Pressure-releasing and cold-reducing launching device and using method thereof

Abstract

The invention provides a pressure-releasing and cold-reducing launching device and a using method thereof. The cold launching device comprises a power cabin, a launching cylinder and a controller. The power cabin is communicated with the launch canister through a high-pressure air passage; high-pressure gas in the power cabin can enter the launching cylinder through the high-pressure gas channel so as to push the load in the launching cylinder to be launched. A main electromagnetic valve is arranged in the high-pressure air channel; a pressure relief channel is further arranged in the launching cylinder, and a pressure relief electromagnetic valve is arranged in the pressure relief channel. A first pressure sensor on the launching cylinder is used for detecting the pressure in the launching cylinder; the controller is electrically connected with the first pressure intensity sensor, the pressure relief electromagnetic valve and the main electromagnetic valve. The controller controls opening and closing of the pressure electromagnetic valve and / or the main electromagnetic valve by receiving a pressure signal of the first pressure sensor; according to the scheme provided by the invention, pressurization and pressure relief can be performed by controlling the high-pressure gas according to the load launching requirements, and the launching purposes of low overload peak value, high cylinder outlet speed and high device reuse rate in the load cold launching process in the launching cylinder are achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of cold launch, and in particular relates to a pressure-releasing and 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 artificial rain bombs to explore and utilize space resources is increasing. Most of the existing payloads carry various precision detection or control instrument components, and the functions of such components are prone to performance deviation or failure under large overload or high temperature conditions. At present, various types of payloads are mainly launched by hot launch and 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 severe ablation and corrosion, low device reuse rate, large instantaneous overload at the beginning of launch, and low power distribution efficiency, which bring uncertainty to the safe launch of the payload. Therefore, in order to solve the uncertainty caused by the instantaneous high pressure and high overload at the beginning of launch during the launch process of traditional hot launch and existing cold launch systems, it is urgent to develop a new type of pressure relief and cooling launch device with small instantaneous overload, stable acceleration, and no ablation of the device to meet the launch needs of various types of drones, high-altitude detectors, artificial rain bombs and other overload-limited payloads at this stage.

[0003] Based on the technical problems existing in the above-mentioned launch overload control technology, there is no relevant solution yet; therefore, it is urgent to find an effective solution to solve the above-mentioned problems. Summary of the invention

[0004] The purpose of the present invention is to address the deficiencies in the above-mentioned technology and to propose a pressure relief and cooling launch device and a method of using the same, in order to solve the problems of high initial peak pressure and high load overload in the launch tube in the existing launch technology.

[0005] The present invention provides a pressure release and cold launch device, which includes a power cabin, a launch tube and a controller; the power cabin is fixedly connected to the launch tube, and the power cabin is connected to the launch tube through a high-pressure air duct; a high-pressure chamber is provided in the power cabin, and the high-pressure gas in the high-pressure chamber can enter the launch tube through the high-pressure air duct to promote the launch of the load in the launch tube; a main solenoid valve is provided in the high-pressure air duct; a pressure relief channel is also provided in the launch tube, and a pressure relief solenoid valve is provided in the pressure relief channel; a first pressure sensor is also provided on the launch tube, and the first pressure sensor is used to detect the pressure in the launch tube; the controller is electrically connected to the first pressure sensor, the pressure relief solenoid valve and the main solenoid valve respectively, and the controller controls the opening and closing of the pressure solenoid valve and / or the main solenoid valve by receiving the pressure signal of the first pressure sensor.

[0006] Furthermore, a tray is provided in the launch tube, the tray can be slidably arranged in the launch tube, and the load is arranged on the tray; the outlet of the high-pressure air duct faces the center position of the tray; the tray can be pushed by the high-pressure gas to drive the load to be ejected from the launch tube.

[0007] Furthermore, the launch tube includes a launch tube body; a launch tube sensor base is provided on the side wall of the launch tube body, and an inner channel of the launch tube sensor base is connected to the inside of the launch tube; a first pressure sensor is provided on the launch tube sensor base, and the first pressure sensor is used to detect the pressure change between the tray and the inner bottom wall of the launch tube.

[0008] Furthermore, the power compartment includes a power compartment shell, and a power compartment assembly platform is arranged at one end of the power compartment shell; a launch rack assembly cavity is arranged in the circumference of one end of the launch cylinder, and the launch cylinder is fixedly connected to the power compartment assembly platform through the launch rack assembly cavity; a stop bracket is also arranged on the other end of the launch cylinder, and the stop bracket is used to limit the tray from detaching from the launch cylinder.

[0009] Furthermore, the end face of the power compartment assembly table is the top plane of the power compartment; a power compartment energy release port is provided at the center position of the top plane of the power compartment, a high-pressure air duct is provided on the power compartment energy release port, and a main solenoid valve is provided on the power compartment energy release port; a power compartment sensor base is provided on the side wall of the power compartment shell, a high-pressure chamber is provided in the power compartment shell, an inflation port is also provided on the power compartment shell, the inflation port is connected with the high-pressure chamber, an inner channel of the power compartment sensor base is connected with the high-pressure chamber, a second pressure sensor is provided on the power compartment sensor base, the second pressure sensor is electrically connected with the controller, and the second pressure sensor is used to detect pressure changes in the high-pressure chamber.

[0010] Furthermore, the pressure relief channel is a power cabin pressure regulating pipe, and the other end of the power cabin shell is arranged to form a bottom plane of the power cabin, and a partial inward depression of the bottom plane of the power cabin forms a cup-shaped bottom cavity of the power cabin; one end of the power cabin pressure regulating pipe is arranged on the power cabin assembly table, and is connected to the cavity between the tray and the inner bottom wall of the launch tube; the other end of the power cabin pressure regulating pipe is arranged in the bottom cavity of the power cabin, and is connected to the outside world.

[0011] Furthermore, a plurality of power compartment limiting plates are arranged at intervals on the circumferential edge of the power compartment assembly table; a pallet mounting groove is provided at one end of the pallet, and the load is installed in the pallet mounting groove; an annular pallet limiting surface is formed in the circumference of one end of the pallet, and a plurality of pallet legs are formed in the circumference of the other end of the pallet; a plurality of power compartment limiting plates are matched with a plurality of pallet legs to install and position the pallet; the stop bracket is an annular structure, and a stop bracket mounting groove is provided along its circumference, and the inner annular surface of the stop bracket is the stop bracket limiting surface, and the stop bracket is fixedly sleeved on the other end of the launch barrel through the stop bracket mounting groove, and the inclination angle of the stop bracket limiting surface is the same as the inclination angle of the pallet limiting surface.

[0012] Furthermore, the power cabin is made of 30CrMnSiA.

[0013] Furthermore, the material of the tray is 7075Al.

[0014] Furthermore, the material of the launching tube is 7075Al.

[0015] Furthermore, the material of the bracket is rubber.

[0016] Correspondingly, in combination with the above scheme, the present invention further provides a method for using the decompression and cooling launch device, using the decompression and cooling launch device described above; the method specifically includes the following process:

[0017] S1: Check the effectiveness of the opening and closing actuation of the main solenoid valve and the pressure release solenoid valve of the cold launch device, check the airtightness of the cold launch device, check the reliability of the movement of the stop bracket and the stop tray in the launch tube; check the reliability of the first pressure sensor on the launch tube;

[0018] S2: Start the controller, close the valves of the main solenoid valve and the pressure relief solenoid valve, fill the power cabin with high-pressure gas to the target pressure, and record the pressure-time curve of the second pressure sensor on the power cabin;

[0019] S3: Install the payload on the pallet and load it into the launch tube, open the main solenoid valve and conduct a cold launch simulation experiment;

[0020] S4: If the device leaks before the main solenoid valve is opened, the pressure value in the power cabin continues to decrease, or the data of the first pressure sensor and the second pressure sensor are abnormal after the main solenoid valve is opened, and the stop bracket does not effectively brake the tray, repeat steps S1 to S3 until the air tightness of the cold launch device, the functional reliability of the first pressure sensor, the second pressure sensor and the stop bracket are verified;

[0021] S5: According to the overload peak value a of the target load max , tray installation slot area A of the tray t 、Mass of pallet m t , mass of load m z , calculate the pressure relief solenoid valve opening threshold pressure p y , and the power cabin gas filling pressure p d and the threshold pressure satisfies p d =50p y relationship;

[0022] S6: The controller starts the main solenoid valve, so that high-pressure gas enters the launch tube to push the tray and the load to move along the axis of the launch tube toward the tube mouth; the controller, the first pressure sensor, the second pressure sensor and the pressure release solenoid valve constitute a closed-loop control system;

[0023] When the pressure p in the launch tube satisfies |pp y | / p y When the pressure is less than or equal to 10%, the controller will actively open the pressure relief solenoid valve, and the gas in the launch tube will be discharged through the power cabin pressure regulating pipe to reduce the pressure in the launch tube and achieve the goal of pressure relief and overload reduction;

[0024] When the pressure p in the launch tube satisfies |pp y | / p y When the pressure is greater than 10%, the controller will actively close the pressure relief solenoid valve until the single launch is completed;

[0025] S7: Check and clean the cold launch device, test data processing and archiving, and complete the launch mission.

[0026] Furthermore, before step S1, the following steps are included:

[0027] According to the overload peak range of the target load, the power cabin, tray, launch tube and stop bracket are designed in a matching manner; the volume of the power cabin V d and load overload peak a max Satisfies the following relationship: V d p d =a max (m z +m t ) ; the inner diameter of the launch tube and the diameter of the tray d p Same, pallet diameter and load diameter d z Satisfaction:d p =1.1d z ; Select a pressure sensor with an appropriate range and a controller with multi-channel signal acquisition and analysis processing capabilities. The range of the first pressure sensor is: 0~1.5p y , the range of the second pressure sensor is: 0~1.2p d , to ensure the installation size is reasonable;

[0028] The processed power cabin, tray, launch tube and stop bracket are assembled into a pressure-releasing and overload-reducing cold launch device.

[0029] Furthermore, in step S5, the following conditions are satisfied:

[0030] The technical solution provided by the present invention has the following technical effects:

[0031] First, the scheme proposed in the present invention is based on modular design thinking. By designing the power cabin pressure regulating pipe, the size of the power cabin energy release port, the selection of the solenoid valve and the power cabin filling pressure, a launch environment with a wide overload range of 0 to 100g and a wide pressure range of 0 to 10MPa can be constructed according to the launch requirements, so as to match the launch overload and pressure with the expected launch mission, and provide technical support for further launching various types of payloads under specific overload or pressure environments;

[0032] Second, the solution proposed by the present invention uses a set of controllers, pressure release solenoid valves, pressure sensors and auxiliary components to achieve the goal of high-precision dynamic pressure control in the launch tube, which is low-cost and effectively reduces the complexity of the system;

[0033] Third, the solution proposed by the present invention, the controller, the pressure sensor and the energy release solenoid valve constitute a closed-loop control system, which can realize the pre-regulation and precise regulation of the peak value of the pressure in the launch tube by presetting the threshold pressure, thereby improving the safety and reliability of the payload launch process;

[0034] Fourth, the solution proposed in the present invention has a simple structure, is easy to process and install, has low maintenance costs, can be customized according to the test task requirements, and can solve the initial overload peak control problem existing in traditional launch methods. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0036] The present invention will be further described below in conjunction with the accompanying drawings:

[0037] Figure 1 This is a cross-sectional view of the structure of a decompression and cooling launch device of the present invention;

[0038] Figure 2 A partial cross-sectional view of the three-dimensional structure of a pressure-releasing and cooling launch device of the present invention;

[0039] Figure 3 This is a schematic diagram of the power cabin structure of the present invention;

[0040] Figure 4 This is a cross-sectional view of the power cabin structure of the present invention;

[0041] Figure 5 This is a schematic diagram of the structure of the tray of the present invention;

[0042] Figure 6 It is a schematic diagram of the structure of the launch tube of the present invention;

[0043] Figure 7 It is a cross-sectional view of the stop bracket structure of the present invention.

[0044] In the figure: 1—power compartment; 2—pressure sensor; 3—pressure relief solenoid valve; 4—main solenoid valve; 5—tray; 6—launch tube; 7—load; 8—stop bracket; 9—controller; 1a—power compartment shell; 1b—power compartment assembly table; 1c—power compartment limit plate; 1d—power compartment top plane; 1e—power compartment sensor base; 1f—power compartment energy release port; 1g—power compartment pressure regulating pipe; 1h—power compartment bottom plane; 1j—power compartment bottom cavity; 5a—tray mounting groove; 5b—tray leg; 5c—tray limit surface; 6a—launch tube body; 6b—launch stand assembly cavity; 6c—launch tube sensor base; 8a—stop bracket mounting groove; 8b—stop bracket limit surface. DETAILED DESCRIPTION

[0045] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0046] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0047] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined. The meaning of "several" is one or more, unless otherwise clearly and specifically defined.

[0048] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by the terms "up", "down", "front", "back", "left", "right", etc. are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation on the present invention.

[0049] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0050] like Figure 1 to Figure 2As shown, the present invention provides a pressure release and cooling launch device, which includes a power cabin 1, a launch tube 6 and a controller 9, and the power cabin 1, the launch tube 6 and the controller 9 are designed as independent modules and then installed. The power cabin 1 is fixedly connected to the launch tube 6, and the power cabin 1 is connected to the launch tube 6 through a high-pressure airway to realize the circulation of high-pressure gas. Further, a high-pressure chamber is provided in the power cabin 1, and the high-pressure gas in the high-pressure chamber can enter the launch tube 6 through the high-pressure airway to promote the launch of the load 7 in the launch tube 6. Further, a main solenoid valve 4 is provided in the high-pressure airway, and the main solenoid valve 4 is electrically connected to the controller 9. Specifically, the main solenoid valve 4 is used to control the high-pressure gas to enter the launch tube 6, so that the main solenoid valve 4 can be opened by the controller 9 to release the high-pressure gas into the launch tube 6, and the launch of the load 7 in the launch tube 6 can be controlled. Further, a pressure relief channel is also provided in the launch tube 6, and a pressure relief solenoid valve 3 is provided in the pressure relief channel, and the pressure relief solenoid valve 3 is used to control the pressure in the launch tube 6. Furthermore, pressure sensors 2 are respectively provided on the power compartment 1 and the launch tube 6, wherein the launch tube 6 is also provided with a first pressure sensor, which is used to detect the pressure inside the launch tube 6; the controller 9 is electrically connected to the first pressure sensor, the pressure relief solenoid valve 3 and the main solenoid valve 4, respectively, to realize a closed-loop connection; specifically, the controller 9 controls the opening and closing of the pressure solenoid valve 3 and / or the main solenoid valve 4 by receiving the pressure signal of the first pressure sensor, thereby realizing the control of the initial peak pressure and load overload in the launch tube. The solution provided by the present invention is to open the main solenoid valve 4 through the controller 9 to release high-pressure gas into the launch tube 6, and the pressure inside the launch tube 6 is measured by the pressure sensor 2. When the threshold pressure is exceeded, the controller 9 opens the pressure relief solenoid valve 3, releases the high-pressure gas in the launch tube 6 to reduce the pressure inside the launch tube 6, and controls the launch of the load 7 in the launch tube 6 to achieve the goal of pressure release and overload reduction. The pressure relief and cooling launch device provided by the present invention can achieve the launch purpose of low overload peak, high tube exit speed and high device reuse rate during the cold launch process of the load in the launch tube by controlling the high-pressure gas filling pressure and the opening time of the pressure relief solenoid valve according to the load launch requirements. At the same time, the pressure relief and cooling launch device provided by the present invention can provide technical support for further launching missions of aircraft such as unmanned aerial vehicles with limited overload peak, sounding devices, artificial rainfall bombs, etc.

[0051] Preferably, in combination with the above scheme, Figures 1 to 5As shown, a tray 5 is provided in the launch tube 6, and the tray 5 is designed as an independent module structure to achieve installation. The tray 5 can be slidably arranged in the launch tube 6, and the load 7 is arranged on the tray 5 and can move with the tray 5. The outlet of the high-pressure airway faces the center position of the tray 5, so that the ejected high-pressure gas can push the tray 5 to move more concentratedly; the tray 5 can be pushed by the high-pressure gas to drive the load 7 to be ejected from the launch tube 6. The main body of the tray 5 is a cup-shaped hollow cylinder with evenly grooved edges and one end closed. The material of the tray 5 is 7075Al, which meets the launch requirements; a plurality of tray legs 5b are evenly distributed on the side of the tray 5, and the tray legs 5b are installed in conjunction with the power cabin limit plate 1c, specifically, they are docked together in mutual intersection. The chamfered tray limit surface 5c of the top edge of the tray 5 is installed in conjunction with the stop bracket 8 to achieve limit. The concave tray mounting groove 5a at the top center position of the tray 5 is installed in conjunction with the load 7, and both are assembled inside the launch tube 6.

[0052] Preferably, in combination with the above scheme, Figures 1 to 4 As shown, the main body of the power cabin 1 is a closed hollow cylinder, and the material of the power cabin 1 is 30CrMnSiA, which meets the launch requirements. The power cabin sensor base 1e on the bottom side wall of the power cabin shell 1a is installed in conjunction with the pressure sensor 2. The boss-type power cabin assembly table 1b on the top edge of the power cabin 1 is used to cooperate with the installation of the launch tube 6. A plurality of raised arc-shaped power cabin limit plates 1c are evenly distributed on the edge of the top plane 1d of the power cabin, and the power cabin limit plates 1c are used to position the installation tray 5. A raised hollow cylindrical power cabin release port 1f is processed at the center of the top plane 1d of the power cabin, which is installed in conjunction with the main solenoid valve 4. The bottom plane 1h of the power cabin is partially recessed to form a cup-shaped bottom cavity 1j of the power cabin; the hollow cylindrical power cabin pressure regulating pipe 1g passes through the top plane 1d of the power cabin and the center position of the bottom cavity 1j of the power cabin, and the bottom of the power cabin pressure regulating pipe 1g is installed in cooperation with the pressure relief solenoid valve 3, and the upper part of the power cabin pressure regulating pipe 1g extends into the launch tube 6, and the gas in the power cabin cannot be discharged through the power cabin pressure regulating pipe 1g.

[0053] Preferably, in combination with the above scheme, Figure 1 and Figure 6 As shown, the launch tube 6 includes a launch tube body 6a; a launch tube sensor base 6c is provided on the side wall of the launch tube body 6a, and the inner channel of the launch tube sensor base 6c is connected to the launch tube 6; the first pressure sensor is arranged on the launch tube sensor base 6c, and the first pressure sensor is used to detect the pressure change between the tray 5 and the inner bottom wall of the launch tube 6.

[0054] Preferably, in combination with the above scheme, Figures 1 to 4As shown, the power compartment 1 includes a power compartment shell 1a, and one end of the power compartment shell 1a is arranged to form a power compartment assembly platform 1b; a launch stand assembly cavity 6b is circumferentially provided at one end of the launch cylinder 6a, and the launch cylinder 6a is fixedly connected to the power compartment assembly platform 1b through the launch stand assembly cavity 6b; a stop bracket 8 is also provided on the other end of the launch cylinder 6a, and the stop bracket 8 is used to limit the tray 5 from detaching from the launch cylinder 6a.

[0055] Preferably, in combination with the above scheme, Figure 1 and Figure 6 As shown, the main body of the launch tube 6 is a hollow cylinder with open ends. The material of the launch tube 6 is 7075Al to achieve the launch intensity requirement; the bottom concave launch tube assembly cavity 6b is installed in conjunction with the power compartment assembly platform 1b; the launch tube sensor base 6c on the wall of one side of the bottom of the launch tube body 6a is installed in conjunction with the pressure sensor 2; a stop bracket 8 is fixedly installed on the top edge to prevent the tray 5 from flying away from the launch tube 6.

[0056] Preferably, in combination with the above scheme, Figures 1 to 4 As shown, the end face of the power compartment assembly platform 1b is the power compartment top plane 1d; a power compartment energy release port 1f is provided at the center position of the power compartment top plane 1d, a high-pressure air duct is provided on the power compartment energy release port 1f, and a main solenoid valve 4 is provided on the power compartment energy release port 1f; a power compartment sensor base 1e is provided on the side wall of the power compartment shell 1a, a high-pressure chamber is provided in the power compartment shell 1a, an inflation port is also provided on the power compartment shell 1a, the inflation port is connected with the high-pressure chamber, an inner channel of the power compartment sensor base 1e is connected with the high-pressure chamber, a second pressure sensor is provided on the power compartment sensor base 1e, the second pressure sensor is electrically connected with the controller, and the second pressure sensor is used to detect the pressure change in the high-pressure chamber.

[0057] Preferably, in combination with the above scheme, Figures 1 to 4 As shown, the pressure relief channel is designed as a power compartment pressure regulating pipe 1g, and the other end of the power compartment shell 1a is arranged to form a power compartment bottom plane 1h, and a partial inner depression of the power compartment bottom plane 1h forms a cup-shaped power compartment bottom concave cavity 1j; one end of the power compartment pressure regulating pipe 1g is arranged on the power compartment assembly table 1b, and is connected to the cavity between the tray 5 and the inner bottom wall of the launch tube 6; the other end of the power compartment pressure regulating pipe 1g is arranged in the power compartment bottom concave cavity 1j, and is connected to the outside world to realize the pressure relief function.

[0058] Preferably, in combination with the above scheme, Figures 1 to 5As shown, a plurality of power compartment limiting plates 1c are provided at intervals on the circumferential edge of the power compartment assembly table 1b; a tray mounting groove 5a is provided at one end of the tray 5, and the load 7 is installed in the tray mounting groove 5a; an annular tray limiting surface 5c is formed in the circumference of one end of the tray 5, and a plurality of tray legs 5b are formed in the circumference of the other end of the tray 5; the plurality of power compartment limiting plates 1c are matched with the plurality of tray legs 5b to install and position the tray 5. Specifically, the plurality of power compartment limiting plates 1c and the plurality of tray legs 5b are cross-engaged with each other to achieve positioning. The main body of the stop bracket 8 is an annular structure, and the material is rubber; the stop bracket 8 is provided with a stop bracket mounting groove 8a along its circumference, and the inner annular surface of the stop bracket 8 is the stop bracket limiting surface 8b. The stop bracket 8 is fixedly sleeved on the other end of the launch barrel 6a through the stop bracket mounting groove 8a, and the inclination angle of the stop bracket limiting surface 8b is the same as the inclination angle of the tray limiting surface 5c. Further, as Figure 7 As shown, the width of the middle concave stop bracket installation groove 8a of the annular stop bracket 8 is consistent with the wall thickness of the launching tube 6, so that the two can be installed in coordination. The specific installation method is: the annular stop bracket installation groove 8a can be directly sleeved and fixed on one end of the launching tube 6.

[0059] Preferably, in combination with the above scheme, Figure 1 to Figure 2 As shown, the two pressure sensors 2 (i.e., the first pressure sensor and the second pressure sensor) are of the same model and size. The pressure sensor 2 installed in the power compartment 1 is used to measure the pressure change in the power compartment 1, and the pressure sensor 2 on the side of the launch tube 6 is located in the unobstructed area formed by the power compartment limit plate 1c and the tray leg 5b, and can measure the pressure change in the launch tube 6.

[0060] Preferably, in combination with the above scheme, Figure 1 to Figure 2 As shown, the material of the power cabin 1 can be selected as 30CrMnSiA; the material of the tray 5 can be selected as 7075Al; the material of the launch tube 6 can be selected as 7075Al; and the material of the stop bracket 8 can be selected as rubber. The above material selections are all selected in consideration of the load launch requirements, and the materials themselves can achieve the launch performance requirements, especially cold launch.

[0061] Accordingly, in combination with the above scheme, Figures 1 to 7 As shown, the present invention also provides a method for using a decompression and cooling transmitting device, using the decompression and cooling transmitting device described above, specifically, the method for using the decompression and cooling transmitting device includes the following process:

[0062] S1: Check the effectiveness of the opening and closing actions of the main solenoid valve 4 and the pressure release solenoid valve 3 of the cold launch device, check the airtightness of the cold launch device, check the reliability of the stop bracket 8 in the launch tube 6 to stop the movement of the tray 5; detect the reliability of the first pressure sensor on the launch tube 6;

[0063] S2: Start the controller 9, close the valves of the main solenoid valve 4 and the pressure relief solenoid valve 3, fill the power cabin 1 with high-pressure gas to the target pressure, and record the pressure-time curve of the second pressure sensor on the power cabin 1;

[0064] S3: Install the payload 7 on the tray 5 and put it into the launch tube 6, and open the main solenoid valve 4 to carry out the cold launch simulation experiment;

[0065] S4: If the device leaks before the main solenoid valve 4 is opened, the pressure value in the power cabin continues to decrease, or the data of the first pressure sensor and the second pressure sensor are abnormal after the main solenoid valve 4 is opened, and the stop bracket 8 does not effectively brake the tray, repeat steps S1 to S3 until the air tightness of the cold launch device, the functional reliability of the first pressure sensor, the second pressure sensor and the stop bracket 8 are verified;

[0066] S5: According to the overload peak value a of target load 7 max , the tray installation groove 5a area A of the tray 5 t 、Mass of tray 5 m t 、The mass of load 7m z , calculate the opening threshold pressure p of the pressure relief solenoid valve 4 y , and the power cabin gas filling pressure p d and the threshold pressure satisfies p d =50p y relationship;

[0067] S6: The controller 9 starts the main solenoid valve 4, so that the high-pressure gas enters the launch tube 6 to push the tray 5 and the load 7 to move along the axis of the launch tube 6 toward the tube mouth; the controller 9, the first pressure sensor, the second pressure sensor and the pressure release solenoid valve 3 constitute a closed-loop control system;

[0068] When the pressure p in the launch tube 6 satisfies |pp y | / p y When the pressure is less than or equal to 10%, the controller 9 actively opens the pressure relief solenoid valve 3, and the gas in the launch tube 6 is discharged through the power cabin pressure regulating pipe 1g to reduce the gas pressure in the launch tube 6, thus achieving the pressure relief and overload reduction target;

[0069] When the pressure p in the launch tube 6 satisfies |pp y | / p y >10%, the controller 9 actively closes the pressure release solenoid valve 3 until the single emission is completed;

[0070] S7: Check and clean the cold launch device, test data processing and archiving, and complete the launch mission.

[0071] Preferably, in combination with the above scheme, Figures 1 to 3 As shown, before step S1, it includes:

[0072] S11: According to the overload peak range of the target load, the power cabin, tray, launch tube and stop bracket are designed in a coordinated manner; specifically, the overload peak range of the target load is composed of the overload peak a of the target load. max Determine, specifically: 0~a max The volume of the power compartment V d , filling pressure p d , Pallet mass m t , Pallet load mass m z and load overload peak value a max Satisfies the following relationship: V d p d =a max (m z +m t ). The inner diameter of the launch tube and the diameter of the tray d p Same, pallet diameter and load diameter d z Satisfaction:d p =1.1d z ;

[0073] Select a pressure sensor with an appropriate range and a controller with multi-channel signal acquisition and analysis processing capabilities to ensure that the installation size is reasonable. Specifically, the range of the pressure sensor of the power compartment (i.e., the second pressure sensor) is: 0~1.2p d The pressure sensor (i.e., the first pressure sensor) of the launch tube (6) has a measuring range of 0 to 1.5 p y .

[0074] S12: Assemble the processed power cabin, tray, launch tube and stop bracket to form a pressure release and overload cold launch device.

[0075] Preferably, in combination with the above scheme, Figures 1 to 3 As shown, in step S5, the opening threshold pressure p of the pressure relief solenoid valve 4 is calculated. y satisfy:

[0076] The technical solution provided by the present invention has the following technical effects:

[0077] First, the scheme proposed in the present invention is based on modular design thinking. By designing the power cabin pressure regulating pipe, the size of the power cabin energy release port, the selection of the solenoid valve and the power cabin filling pressure, a launch environment with a wide overload range of 0 to 100g and a wide pressure range of 0 to 10MPa can be constructed according to the launch requirements, so as to match the launch overload and pressure with the expected launch mission, and provide technical support for further launching various types of payloads under specific overload or pressure environments;

[0078] Second, the solution proposed by the present invention uses a set of controllers, pressure release solenoid valves, pressure sensors and auxiliary components to achieve the goal of high-precision dynamic pressure control in the launch tube, which is low-cost and effectively reduces the complexity of the system;

[0079] Third, the solution proposed by the present invention, the controller, the pressure sensor and the energy release solenoid valve constitute a closed-loop control system, which can realize the pre-regulation and precise regulation of the peak value of the pressure in the launch tube by presetting the threshold pressure, thereby improving the safety and reliability of the payload launch process;

[0080] Fourth, the solution proposed in the present invention has a simple structure, is easy to process and install, has low maintenance costs, can be customized according to the test task requirements, and can solve the initial overload peak control problem existing in traditional launch methods.

[0081] The above is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any technician familiar with the art can make many possible changes and modifications to the technical solution of the present invention by using the above-mentioned technical content without departing from the scope of the technical solution of the present invention, or modify it into an equivalent embodiment of equivalent changes. Therefore, any changes, modifications, equivalent changes and modifications made to the above embodiments based on the technology of the present invention without departing from the content of the technical solution of the present invention belong to the protection scope of the present technical solution.

Claims

1. A decompression and cooling launch device, characterized in that: The cold launch device comprises a power cabin (1), a launch tube (6) and a controller (9); the power cabin (1) is fixedly connected to the launch tube (6), and the power cabin (1) is communicated with the launch tube (6) through a high-pressure air duct; a high-pressure chamber is provided in the power cabin (1), and the high-pressure gas in the high-pressure chamber can enter the launch tube (6) through the high-pressure air duct to push the load (7) in the launch tube (6) to launch; a main solenoid valve (4) is provided in the high-pressure air duct; a pressure relief channel is also provided in the launch tube (6), and a pressure relief solenoid valve (3) is provided in the pressure relief channel; a first pressure sensor is also provided on the launch tube (6), and the first pressure sensor is used to detect the pressure in the launch tube (6); the controller (9) is electrically connected to the first pressure sensor, the pressure relief solenoid valve (3) and the main solenoid valve (4) respectively, and the controller (9) controls the opening and closing of the pressure solenoid valve (3) and / or the main solenoid valve (4) by receiving the pressure signal of the first pressure sensor.

2. The decompression and cooling emission device according to claim 1, characterized in that: The launch tube (6) is provided with a tray (5), the tray (5) can be slidably arranged in the launch tube (6), and the load (7) is arranged on the tray (5); the outlet of the high-pressure gas passage faces the center position of the tray (5); the tray (5) can be pushed by the high-pressure gas to drive the load (7) to be ejected from the launch tube (6).

3. The decompression and cooling emission device according to claim 2, characterized in that: The launch tube (6) comprises a launch tube body (6a); a launch tube sensor base (6c) is provided on the side wall of the launch tube body (6a), and the inner channel of the launch tube sensor base (6c) is connected to the inside of the launch tube (6); the first pressure sensor is arranged on the launch tube sensor base (6c), and the first pressure sensor is used to detect the pressure change between the tray (5) and the inner bottom wall of the launch tube (6).

4. The decompression and cooling emission device according to claim 3, characterized in that: The power cabin (1) comprises a power cabin shell (1a), one end of which is provided with a power cabin assembly platform (1b); a launch stand assembly cavity (6b) is provided in the circumferential direction of one end of the launch cylinder (6a), and the launch cylinder (6a) is fixedly connected to the power cabin assembly platform (1b) through the launch stand assembly cavity (6b); a stop bracket (8) is also provided on the other end of the launch cylinder (6a), and the stop bracket (8) is used to limit the tray (5) from detaching from the launch cylinder (6a).

5. The decompression and cooling launch device according to claim 4, characterized in that: The end face of the power compartment assembly platform (1b) is the power compartment top plane (1d); a power compartment energy release port (1f) is provided at the center position of the power compartment top plane (1d); the high-pressure air duct is provided on the power compartment energy release port (1f), and the main solenoid valve (4) is provided on the power compartment energy release port (1f); a power compartment sensor base (1e) is provided on the side wall of the power compartment shell (1a); the high-pressure chamber is provided in the power compartment shell (1a); an air charging port is also provided on the power compartment shell (1a); the air charging port is communicated with the high-pressure chamber; the inner channel of the power compartment sensor base (1e) is communicated with the high-pressure chamber; the power compartment sensor base (1e) is provided with a second pressure sensor; the second pressure sensor is electrically connected to the controller; the second pressure sensor is used to detect the pressure change in the high-pressure chamber.

6. The decompression and cooling emission device according to claim 4, characterized in that: The pressure relief channel is a power cabin pressure regulating pipe (1g); the other end of the power cabin shell (1a) is arranged to form a power cabin bottom plane (1h); a part of the power cabin bottom plane (1h) is partially recessed to form a cup-shaped power cabin bottom cavity (1j); one end of the power cabin pressure regulating pipe (1g) is arranged on the power cabin assembly table (1b) and is connected to the cavity between the tray (5) and the inner bottom wall of the launch tube (6); the other end of the power cabin pressure regulating pipe (1g) is arranged in the power cabin bottom cavity (1j) and is connected to the outside.

7. The decompression and cooling emission device according to claim 4, characterized in that: A plurality of power cabin limiting plates (1c) are also arranged at intervals on the edge of the power cabin assembly platform (1b); a tray installation groove (5a) is arranged at one end of the tray (5), and the load (7) is installed in the tray installation groove (5a); an annular tray limiting surface (5c) is formed in the circumference of one end of the tray (5), and a plurality of tray legs (5b) are formed in the circumference of the other end of the tray (5); the plurality of power cabin limiting plates (1c) and the plurality of tray legs (5b) are connected to each other. ) to install and position the tray (5); the stop bracket (8) is an annular structure, the stop bracket (8) is provided with a stop bracket installation groove (8a) along its circumference, the inner annular surface of the stop bracket (8) is a stop bracket limiting surface (8b), the stop bracket (8) is fixedly sleeved on the other end of the launch tube (6a) through the stop bracket installation groove (8a), and the inclination angle of the stop bracket limiting surface (8b) is the same as the inclination angle of the tray limiting surface (5c).

8. The decompression and cooling emission device according to claim 4, characterized in that: The material of the power cabin (1) is 30CrMnSiA; the material of the tray (5) is 7075Al; the material of the launch tube (6) is 7075Al; and the material of the stop bracket (8) is rubber.

9. A method for using a decompression and cooling launch device, using the decompression and cooling launch device as claimed in any one of claims 1 to 8; characterized in that: The method of use The process includes: S1: Check the effectiveness of the opening and closing actions of the main electromagnetic valve (4) and the pressure release electromagnetic valve (3) of the cold launch device, check the airtightness of the cold launch device, check the reliability of the movement of the stop bracket (8) of the stop tray (5) in the launch tube (6); detect the reliability of the first pressure sensor on the launch tube (6); S2: starting the controller (9), closing the valves of the main electromagnetic valve (4) and the pressure release electromagnetic valve (3), filling the power cabin (1) with high-pressure gas to a target pressure, and recording a pressure-time curve of a second pressure sensor on the power cabin (1); S3: installing the load (7) on the tray (5), and loading it into the launch tube (6), and opening the main solenoid valve (4) to carry out a cold launch simulation experiment; S4: If the device leaks air before the main solenoid valve (4) is opened, the pressure value in the power cabin continues to decrease, or if the data of the first pressure sensor and the second pressure sensor are abnormal after the main solenoid valve (4) is opened, and the stop bracket (8) does not effectively brake the tray, then repeat steps S1 to S3 until the air tightness of the cold launch device, the functional reliability of the first pressure sensor, the second pressure sensor and the stop bracket (8) are verified; S5: Overload peak value a of the load (7) according to the target max , the tray installation groove (5a) area A of the tray (5) t , the mass m of the tray (5) t , the mass of the load (7) m z , calculate the opening threshold pressure p of the pressure relief solenoid valve (4) y , and the power cabin gas filling pressure p d and the threshold pressure satisfies p d =50p y relationship; S6: The controller (9) activates the main solenoid valve (4), so that high-pressure gas enters the launch tube (6) to push the tray (5) and the load (7) to move along the axis of the launch tube (6) toward the tube mouth; the controller (9), the first pressure sensor, the second pressure sensor and the pressure release solenoid valve (3) constitute a closed-loop control system; when the pressure p in the launch tube (6) satisfies | p-py | / py When the pressure is ≤10%, the controller (9) actively opens the pressure relief solenoid valve (3), and the gas in the launch tube (6) is discharged through the power cabin pressure regulating pipe (1g) to reduce the pressure of the gas in the launch tube (6), thereby achieving the pressure relief and overload reduction target; When the pressure p in the launch tube (6) satisfies | p-py | / py When the pressure is greater than 10%, the controller (9) actively closes the pressure release solenoid valve (3) until the single emission is completed; S7: Check and clean the cold launch device, test data processing and archiving, and complete the launch mission.

10. The method for using the pressure release and cooling emission device according to claim 9, characterized in that: The S1 step includes: S11: According to the overload peak range of the target load, the power cabin, tray, launch tube and stop bracket are designed in a matching manner; the volume of the power cabin is V d and the load overload peak value a max Satisfies the following relationship: V d p d =a max (m z +m t ); The inner diameter of the launch tube and the diameter of the tray d p The same, the tray diameter and the load diameter d z Satisfaction:d p =1.1d z ; Select a pressure sensor with an appropriate range, the range of the first pressure sensor is: 0~1.5p y ; The measuring range of the second pressure sensor is: 0~1.2p d ; S12: Assembling the processed power cabin, tray, launch tube and stop bracket to form the pressure relief and overload reduction cold launch device; and / or, The step S5 satisfies:

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