Liquid rocket engine starting device and starting method

Abstract

The invention discloses a liquid rocket engine starting device and method. The liquid rocket engine starting device comprises a gas cylinder set, a starting system and a pressurization system. High-pressure gas used for starting the turbine and pressurizing the propellant in the fuel storage tank is stored in the gas cylinder group; the starting system comprises a starting controller and a plurality of starting branches, and the pressure and the flow entering the turbine pump are adjusted by controlling the opening and closing number and the opening and closing time of the starting branches. The pressurization system comprises a pressurization controller and a plurality of pressurization branches, and the pressure and the flow in the gas cavity of the fuel storage tank are adjusted by controlling the opening and closing number and the opening and closing time of the pressurization branches. According to the invention, multiple starting of the liquid rocket engine can be realized, the advantages of low development difficulty and low development cost of gas cylinder starting are exerted, and meanwhile, the gas source utilization rate of traditional gas cylinder starting is optimized.

Description

Technical Field

[0001] The present invention relates to the field of liquid launch vehicle power systems, and in particular to a liquid rocket engine starting device and a starting method. Background Art

[0002] Multiple starts of liquid rocket engines are crucial for achieving precise orbital deployment, landing, and recovery. Multiple ignitions allow for orbital corrections. For rockets carrying multiple satellites, multiple ignitions can be used to deliver each satellite to its target orbit. Furthermore, multiple ignitions are crucial for rocket recovery and reuse.

[0003] Liquid rocket engines can be started using either self-start or forced start. Forced start primarily involves starting with a pyrotechnic starter and starting with a gas cylinder. Engines that require multiple starts require multiple pyrotechnic starters. However, due to space limitations on the turbine inlet, pyrotechnic starters are generally not used for engines requiring more than three starts.

[0004] The gas cylinder is started by blowing the turbine with high-pressure nitrogen or helium to drive the pump to rotate. The development difficulty and cost are low, but the high-pressure gas cylinder has a large structural mass. After the liquid rocket engine is started, a large amount of low-pressure gas will still remain in the gas cylinder, affecting the carrying weight of the liquid rocket.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0006] In order to solve the above technical problems, the present application provides a liquid rocket engine starting device and starting method, which can realize multiple starts of the liquid rocket engine, give full play to the advantages of low development difficulty and cost of gas cylinder starting, and optimize the utilization rate of traditional gas cylinder starting gas source.

[0007] A liquid rocket engine starting device, comprising:

[0008] A gas cylinder group; the gas cylinder group includes a plurality of gas cylinders arranged in series; the gas cylinder group stores high-pressure gas for starting the turbine and pressurizing the propellant in the fuel tank;

[0009] A starting system comprising a starting controller and a plurality of starting branches; the gas cylinder assembly is connected to the turbine pump via the starting branches; the starting controller is configured to adjust the pressure and flow entering the turbine pump by controlling the number and duration of opening and closing of the starting branches according to the pressure in the gas cylinders, thereby driving the turbine to rotate;

[0010] A boost system; the boost system includes a boost controller and a plurality of boost branches; the gas cylinder assembly is connected to the fuel tank air cavity through the boost branches; the boost controller is configured to adjust the pressure and flow rate in the fuel tank air cavity according to the pressure in the fuel tank by controlling the number and opening and closing time of the boost branches to ensure a stable supply of propellant.

[0011] Preferably, each starting branch is provided with a starting solenoid valve, a starting one-way valve and a starting throttle ring connected by pipelines; the inlet end of the starting one-way valve is connected to the gas cylinder, and the outlet end of the starting one-way valve is connected to the turbine pump.

[0012] Preferably, each of the boost branches is provided with a boost solenoid valve, a pressure reducing valve and a boost throttle ring connected through pipelines.

[0013] Preferably, the system further comprises a gas cylinder pressure sensor for monitoring the internal pressure of the gas cylinder and a tank pressure sensor for monitoring the internal pressure of the fuel tank.

[0014] Preferably, it further comprises an inflation valve for inflating gas into the gas cylinder.

[0015] Preferably, it also includes an inflation hole plate for controlling the inflation rate during inflation.

[0016] Preferably, the high-pressure gas stored in the gas cylinder is nitrogen.

[0017] According to another aspect of the present application, a liquid rocket engine starting method is provided, comprising:

[0018] One or more starting branches in the starting system are opened, and the high-pressure gas in the gas cylinder group enters the turbine pump through the starting branches and drives the turbine to rotate;

[0019] One or more boost branches in the boost system are opened, and the high-pressure gas in the gas cylinder group enters the gas cavity of the fuel tank through the boost branches, driving the propellant in the fuel tank to fill the engine inlet pipe and enter the oxygen pump and fuel pump under the action of the tank pressure and the liquid column pressure;

[0020] Driven by the turbine, the oxygen pump and fuel pump convert mechanical energy into the pressure potential energy of the propellant. After the propellant is pumped, the pressure is increased and it enters the gas generator and thrust chamber for combustion, thus completing the starting process of the liquid rocket engine.

[0021] The opening and closing quantity and opening and closing time of the starting branch are adjusted by the starting controller according to the pressure in the gas cylinder, and the turbine is driven to rotate by controlling the pressure and flow entering the turbine pump;

[0022] The opening and closing quantity and opening and closing time of the boost branch are adjusted by the boost controller according to the pressure in the fuel tank. By controlling the pressure and flow entering the air cavity of the fuel tank, the stable supply of propellant is controlled.

[0023] Preferably, one or more starting branches in the starting system are opened, and the high-pressure gas in the gas cylinder group enters the turbine pump through the starting branches and drives the turbine to rotate, including:

[0024] Open the starting solenoid valve in one or more starting branches; after the starting solenoid valve is opened, the high-pressure gas passing through the filter flows through the starting solenoid valve, the starting one-way valve and the starting throttle ring and enters the turbine, serving as the initial energy for starting the turbine and driving the turbine to rotate.

[0025] Preferably, when one or more boost branches in the boost system are opened, the high-pressure gas in the gas cylinder group enters the air cavity of the fuel tank through the boost branches, driving the propellant in the fuel tank to fill the engine inlet pipeline and enter the oxygen pump and the fuel pump under the action of the tank pressure and the liquid column pressure. The pressure in the fuel tank is obtained through the tank pressure sensor. When the fuel tank pressure is higher than the upper limit of the set value, the boost solenoid valves in one or more boost branches are closed. When the fuel tank pressure is lower than the lower limit of the set value, the boost solenoid valves in one or more boost branches are opened.

[0026] Compared with the prior art, this application has at least the following beneficial effects:

[0027] 1. The present invention can realize multiple starts of liquid rocket engines, giving full play to the advantages of gas cylinder starting in terms of difficulty and low development cost, while optimizing the problem of low utilization rate of traditional gas cylinder starting gas source and reducing the weight of the carrier rocket starting device.

[0028] 2. The present invention combines the starting gas cylinder and the boosting gas cylinder into a group of gas cylinders. Taking advantage of the fact that the pressure requirement of the boosting gas for the gas source is much lower than the gas source requirement during the engine starting process, the gas in the high-pressure gas cylinder after starting is used to pressurize the fuel tank, effectively simplifying the system and improving the gas source utilization rate.

[0029] 3. The present invention effectively solves the problem of large space occupied by existing integral large gas cylinders by configuring the starting gas cylinders as a plurality of gas cylinders connected in series, thereby improving the rationality of the gas cylinder layout. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Hereinafter, some specific embodiments of the present invention will be described in detail in an illustrative and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0031] Figure 1The figure is a schematic diagram showing the connection of components of the liquid rocket engine starting device of the present invention.

[0032] The above drawings include the following reference numerals:

[0033] 1. Inflatable orifice plate; 2. Inflating valve; 3. Gas cylinder; 4. Filter; 5. Tank pressure sensor; 6. Boost controller; 7. Thrust chamber; 8. Oxygen pump; 9. Fuel pump; 10. Turbine; 11. Gas cylinder pressure sensor; 12. Starting controller; 13. Starting solenoid valve; 14. Starting check valve; 15. Starting throttle; 16. Oxygen tank; 17. Fuel tank; 18. Boost solenoid valve; 19. Pressure reducing valve; 20. Boost throttle; 21. Inflatable port. DETAILED DESCRIPTION

[0034] To make the purpose, technical solutions, and advantages of this application more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the specific embodiments of this application and the corresponding drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0035] Example 1

[0036] like Figure 1 As shown, a liquid rocket engine starting device includes: a gas cylinder group, a starting system and a pressurization system.

[0037] The gas cylinder group includes a plurality of gas cylinders 3 arranged in series, and the gas cylinder group stores high-pressure gas for starting the turbine and pressurizing the propellant in the fuel tank 17. Preferably, the high-pressure gas stored in the gas cylinders 3 is nitrogen.

[0038] The starting system includes a starting controller 12 and several starting branches, which connect the gas cylinder assembly to the turbo pump. The starting controller 12 is configured to regulate the pressure and flow entering the turbo pump by controlling the number and duration of opening and closing the starting branches based on the pressure within the gas cylinders, thereby driving the turbine 10.

[0039] The boost system includes a boost controller 6 and several boost branches, which connect the gas cylinder assembly to the air chamber of the fuel tank 17. The boost controller 6 is configured to regulate the pressure and flow rate within the air chamber of the fuel tank 17 by controlling the number and duration of opening and closing the boost branches, based on the pressure within the fuel tank 17, to ensure a stable supply of propellant.

[0040] Each starting branch is provided with a starting solenoid valve 13, a starting one-way valve 14 and a starting throttle ring 15 connected by pipelines; the inlet end of the starting one-way valve 14 is connected to the gas cylinder 3, and the outlet end of the starting one-way valve 14 is connected to the turbine pump.

[0041] Each boost branch is provided with a boost solenoid valve 18, a pressure reducing valve 19 and a boost throttle ring 20 which are connected by pipelines.

[0042] The starting solenoid valve 13 on each starting branch line can be a solenoid valve of the same specification or different specifications. When each starting branch line is provided with a solenoid valve of different specifications, gases with different pressures and different flows can pass through different starting branches.

[0043] Similarly, the boost solenoid valve 18 on each boost branch line can be a solenoid valve of the same specification or different specifications. When each boost branch line is provided with a solenoid valve of different specifications, gases with different pressures and different flows can pass through different boost branches.

[0044] In addition, the liquid rocket engine starting device further includes a gas cylinder pressure sensor 11 for monitoring the internal pressure of the gas cylinder and a tank pressure sensor 5 for monitoring the internal pressure of the fuel tank 17 .

[0045] It should be noted that the oxygen tank 16 adopts an oxygen self-pressurization scheme, that is, a line of liquid oxygen is drawn out from behind the oxygen pump 8, the liquid oxygen flow is controlled by a pressurization venturi, and then passes through the oxygen pressurization one-way valve and the tube bundle heat exchanger and oxygen pressurization orifice plate in the turbine exhaust pipe to connect with the rocket self-pressurization pipeline.

[0046] As another embodiment of the present invention, a liquid rocket engine starting device further includes an inflation valve 2 for inflating gas into the gas cylinder.

[0047] Furthermore, a liquid rocket engine starting device also includes an inflation orifice plate 1 for controlling the inflation rate during inflation, and the inlet end of the inflation orifice plate 1 is connected to the inflation port 21 through a pipeline.

[0048] As another embodiment of the present invention, a liquid rocket engine starting device further includes a filter 4 connected to the outlet of the gas cylinder assembly.

[0049] Example 2

[0050] A liquid rocket engine starting method comprising:

[0051] S1. One or more starting branches in the starting system are opened, and the high-pressure gas in the gas cylinder group enters the turbine pump through the starting branches and drives the turbine 10 to rotate.

[0052] The opening and closing quantity and opening and closing time of the starting branch are adjusted by the starting controller 12 according to the pressure in the gas cylinder 3, and the turbine 10 is driven to rotate by controlling the pressure and flow entering the turbine pump.

[0053] Specifically, one or more starting branches in the starting system are opened, and the high-pressure gas in the gas cylinder group enters the turbine pump through the starting branches and drives the turbine 10 to rotate, including:

[0054] One or more starting solenoid valves 13 in the starting branch circuit are opened. Once these valves are opened, high-pressure gas from filter 4 flows through solenoid valve 13, starting check valve 14, and starting throttle 15 before entering turbine 10. This serves as the initial energy source for starting turbine 10, driving it to rotate. The number of openings of solenoid valve 13 is controlled by a computer system based on cylinder pressure feedback detected by cylinder pressure sensor 11.

[0055] S2. One or more boost branches in the boost system are opened, and the high-pressure gas in the gas cylinder group enters the air cavity of the fuel tank 17 through the boost branches. The propellant in the fuel tank 17 is driven by the tank pressure and the liquid column pressure to fill the engine inlet pipe and enter the oxygen pump 8 and the fuel pump 9.

[0056] The opening and closing number and opening and closing time of the boost branch are adjusted by the boost controller 6 according to the pressure in the fuel tank 17. By controlling the pressure and flow into the air cavity of the fuel tank 17, the stable supply of propellant is controlled.

[0057] Specifically, the pressure within the fuel tank 17 is detected by the tank pressure sensor 5. When the pressure in the fuel tank 17 exceeds the upper set point, one or more boost solenoid valves 18 in the boost circuits close. When the pressure in the fuel tank 17 falls below the lower set point, one or more boost solenoid valves 18 in the boost circuits open. A boost controller controls the number and duration of boost solenoid valve openings to maintain the fuel tank 17 pressure near the set point, ensuring stable and reliable engine operation. The number of boost solenoid valves 18 openings is controlled by the computer system based on tank pressure feedback detected by the tank pressure sensor 5.

[0058] Driven by the turbine 10, S3, oxygen pump 8 and fuel pump 9 convert mechanical energy into pressure potential energy of propellant. After the propellant pressure is increased after the pump, it enters the gas generator and thrust chamber 7 for combustion, thereby completing the starting process of the liquid rocket engine.

[0059] It should be noted that the oxygen tank 16 adopts an oxygen self-pressurization scheme, that is, a line of liquid oxygen is drawn out from behind the oxygen pump 8, the liquid oxygen flow is controlled by a pressurization venturi, and then passes through the oxygen pressurization one-way valve and the tube bundle heat exchanger and oxygen pressurization orifice plate in the turbine exhaust pipe to connect with the rocket self-pressurization pipeline.

[0060] As another embodiment of the present invention, before starting the liquid rocket engine, it also includes a gas cylinder group inflation process: connecting the inflation port 21 to the nitrogen source, opening the inflation valve 2, and the gas passes through the inflation orifice plate 1 and the inflation valve 2 into each gas cylinder 3 of the gas cylinder group. When the pressure of the gas cylinder 3 reaches the target pressure, the inflation valve 2 is closed to complete the inflation of the gas cylinder group.

[0061] Furthermore, after the pressure built up after the pump reaches the target pressure, the gas generator takes over the high-pressure gas to work on the turbine, realizing the transition from the starting condition to the main stage condition.

[0062] Each start-up process is identical, but as the start-up progresses, the pressure in the gas cylinder group decreases. Subsequent starts have lower pressure than previous ones. To ensure the reliability of each start-up, multiple starting solenoid valves 13 of different specifications are provided based on the number of starts required by the rocket. The rocket computer calculates the number of solenoid valves required for each start-up.

[0063] Preferably, during the inflation process of the gas cylinder assembly, the inflation rate is no more than 1 MPa / min.

[0064] As another embodiment of the present invention, before the gas cylinder group is inflated, a gas cylinder group replacement process is also included: nitrogen is filled into each gas cylinder 3 of the gas cylinder group through the inflation port 21 to 0.1 MPa (gauge pressure), the inflation port 21 is opened to deflate, and the above inflation and deflation process is repeated two to three times to reduce the air concentration in the gas cylinder group.

[0065] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship of a device or feature to other devices or features as shown in the figures. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figures. For example, if the device in the drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0066] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they indicate the presence of features, steps, tasks, devices, components and / or combinations thereof.

[0067] It should be noted that the terms "first," "second," and the like in the specification and claims of this application and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than that illustrated or described herein.

[0068] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A liquid rocket engine starting device, characterized in that: include: A gas cylinder group; the gas cylinder group includes a plurality of gas cylinders arranged in series; the gas cylinder group stores high-pressure gas for starting the turbine and pressurizing the propellant in the fuel tank; A starting system comprising a starting controller and a plurality of starting branches; the gas cylinder assembly is connected to the turbine pump via the starting branches; the starting controller is configured to adjust the pressure and flow entering the turbine pump by controlling the number and duration of opening and closing of the starting branches according to the pressure in the gas cylinders, thereby driving the turbine to rotate; A boost system; the boost system includes a boost controller and a plurality of boost branches; the gas cylinder assembly is connected to the fuel tank air cavity through the boost branches; the boost controller is configured to adjust the pressure and flow rate in the fuel tank air cavity according to the pressure in the fuel tank by controlling the number and opening and closing time of the boost branches to ensure a stable supply of propellant.

2. The liquid rocket engine starting device according to claim 1, characterized in that: Each starting branch is provided with a starting solenoid valve, a starting one-way valve and a starting throttle ring connected by pipelines; the inlet end of the starting one-way valve is connected to the gas cylinder, and the outlet end of the starting one-way valve is connected to the turbine pump.

3. The liquid rocket engine starting device according to claim 1, characterized in that: Each of the boost branches is provided with a boost solenoid valve, a pressure reducing valve and a boost throttle ring which are connected through pipelines.

4. The liquid rocket engine starting device according to claim 1, characterized in that: The system also includes a cylinder pressure sensor for monitoring the internal pressure of the gas cylinder and a tank pressure sensor for monitoring the internal pressure of the fuel tank.

5. The liquid rocket engine starting device according to claim 1, characterized in that: Also included is a gas filling valve for filling the gas cylinder.

6. The liquid rocket engine starting device according to claim 5, characterized in that: Also included is an inflation orifice plate for controlling the inflation rate during inflation.

7. The liquid rocket engine starting device according to claim 1, characterized in that: The high-pressure gas stored in the gas cylinder is nitrogen.

8. A method for starting a liquid rocket engine, characterized in that: include: One or more starting branches in the starting system are opened, and the high-pressure gas in the gas cylinder group enters the turbine pump through the starting branches and drives the turbine to rotate; One or more boost branches in the boost system are opened, and the high-pressure gas in the gas cylinder group enters the gas cavity of the fuel tank through the boost branches, driving the propellant in the fuel tank to fill the engine inlet pipe and enter the oxygen pump and fuel pump under the action of the tank pressure and the liquid column pressure; Driven by the turbine, the oxygen pump and fuel pump convert mechanical energy into the pressure potential energy of the propellant. After the propellant is pumped, the pressure is increased and it enters the gas generator and thrust chamber for combustion, thus completing the starting process of the liquid rocket engine. The opening and closing quantity and opening and closing time of the starting branch are adjusted by the starting controller according to the pressure in the gas cylinder, and the turbine is driven to rotate by controlling the pressure and flow entering the turbine pump; The opening and closing quantity and opening and closing time of the boost branch are adjusted by the boost controller according to the pressure in the fuel tank. By controlling the pressure and flow entering the air cavity of the fuel tank, the stable supply of propellant is controlled.

9. The liquid rocket engine starting method according to claim 8, wherein: Open one or more starting branches in the starting system. The high-pressure gas in the gas cylinder group enters the turbine pump through the starting branch and drives the turbine to rotate, including: Open the starting solenoid valve in one or more starting branches; after the starting solenoid valve is opened, the high-pressure gas passing through the filter flows through the starting solenoid valve, the starting one-way valve and the starting throttle ring and enters the turbine, serving as the initial energy for starting the turbine and driving the turbine to rotate.

10. The liquid rocket engine starting method according to claim 8, wherein: When one or more boost branches in the boost system are opened, the high-pressure gas in the gas cylinder group enters the gas cavity of the fuel tank through the boost branches, driving the propellant in the fuel tank to fill the engine inlet pipeline and enter the oxygen pump and fuel pump under the action of the tank pressure and the liquid column pressure. The pressure in the fuel tank is obtained through the tank pressure sensor. When the fuel tank pressure is higher than the upper limit of the set value, the boost solenoid valves in one or more boost branches are closed. When the fuel tank pressure is lower than the lower limit of the set value, the boost solenoid valves in one or more boost branches are opened.

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