Interstage separation test system, pneumatic function test method, control method and device

Abstract

The application provides an interstage separation test system, a pneumatic function test method, a control method and device. The pneumatic function test control method comprises the following steps: receiving a launch vehicle interstage separation instruction; controlling a first electromagnetic valve to open through an electromagnetic valve time sequence controller, unlocking a pneumatic mechanical connection unlocking device through a first gas cylinder, and then driving a lower stage separation mass to move through a pneumatic push rod; collecting the thrust and time data and the displacement and time data of the pneumatic push rod through a sensor on the pneumatic push rod; obtaining the interstage separation speed, the interstage separation displacement and the interstage separation time according to the thrust and time data and the displacement and time data; calculating the interstage separation energy according to the interstage separation speed, the interstage separation displacement and the interstage separation time; and verifying whether the launch vehicle can reach the interstage separation standard according to the interstage separation energy. The embodiment of the application can actually perform the pneumatic function test of the interstage separation on the ground to verify whether the existing design meets the interstage requirement.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of carrier rockets, in particular to a stage separation test system, a pneumatic function test method, a control method and device. BACKGROUND

[0002] The stage separation of a carrier rocket refers to the separation between two adjacent stages of a multi-stage rocket, and the purpose is to discard the propellant depleted stage. With the research and exploration of recoverable rockets, the development trend of stage separation technology gradually moves towards cold separation, and the cold separation technology is used by the American Falcon 9 rocket. In order to improve the reliability of cold separation, the stage cold separation test of a carrier rocket becomes particularly important. However, there is no system that can truly simulate the stage separation of a rocket in the prior art, and there is no test method that can truly simulate the stage separation of a carrier rocket on the ground.

[0003] Therefore, there is an urgent need for a stage separation test system and a pneumatic function test method that can truly perform pneumatic function tests on the ground and verify whether the existing design meets the stage separation requirements. SUMMARY

[0004] Therefore, the purpose of the embodiments of the present application is to provide a stage separation test system, a pneumatic function test method, a control method and device, which can truly perform pneumatic function tests of stage separation on the ground to verify whether the existing design meets the stage separation requirements.

[0005] To achieve the above purpose, in a first aspect, the embodiments of the present application provide a stage separation test system, which comprises: an upper stage separation mass, a lower stage separation mass, a pull rod and a pneumatic push rod; wherein,

[0006] One end of the pull rod is movably connected to the upper stage separation mass, and the other end of the pull rod is connected to the lower stage separation mass through a pneumatic mechanical connection unlocking device, wherein the pneumatic mechanical connection unlocking device is connected to a first gas cylinder, and a first electromagnetic valve is arranged between the pneumatic mechanical connection unlocking device and the first gas cylinder, and the first electromagnetic valve is controlled by an electromagnetic valve time sequence controller to unlock the pneumatic mechanical unlocking device;

[0007] One end of the pneumatic push rod is movably connected to the upper stage separation mass, and the other end of the pneumatic push rod is connected to the lower stage separation mass, and a sensor is arranged on the pneumatic push rod, and the sensor collects the push force and time data and displacement and time data of the pneumatic push rod and transmits them to a data acquisition device.

[0008] In some possible implementation manners, the separation test system further comprises a second gas cylinder connected with the pneumatic push rod, and a second electromagnetic valve is arranged between the second gas cylinder and the pneumatic push rod, and the electromagnetic valve time sequence controller controls the opening and closing of the second electromagnetic valve by controlling the second electromagnetic valve.

[0009] In some possible implementation manners, the separation test system further comprises a gas distribution platform and a blocking component, the gas distribution platform is used to provide gas for the pneumatic push rod, the first gas cylinder and the second gas cylinder, and the blocking component is connected with the lower stage separation mass and used to block the lower stage separation mass pushed out by the pneumatic push rod.

[0010] In the second aspect, a method for testing the inter-stage separation pneumatic function is provided, and the method is based on any one of the separation test systems in the first aspect, and the method comprises the following steps.

[0011] The first electromagnetic valve is opened, the pneumatic mechanical connection unlocking device is unlocked by the first gas cylinder, the pull rod is disconnected with the lower stage separation mass, and then the pneumatic push rod pushes the lower stage separation mass to move;

[0012] During the movement of the lower stage separation mass pushed by the pneumatic push rod, the sensor on the pneumatic push rod collects the push force-time data and displacement-time data of the pneumatic push rod in real time;

[0013] The inter-stage separation speed is calculated according to the displacement-time data, and the inter-stage separation energy is calculated according to the inter-stage separation speed and the mass of the lower stage separation mass;

[0014] Whether the push force of the pneumatic push rod can reach the standard of the inter-stage separation of the carrier rocket is verified according to the inter-stage separation energy.

[0015] In the third aspect, an inter-stage separation pneumatic function test method is provided, and the pneumatic function test control method is based on any one of the separation test systems in the first aspect, and the method comprises the following steps.

[0016] A command for the inter-stage separation of the carrier rocket is received;

[0017] The first electromagnetic valve is opened by the electromagnetic valve time sequence controller, the pneumatic mechanical connection unlocking device is unlocked by the first gas cylinder, and then the pneumatic push rod pushes the lower stage separation mass to move;

[0018] The push force-time data and displacement-time data of the pneumatic push rod are collected by the sensor on the pneumatic push rod;

[0019] The inter-stage separation speed is obtained according to the displacement-time data;

[0020] calculate the inter-stage separation energy according to the inter-stage separation speed and the mass of the lower stage separation mass;

[0021] verify whether the thrust of the pneumatic push rod can reach the standard of the inter-stage separation of the launch vehicle according to the inter-stage separation energy.

[0022] In some possible embodiments, the sensors include an air pressure sensor, a thrust sensor and a displacement sensor, the air pressure sensor is arranged at the front end of the pneumatic push rod, and the thrust sensor and the displacement sensor are arranged at the tail end of the pneumatic push rod; and the method further includes:

[0023] collecting, by the air pressure sensor, the air pressure and time data on the pneumatic push rod, and when the air pressure value of the pneumatic push rod reaches a preset air pressure threshold, the electromagnetic valve time sequence controller controls the second electromagnetic valve to open, and the pneumatic push rod is supplemented with gas by the second gas cylinder.

[0024] In a fourth aspect, an embodiment of the present application provides a device for controlling an inter-stage separation pneumatic function test, and the device includes:

[0025] an inter-stage separation instruction receiving unit configured to receive an inter-stage separation instruction of a launch vehicle;

[0026] an inter-stage separation executing unit configured to control, by an electromagnetic valve time sequence controller, a first electromagnetic valve to open, and after the pneumatic mechanical connection unlocking device is unlocked by a first gas cylinder, the pneumatic push rod pushes the lower stage separation mass to move;

[0027] an inter-stage separation data collecting unit configured to collect, by sensors on the pneumatic push rod, the thrust and time data and the displacement and time data of the pneumatic push rod;

[0028] an inter-stage separation data obtaining unit configured to obtain the inter-stage separation speed according to the displacement and time data;

[0029] an inter-stage separation energy calculating unit configured to calculate the inter-stage separation energy according to the inter-stage separation speed and the mass of the lower stage separation mass;

[0030] an inter-stage separation standard verifying unit configured to verify whether the thrust of the pneumatic push rod can reach the standard of the inter-stage separation of the launch vehicle according to the inter-stage separation energy.

[0031] In some possible embodiments, the sensors include an air pressure sensor, a thrust sensor and a displacement sensor, the air pressure sensor is arranged at the front end of the pneumatic push rod, and the thrust sensor and the displacement sensor are arranged at the tail end of the pneumatic push rod;

[0032] The interstage separation data acquisition unit is further configured to acquire the air pressure on the air push rod and time data through the air pressure sensor.

[0033] The device further comprises an electromagnetic valve timing controller configured to control the second electromagnetic valve to open when the air pressure value of the air push rod reaches a preset air pressure threshold, so as to supplement the air push rod with the second gas cylinder.

[0034] In a fifth aspect, an electronic device is provided, comprising:

[0035] one or more processors;

[0036] a storage device configured to store one or more programs, when the one or more programs are executed by the one or more processors, so that the one or more processors implement the interstage separation air function test control method of any one of the second aspect.

[0037] In a sixth aspect, a computer readable medium is provided, which stores a computer program, and the program is executed by a processor to implement the interstage separation air function test control method of any one of the second aspect.

[0038] The above technical solution has the following beneficial technical effects:

[0039] The interstage separation test system, the air function test method, the control method and the device provided by the embodiments of the present application, the air function test method comprises: receiving a launch vehicle interstage separation instruction; controlling the first electromagnetic valve to open through the electromagnetic valve timing controller, after the air push rod pushes the lower stage separation mass to move through the air push rod after the air dynamic mechanical connection unlocking device is unlocked by the first gas cylinder; collecting the thrust and time data and the displacement and time data of the air push rod through the sensor on the air push rod; obtaining the interstage separation speed, the interstage separation displacement and the interstage separation time according to the thrust and time data and the displacement and time data; calculating the interstage separation energy according to the interstage separation speed, the interstage separation displacement and the interstage separation time; verifying whether the launch vehicle can reach the interstage separation standard according to the interstage separation energy. The embodiments of the present application can actually perform the air function test of interstage separation on the ground to verify whether the existing design meets the interstage separation standard. BRIEF DESCRIPTION OF DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor on the basis of these drawings.

[0041] Figure 1A is a structural schematic diagram of a stage separation test system according to an embodiment of the present application;

[0042] Figure 1A is a structural schematic diagram of another stage separation test system according to an embodiment of the present application;

[0043] Figure 2 is a flow chart of a stage separation aerodynamic function test method according to an embodiment of the present application;

[0044] Figure 3 is a flow chart of a stage separation aerodynamic function test control method according to an embodiment of the present application;

[0045] Figure 4 is a structural block diagram of a stage separation aerodynamic function test control device according to an embodiment of the present application;

[0046] Figure 5 is a functional block diagram of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0047] Features and exemplary embodiments of various aspects of the present application will be described below in detail. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some of these specific details. The description of the embodiments is merely intended to provide a better understanding of the present application by showing examples of the present application. In the drawings and the following description, well-known structures and techniques have not been shown in order to avoid unnecessary obscuring of the present application; and, for clarity, the dimensions of some structures can be exaggerated. Furthermore, features, structures or characteristics described hereinafter can be loaded in one or more embodiments in any suitable manner.

[0048] Terminology explanation:

[0049] SSP: Stage Separation Pneumatic Pushrod, abbreviated as aerodynamic pushrod or SSP, a multi-stage elongated pushrod powered by liquid or gas.

[0050] MCD: Pneumatic Mechanical Connection Disengagement Device.

[0051] The embodiment of the present application realizes simulation of real separation by simulation of the separation body and simulation of the stage separation section; this is a new test method with improved ground stage separation cold separation test efficiency, test safety and test accuracy.

[0052] The main purposes of the pneumatic function test provided in this embodiment of the invention include:

[0053] Verify whether the SSP can meet the requirements of the primary and secondary separation processes;

[0054] Observe the structural stability, coordination, and safety of the SSP;

[0055] Obtain thrust-time data for the SSP during the simulated separation process;

[0056] Obtain the displacement-time data of SSP during the simulated separation process.

[0057] Example 1

[0058] Figure 1A This is a schematic diagram of the structure of an interstage separation test system according to an embodiment of the present invention, as shown below. Figure 1A As shown, the separation system includes: an upper-stage separation mass M1, a lower-stage separation mass M2, a pull rod, and a pneumatic push rod SSP. One end of the pull rod is movably connected to the upper-stage separation mass M1, and the other end is connected to the lower-stage separation mass M2 via a pneumatic mechanical connection unlocking device MCD. The pneumatic mechanical connection unlocking device MCD is connected to a first gas cylinder, and a first solenoid valve is installed between the MCD and the MCD gas cylinder. The first solenoid valve is opened by a solenoid valve timing controller. After the first solenoid valve opens, the pneumatic mechanical connection unlocking device MCD is inflated and unlocked via the first gas cylinder, separating the pull rod from the lower-stage separation mass M2. One end of the pneumatic push rod SSP is movably connected to the upper-stage separation mass M1, and the other end is connected to the lower-stage separation mass M2. A sensor is installed on the pneumatic push rod SSP. The sensor collects thrust and time data and displacement and time data of the pneumatic push rod SSP and transmits them to terminal equipment such as a data acquisition device for storage and processing.

[0059] Specifically, the pneumatic push rod SSP can be connected with both the upper stage separation mass M1 and the lower stage separation mass M2 through an adapter tool, wherein the adapter tool comprises a thrust dispersion seat and a buffer pad, the top of the pneumatic push rod SSP is connected to the upper stage separation mass M1 through the thrust dispersion seat, the thrust of the pneumatic push rod SSP is dispersed through the thrust dispersion seat, the bottom is connected to the lower stage separation mass M2 through a buffer pad, the buffer pad is made of soft material, the soft material is used to simulate the real state of the rocket to protect the structure at the position where the pneumatic push rod SSP contacts the lower stage separation mass M2 from being damaged. In addition, the number of pull rods can be determined according to actual conditions, for example, three pull rods, the three pull rods are distributed in a triangular form, the pneumatic push rod SSP is located at the center of the triangular row formed by the three pull rods to maintain the balance of the system, and a pneumatic mechanical connection unlocking device is connected between each pull rod and the lower stage separation mass M2. Sensors such as air pressure sensors, thrust sensors and displacement sensors are arranged at the top and bottom of the pneumatic push rod SSP respectively, which are used to measure the air pressure, thrust and displacement of the pneumatic push rod SSP, wherein the displacement of the pneumatic push rod SSP is also the displacement of the rail car, and is transmitted to a data acquisition device for subsequent data analysis.

[0060] In the actual launching process of the launch vehicle of the embodiment of the present application, the mass of the upper stage separation body of the rocket is much larger than the mass of the lower stage separation body, so in the embodiment, the upper stage separation mass M1 can be a fixed wall or other large mass fixture, the fixed wall or other object is used to simulate the mass of the upper stage separation body with large mass, the lower stage separation mass M2 can be a rail car with a certain mass, the rail car is used to simulate the mass of the lower stage separation body, and a sufficient amount of mass (for example, 30t of sand loaded in the rail car) is arranged in the rail car to simulate the mass of the lower stage separation body. In addition, the rail can be raised at the near end by a wedge-shaped steel to form a downhill, the pull rod is connected between the fixed wall and the rail car, and the rail car is fixed through the pull rod. Since the gas pressure of the pneumatic push rod SSP is as high as tens of megapascals, in order to prevent the situation of high-pressure gas leakage from occurring in the test, the entire test system can be isolated by two isolation walls or isolation plates on the side, so that the relevant tools in the test process are placed inside the partition wall, for example, the pneumatic push rod SSP, the pull rod and the first gas cylinder.

[0061] Figure 1B is a structural schematic view of another interstage separation test system of the embodiment of the present application, like Figure 1BAs shown in the figure, in some embodiments, the separation test system further comprises: a second gas cylinder connected with the pneumatic push rod SSP, a second electromagnetic valve is arranged between the second gas cylinder and the pneumatic push rod SSP, and the electromagnetic valve timing controller controls the opening and closing of the second electromagnetic valve. In this embodiment, after the pneumatic push rod SSP is pushed out, the internal volume becomes larger and the air pressure becomes smaller, so the second electromagnetic valve needs to be controlled to open and close at intervals by the electromagnetic valve timing controller to inflate the pneumatic push rod SSP.

[0062] As shown in the figure, in some embodiments, the separation test system further comprises: a gas distribution platform and a stopping component, the gas distribution platform provides gas to the pneumatic push rod SSP, the first gas cylinder and the second gas cylinder through the inflation hose; and the stopping component is connected with the lower stage separation mass M2 and used to stop the lower stage separation mass M2 pushed out by the pneumatic push rod SSP. Figure 1B

[0063] Since the energy of the whole system in this embodiment comes from high-pressure gas, the SSP gas cylinder, the MCD gas cylinder and the pneumatic push rod SSP need to be inflated by the gas distribution platform to provide initial energy at the beginning; and the stopping component is placed on both sides of the rail car and connected with both sides of the rail car to stop the rail car pushed out by the pneumatic push rod SSP, so as to facilitate the recovery and resetting after the test.

[0064] In this embodiment, since the pull rod and the pneumatic push rod SSP are both suspended, in order to reduce the bending moment load generated by the self-weight, the pull rod can be supported by a support frame near the MCD, and the pull rod is supported by the support frame after the pull rod is disconnected from the lower stage separation mass M2 after the unlocking of the pneumatic mechanical connection unlocking device. In addition, a crane and a cart can be prepared outside the partition wall for resetting the corresponding tooling after the test for subsequent repeated use. In this embodiment, before the test starts, the pneumatic push rod SSP, the first gas cylinder and the second gas cylinder are inflated by the gas distribution platform (after the pneumatic push rod SSP is inflated, a pushing force will gradually be generated until the air pressure reaches a predetermined value, and the pushing force gradually stabilizes), and the test is ready to start. After the rail car releases the brake, the first electromagnetic valve of the MCD is unlocked, the pull rod is disconnected from the lower stage separation mass M2, the pneumatic push rod SSP starts to work, the sensor starts to collect data, after a period of time, the second electromagnetic valve of the pneumatic push rod SSP opens, the second gas cylinder of the pneumatic push rod SSP starts to supplement air to the pneumatic push rod SSP, and after the pneumatic push rod SSP and the rail car are stable, the data collection is stopped, and the test is completed.

[0065] In the embodiment of the application, the rail car can be a large truck, an engineering vehicle or other modified movable heavy vehicle, the fixed wall can be replaced by a fixed steel member, the SSP can be replaced by a hydraulic push rod or other separation device, and the rail can be replaced by a smooth or low-friction road surface.

[0066] ​The launch vehicle interstage separation system provided by the embodiment can effectively eliminate or reduce the friction of the separated body during the separation process, and can also control the deceleration and reset of the separated body.

[0067] Figure 2 is a flow chart of an interstage separation aerodynamic function test method of the embodiment, as shown in the figure, the aerodynamic function test method is based on the aerodynamic separation system described above, and the method comprises the following steps: Figure 2

[0068] Step S11, open the first electromagnetic valve, unlock the aeromechanical connection unlocking device through the first gas cylinder to disconnect the pull rod from the lower stage separation mass, and then the aerodynamic push rod pushes the lower stage separation mass to move.

[0069] Step S12, in the process of the aerodynamic push rod pushing the lower stage separation mass to move, the sensor on the aerodynamic push rod collects the push force and time data and displacement and time data of the aerodynamic push rod in real time.

[0070] In this embodiment, the interstage separation process is divided into two steps, first, unlocking, and then providing separation energy through the SSP. The traditional separation energy in China is mostly positive and negative thrust rockets (firecrackers are separation energy), and a small part of models use thermal separation (separation energy is the high-temperature gas flow of the upper stage engine). Unlike the traditional separation energy in China, the aerodynamic push rod SSP in this embodiment provides energy to the push rod through air pressure, which is easier to control the separation force.

[0071] Step S13, calculate the interstage separation speed according to the displacement and time data, and calculate the interstage separation energy according to the interstage separation speed and the mass of the lower stage separation mass.

[0072] In this embodiment, the interstage separation displacement is a design index, the interstage separation time is obtained by the sensor according to the interstage separation displacement measurement, and the interstage separation speed can be calculated by taking the first derivative of the displacement and time curve. Before the test, the entire separation process will be simulated through simulation software to obtain the separation time, thrust and speed. After obtaining the test data, comparison is made, and the simulation model is corrected according to the comparison result.

[0073] In this embodiment, the interstage separation energy can be obtained according to the formula E = (m*v 2 ) / 2, wherein E is the interstage separation energy, m is the mass of the lower stage separation mass M2, and v is the interstage separation speed.

[0074] Step S14, verify whether the thrust of the aerodynamic push rod can meet the standard of launch vehicle interstage separation according to the interstage separation energy.

[0075] ​This embodiment verifies whether the interstage separation energy meets the requirements through computer simulation and ground tests. The simulation can help predict various situations during the separation process, while the ground tests provide actual verification, and the simulation model is modified after verification. For example, if the rocket has already flown, the flight data can be analyzed to verify whether the interstage separation is performed as expected. The calculated interstage separation energy E can also be compared with the design standard and safety margin. If the calculated energy is greater than or equal to the energy required by the design standard and safety margin, it is considered that the rocket can meet the interstage separation standard. If the energy is insufficient, the separation mechanism or the rocket design needs to be re-evaluated to ensure that the separation can be successfully performed. The safety margin refers to the fact that in actual engineering, a certain safety margin is usually designed to ensure that the separation can be reliably performed under various conditions, including extreme conditions.

[0076] Figure 3 is a flowchart of an interstage separation aerodynamic function test control method according to an embodiment of the present application, as shown in Figure 3 The aerodynamic function test control method is based on the aerodynamic separation system described above, and the method includes the following steps:

[0077] Step S21, receiving an interstage separation command of the launch vehicle.

[0078] Step S22, controlling the first electromagnetic valve to open through the electromagnetic valve time sequence controller, and after unlocking the aeromechanical connection unlocking device through the first gas cylinder, the aerodynamic push rod pushes the lower stage separation mass to move.

[0079] In this embodiment, the interstage separation process is divided into two steps, first unlocking, and then providing separation energy through the SSP. The traditional separation energy in China is mostly positive and negative thrust rockets (pyrotechnic products are separation energy), and a small part of models use thermal separation (separation energy is the high-temperature gas flow of the upper stage engine). Unlike the traditional separation energy in China, the aerodynamic push rod SSP in this embodiment provides energy to the push rod through air pressure, which is easier to control the separation force.

[0080] Step S23, collecting the thrust and time data and displacement and time data of the aerodynamic push rod through the sensor on the aerodynamic push rod.

[0081] Step S24, obtaining the interstage separation speed according to the displacement and time data.

[0082] In this embodiment, the interstage separation displacement is a design index, the interstage separation time is measured by the sensor according to the interstage separation displacement, and the interstage separation speed can be calculated by taking the first derivative of the displacement and time curve. Before the test, the entire separation process will be simulated through simulation software to obtain the separation time, thrust, and speed. After obtaining the test data, comparison is made, and the simulation model is corrected according to the comparison result.

[0083] Step S25, calculate the interstage separation energy according to the interstage separation speed and the mass of the lower stage separation mass M2.

[0084] In this embodiment, the interstage separation energy can be obtained according to the formula E = (m * v 2 ) / 2, where E is the interstage separation energy, m is the mass of the lower stage separation mass M2, and v is the interstage separation speed.

[0085] Step S26, verify whether the thrust of the aerodynamic push rod can meet the standard of interstage separation of the launch vehicle according to the interstage separation energy.

[0086] In this embodiment, computer simulation and ground testing are used to verify whether the interstage separation energy meets the requirements. Simulation can help predict various situations during separation, while ground testing provides actual verification, and the simulation model is modified after verification. For example, if the rocket has already flown, flight data can be analyzed to verify whether the interstage separation has been performed as expected. The calculated interstage separation energy E can also be compared with the design standard and safety margin. If the calculated energy is greater than or equal to the energy required by the design standard and safety margin, it is considered that the rocket can meet the standard of interstage separation. If the energy is insufficient, the separation mechanism or rocket design needs to be re-evaluated to ensure that the separation can be successfully performed. The safety margin refers to the fact that in actual engineering, a certain safety margin is usually designed to ensure that the separation can be reliably performed under various conditions, including extreme conditions.

[0087] Specifically, in this embodiment, after receiving the interstage separation command of the launch vehicle, the aeromechanical connection unlocking device is unlocked, the pull rod is separated from the lower stage separation mass M2, and the aerodynamic push rod SSP starts to move the lower stage separation mass M2. The sensor collects the thrust and time data and displacement and time data on the aerodynamic push rod SSP, obtains the interstage separation speed according to the displacement and time data, calculates the interstage separation energy according to the interstage separation speed and the mass of the lower stage separation mass M2, and verifies whether the existing SSP design meets the separation standard through the interstage separation energy. If the calculated separation energy is greater than or equal to the energy required by the design standard and safety margin, it is considered that the rocket can meet the standard of interstage separation. If the separation energy is insufficient, the separation mechanism or rocket design needs to be re-evaluated to ensure that the separation can be successfully performed.

[0088] This embodiment can eliminate or reduce the friction of the separated body during the separation process to conduct aerodynamic function tests on the ground, realistically simulating the interstage separation process of a launch vehicle, thereby verifying whether the SSP can meet the first and second stage separation process. At the same time, it can also observe the structural stability, coordination and safety of the SSP to verify whether the existing design meets the interstage separation standard. In addition, it can control the deceleration and resetting of the separated body after separation to repeat the test and improve the utilization rate of the system.

[0089] In some embodiments, the method further includes: collecting air pressure and time data on the pneumatic push rod SSP through sensors on the pneumatic push rod SSP; when the air pressure value of the pneumatic push rod SSP reaches a preset air pressure threshold, the solenoid valve timing controller controls the second solenoid valve to open, and replenishes the pneumatic push rod SSP with gas through the second gas cylinder. In this embodiment, after the pneumatic push rod SSP is extended, the air pressure decreases due to the increased internal volume, so the solenoid valve timing controller needs to periodically control the opening and closing of the second solenoid valve to inflate the pneumatic push rod SSP, so as to maintain sufficient thrust of the pneumatic push rod SSP to simulate interstage separation.

[0090] In some embodiments, before receiving instructions from the launch vehicle, the process further includes: inflating the pneumatic push rod SSP, the first gas cylinder, and the second gas cylinder via a gas distribution platform; checking the safety of the test site; checking whether the data acquisition device is working properly; and recording the separation process via a camera.

[0091] Since the energy of the entire system in this embodiment comes from high-pressure gas, the first gas cylinder, the second gas cylinder, and the pneumatic push rod SSP need to be filled with gas via a gas distribution platform initially to provide initial energy. Additionally, during the test, a high-definition camera can be used to record the entire pneumatic function test process. Each frame recorded by the camera can be used to verify the accuracy of the data collected by the sensors, improving the accuracy of the test. After the test, the railcar can be restored to its original position using a crane or other tools, and the tie rods and pneumatic push rod SSP, along with other supporting fixtures, can be reinstalled. The air pipes, cables, sensors, and high-speed camera can then be inspected for damage for subsequent tests.

[0092] Figure 4 This is a structural block diagram of an interstage separation pneumatic function test control device according to an embodiment of the present invention, as shown below. Figure 4 As shown, the device 100 includes:

[0093] Interstage separation receiving unit 110 is used to receive interstage separation commands from the launch vehicle.

[0094] The inter-stage separation execution unit 120 is configured to control the first electromagnetic valve to open by the electromagnetic valve timing controller, and after the gas cylinder unlocking pneumatic mechanical connection unlocking device is unlocked, the pneumatic push rod pushes the lower stage separation mass to move.

[0095] The inter-stage separation data acquisition unit 130 is configured to acquire the thrust and time data and the displacement and time data of the pneumatic push rod by the sensor on the pneumatic push rod.

[0096] The inter-stage separation data acquisition unit 140 is configured to acquire the inter-stage separation speed according to the displacement and time data.

[0097] The inter-stage separation energy calculation unit 150 is configured to calculate the inter-stage separation energy according to the inter-stage separation speed and the mass of the lower stage separation mass.

[0098] The inter-stage separation standard verification unit 160 is configured to verify whether the thrust of the pneumatic push rod can meet the standard of the inter-stage separation of the launch vehicle according to the inter-stage separation energy.

[0099] In some embodiments, the data acquisition unit is further configured to acquire the air pressure and time data of the pneumatic push rod SSP by the sensor on the pneumatic push rod SSP; and the electromagnetic valve timing controller is configured to control the second electromagnetic valve to open when the air pressure value of the pneumatic push rod SSP reaches a preset air pressure threshold, and to supplement the pneumatic push rod SSP with gas by the second gas cylinder.

[0100] For specific details, please refer to the method embodiments shown in the description. Figure 3

[0101] Since the embodiment can eliminate or reduce the frictional force of the separation body in the separation process in the test process, the pneumatic function test can be performed on the ground, the inter-stage separation process of the launch vehicle is truly simulated, and then it is verified whether the SSP can meet the inter-stage separation process. In addition, the structural stability, coordination and safety of the SSP can be observed to verify whether the existing design meets the inter-stage separation standard, in addition, the deceleration and reset of the separation body after separation can be controlled to repeat the test and improve the utilization rate of the system.

[0102] ​The integrated module / unit, if implemented in the form of a software functional unit and sold or used as an independent product, can be stored in a computer readable storage medium. Based on such an understanding, all or part of the processes in the above-mentioned embodiment methods can also be completed by a computer program instructing related hardware, and the computer program can be stored in a computer readable storage medium. The computer program can implement the steps of each method embodiment when executed by a processor. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or some intermediate forms of the above. The computer readable medium can include any entity or device capable of carrying the computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc. Of course, there are other ways of readable storage medium, such as quantum memory, graphene memory, etc. It should be noted that the contents of the computer readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction, for example, in some jurisdictions, according to legislation and patent practice, the computer readable medium does not include electrical carrier signals and telecommunication signals.

[0103] Embodiment three

[0104] Reference will now be made to Figure 5 which shows an electronic device suitable for implementing the embodiments of the present disclosure.

[0105] The terminal device in the embodiments of the present disclosure can include, but is not limited to, mobile terminals such as mobile phones, notebook computers, digital broadcast receivers, PDAs (Personal Digital Assistants), PADs (Tablet Personal Computers), PMPs (Portable Multimedia Players), car terminals (such as car navigation terminals), and the like, and fixed terminals such as digital TVs, desktop computers, and the like. Figure 5 The electronic device shown is merely an example and should not impose any limitation on the functions and use range of the embodiments of the present disclosure.

[0106] As Figure 5As shown, the electronic device can include a processing device (e.g., a central processing unit, a graphics processing unit, etc.) 401 that can perform various appropriate actions and processes according to programs stored in a read-only memory (ROM) 402 or loaded into a random access memory (RAM) 403 from a storage device 408. Various programs and data required for operation of the electronic device are also stored in the RAM 403. The processing device 401, the ROM 402, and the RAM 403 are connected to each other through a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0107] Generally, the following devices can be connected to the I / O interface 405: input devices 406 including, for example, a touch screen, a touch pad, a keyboard, a mouse, a camera, a microphone, an accelerometer, a gyroscope, etc.; output devices 407 including, for example, a liquid crystal display (LCD), a speaker, a vibrator, etc.; storage devices 408 including, for example, a magnetic tape, a hard disk, etc.; and communication devices 409. The communication devices 409 can allow the electronic device to communicate wirelessly or wired with other devices to exchange data. Although Figure 4 The electronic device is shown with various devices, but it is understood that all of the shown devices are not required to be implemented or present. More or fewer devices can alternatively be implemented or present.

[0108] In particular, the processes described above with reference to the flowcharts can be implemented as a computer software program according to embodiments of the present disclosure. For example, embodiments of the present disclosure include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods illustrated by the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network through the communication devices 409, or installed from the storage devices 408, or installed from the ROM 402. When the computer program is executed by the processing device 401, the above-described functions defined in the methods of embodiments of the present disclosure are performed.

[0109] It should be noted that the computer-readable medium described above can be a computer-readable signal medium or a computer-readable storage medium or any combination thereof. The computer-readable storage medium can be, for example but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus or device, or any suitable combination of the foregoing. More specific examples of the computer-readable storage medium can include, but are not limited to, an electrical connection having one or more wires, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the disclosure, the computer-readable storage medium can be any tangible medium that contains or stores a program used by or in connection with an instruction execution system, apparatus or device. In the disclosure, the computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, in which the computer-readable program code is contained. Such a propagated data signal can take any of a variety of forms, including but not limited to electro-magnetic, optical, or any suitable combination thereof. The computer-readable signal medium can also be any computer-readable medium that is not a storage medium and that can communicate, propagate or transport a program for use by or in connection with an instruction execution system, apparatus or device. The program code contained in the computer-readable medium can be transmitted using any suitable medium, including but not limited to wire, cable, RF (radio frequency), etc., or any suitable combination of the foregoing.

[0110] In some embodiments, the client, server, or both can communicate using any current known or future developed network protocol, such as HTTP (HyperText Transfer Protocol), and can be interconnected with any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include local area networks ("LAN"), wide area networks ("WAN"), the Internet, and peer-to-peer networks (e.g., ad hoc peer-to-peer networks), as well as any current known or future developed networks.

[0111] The computer-readable medium described above can be included in the electronic device; or can exist separately from the electronic device, and can be accessed via the electronic device.

[0112] The computer-readable medium described above carries one or more programs, which when executed by the electronic device, cause the electronic device to:

[0113] Receive a launch vehicle stage separation command.

[0114] The first electromagnetic valve is opened by the electromagnetic valve timing controller, and the pneumatic push rod pushes the lower stage separation mass to move after the unlocking device is unlocked by the first gas cylinder.

[0115] The data of the pushing force and time and the displacement and time of the pneumatic push rod are collected by the sensor on the pneumatic push rod.

[0116] The interstage separation speed is obtained according to the displacement and time data.

[0117] The interstage separation energy is calculated according to the interstage separation speed and the mass of the lower stage separation mass.

[0118] Whether the pushing force of the pneumatic push rod can reach the standard of the interstage separation of the launch vehicle is verified according to the interstage separation energy.

[0119] Computer program code for carrying out operations of the present disclosure can be written in one or more programming languages or combinations of languages including object oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code can execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer, or entirely on the remote computer or server. In the latter scenario, the remote computer can be connected to the user's computer through any type of network, including a local area network (LAN) or a wide area network (WAN), or the connection can be made to an external computer (for example, through the Internet using an Internet Service Provider).

[0120] The flow diagrams and the block diagrams in the drawings are illustrations of architectures, functionalities, and operations of possible implementations of systems, methods, and computer program products according to various embodiments of the present disclosure. In this regard, each block in the flow diagrams or block diagrams can represent a module, a segment, or a portion of code, which comprises one or more executable instructions for implementing the specified logical functions. It should also be noted that in some alternative implementations, the functions noted in the blocks can occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and / or flow diagrams, and combinations of blocks in the block diagrams and / or flow diagrams, can be implemented by special purpose hardware-based systems that perform the specified functions or operations, or combinations of special purpose hardware and computer instructions.

[0121] The units described in the embodiments of the present disclosure can be implemented by software or by hardware. In some cases, the name of the unit does not constitute a limitation on the unit itself.

[0122] The functions described above in this document can be performed, at least in part, by one or more hardware logic components. For example, non-limiting examples of exemplary types of hardware logic components that can be used include field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), system on a chip (SOCs), complex programmable logic devices (CPLDs), etc.

[0123] In the context of the present disclosure, a machine-readable medium can be a tangible medium that contains or stores a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples of the machine-readable storage medium will include one or more lines of a program of a processor, a portable computer diskette, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or Flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0124] The above description is merely exemplary of the disclosure and the application of the principles thereof. It is not intended to limit the disclosure to the specific form set forth above. Rather, the disclosure is to cover by the appended claims whatever falls within the true scope of the disclosure, including equivalents. For example, although specific features are described above, one of ordinary skill in the art will appreciate that the features can be combined with other features disclosed herein (but not limited to) to form a technical solution.

[0125] Moreover, while operations can be depicted in the drawings in a particular, sequential order, this should not be understood as a requirement that such operations be performed in the order in which they are depicted. Rather, the operations can be performed in any order or concurrently that is deemed appropriate. Similarly, while discussions above can include a particular sequence of steps, it should be appreciated that unless otherwise specified, steps can be performed in other sequences, or omitted. Certain features that are described in the context of separate embodiments can also be implemented in combination in a single embodiment. Conversely, various features that are described in the context of a single embodiment can also be implemented in multiple embodiments separately or in any suitable sub-combination.

[0126] Although the subject matter has been described in language specific to structural features and / or methodological acts, it is to be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or acts described above. Rather, the specific features and acts described above are disclosed as example forms of implementing the claims.

Claims

1. A method for controlling an interstage separation pneumatic function test, characterized by, The pneumatic function test control method is based on an interstage separation test system, the interstage separation test system comprises: an upper stage separation mass, a lower stage separation mass, a pull rod and a pneumatic push rod; wherein, one end of the pull rod is movably connected with the upper stage separation mass, and the other end of the pull rod is connected with the lower stage separation mass through a pneumatic mechanical connection unlocking device, wherein the pneumatic mechanical connection unlocking device is connected with a first gas cylinder, and a first electromagnetic valve is arranged between the pneumatic mechanical connection unlocking device and the first gas cylinder; one end of the pneumatic push rod is movably connected with the upper stage separation mass, and the other end of the pneumatic push rod is movably connected with the lower stage separation mass, a sensor is arranged on the pneumatic push rod, the sensor collects the thrust and time data and displacement and time data of the pneumatic push rod and transmits them to a data acquisition device; the pneumatic function test control method comprises: sending a control signal to open the first electromagnetic valve, and after unlocking the pneumatic mechanical connection unlocking device through the first gas cylinder, the pneumatic push rod pushes the lower stage separation mass to move; acquiring the thrust and time data and displacement and time data of the pneumatic push rod collected by the sensor on the pneumatic push rod; calculating the interstage separation speed according to the displacement and time data; calculating the interstage separation energy according to the interstage separation speed and the mass of the lower stage separation mass; judging whether the thrust of the pneumatic push rod can realize the interstage separation of the launch vehicle according to the interstage separation energy.

2. The pneumatic function test control method according to claim 1, characterized in that The interstage separation test system further comprises a second gas cylinder connected with the pneumatic push rod, and a second electromagnetic valve is arranged between the second gas cylinder and the pneumatic push rod.

3. The pneumatic function test control method according to claim 2, characterized in that The sensor comprises an air pressure sensor arranged at one end of the pneumatic push rod close to the upper stage separation mass, and the method further comprises: collecting the air pressure and time data on the pneumatic push rod through the air pressure sensor, and opening the second electromagnetic valve when the air pressure value of the pneumatic push rod reaches a preset air pressure threshold, and supplementing the pneumatic push rod with gas through the second gas cylinder.

4. The pneumatic function test control method according to claim 2, characterized by The interstage separation test system further comprises a gas distribution platform and a blocking component, the gas distribution platform is used to provide gas for the pneumatic push rod, the first gas cylinder and the second gas cylinder, and the blocking component is connected with the lower stage separation mass and used to block the lower stage separation mass pushed out by the pneumatic push rod.

5. An apparatus for controlling a test of an interstage separation aerodynamic function, characterized by The control device is suitable for the method of any one of claims 1-4, and comprises: a signal sending unit for controlling the first electromagnetic valve to open, and after unlocking the pneumatic mechanical connection unlocking device through the first gas cylinder, the pneumatic push rod pushes the lower stage separation mass to move; a data acquisition unit for acquiring the thrust and time data and displacement and time data of the pneumatic push rod collected by the sensor on the pneumatic push rod; a data calculation unit for calculating the interstage separation speed according to the displacement and time data; an energy calculation unit for calculating the interstage separation energy according to the interstage separation speed and the mass of the lower stage separation mass; The thrust judging unit is configured to judge whether the thrust of the aerodynamic push rod can realize the inter-stage separation of the launch vehicle according to the inter-stage separation energy.

6. The pneumatic function test control device according to claim 5, characterized in that The sensor comprises an air pressure sensor arranged at one end of the aerodynamic push rod close to the upper stage separation mass, The data acquisition unit is further configured to acquire air pressure and time data of the aerodynamic push rod collected by the air pressure sensor; The signal sending unit is further configured to control the second electromagnetic valve to open and supplement the aerodynamic push rod with gas from the second gas cylinder when the air pressure value of the aerodynamic push rod reaches a preset air pressure threshold.

7. An electronic device, comprising: Comprising: one or more processors; a storage device for storing one or more programs, when the one or more programs are executed by the one or more processors, so that the one or more processors implement a kind of inter-stage separation aerodynamic function test control method as claimed in any one of claims 1-4.

8. A computer readable medium having stored thereon a computer program, characterized in that The program is executed by the processor to implement a kind of inter-stage separation aerodynamic function test control method as claimed in any one of claims 1-4.

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