellant decomposes into high-temperature and high-pressure gas, which expands and accelerates through the Laval nozzle of the single-component thrust chamber (7) to generate thrust. After the propellant is completely exhausted, the single-component thrust chamber (7) is shut down.

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