Integrated cold gas propulsion system

Abstract

The application relates to the technical field of rocket and missile attitude and orbit control, and particularly relates to an integrated cold gas dynamic system, which comprises a gas cylinder and a frame, the gas cylinder is used for storing cold gas medium, a flow channel is formed in the frame, one end of the flow channel is communicated with an output end of the gas cylinder, the other end of the flow channel is communicated with a thruster assembly, and the cold gas medium reaches the thruster assembly through the flow channel. The frame and the built-in flow channel are integrally formed through 3D printing, a large number of external pipelines and joints of a traditional system are cancelled, and the overall volume of the system is reduced by more than 50% compared with the traditional scheme. The compact structure can be adapted to small missiles, micro-nano satellites and other flight vehicles with narrow installation spaces. The integrated design has the built-in flow channel, more than 90% of external connection points are reduced, and the risk of pipeline leakage and loosening is reduced from the root. Meanwhile, the overall structure of 3D printing has stronger vibration resistance and impact resistance, and can adapt to harsh working conditions of high-speed flight of the flight vehicle.

Description

Technical Field

[0001] This application relates to the field of rocket and missile attitude and orbit control technology, and in particular to an integrated cold gas propulsion system. Background Technology

[0002] The cold gas propulsion system is a core subsystem for attitude and orbit control of rockets, missiles and other aircraft. It generates reaction force by injecting high-pressure cold gas to achieve attitude corrections such as pitch, yaw and roll, as well as key actions such as orbit transfer and orbital insertion accuracy adjustment.

[0003] Traditional air-cooled power systems employ a distributed piping architecture, where core components such as gas cylinders, valves, and thrusters must be connected in series via welded pipes. This architecture presents significant technical bottlenecks. Low space utilization: The processing and assembly of welded pipes require a large amount of operating space, and components such as pipe bends and joints further increase the system volume, making it difficult to adapt to the design requirements of miniaturized and highly integrated aircraft.

[0004] Large weight redundancy: The weight of the pipeline itself, made of metal, plus the reinforcement structure set up to ensure connection strength, greatly increases the overall weight of the system and reduces the payload ratio of the aircraft.

[0005] Numerous reliability risks: The multi-pipeline and multi-connector connection method has multiple potential leakage points. Under the vibration and impact environment of high-speed flight of the aircraft, failures such as pipeline loosening and seal failure are likely to occur, affecting the stable operation of the system.

[0006] Low assembly efficiency: Distributed components need to be assembled and debugged one by one, the assembly process is cumbersome, and the installation errors of different components are easy to accumulate, which increases the difficulty of system debugging.

[0007] With the development of aerospace technology, the requirements for miniaturization, lightweighting, and high reliability of aircraft power systems are becoming increasingly stringent. The maturity of 3D printing technology provides technical support for the integrated innovation of cold gas propulsion systems, enabling the one-piece molding of complex structures and providing a feasible path to solve the technical pain points of traditional systems. Summary of the Invention

[0008] This application provides an integrated air-cooled propulsion system to solve the problems of large size and complex piping in existing air-cooled propulsion systems, thereby achieving miniaturization and lightweight design of the system while ensuring the accuracy of attitude and orbit control.

[0009] This application provides an integrated air conditioning power system, including: Gas cylinders are used to store cold air media. The frame contains a flow channel. One end of the flow channel is connected to the output end of the gas cylinder, and the other end is connected to the thruster assembly. The cold gas medium reaches the thruster assembly through the flow channel.

[0010] In one possible design, the frame and flow channels are 3D printed structures, with the frame made of aluminum alloy.

[0011] In one possible design, the gas cylinder is a 3D-printed structure made of all-metal titanium alloy.

[0012] In one possible design, the frame includes a first ring, a second ring, and an intermediate connecting part. The first ring and the second ring are respectively annular and coaxially arranged. The intermediate connecting part is rod-shaped. The flow channels in the first ring and the second ring extend along their respective circumferential directions. The flow channel in the intermediate connecting part extends along its length direction. One end of the intermediate connecting part is connected to the flow channel of the first ring, and the other end is connected to the flow channel of the second ring.

[0013] In one possible design, the gas cylinder is fixed between a columnar frame formed by multiple intermediate connecting parts.

[0014] In one possible design, the outer wall of the gas cylinder is provided with a first ear bracket, and the middle connecting part is provided with a second ear bracket. The gas cylinder is fixed between the columnar frames formed by the first ear bracket and the second ear bracket.

[0015] In one possible design, an inflation valve is installed at the input end of the gas cylinder, an electric explosion valve is installed at the output end of the gas cylinder, and a pressure reducing valve is installed on the intermediate connection. The input end of the pressure reducing valve and the output end of the electric explosion valve are connected by a pipeline.

[0016] In one possible design, the thruster assembly includes an attitude control thruster and an orbit control thruster, with the attitude control thrusters spaced apart on a first ring and the orbit control thrusters spaced apart on a second ring.

[0017] In one possible design, a first electric explosion branch valve is installed on the side of the intermediate connecting part near the first ring of the pressure reducing valve, and a second electric explosion branch valve is installed on the side of the intermediate connecting part near the second ring of the pressure reducing valve.

[0018] In one possible design, a safety valve is installed on at least one of the first ring, the second ring, and the intermediate connecting part.

[0019] The beneficial effects of this application are as follows: The integrated cold air propulsion system of this application features a frame and internal flow channels formed by 3D printing, eliminating a large number of external pipes and joints compared to traditional systems. The overall system volume is reduced by more than 50% compared to traditional solutions. The compact structure can be adapted to aircraft with limited installation space, such as small missiles and micro / nano satellites, significantly expanding the system's application scenarios.

[0020] The frame is made of lightweight, high-strength aluminum alloy, and the gas cylinders are 3D-printed from high-strength titanium alloy. Combined with a streamlined piping design, the overall system weight is reduced by more than 40% compared to traditional solutions. This lightweight design directly improves the aircraft's payload ratio, allowing it to carry more functional modules or extend its flight time.

[0021] The integrated design incorporates the flow channels, reducing external connection points by more than 90% and fundamentally lowering the risk of pipe leakage and loosening. Simultaneously, the 3D-printed overall structure exhibits stronger vibration and impact resistance, enabling it to withstand the harsh conditions of high-speed aircraft flight, and increasing the system's mean time between failures (MTBF) to more than three times that of traditional solutions.

[0022] The system's core components are directly integrated into the frame via threaded interfaces, reducing assembly steps by over 60% and eliminating the need for complex pipe welding and debugging, thus significantly shortening the production cycle. During maintenance, damaged components can be individually removed and replaced without disassembling the entire system, reducing maintenance costs and time.

[0023] The smooth, streamlined structure of the annular flow channel reduces frictional resistance and localized eddies in the working fluid flow, lowering pressure loss by more than 30% and significantly improving thrust output stability. Combined with the millisecond-level response characteristics of the electro-explosive valve, the system can quickly respond to flight control commands, improving the accuracy of attitude and trajectory adjustments by 25% compared to traditional solutions. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the structure of the integrated air conditioning power system provided in the embodiments of this application; Figure label: 1. Gas cylinder; 2. Frame; 21. First ring; 22. Second ring; 23. Intermediate connecting part; 3. Inflation valve; 4. Electric explosion valve; 5. Pressure reducing valve; 6. Safety valve; 7. Attitude control thruster; 8. Rail control thruster. Detailed Implementation

[0026] The technical solutions of this application will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0027] The following is combined with Figure 1 This describes the integrated air conditioning power system provided in the embodiments of this application.

[0028] Reference Figure 1 As shown, the integrated cold gas power system provided in this embodiment includes a gas cylinder 1 and a frame 2. The gas cylinder 1 is used to store a cold gas medium, which is helium in this embodiment. A flow channel is formed inside the frame 2, one end of which is connected to the output end of the gas cylinder 1, and the other end is connected to the thruster assembly, allowing the cold gas medium to reach the thruster assembly through the flow channel.

[0029] Both the frame 2 and the flow channel are 3D printed integrated structures, with the frame 2 made of aluminum alloy. The frame 2 specifically includes a first ring portion 21, a second ring portion 22, and an intermediate connecting portion 23. The first ring portion 21 and the second ring portion 22 are each annular in structure and are coaxially arranged. The intermediate connecting portion 23 is rod-shaped, with both ends fixedly connected to the first ring portion 21 and the second ring portion 22, respectively.

[0030] By integrating the frame 2 with the built-in flow channel through 3D printing, a large number of external pipes and joints in traditional systems are eliminated, reducing the overall system volume by more than 50% compared to traditional solutions. The compact structure is adaptable to aircraft with limited installation space, such as small missiles and micro / nano satellites. The integrated design with the flow channel built-in reduces external connection points by more than 90%, fundamentally lowering the risk of pipe leaks and loosening.

[0031] In some specific embodiments, the flow channels within the first ring portion 21 and the second ring portion 22 extend circumferentially and are annular. The smooth, streamlined structure of the annular flow channels reduces frictional resistance and localized eddies in the working fluid flow, lowers pressure loss by more than 30%, and significantly improves thrust output stability.

[0032] The flow channel within the intermediate connecting portion 23 extends along its length and is linear. One end of the intermediate connecting portion 23 communicates with the flow channel of the first ring portion 21, and the other end communicates with the flow channel of the second ring portion 22. The intermediate connecting portion 23 delivers the cooling medium to the flow channel of the first ring portion 21 or the second ring portion 22.

[0033] In some specific embodiments, the gas cylinder 1 is a 3D-printed structure made of all-metal titanium alloy. The gas cylinder 1 is fixed between columnar frames 2 formed by multiple intermediate connecting parts 23.

[0034] Specifically, the outer wall of the gas cylinder 1 is provided with a first lug, and the middle connecting part 23 is provided with a second lug. The gas cylinder 1 is fixed by the cooperation of the first lug and the second lug, for example by welding or threaded connection, to achieve a stable connection and convenient assembly and disassembly.

[0035] In some specific embodiments, a filling valve 3 is installed at the input end of gas cylinder 1 for replenishing high-pressure helium gas into gas cylinder 1. An electric explosion valve 4 is installed at the output end of gas cylinder 1 for controlling the flow of cold gas medium inside gas cylinder 1.

[0036] A pressure reducing valve 5 is installed on the intermediate connection part 23. The input end of the pressure reducing valve 5 is connected to the output end of the electric explosion valve 4 through a pipe. The output end of the pressure reducing valve 5 is connected to the flow channel in the intermediate connection part 23. The pressure reducing valve 5 can reduce the pressure of the high-pressure cold gas medium output from the gas cylinder 1 to the system working pressure.

[0037] The thruster assembly includes an attitude control thruster 7 and an orbit control thruster 8. The attitude control thrusters 7 are spaced apart on the first ring 21 and are used to adjust the attitude of the aircraft. The orbit control thrusters 8 are spaced apart on the second ring 22 and are used to transfer the aircraft's orbit. The cool gas medium, after being depressurized by the pressure reducing valve 5, flows into the attitude control thrusters 7 and the orbit control thrusters 8.

[0038] In some specific embodiments, the pressure reducing valve 5 is installed in the middle of the intermediate connecting part 23, and a first electrically detonating branch valve is installed on the intermediate connecting part 23 on the side of the pressure reducing valve 5 near the first ring part 21. A second electrically detonating branch valve is installed on the intermediate connecting part 23 on the side of the pressure reducing valve 5 near the second ring part 22. This allows for a rapid change in the flow direction of the cooling gas medium to quickly reach the attitude control thruster 7 or the orbital control thruster 8. Specifically: When the flight control system sends a power-on command to the attitude control branch electro-explosive valve 4, the first electro-explosive branch valve is triggered and opened, while the orbit control branch electro-explosive valve 4 remains de-energized and closed. High-pressure helium gas enters the attitude control thruster 7 through the main flow channel and the attitude control branch flow channel, generating a small thrust for attitude adjustment.

[0039] When the flight control system sends a power-on command to the orbit control branch electro-explosive valve 4, the second electro-explosive branch valve is triggered and opened, while the attitude control branch electro-explosive valve 4 remains de-energized and closed. High-pressure helium gas enters the orbit control thruster 8 through the main flow channel and the orbit control branch flow channel, generating a large thrust for orbit transfer.

[0040] If attitude and trajectory need to be adjusted simultaneously, the flight control system simultaneously sends energizing commands to the first and second electric blast valves, and the two thrusters work synchronously.

[0041] In some embodiments, at least one of the first ring portion 21, the second ring portion 22, and the intermediate connecting portion 23 is equipped with a safety valve 6. When the pressure in the system exceeds a preset threshold, the safety valve 6 automatically opens to release pressure and ensure system safety.

[0042] The initial state of the integrated air conditioning power system of this application: Cylinder 1 is pre-filled with high-pressure helium, maintaining a pressure of 30 MPa, and filling valve 3 is in a closed and sealed state. The main electric explosion valve 4, the first electric explosion branch valve, and the second electric explosion branch valve at the output end of cylinder 1 are all in a de-energized and closed state. Pressure reducing valve 5 has a preset working pressure of 5 MPa, and safety valve 6 has a preset pressure relief threshold of 6 MPa. No working propellant is ejected from the nozzles of attitude control thruster 7 and orbit control thruster 8; the system is in standby mode.

[0043] The operating status of the integrated air conditioning power system in this application: Step 1: Pressurization and replenishment (system maintenance phase) Connect the external pressurization device to the inflation valve 3 at the input end of gas cylinder 1, and open the inflation valve 3.

[0044] High-pressure helium gas is injected into titanium alloy cylinder 1 through filling valve 3, and the pressure of cylinder 1 is monitored in real time.

[0045] When the pressure inside cylinder 1 reaches 30MPa, close inflation valve 3, disconnect the external pressurization equipment, and complete the pressurization process.

[0046] Step 2: Command Reception and Main Valve Opening (Flight Control Phase) The aircraft's flight control system sends attitude or trajectory adjustment commands to the system control module based on flight requirements. The control module sends an energizing trigger signal to the main electro-explosive valve 4 at the output end of gas cylinder 1. Upon receiving the electrical signal, the main electro-explosive valve 4 opens its flow channel within milliseconds, allowing high-pressure helium gas to flow from gas cylinder 1 into the connecting pipeline and into the input end of the pressure reducing valve 5.

[0047] Step 3: Pressure Adjustment High-pressure helium gas flows through pressure reducing valve 5, which stabilizes the input pressure from 30 MPa to a working pressure of 5 MPa. The depressurized helium gas then enters the main flow channel of the aluminum alloy frame 2, awaiting the opening command of the branch flow channel.

[0048] Step 4: Mode Switching and Thrust Output This system supports three working modes: attitude control, track control, and collaborative operation. Switching between these modes is achieved by controlling the opening and closing of the first and second electric blasting branch valves.

[0049] Attitude control mode: The flight control system sends an attitude adjustment command, and the control module sends an energizing signal to the first electro-explosive branch valve, while the second electro-explosive branch valve remains closed. The first electro-explosive branch valve opens, and helium gas enters the circumferential channel of the first ring section 21 through the flow channel of the intermediate connecting part 23. The helium gas is evenly distributed to each attitude control thruster 7 on the first ring section 21, and the thrusters eject helium gas to generate a small thrust, realizing the pitch, yaw, and roll attitude correction of the aircraft.

[0050] Track control mode: The flight control system sends an orbit transfer command, and the control module sends an energizing signal to the second electro-explosive branch valve, while the first electro-explosive branch valve remains closed. The second electro-explosive branch valve opens, and helium gas enters the circumferential channel of the second ring section 22 through the flow channel of the intermediate connecting part 23. The helium gas is evenly distributed to each orbit control thruster 8 on the second ring section 22. The thrusters eject helium gas to generate a large thrust, changing the flight speed and direction of the aircraft and completing the orbit adjustment.

[0051] Collaborative Mode: The flight control system sends attitude and orbit adjustment commands, and the control module simultaneously sends energizing signals to the first and second electrically operated valves. The two electrically operated valves open synchronously, and helium gas enters the two annular flow channels respectively. The attitude control and orbit control thrusters 8 work simultaneously to achieve coordinated correction of the aircraft's attitude and orbit.

[0052] Step 5: Safety pressure relief protection If the pressure in the system flow channel exceeds the safety threshold of 6MPa due to valve failure or pressure fluctuations.

[0053] The safety valve 6 installed in the ring or intermediate connection 23 opens automatically to release excess helium.

[0054] Once the system pressure drops back to a safe range, safety valve 6 will automatically close, ensuring the safety of the system structure and components.

[0055] Step 6: Work completed and system reset After the flight control system completes its adjustments, it sends a stop command, and the control module cuts off the power supply to the electric explosion valve 4. The main electric explosion valve 4, the first electric explosion branch valve, and the second electric explosion branch valve reset and close, the flow path is disconnected, and the thruster stops injecting power. The system returns to its initial standby state, awaiting the next control command.

[0056] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0057] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0058] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between components; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0059] In this application, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0060] Although embodiments of this application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting this application. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of this application.

Claims

1. An integrated air conditioning power system, characterized in that, include: Gas cylinder, the gas cylinder being used to store a cold gas medium; A frame with a flow channel formed within it, one end of which is connected to the output end of the gas cylinder and the other end of which is connected to the thruster assembly, through which the cold gas medium reaches the thruster assembly.

2. The integrated air conditioning power system according to claim 1, characterized in that, The frame and the flow channel are 3D printed structures, and the frame is made of aluminum alloy.

3. The integrated air conditioning power system according to claim 2, characterized in that, The gas cylinder is a 3D printed structure and is made of all-metal titanium alloy material.

4. The integrated air conditioning power system according to claim 3, characterized in that, The frame includes a first ring portion, a second ring portion, and an intermediate connecting portion. The first ring portion and the second ring portion are respectively annular and coaxially arranged. The intermediate connecting portion is rod-shaped. The flow channels in the first ring portion and the second ring portion extend along their respective circumferential directions. The flow channel in the intermediate connecting portion extends along its length direction. One end of the intermediate connecting portion is connected to the flow channel of the first ring portion, and the other end is connected to the flow channel of the second ring portion.

5. The integrated air conditioning power system according to claim 4, characterized in that, The gas cylinder is fixed between the columnar frames formed by the multiple intermediate connecting parts.

6. The integrated air conditioning power system according to claim 5, characterized in that, The outer wall of the gas cylinder is provided with a first ear bracket, and the intermediate connecting part is provided with a second ear bracket. The gas cylinder is fixed between the columnar frames formed by the first ear bracket and the second ear bracket.

7. The integrated air conditioning power system according to any one of claims 4-6, characterized in that, The gas cylinder is equipped with an inflation valve at its input end and an electric explosion valve at its output end. A pressure reducing valve is installed on the intermediate connecting part, and the input end of the pressure reducing valve is connected to the output end of the electric explosion valve through a pipeline.

8. The integrated air conditioning power system according to any one of claims 4-6, characterized in that, The thruster assembly includes an attitude control thruster and an orbit control thruster, wherein the attitude control thrusters are spaced apart on the first ring portion and the orbit control thrusters are spaced apart on the second ring portion.

9. The integrated air conditioning power system according to any one of claims 4-6, characterized in that, A first electric explosion branch valve is installed on the intermediate connecting part on the side of the pressure reducing valve near the first ring, and a second electric explosion branch valve is installed on the intermediate connecting part on the side of the pressure reducing valve near the second ring.

10. The integrated air conditioning power system according to any one of claims 4-6, characterized in that, A safety valve is installed on at least one of the first ring portion, the second ring portion, and the intermediate connecting portion.

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