Cold launch device and method of using the same

Abstract

The present invention discloses a cold launch device, comprising a volume regulating plug, a nut, a power compartment, an O-ring, a power compartment pressure sensor, a plug, a solenoid valve, an intermediate compartment, a stepper motor, a pressure reducing valve, an intermediate compartment pressure sensor, a pressure gauge, a tray, a launch tube, a payload, and a controller. The present invention also discloses a method for using the cold launch device. The cold launch device and its method of use have a simple structure, are easy to manufacture and install, and have low maintenance costs. They can be customized according to test mission requirements, resolving the issues of high initial launch acceleration peaks and difficulty in precisely controlling the launch process, which are common in traditional launch methods.

Description

Technical Field

[0001] The present invention relates to the technical field of cold launch devices, and in particular to a cold launch device and a method for using the same. Background Art

[0002] With the continuous development of aerospace and natural science and technology, the demand for launching payloads such as drones, high-altitude probes, and meteorological bombs to explore and utilize space resources is increasing. Existing payloads often carry various precision detection or control instrument components. These components have limited ability to withstand peak flight acceleration and are prone to performance drift or failure under high launch acceleration or high temperature conditions. To address this high peak acceleration, some aircraft require thrust reduction during certain flight phases to prevent damage to their structures or precision instruments. Currently, various payloads are primarily launched using thermal launch or cold launch methods such as gas, compressed air, and gas-steam. While these launch methods can achieve the intended launch mission objectives, they present numerous practical challenges, including high infrared signatures during the launch process, device ablation and corrosion, high initial acceleration peaks, unstable exit velocity, and low power distribution efficiency, which introduce uncertainty into the safe launch of the payloads.

[0003] To address the launch uncertainty caused by the high peak acceleration induced by transient high pressure during the initial launch phase of traditional hot launch and existing cold launch systems, there is an urgent need to develop a new cold launch device with low transient acceleration, smooth payload acceleration, and no ablation. This can meet the current launch requirements of various types of drones, high-altitude probes, meteorological missiles, and other payloads with limited peak acceleration. There are no solutions to the technical problems of launch acceleration control technology, and therefore, an effective solution is urgently needed to address these issues. Summary of the Invention

[0004] In order to solve the above problems, the purpose of the present invention is to provide a cold launch device and a method of use thereof, so as to solve the technical problem of launch uncertainty caused by the large acceleration peak induced by the instantaneous high pressure at the initial stage of launch during the launch process of traditional hot launch and existing cold launch systems; it has a simple structure, is easy to process and install, and has low maintenance costs. It can be customized according to the requirements of the test mission, so as to realize the advance grasp and precise control of the launch acceleration peak of the load in the launch tube, thereby improving the safety and reliability of the load launch process.

[0005] In order to achieve the above object, the technical solution of the present invention is as follows:

[0006] The present invention provides a cold launch device, comprising a volume regulating plug, a nut, a power cabin, an O-ring, a power cabin pressure sensor, a plug, a solenoid valve, an intermediate cabin, a stepping motor, a pressure reducing valve, an intermediate cabin pressure sensor, a pressure gauge, a tray, a launch tube, a payload, and a controller; the volume regulating plug and the O-ring are provided inside the power cabin, and the position of the volume regulating plug is controlled by the nut; the power cabin pressure sensor and the plug are symmetrically installed on both sides of the power cabin; the power cabin is installed in coordination with the intermediate cabin, and the intermediate cabin is assembled and connected to the launch tube; the tray is installed in coordination with the payload inside the launch tube and moves along the launch tube, the intermediate cabin pressure sensor and the pressure gauge are installed on one side of the intermediate cabin, and the stepping motor is installed on the other side; the solenoid valve and the pressure reducing valve are installed at the center of the top of the power cabin; the pressure reducing valve is assembled and connected to the pressure gauge and the stepping motor respectively; the controller is connected to the stepping motor, the power cabin pressure sensor, the intermediate cabin pressure sensor, and the solenoid valve respectively through data cables.

[0007] Furthermore, the power cabin main body is a closed hollow cylinder, including a power cabin body, a power cabin sensor interface and a power cabin filling port arranged on the side wall of the power cabin body, a power cabin valve interface arranged on the top of the power cabin body, and a power cabin threaded port arranged on the bottom of the power cabin body; the power cabin sensor interface is installed in cooperation with the power cabin pressure sensor, and the power cabin filling port is installed in cooperation with the plug; the power cabin valve interface is installed in cooperation with the solenoid valve and the pressure reducing valve, the power cabin top is installed in cooperation with the middle cabin, and the power cabin threaded port is installed in cooperation with the volume regulating plug.

[0008] Furthermore, the main body of the volume regulating plug is a T-shaped cylinder, including a volume regulating plug body, a volume regulating plug groove arranged circumferentially on the side wall of the volume regulating plug body, and a volume regulating plug threaded rod fixedly connected to the volume regulating plug body; the volume regulating plug groove is used to assemble the O-ring, the volume regulating plug body and the O-ring are installed in cooperation with the inside of the power compartment body, and the volume regulating plug threaded rod is installed in cooperation with the threaded port of the power compartment.

[0009] Furthermore, the main body of the intermediate cabin is a hollow cylinder, including an intermediate cabin body, a pressure gauge interface and a sensor interface arranged on the wall of one side of the intermediate cabin body, an intermediate cabin screw mouth arranged on the wall of the other side of the intermediate cabin body, an intermediate cabin main slot arranged at the bottom of the intermediate cabin, and an intermediate cabin secondary slot arranged at the top of the intermediate cabin; the pressure gauge interface is installed in conjunction with the pressure gauge, the sensor interface is used to fixedly install the intermediate cabin pressure sensor, the intermediate cabin main slot is installed in conjunction with the power cabin, and the intermediate cabin secondary slot is fixedly installed on the launch tube.

[0010] Furthermore, the pressure reducing valve includes a pressure reducing valve slot, a pressure reducing valve wire and a pressure reducing valve screw at the bottom; the pressure reducing valve is installed in cooperation with the solenoid valve through the pressure reducing valve slot, and the pressure reducing valve wire is connected to the pressure gauge; the pressure reducing valve screw is installed in cooperation with the screw port of the intermediate compartment.

[0011] Furthermore, the launch tube body is a hollow cylinder, including a launch tube body, a launch tube slot arranged at the bottom of the launch tube body, and a launch tube platform arranged inside the launch tube; the launch tube slot is installed in cooperation with the middle compartment slot, and the launch tube platform is installed in cooperation with the tray.

[0012] Furthermore, the pallet includes a pallet main end surface and a pallet secondary end surface cavity; the outer diameter of the pallet main end surface is smaller than the inner diameter of the launch tube body, and the pallet secondary end surface cavity is installed in cooperation with the load.

[0013] The present invention also provides a method for using the cold emission device, comprising the following steps:

[0014] S1. Cold launch device assembly and preparation;

[0015] S2. Launch experiment of cold launch device.

[0016] Furthermore, the S1 includes the following steps:

[0017] S11. Design the power compartment, volume regulating plug, launch tube, and tray, and select appropriate solenoid valves and pressure reducing valves, as well as pressure sensors and controllers with appropriate ranges.

[0018] S12. Assemble the selected components according to the cold launch device to form a cold launch device;

[0019] S13. Check the rationality of the assembly relationship of each component, the effectiveness of the solenoid valve's opening and closing action, the reliability of the stepper motor's ability to regulate the pressure reducing valve, and the overall airtightness of the cold launch device;

[0020] S14. Start the controller, close the solenoid valve and the pressure reducing valve, fill the power compartment with high-pressure gas to the target pressure, and record the pressure-time curve of the power compartment pressure sensor;

[0021] S15. Load the payload and tray into the cold launch device and sequentially open the solenoid valve and pressure relief valve to conduct a cold launch simulation experiment.

[0022] S16. If the pressure value in the power cabin continues to decrease before the solenoid valve is opened, or if the data of the power cabin pressure sensor and the intermediate cabin pressure sensor are abnormal and the stepper motor cannot effectively adjust the pressure control capability of the pressure reducing valve after the solenoid valve and the pressure reducing valve are opened, repeat steps S11 to S14 until the overall air tightness of the cold launch device, the reliability of the pressure control functions of the power cabin pressure sensor, the intermediate cabin pressure sensor, the solenoid valve, and the pressure reducing valve are verified.

[0023] Furthermore, the S2 includes the following steps:

[0024] S21. According to the load acceleration peak a max , the main end surface area of ​​the tray is A t , pallet mass m t , load mass m z , calculate the pressure reducing valve opening threshold pressure p y , power cabin gas filling pressure p d and the pressure reducing valve opening threshold pressure p y Satisfied: p d =50p y relation:

[0025]

[0026] S22. For the power compartment volume V d , whose size is determined by the volume V of the intermediate compartment m , launch tube volume V f Jointly determine the following:

[0027]

[0028] S23. Preset the power compartment volume V according to steps S21 and S22. d and filling pressure p d The controller starts the solenoid valve and stepper motor. The high-pressure gas enters the intermediate cabin through the solenoid valve and the pressure reducing valve in turn, pushing the tray and the load in the launch tube to move along the axis of the launch tube toward the tube mouth. The controller, the intermediate cabin pressure sensor and the stepper motor form a closed-loop control system. When the pressure p in the intermediate cabin meets |pp y | / p y When the pressure is less than or equal to 10%, the controller actively sends a pressure reduction control command to the stepper motor, and the stepper motor drives the pressure reducing valve screw to reduce the flow and pressure of the high-pressure gas through the pressure reducing valve, thereby reducing the gas pressure in the launch tube and the intermediate cabin, and completing the throttling pressure control and load reduction acceleration goals. Conversely, the controller actively sends a pressure increase control command to the stepper motor until the single launch is completed;

[0029] S24. Check and clean the cold launch equipment, test data processing and archiving, and complete the launch mission.

[0030] By adopting the above technical solution, the present invention has the following advantages:

[0031] First, the present invention proposes a cold launch device and a method for using the same. Based on modular design thinking, the power cabin volume change function can be realized by co-installing the volume adjustment plug and the power cabin; by replacing the intermediate cabin and the launch tube bayonet size, the launch function of payloads of different sizes can be realized, effectively solving the problem of replacing the launch power cabin for launching different payloads.

[0032] Second, the present invention proposes a cold launch device and its use method. By designing the power cabin volume and filling pressure, the pressure control range of the pressure reducing valve and the size of the intermediate cabin, a wide acceleration range of 0 to 150g and a wide pressure range of 0 to 10MPa can be created according to the payload launch requirements, so as to match the launch acceleration with the target launch mission, and provide technical support for further launching various types of aircraft under specific acceleration conditions.

[0033] Third, the present invention proposes a cold launch device and its use method, which adopts a set of controllers, pressure reducing valves, pressure sensors and auxiliary components to achieve the goal of efficient and accurate dynamic control of the launch acceleration of the internal load of the device, with low cost and effective reduction of system complexity.

[0034] Fourth, the present invention proposes a cold launch device and its use method. The controller, pressure sensor, stepper motor, pressure reducing valve and other components constitute a closed-loop control system. By presetting the threshold pressure, the peak value of the launch acceleration of the load in the launch tube can be pre-grasped and precisely controlled, thereby improving the safety and reliability of the load launch process.

[0035] Fifth, the present invention proposes a cold launch device and its use method, which has a simple structure, is easy to process and install, and has low maintenance costs. It can be customized according to the requirements of the test mission, and solves the problems of high initial launch acceleration peak and difficulty in precise control of the launch process in traditional launch methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a cross-sectional view of the cold emission device of the present invention;

[0037] Figure 2 A three-dimensional partial cross-sectional view of the cold emission device of the present invention;

[0038] Figure 3 This is a schematic structural diagram of the volume regulating plug of the cold emission device of the present invention;

[0039] Figure 4 A structural cross-sectional view of the power cabin of the cold launch device of the present invention;

[0040] Figure 5 This is a schematic structural diagram of the intermediate cabin of the cold launch device of the present invention;

[0041] Figure 6 This is a schematic structural diagram of a pressure reducing valve of a cold emission device according to the present invention;

[0042] Figure 7 This is a schematic structural diagram of the launch tube of the cold launch device of the present invention;

[0043] Figure 8 This is a structural cross-sectional view of the tray of the cold launch device of the present invention.

[0044] Figure 1: 1-volume regulating plug; 2-nut; 3-power compartment; 4-O-ring; 5-power compartment pressure sensor; 6-plug; 7-solenoid valve; 8-middle compartment; 9-stepping motor; 10-pressure reducing valve; 11-middle compartment pressure sensor; 12-pressure gauge; 13-tray; 14-launch tube; 15-payload; 16-controller; 1a-volume regulating plug body; 1b-volume regulating plug groove; 1c-volume regulating plug threaded rod; 3a-power compartment body; 3b-power compartment sensor interface; 3c —Power compartment valve interface; 3d—Power compartment filling port; 3e—Power compartment threaded port; 8a—Intermediate compartment body; 8b—Pressure gauge interface; 8c—Sensor interface; 8d—Intermediate compartment main slot; 8e—Intermediate compartment secondary slot; 8f—Intermediate compartment screw port; 10a—Pressure reducing valve slot; 10b—Pressure reducing valve wire; 10c—Pressure reducing valve screw; 13a—Pallet main end face; 13b—Pallet secondary end face cavity; 14a—Launch tube body; 14b—Launch tube slot; 14c—Launch tube platform. DETAILED DESCRIPTION

[0045] The technical solution of the present invention is described in detail below with reference to the accompanying drawings. It should be noted that, in this document, relational terms such as first and second, etc., are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include," "comprise," or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article, or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article, or apparatus.

[0046] like Figure 1 、 Figure 2 As shown, the present invention provides a cold launch device, which includes a volume regulating plug 1, a nut 2, a power cabin 3, an O-ring 4, a power cabin pressure sensor 5, a plug 6, a solenoid valve 7, an intermediate cabin 8, a stepper motor 9, a pressure reducing valve 10, an intermediate cabin pressure sensor 11, a pressure gauge 12, a tray 13, a launch tube 14, a payload 15 and a controller 16.

[0047] The volume regulating plug 1 and O-ring 4 are installed in conjunction with each other inside the power compartment 3, with the position of the volume regulating plug 1 controlled by a nut 2. A power compartment pressure sensor 5 and a plug 6 are symmetrically mounted on both sides of the power compartment 3. The top of the power compartment 3 is mounted in conjunction with the bottom of the intermediate compartment 3, and the top of the intermediate compartment 3 is assembled with the launch tube 14. An intermediate compartment pressure sensor 11 and a pressure gauge 12 are installed on one side of the intermediate compartment 8, and a stepper motor 9 is installed on the other side. A solenoid valve 7 and a pressure reducing valve 10 are installed in sequence at the center of the top of the power compartment 3. The pressure reducing valve 10 is connected to the pressure gauge 12 and the stepper motor 9, respectively. The stepper motor 9, the power compartment pressure sensor 5, the intermediate compartment pressure sensor 11, and the solenoid valve 7 are connected to the controller 16 via data cables. The tray 13 and the payload 15 are installed in conjunction with each other inside the launch tube 14. The controller 16 sequentially opens the solenoid valve 7 and the pressure reducing valve 10 to release high-pressure gas into the intermediate compartment 8, pushing the tray 13 and the payload 15 along the launch tube 14, completing the launch mission of the payload 15.

[0048] like Figure 3 As shown, the main body of the power cabin 3 is a closed hollow cylinder made of 304 stainless steel, including a power cabin body 3a, a power cabin sensor interface 3b and a power cabin filling port 3d arranged on the side wall of the power cabin body, a power cabin valve interface 3c arranged on the top of the power cabin body and a power cabin threaded port 3e arranged on the bottom of the power cabin body; the power cabin sensor interface 3b is installed in conjunction with the power cabin pressure sensor 5, and the power cabin filling port 3d at the same height position on the symmetrical side wall is installed in conjunction with the plug 6; the hollow power cabin valve interface 3c in the shape of a boss at the center of the top of the power cabin 3 is installed in sequence with the solenoid valve 7 and the pressure reducing valve 10, the top of the power cabin 3 is installed in conjunction with the middle cabin 8, and the hollow power cabin threaded port 3d in the center of the bottom is installed in conjunction with the volume regulating plug 1.

[0049] like Figure 4 As shown, the main body of the volume regulating plug 1 is a T-shaped cylinder made of 45# steel, including a volume regulating plug body 1a, a volume regulating plug groove 1b arranged on the circumferential side wall of the volume regulating plug body, and a volume regulating plug threaded rod 1c fixedly connected to the volume regulating plug body; wherein, the diameter of the volume regulating plug body 1a is the same as the diameter of the power compartment body 3a, the volume regulating plug groove 1b on the circumferential side wall of the volume regulating plug body 1a is used to assemble the O-ring 4, the volume regulating plug body 1a and the O-ring are installed in cooperation with the interior of the power compartment body 3a, the volume regulating plug threaded rod 1c is installed in cooperation with the power compartment threaded port 3e, and the position of the volume regulating plug body 1a is adjusted by the volume regulating plug threaded rod 1c and the nut 2;

[0050] like Figure 5As shown, the main body of the intermediate cabin 8 is a hollow cylinder made of 7075Al, including an intermediate cabin body 8a, a pressure gauge interface 8b and a sensor interface 8c arranged on the wall of one side of the intermediate cabin body, an intermediate cabin screw port 8f arranged on the wall of the other side of the intermediate cabin body, an intermediate cabin main slot 8d arranged at the bottom of the intermediate cabin, and an intermediate cabin secondary slot 8e arranged at the top of the intermediate cabin; wherein, the pressure gauge interface 8b is installed in conjunction with the pressure gauge 12, the sensor interface 8c is used to fix the intermediate cabin pressure sensor 11, the intermediate cabin main slot 8d is installed in conjunction with the power cabin 3, the intermediate cabin secondary slot 8e is fixedly installed on the launch tube 14, and the intermediate cabin screw port 8f is used to connect the pressure reducing valve screw 10d and the stepper motor 9.

[0051] like Figure 6 As shown, the pressure reducing valve 10 includes a pressure reducing valve slot 10a at the bottom, a pressure reducing valve wire 10b, and a pressure reducing valve screw 10c. The pressure reducing valve 10 is mounted on the solenoid valve 7 via the pressure reducing valve slot 10a, and the pressure reducing valve wire 10b is connected to the pressure gauge 12. The pressure reducing valve screw 10c is mounted on the screw port 8f of the intermediate chamber. The pressure reducing valve 10 is connected to the pressure gauge 12 and the stepping motor 9 via the pressure reducing valve wire 10b and the pressure reducing valve screw 10c, respectively.

[0052] like Figure 7 As shown, the main body of the launch tube 14 is a hollow cylinder made of carbon fiber, including a launch tube body 14a, a launch tube slot 14b set at the bottom of the launch tube body, and a launch tube platform 14c set inside the launch tube. The launch tube slot 14b is mounted in conjunction with the intermediate compartment slot 8e, and the launch tube platform 14c is mounted in conjunction with the tray 13.

[0053] like Figure 8 As shown, the tray 13 includes a main end surface 13a and a secondary end surface cavity 13b. The outer diameter of the main end surface 13a is smaller than the inner diameter of the launch tube body 14a. The secondary end surface cavity 13b is mounted in conjunction with the payload 15. Both are built into the launch tube body 14a and can move along the launch tube 14.

[0054] The power compartment pressure sensor 5 and the intermediate compartment pressure sensor 11 have identical dimensions and measure pressure changes within the power compartment 3 and intermediate compartment 8, respectively. The pressure-regulating process of the pressure reducing valve 10 is accomplished by the stepper motor 9, which drives the pressure reducing valve screw 10c. This process is monitored by a pressure gauge 12. The power compartment pressure sensor 5, stepper motor 9, solenoid valve 7, and intermediate compartment pressure sensor 11 are all connected to the controller 16 via wires, which processes and analyzes data instructions.

[0055] In combination with the above solution, the present invention also provides a method for using the above cold emission device, which includes the following steps:

[0056] S1. Cold launch device assembly and preparation;

[0057] S1 includes the following specific steps:

[0058] S11. Based on the acceleration range that the target payload 15 can withstand, design the power nacelle 3, volume control plug 1, launch tube 14, tray 13, and other components. Select the solenoid valve 7 and pressure reducing valve 10 of appropriate size and pressure regulating capacity, the pressure sensors 5 and 11 of appropriate range, and the controller 16 with multi-channel signal acquisition and analysis capabilities to ensure the appropriate installation dimensions of each component.

[0059] S12: Assembling the selected components according to the cold launch device to form the cold launch device;

[0060] S13: Check the rationality of the assembly relationship of the various components of the device, the effectiveness of the opening and closing actuation of the solenoid valve 7, the reliability of the pressure control ability of the stepping motor 9 to adjust the pressure reducing valve 10, and the overall airtightness of the cold launch device;

[0061] S14: Start the controller, close the solenoid valve 7 and the pressure reducing valve 10, fill the power cabin 3 with high-pressure gas to the target pressure, and record the pressure-time curve of the power cabin pressure sensor 5.

[0062] S15: Load the payload 15 and the tray 13 into the cold launch device, and open the solenoid valve 7 and the pressure reducing valve 10 in sequence to carry out the cold launch simulation experiment.

[0063] S16: If the pressure value in the power cabin 3 continues to decrease before the solenoid valve 7 is opened, or after the solenoid valve 7 and the pressure reducing valve are opened, the data of the power cabin pressure sensor 5 and the intermediate cabin pressure sensor 11 are abnormal, and the stepper motor 9 cannot effectively adjust the pressure control capability of the pressure reducing valve 10, then repeat steps S1 to S4 until the overall air tightness of the cold launch device, the reliability of the pressure control function of the power cabin pressure sensor 5, the intermediate cabin pressure sensor 11 and the solenoid valve 7 and the pressure reducing valve 10 are verified.

[0064] S2. Launch experiment of cold launch device.

[0065] S2 includes the following specific steps:

[0066] S21: According to the load 15 acceleration peak a max , Area A of the main end surface of the tray 13 t , pallet 13 mass m t , load 15 mass m z , calculate the opening threshold pressure p of the pressure reducing valve 10 y , power cabin 3 gas filling pressure p d The opening threshold pressure p of the pressure reducing valve 10 y Satisfied: p d =50p y relation:

[0067]

[0068] S22: For power compartment 3 volume V d , whose size is determined by the volume V of the intermediate compartment m , launch tube volume V f Jointly decide to satisfy the following relationship:

[0069]

[0070] S9: Preset the volume V of the power compartment 3 according to S21 and S22 d and filling pressure p d Then the controller starts the solenoid valve 7 and the stepper motor 9. The high-pressure gas enters the intermediate cabin 8 through the solenoid valve 7 and the pressure reducing valve 10 in sequence, pushing the tray 13 and the payload 15 in the launch tube 14 to move along the axis of the launch tube 14 toward the muzzle of the launch tube. The controller 16, the intermediate cabin pressure sensor 11 and the stepper motor 9 form a closed-loop control system. When the pressure p in the intermediate cabin 8 meets |pp y | / p y When the pressure drops below 10%, controller 16 actively sends a pressure reduction control command to stepper motor 9, which drives pressure reducing valve screw 10c to reduce the flow and pressure of high-pressure gas through pressure reducing valve 10, lowering the gas pressure within launch tube 14 and intermediate chamber 8, achieving the goals of throttling pressure control and reducing acceleration of payload 15. Conversely, controller 16 actively sends a pressure increase control command to stepper motor 9 until the single launch is completed.

[0071] S10: Check and clean the cold launch device, test data processing and archiving, and complete the launch mission.

[0072] Finally, it should be pointed out that although the present invention has been described with reference to the current specific embodiments, ordinary technicians in this technical field should realize that the above embodiments are only used to illustrate the present invention and are not used to limit the present invention. Various equivalent changes or substitutions can be made without departing from the concept of the present invention. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the essential spirit of the present invention, they will fall within the scope of the claims of the present invention.

Claims

1. A cold launch device, characterized in that: It includes a volume regulating plug, a nut, a power cabin, an O-ring, a power cabin pressure sensor, a plug, a solenoid valve, an intermediate cabin, a stepper motor, a pressure reducing valve, an intermediate cabin pressure sensor, a pressure gauge, a tray, a launch tube, a payload and a controller; the volume regulating plug and the O-ring are provided inside the power cabin, and the position of the volume regulating plug is controlled by the nut; the power cabin pressure sensor and the plug are symmetrically installed on both sides of the power cabin; the power cabin is installed in conjunction with the intermediate cabin, and the intermediate cabin is assembled and connected to the launch tube; the tray is installed in conjunction with the payload inside the launch tube and moves along the launch tube, the intermediate cabin pressure sensor and the pressure gauge are installed on one side of the intermediate cabin, and the stepper motor is installed on the other side. Into the motor; the solenoid valve and the pressure reducing valve are installed at the center of the top of the power cabin; the pressure reducing valve is respectively assembled and connected with the pressure gauge and the stepper motor; the controller is respectively connected with the stepper motor, the power cabin pressure sensor, the intermediate cabin pressure sensor and the solenoid valve through data lines; the power cabin body is a closed hollow cylinder, including a power cabin body, a power cabin sensor interface and a power cabin filling port arranged on the side wall of the power cabin body, a power cabin valve interface arranged on the top of the power cabin body and a power cabin threaded port arranged at the bottom of the power cabin body; the power cabin sensor interface is installed in conjunction with the power cabin pressure sensor, and the power cabin filling port is installed in conjunction with the plug ; The power compartment valve interface is installed in cooperation with the solenoid valve and the pressure reducing valve, the power compartment top is installed in cooperation with the intermediate compartment, and the power compartment threaded port is installed in cooperation with the volume regulating plug; the main body of the volume regulating plug is a T-shaped cylinder, including a volume regulating plug body, a volume regulating plug groove arranged on the circumference of the side wall of the volume regulating plug body, and a volume regulating plug threaded rod fixedly connected to the volume regulating plug body; the volume regulating plug groove is used to assemble the O-ring, the volume regulating plug body and the O-ring are installed inside the power compartment body, and the volume regulating plug threaded rod is installed in cooperation with the power compartment threaded port; the main body of the intermediate compartment is a hollow cylinder, including an intermediate compartment body, a pressure gauge interface arranged on one side wall of the intermediate compartment body , a sensor interface, an intermediate cabin screw port arranged on the other side wall of the intermediate cabin body, an intermediate cabin main slot arranged at the bottom of the intermediate cabin, and an intermediate cabin secondary slot arranged at the top of the intermediate cabin; the pressure gauge interface is installed in conjunction with the pressure gauge, the sensor interface is used to fix the intermediate cabin pressure sensor, the intermediate cabin main slot is installed in conjunction with the power cabin, and the intermediate cabin secondary slot is fixedly installed on the launch tube; the pressure reducing valve includes a pressure reducing valve slot at the bottom, a pressure reducing valve wire and a pressure reducing valve screw; the pressure reducing valve is installed in conjunction with the solenoid valve through the pressure reducing valve slot, and the pressure reducing valve wire is connected to the pressure gauge; the pressure reducing valve screw is installed in conjunction with the intermediate cabin screw port.

2. A cold emission device according to claim 1, characterized in that: The launch tube body is a hollow cylinder, including a launch tube body, a launch tube slot arranged at the bottom of the launch tube body, and a launch tube platform arranged inside the launch tube; the launch tube slot is installed in cooperation with the middle compartment slot, and the launch tube platform is installed in cooperation with the tray.

3. A cold emission device according to claim 2, characterized in that: The pallet includes a pallet main end surface and a pallet secondary end surface cavity; the outer diameter of the pallet main end surface is smaller than the inner diameter of the launch tube body, and the pallet secondary end surface cavity is installed in cooperation with the load.

4. A method for using a cold launch device, using the cold launch device according to any one of claims 1 to 3; characterized in that: The following steps are involved: S1. Cold launch device assembly and preparation; S2. Launch experiment of cold launch device.

5. A method for using a cold emission device according to claim 4, characterized in that: Said S1 comprises the following steps: S11. Design the power compartment, volume regulating plug, launch tube, and tray, and select appropriate solenoid valves and pressure reducing valves, as well as pressure sensors and controllers with appropriate ranges. S12. Assemble the selected components according to the cold launch device to form a cold launch device; S13. Check the rationality of the assembly relationship of each component, the effectiveness of the solenoid valve's opening and closing action, the reliability of the stepper motor's ability to regulate the pressure reducing valve, and the overall airtightness of the cold launch device; S14. Start the controller, close the solenoid valve and the pressure reducing valve, fill the power compartment with high-pressure gas to the target pressure, and record the pressure-time curve of the power compartment pressure sensor; S15. Load the payload and tray into the cold launch device and sequentially open the solenoid valve and pressure relief valve to conduct a cold launch simulation experiment. S16. If the pressure value in the power cabin continues to decrease before the solenoid valve is opened, or if the data of the power cabin pressure sensor and the intermediate cabin pressure sensor are abnormal and the stepper motor cannot effectively adjust the pressure control capability of the pressure reducing valve after the solenoid valve and the pressure reducing valve are opened, repeat steps S11 to S14 until the overall air tightness of the cold launch device, the reliability of the pressure control functions of the power cabin pressure sensor, the intermediate cabin pressure sensor, the solenoid valve, and the pressure reducing valve are verified.

6. A method for using a cold emission device according to claim 4, characterized in that: The S2 comprises the following steps: S21. According to the load acceleration peak a max , the main end surface area of ​​the tray is A t , pallet mass m t , load mass m z , calculate the pressure reducing valve opening threshold pressure p y , power cabin gas filling pressure p d and the pressure reducing valve opening threshold pressure p y Satisfied: p d =50p y relation: S22. For the power compartment volume V d , whose size is determined by the volume V of the intermediate compartment m , launch tube volume V f Jointly determine the following: S23. Preset the power compartment volume V according to steps S21 and S22. d and filling pressure p d The controller starts the solenoid valve and stepper motor. The high-pressure gas enters the intermediate cabin through the solenoid valve and the pressure reducing valve in turn, pushing the tray and the load in the launch tube to move along the axis of the launch tube toward the tube mouth. The controller, the intermediate cabin pressure sensor and the stepper motor form a closed-loop control system. When the pressure p in the intermediate cabin meets |pp y | / p y When the pressure is less than or equal to 10%, the controller actively sends a pressure reduction control command to the stepper motor, and the stepper motor drives the pressure reducing valve screw to reduce the flow and pressure of the high-pressure gas through the pressure reducing valve, thereby reducing the gas pressure in the launch tube and the intermediate cabin, and completing the throttling pressure control and load reduction acceleration goals. Conversely, the controller actively sends a pressure increase control command to the stepper motor until the single launch is completed; S24. Check and clean the cold launch equipment, test data processing and archiving, and complete the launch mission.

Images