An exhaust attitude control system based on a recyclable low-temperature liquid stainless steel rocket tank

Abstract

The utility model discloses a kind of exhaust attitude control systems based on recyclable low-temperature liquid stainless steel rocket storage tank, it is related to rocket storage tank exhaust attitude control technical field, the exhaust attitude control system based on recyclable low-temperature liquid stainless steel rocket storage tank, including rocket storage tank and control gas cylinder, the rocket storage tank is connected with control gas cylinder by control gas component, the control gas cylinder is connected with gas charging and discharging valve by control gas pipeline;The control gas pipeline is connected with rocket storage tank by attitude control component, the attitude control component and control gas component are connected with rocket-borne control system by with control cable, storage tank exhaust and attitude control system integration is set, both can meet rocket during pre-launch filling period storage tank exhaust, can also meet rocket unpowered taxiing stage provides self-control force, and also can meet rocket ground recovery after storage tank air pillow gas discharge pressure relief, system is simple and reliable, air pillow gas can be fully utilized.

Description

Technical Field

[0001] This utility model relates to the field of rocket propellant tank exhaust attitude control technology, specifically an exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank. Background Technology

[0002] The propellant tank venting system is used to release gases from the gas cushions within the propellant tanks during propellant loading before launch, during flight, and after ground recovery. The attitude control system is used for attitude control during the unpowered gliding phase of rocket recovery. Typically, the propellant tank venting system consists of pneumatically controlled venting valves, safety valves, or electrically controlled venting valves. Pneumatically controlled venting valves are supplied with control gas from the ground and open during propellant loading before launch to maintain tank pressure. During flight, the safety valve opens due to overpressure or the tank pressure band opens to close the electrically controlled venting valve, maintaining the tank pressure at normal levels.

[0003] Generally, a rocket's attitude control system is equipped with an auxiliary propulsion system (consisting of high-pressure gas cylinders, high-pressure solenoid valves, pressure reducing valves, gas supply lines, nozzles, etc.) to achieve attitude control. High-pressure gas is ejected from the cylinders, accelerated through the nozzles, and then used to generate thrust, which in turn provides the rocket's attitude control force. However, because rockets have a large demand for attitude control force, that is, a large amount of gas is required to generate thrust. This results in the rocket carrying a large number of high-pressure gas cylinders, increasing the weight of the system and the cost of supporting products. At the same time, high-pressure gas cylinders pose safety risks.

[0004] Alternatively, it can be equipped with an auxiliary propulsion system (consisting of propellant tanks, oxidizer tanks, electro-explosive valves, pressure reducing valves, gas supply lines, nozzles, etc.), which uses propellant ignition and combustion to generate high-temperature and high-pressure gas that is ejected and accelerated through the nozzle to generate thrust, thereby providing rocket attitude control force. However, this requires designing propellant and oxidizer tanks on the rocket to fill the propellant, which increases the complexity of the system and the cost of product matching. At the same time, the propellant and oxidizer tanks usually need to be filled in advance before launch, which increases the pre-launch filling process. Moreover, the use and maintenance requirements of this type of auxiliary propulsion system are relatively high.

[0005] The existing tank exhaust system and attitude control system are used separately and independently, making it impossible to achieve an integrated design of tank exhaust and attitude control system. Furthermore, when the tank exhaust system and attitude control system are used separately and independently, the gas in the tank cushion is only discharged from the tank as excess gas, and the attitude control system needs to introduce an additional air source or power source. This results in the gas in the tank cushion not being fully utilized. Utility Model Content

[0006] This invention provides an exhaust and attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank, which solves the problem that existing propellant tank exhaust and attitude control systems are difficult to integrate and set up in a unified manner. When used separately, the gas cushion gas in the propellant tank is only discharged from the tank as excess gas and cannot be fully utilized.

[0007] This utility model provides the following technical solution: an exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket tank, comprising a rocket tank and a control gas cylinder. The rocket tank is connected to the control gas cylinder via a control gas assembly, and the control gas cylinder is connected to a filling / discharging valve via a control gas pipeline. The control gas pipeline is connected to the rocket tank via an attitude control assembly, and both the attitude control assembly and the control gas assembly are connected to the rocket-borne control system via control cables.

[0008] As a preferred embodiment of this utility model, the gas control assembly includes a normally open solenoid valve and a second gas-controlled exhaust valve. The normally open solenoid valve is connected to a control gas cylinder via a control gas pipeline. The side of the normally open solenoid valve away from the control gas cylinder is connected to the first end of the second gas-controlled exhaust valve. The second end of the second gas-controlled exhaust valve is connected to the rocket storage tank. The third end of the second gas-controlled exhaust valve is connected to the exhaust guide shield. The second gas-controlled exhaust valve is connected to the rocket's onboard control system via a control cable.

[0009] As a preferred embodiment of the present invention, the attitude control component includes a first control component and a second control component. Both the first control component and the second control component are connected to the onboard control system via control cables, and the first control component and the second control component are connected to the control air pipeline.

[0010] As a preferred embodiment of this utility model, the first control component includes a first normally closed solenoid valve and a first pneumatically controlled exhaust valve. The first normally closed solenoid valve is connected to a control air pipeline and is also connected to the rocket's onboard control system via a control cable. The first normally closed solenoid valve is connected to the first end of the first pneumatically controlled exhaust valve, the second end of the first pneumatically controlled exhaust valve is connected to the first Laval nozzle, and the third end of the first pneumatically controlled exhaust valve is connected to the rocket's storage tank.

[0011] As a preferred embodiment of this utility model, the second control component includes a second normally closed solenoid valve and a third pneumatically controlled exhaust valve. The second normally closed solenoid valve is connected to a control air pipeline and is also connected to the rocket's onboard control system via a control cable. The second normally closed solenoid valve is connected to the first end of the third pneumatically controlled exhaust valve, the second end of the third pneumatically controlled exhaust valve is connected to the second Laval nozzle, and the third end of the third pneumatically controlled exhaust valve is connected to the rocket's storage tank.

[0012] Compared with the prior art, this utility model provides an exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank, which has the following beneficial effects:

[0013] 1. The exhaust attitude control system based on the reusable cryogenic liquid stainless steel rocket propellant tank integrates the tank exhaust and attitude control system. It can not only meet the needs of tank exhaust during the rocket's pre-launch fueling, but also provide self-control force during the rocket's unpowered gliding phase, and also meet the needs of exhaust and depressurization of the tank's gas cushion gas after the rocket's ground recovery. The system is simple and reliable, and the gas cushion gas can be fully utilized.

[0014] 2. This exhaust attitude control system based on a reusable cryogenic liquid stainless steel rocket tank integrates the tank exhaust and attitude control system, reducing the need for an additional auxiliary power attitude control system on the rocket. This reduces the number of onboard components and lowers product costs. The system controls the opening and closing of onboard solenoid valves according to different rocket stages, and provides attitude control force through real-time control of the exhaust at the unpowered gliding end of the rocket via the onboard control system, thus improving the reliability of rocket operation. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of this utility model.

[0016] In the diagram: 1. Rocket propellant tank; 2. Inflation / discharge valve; 3. First Laval nozzle; 4. First pneumatically controlled exhaust valve; 5. Control gas line; 6. Exhaust shield; 7. First normally closed solenoid valve; 8. Second pneumatically controlled exhaust valve; 9. Control gas cylinder; 10. Normally open solenoid valve; 11. Second normally closed solenoid valve; 12. Third pneumatically controlled exhaust valve; 13. Second Laval nozzle; 14. Onboard control system; 15. Control cables. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0018] Please see Figure 1 This utility model discloses an exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket tank, including a rocket tank 1 and a control gas cylinder 9. The rocket tank 1 is connected to the control gas cylinder 9 through a control gas assembly, and the control gas cylinder 9 is connected to the filling and discharging valve 2 through a control gas pipeline 5. The control gas pipeline 5 is connected to the rocket tank 1 through an attitude control assembly, and both the attitude control assembly and the control gas assembly are connected to the rocket onboard control system 14 through a control cable 15.

[0019] Specifically, the gas control assembly includes a normally open solenoid valve 10 and a second gas-controlled exhaust valve 8. The normally open solenoid valve 10 is connected to the control gas cylinder 9 via the control gas pipeline 5. The side of the normally open solenoid valve 10 away from the control gas cylinder 9 is connected to the first end of the second gas-controlled exhaust valve 8. The second end of the second gas-controlled exhaust valve 8 is connected to the rocket storage tank 1. The third end of the second gas-controlled exhaust valve 8 is connected to the exhaust guide 6. The second gas-controlled exhaust valve 8 is connected to the rocket-borne control system 14 via the control cable 15.

[0020] In this implementation scheme, by connecting the normally open solenoid valve 10 to the control gas cylinder 9 and the second pneumatically controlled exhaust valve 8, and by connecting the second pneumatically controlled exhaust valve 8 to the rocket propellant tank 1 and the exhaust deflector 6 respectively, effective control and discharge of gas inside the rocket propellant tank 1 can be achieved. The second pneumatically controlled exhaust valve 8 is connected to the rocket-borne control system 14 via the control cable 15, and under the control of the rocket-borne control system 14, it can accurately complete the venting of the propellant tank during pre-launch propellant loading and the depressurization of the propellant tank's gas pillow after ground recovery, ensuring the stable operation of the relevant processes.

[0021] Specifically, the attitude control component includes a first control component and a second control component. Both the first control component and the second control component are connected to the onboard control system 14 via control cable 15, and the first control component and the second control component are connected to the control air line 5.

[0022] In this embodiment, the first and second control components are connected to the control air pipeline 5, which provides the power source for attitude control. Both are connected to the rocket-borne control system 14 via control cables 15, enabling the rocket-borne control system 14 to control the first and second control components in real time and with precision. Thus, during the unpowered gliding phase of the rocket, attitude control force is provided by adjusting these two components according to the actual flight attitude of the rocket, meeting the attitude control requirements during the unpowered gliding phase.

[0023] Specifically, the first control component includes a first normally closed solenoid valve 7 and a first pneumatically controlled exhaust valve 4. The first normally closed solenoid valve 7 is connected to the control air pipeline 5 and is also connected to the rocket-borne control system 14 via a control cable 15. The first normally closed solenoid valve 7 is connected to the first end of the first pneumatically controlled exhaust valve 4, the second end of the first pneumatically controlled exhaust valve 4 is connected to the first Laval nozzle 3, and the third end of the first pneumatically controlled exhaust valve 4 is connected to the rocket propellant tank 1.

[0024] Specifically, the second control component includes a second normally closed solenoid valve 11 and a third pneumatically controlled exhaust valve 12. The second normally closed solenoid valve 11 is connected to the control air line 5 and is also connected to the rocket-borne control system 14 via a control cable 15. The second normally closed solenoid valve 11 is connected to the first end of the third pneumatically controlled exhaust valve 12, the second end of the third pneumatically controlled exhaust valve 12 is connected to the second Laval nozzle 13, and the third end of the third pneumatically controlled exhaust valve 12 is connected to the rocket propellant tank 1.

[0025] In this embodiment, in the first control component, the first normally closed solenoid valve 7 is connected to the control gas pipeline 5 and the rocket-borne control system 14, and can be controlled by it to turn the gas source on and off, thereby controlling the state of the first gas-controlled exhaust valve 4; the first gas-controlled exhaust valve 4 is connected to the rocket tank 1 and the first Laval nozzle 3, and can eject the gas cushion gas in the rocket tank 1 through the first Laval nozzle 3 to generate thrust.

[0026] In the second control component, the second normally closed solenoid valve 11 is connected to the control gas pipeline 5 and the rocket-borne control system 14, and can be controlled by it to turn the gas source on and off, thereby controlling the state of the third gas-controlled exhaust valve 12; the third gas-controlled exhaust valve 12 is connected to the rocket tank 1 and the second Laval nozzle 13, and can eject the gas cushion gas in the rocket tank 1 through the second Laval nozzle 13 to generate thrust.

[0027] The two work together to enable the rocket-borne control system 14 to precisely control the jetting of the first Laval nozzle 3 and the second Laval nozzle 13 by controlling the first normally closed solenoid valve 7 and the second normally closed solenoid valve 11 according to the rocket's attitude requirements, thereby providing the necessary attitude control force for the rocket's unpowered gliding phase and achieving attitude regulation.

[0028] The working principle and usage process of this utility model are as follows: During the pre-launch refueling process of rocket tank 1, the filling and discharging valve 2 is opened and connected to the ground air supply pipeline. The normally open solenoid valve 10 is not energized and is in the open state. The first normally closed solenoid valve 7 and the second normally closed solenoid valve 11 are energized and are in the open state. The ground supplies control gas, and the first air-controlled exhaust valve 4, the second air-controlled exhaust valve 8, and the third air-controlled exhaust valve 12 are opened to exhaust the rocket tank 1.

[0029] After the rocket propellant tank 1 is filled with fuel before launch, the inflation / deflation valve 2 opens and connects to the ground gas supply line. The normally open solenoid valve 10 is energized and closed, while the first normally closed solenoid valve 7 and the second normally closed solenoid valve 11 are de-energized and closed. The first gas-controlled exhaust valve 4, the second gas-controlled exhaust valve 8, and the third gas-controlled exhaust valve 12 are closed, and the rocket propellant tank 1 stops venting. The ground continues to supply gas, and after the gas cylinder 9 is filled to the specified pressure, the inflation / deflation valve 2 closes.

[0030] During rocket flight, normally open solenoid valve 10 is energized and closed, first normally closed solenoid valve 7 and second normally closed solenoid valve 11 are de-energized and closed, first pneumatic exhaust valve 4, second pneumatic exhaust valve 8 and third pneumatic exhaust valve 12 are closed, and rocket tank 1 stops venting.

[0031] After the rocket engine shuts down, during the unpowered gliding phase, the rocket is in a state without attitude control constraints. The onboard control system 14 judges the rocket's attitude in real time based on the rocket's flight attitude. When the rocket's attitude deflection is too large, it controls the first normally closed solenoid valve 7 or the second normally closed solenoid valve 11 to be energized; when the rocket's attitude is within the preset deflection range, it controls the first normally closed solenoid valve 7 or the second normally closed solenoid valve 11 to be de-energized. This, in turn, controls the first pneumatic exhaust valve 4 and the third pneumatic exhaust valve 12 to open or close, providing attitude control force for the rocket during the unpowered gliding phase.

[0032] After the rocket is recovered on the ground, the normally open solenoid valve 10 is de-energized and in the open state, the second pneumatic exhaust valve 8 is open, the first normally closed solenoid valve 7 and the second normally closed solenoid valve 11 are de-energized, the first pneumatic exhaust valve 4 and the third pneumatic exhaust valve 12 are closed, and the rocket tank 1 is depressurized by exhaust through the exhaust guide 6.

[0033] It should be noted that, in this document, terms such as "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0034] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank, comprising a rocket propellant tank (1) and a control gas cylinder (9), characterized in that: The rocket storage tank (1) is connected to the control gas cylinder (9) through the gas control assembly, and the control gas cylinder (9) is connected to the filling and discharging valve (2) through the control gas pipeline (5); The control gas pipeline (5) is connected to the rocket tank (1) through the attitude control component. Both the attitude control component and the control gas component are connected to the rocket control system (14) through the control cable (15).

2. The exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank according to claim 1, characterized in that: The gas control assembly includes a normally open solenoid valve (10) and a second gas control exhaust valve (8). The normally open solenoid valve (10) is connected to the control gas cylinder (9) through the control gas pipeline (5). The normally open solenoid valve (10) is connected to the first end of the second pneumatic exhaust valve (8) on the side away from the control gas cylinder (9), the second end of the second pneumatic exhaust valve (8) is connected to the rocket storage tank (1), and the third end of the second pneumatic exhaust valve (8) is connected to the exhaust guide shroud (6). The second pneumatic exhaust valve (8) is connected to the rocket-borne control system (14) via a control cable (15).

3. The exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank according to claim 1, characterized in that: The attitude control component includes a first control component and a second control component. Both the first control component and the second control component are connected to the rocket-borne control system (14) via control cables (15). The first control component and the second control component are connected to the control air pipeline (5).

4. The exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank according to claim 3, characterized in that: The first control component includes a first normally closed solenoid valve (7) and a first pneumatic exhaust valve (4). The first normally closed solenoid valve (7) is connected to the control air pipeline (5). The first normally closed solenoid valve (7) is also connected to the rocket-borne control system (14) through a control cable (15). The first normally closed solenoid valve (7) is connected to the first end of the first pneumatic exhaust valve (4), the second end of the first pneumatic exhaust valve (4) is connected to the first Laval nozzle (3), and the third end of the first pneumatic exhaust valve (4) is connected to the rocket tank (1).

5. The exhaust attitude control system based on a recyclable cryogenic liquid stainless steel rocket propellant tank according to claim 3, characterized in that: The second control component includes a second normally closed solenoid valve (11) and a third pneumatic exhaust valve (12). The second normally closed solenoid valve (11) is connected to the control air pipeline (5). The second normally closed solenoid valve (11) is also connected to the rocket-borne control system (14) via a control cable (15). The second normally closed solenoid valve (11) is connected to the first end of the third pneumatic exhaust valve (12), the second end of the third pneumatic exhaust valve (12) is connected to the second Laval nozzle (13), and the third end of the third pneumatic exhaust valve (12) is connected to the rocket tank (1).

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