Cold emission device and use method thereof

Abstract

The invention discloses a cold launching device. The cold launching device comprises a capacity adjusting plug, a nut, a power cabin, an O-shaped ring, a power cabin pressure sensor, a plug, an electromagnetic valve, a middle cabin, a stepping motor, a pressure reducing valve, a middle cabin pressure sensor, a pressure meter, a tray, a launching cylinder, a load and a controller. The invention further discloses a using method of the cold emission device. The cold launching device and the using method thereof are simple in structure, convenient to machine and install and low in maintenance cost, can be customized and designed according to test task requirements, and solve the problems that in a traditional launching mode, the initial launching acceleration peak value is high, and the launching process is difficult to accurately control.

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, people's demand for launching payloads such as drones, high-altitude detectors, and meteorological bombs to explore and utilize space resources is increasing. Most existing payloads carry various precision detection or control instrument components. Such 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. In order to solve the problem of high peak acceleration, some aircraft need to reduce some thrust in a certain flight phase to achieve the purpose of reducing peak acceleration to prevent damage to their structures or precision instruments. At present, various payloads are mainly launched by hot launch or cold launch methods such as gas, compressed air, and gas-steam. Although the above launch methods can complete the established launch mission objectives, there are many practical problems such as large infrared characteristics of the launch process, device ablation and corrosion, high initial acceleration peak, unstable barrel speed, and low power distribution efficiency, which bring uncertainty to the safe launch of the payload.

[0003] In order to solve the launch uncertainty caused by the large acceleration peak induced by the instantaneous high pressure at the beginning of the launch during the launch of traditional hot launch and existing cold launch systems, it is urgent to develop a new cold launch device with low instantaneous acceleration, smooth acceleration process of load movement, and no ablation of the device, so as to meet the launch requirements of various types of drones, high-altitude detectors, meteorological bombs and other loads with limited peak acceleration. There is no relevant solution to the technical problems existing in the launch acceleration control technology; therefore, it is urgent to find an effective solution to solve the above problems. 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 using the same, 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; the device 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 achieve 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 arranged 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 cooperation with the intermediate cabin, and the intermediate cabin is assembled and connected with the launch tube; the tray is installed in cooperation with the load 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 with the pressure gauge and the stepping motor respectively; the controller is connected with the stepping motor, the power cabin pressure sensor, the intermediate cabin pressure sensor and the solenoid valve respectively through data lines.

[0007] Furthermore, the power compartment body is a closed hollow cylinder, including a power compartment body, a power compartment sensor interface and a power compartment filling port arranged on the side wall of the power compartment body, a power compartment valve interface arranged on the top of the power compartment body, and a power compartment threaded port arranged on the bottom of the power compartment body; the power compartment sensor interface is installed in cooperation with the power compartment pressure sensor, and the power compartment filling port is installed in cooperation 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 middle compartment, and the power compartment 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 opening 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 cooperation with the pressure gauge, the sensor interface is used for fixedly installing the intermediate cabin pressure sensor, the intermediate cabin main slot is installed in cooperation 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 main end surface of the pallet and a concave cavity of a secondary end surface of the pallet; the outer diameter of the main end surface of the pallet is smaller than the inner diameter of the barrel of the launch tube, and the concave cavity of the secondary end surface of the pallet 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 comprises the following steps:

[0017] S11. Design the power cabin, volume regulating plug, launch tube, tray, and select appropriate solenoid valves and pressure reducing valves, 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 opening and closing action of the solenoid valve, the reliability of the pressure control ability of the stepper motor to adjust 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 cabin with high-pressure gas to the target pressure, and record the pressure-time curve of the power cabin pressure sensor;

[0021] S15. Load the payload and the tray into the cold launch device, and open the solenoid valve and the pressure reducing valve in sequence to carry out the cold launch simulation experiment;

[0022] S16. If the pressure value in the power cabin keeps decreasing 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] Further, the S2 comprises the following steps:

[0024] S21. According to the load acceleration peak value a max , tray main end surface area A t , pallet mass m t , load mass m z , calculate the pressure relief valve opening threshold pressure p y , power cabin gas filling pressure p d The pressure reducing valve opening threshold pressure p y Satisfaction: 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 , the volume of the launch tube V f Decide together to satisfy the following formula:

[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 the stepper motor. The high-pressure gas enters the intermediate cabin through the solenoid valve and the pressure reducing valve in turn to push 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 of using the same. Based on modular design thinking, the power cabin variable volume function can be realized by cooperating and installing the volume adjustment plug and the power cabin. The launch function of payloads of different sizes can be realized by replacing the size of the intermediate cabin and the launch tube bayonet, which effectively solves the problem of replacing the launch power cabin for launching different payloads.

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

[0033] Third, the present invention proposes a cold launch device and a method of using the same, which uses a set of controllers, pressure reducing valves, pressure sensors and accessories 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 a method of using the same. 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 grasped in advance and accurately controlled, thereby improving the safety and reliability of the load launch process.

[0035] Fifth, the present invention proposes a cold launch device and a method of using the same, which has a simple structure, is easy to process and install, has low maintenance costs, and can be customized according to the test mission requirements, thereby solving 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 It is a three-dimensional partial stereoscopic cross-sectional view of the cold emission device of the present invention;

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

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

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

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

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

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

[0044] Figure numerals: 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—load; 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 in conjunction with the drawings in the specification. It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including 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 device.

[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] Among them, the volume regulating plug 1 and the O-ring 4 are installed in the power cabin 3, and the position of the volume regulating plug 1 is controlled by the nut 2; the power cabin pressure sensor 5 and the plug 6 are symmetrically installed on both sides of the power cabin 3; the top of the power cabin 3 is installed in cooperation with the bottom of the intermediate cabin 3, and the top of the intermediate cabin 3 is assembled with the launch tube 14; the intermediate cabin pressure sensor 11 and the pressure gauge 12 are installed on one side of the intermediate cabin 8, and the stepper motor 9 is installed on the other side; the electromagnetic valve 7 and the pressure reducing valve 10 are installed in sequence at the center of the top of the power cabin 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 cabin pressure sensor 5, the intermediate cabin pressure sensor 11 and the electromagnetic valve 7 are connected to the controller 16 through the data line; the tray 13 and the payload 15 are installed in cooperation with the launch tube 14. The electromagnetic valve 7 and the pressure reducing valve 10 are opened in sequence by the controller 16 to release the high-pressure gas into the intermediate cabin 8, and the tray 13 and the payload 15 in the launch tube 14 are pushed to move along the tube to complete 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 conjunction with the solenoid valve 7 and the pressure reducing valve 10 in sequence, the top of the power cabin 3 is installed in conjunction with the intermediate cabin 8, and the hollow power cabin threaded port 3d in the bottom center 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 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 launching tube 14, and the intermediate cabin screw port 8f is used to connect the pressure reducing valve screw 10d and the stepping 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 installed in cooperation with the solenoid valve 7 through 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 installed in cooperation with the screw port 8f of the intermediate cabin. The pressure reducing valve 10 is connected to the pressure gauge 12 and the stepping motor 9 through the pressure reducing valve wire 10b and the pressure reducing valve screw 10c.

[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 arranged at the bottom of the launch tube body, and a launch tube platform 14c arranged inside the launch tube. The launch tube slot 14b is installed in conjunction with the intermediate compartment slot 8e, and the launch tube platform 14c is installed in conjunction with the tray 13.

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

[0054] The power cabin pressure sensor 5 and the intermediate cabin pressure sensor 11 have the same structure and size, and measure the pressure changes in the power cabin 3 and the intermediate cabin 8 respectively. The pressure regulating process of the pressure reducing valve 10 is completed by the stepping motor 9 driving the pressure reducing valve screw 10c to rotate, and the pressure regulating process is monitored by the pressure gauge 12. The power cabin pressure sensor 5, the stepping motor 9, the solenoid valve 7 and the intermediate cabin pressure sensor 11 are all connected to the controller 16 through wires to complete the processing and analysis of data instructions.

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

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

[0057] S1 includes the following specific steps:

[0058] S11. According to the acceleration range that the target load 15 can withstand, the power cabin 3, the volume regulating plug 1, the launch tube 14, the tray 13 and other components are designed in a matching manner, and the solenoid valve 7 and the pressure reducing valve 10 of appropriate size and pressure regulating capacity, the pressure sensors 5, 11 of appropriate range and the controller 16 with multi-channel signal acquisition and analysis processing capabilities are selected to ensure that the installation size of each component is reasonable;

[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 parts 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 stepper 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 a 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 ability of the pressure reducing valve 10, repeat steps S1 to S4 until the overall air tightness of the cold launch device, the reliability of the pressure control functions 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 13 of the tray 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 Satisfaction: 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 , the volume of the launch tube V f Decide together 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 turn, pushing the tray 13 and the load 15 in the launch tube 14 to move along the axis of the launch tube 14 toward the barrel mouth 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 is less than or equal to 10%, the controller 16 actively sends a pressure reduction control command to the stepper motor 9, and the stepper motor 9 drives the pressure reducing valve screw 10c to reduce the flow and pressure of the high-pressure gas through the pressure reducing valve 10, thereby reducing the gas pressure in the launch tube 14 and the intermediate cabin 8, and completing the throttling pressure control and load 15 acceleration reduction goals. Conversely, the controller 16 actively sends a pressure increase control command to the 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 as a limitation of 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 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 arranged 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 with the launch tube; the tray is installed in coordination with the load 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; the solenoid valve and the pressure reducing valve are installed at the top center of the power cabin; the pressure reducing valve is assembled and connected with the pressure gauge and the stepper motor respectively; the controller is connected with the stepper motor, the power cabin pressure sensor, the intermediate cabin pressure sensor and the solenoid valve respectively through data lines.

2. A cold emission device according to claim 1, characterized in that: The power compartment body is a closed hollow cylinder, including a power compartment body, a power compartment sensor interface and a power compartment filling port arranged on the side wall of the power compartment body, a power compartment valve interface arranged on the top of the power compartment body, and a power compartment threaded port arranged on the bottom of the power compartment body; the power compartment sensor interface is installed in cooperation with the power compartment pressure sensor, and the power compartment filling port is installed in cooperation 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 middle compartment, and the power compartment threaded port is installed in cooperation with the volume regulating plug.

3. A cold emission device according to claim 2, characterized in that: 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 the interior of the power compartment body, and the volume regulating plug threaded rod is installed in cooperation with the threaded opening of the power compartment.

4. A cold emission device according to claim 3, characterized in that: 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 cooperation with the pressure gauge, the sensor interface is used for fixedly installing the intermediate cabin pressure sensor, the intermediate cabin main slot is installed in cooperation with the power cabin, and the intermediate cabin secondary slot is fixedly installed on the launch tube.

5. A cold emission device according to claim 4, characterized in that: The pressure reducing valve comprises 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.

6. A cold emission device according to claim 5, 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.

7. A cold emission device according to claim 6, 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.

8. A method for using a cold launch device, characterized in that: The following steps are involved: S1. Cold launch device assembly and preparation; S2. Launch experiment of cold launch device.

9. A method for using a cold emission device according to claim 8, characterized in that: The S1 comprises the following steps: S11. Design the power cabin, volume regulating plug, launch tube, tray, and select appropriate solenoid valves and pressure reducing valves, pressure sensors and controllers with appropriate ranges; S12. Assembling 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 opening and closing action of the solenoid valve, the reliability of the pressure control ability of the stepper motor to adjust 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 cabin with high-pressure gas to the target pressure, and record the pressure-time curve of the power cabin pressure sensor; S15. Load the payload and the tray into the cold launch device, and open the solenoid valve and the pressure reducing valve in sequence to carry out the cold launch simulation experiment; S16. If the pressure value in the power cabin keeps decreasing 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.

10. A method for using a cold emission device according to claim 8, characterized in that: The S2 comprises the following steps: S21. According to the load acceleration peak value a max , tray main end surface area A t , pallet mass m t , load mass m z , calculate the pressure relief valve opening threshold pressure p y , power cabin gas filling pressure p d The pressure relief valve opening threshold pressure p y Satisfaction: 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 , the volume of the launch tube V f Decide together to satisfy the following formula: 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 the stepper motor. The high-pressure gas enters the intermediate cabin through the solenoid valve and the pressure reducing valve in turn to push 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.

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