Interstage separation test system, force-thermal environment identification level test method and device

Abstract

The application provides a stage separation test system, a force-thermal environment identification level test method and a device.The test method comprises the following steps: arranging a stage separation push rod on a vibration test table, performing vibration test on the stage separation push rod by using the stage separation working condition in rocket flight, and checking whether the stage separation push rod can meet the mechanical environment in the rocket flight process; when the mechanical environment in the rocket flight process is met, continuously heating the stage separation push rod to a first preset temperature and keeping the first preset temperature for a first preset time; verifying whether the stage separation push rod meets the stage separation standard at the first preset temperature; continuously cooling the stage separation push rod to a second preset temperature and keeping the second preset temperature for a second preset time; and verifying again whether the stage separation push rod meets the stage separation standard at the first preset temperature. The embodiment of the application can completely simulate the force and thermal environment on the rocket, and can complete the stage separation test under the condition of simulating the force and thermal environment on the rocket.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of carrier rockets, in particular to a stage separation test system, a force and thermal environment identification level test 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 in 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, the stage separation test method in the prior art cannot completely simulate the force and thermal environment on the rocket, and cannot complete the stage separation test under the condition of simulating the force and thermal environment on the rocket.

[0003] Therefore, there is an urgent need for a stage separation test system and a force and thermal environment test method, which can completely simulate the force and thermal environment on the rocket and can complete the stage separation test under the condition of simulating the force and thermal environment on the rocket. SUMMARY

[0004] Therefore, the purpose of the embodiments of the present application is to provide a stage separation test system, a force and thermal environment identification level test method and device, which can completely simulate the force and thermal environment on the rocket and can complete the stage separation test under the condition of simulating the force and thermal environment on the rocket.

[0005] To achieve the above purpose, in a first aspect, the embodiments of the present application provide a carrier rocket stage separation test system, the separation system comprising: a first mass body for simulating an upper stage and a second mass body for simulating a lower stage;

[0006] A stage separation fixed rod, one end of the stage separation fixed rod being connected with the first mass body, and the other end of the stage separation fixed rod being connected with the second mass body through an unlocking mechanism;

[0007] A stage separation push rod, one end of the stage separation push rod being fixedly connected with the first mass body, and the other end of the stage separation push rod being movably connected with the second mass body;

[0008] A push force sensor and a displacement sensor, both arranged on the stage separation push rod, for collecting push force and time data and displacement and time data of the stage separation push rod.

[0009] In some possible implementations, the separation test system further comprises: a first gas cylinder, a second gas cylinder, an electromagnetic valve time sequence controller and a pressure sensor;

[0010] The first gas cylinder is connected with the unlocking mechanism, and a first electromagnetic valve is arranged between the first gas cylinder and the second gas cylinder;

[0011] The second gas cylinder is connected with the inter-stage separation push rod, and a second electromagnetic valve is arranged between the second gas cylinder and the inter-stage separation push rod.

[0012] The electromagnetic valve timing controller is used for controlling the opening and closing of the first electromagnetic valve and the second electromagnetic valve.

[0013] The pressure sensor is used for collecting the gas pressure on the inter-stage separation push rod, and obtaining the gas pressure value on the inter-stage separation push rod in real time.

[0014] In some possible embodiments, the separation test system further comprises a gas distribution platform and a stop mechanism, the gas distribution platform is used for providing gas for the inter-stage separation push rod, the first gas cylinder and the second gas cylinder, and the stop mechanism is connected with the second mass body and used for stopping the second mass body pushed out by the inter-stage separation push rod.

[0015] In a second aspect, an embodiment of the present application provides a method for identifying a level of an inter-stage separation force thermal environment test, the method comprising:

[0016] The inter-stage separation push rod arranged on the vibration test table is subjected to a vibration test using the inter-stage working condition in rocket flight, so as to verify whether the inter-stage separation push rod can meet the mechanical environment in the process of rocket flight.

[0017] When the inter-stage separation push rod meets the mechanical environment in the process of rocket flight, the inter-stage separation push rod is continuously heated to a first preset temperature and kept for a first preset time.

[0018] The inter-stage separation test system of any one of the first aspect is used to perform a pneumatic function test, and whether the inter-stage separation push rod meets the inter-stage separation standard at the first preset temperature is verified through the pneumatic function test.

[0019] When the inter-stage separation push rod meets the inter-stage separation standard at the first preset temperature, the inter-stage separation push rod is continuously cooled to a second preset temperature and kept for a second preset time.

[0020] The inter-stage separation test system of any one of the first aspect is used to perform a pneumatic function test, and whether the inter-stage separation push rod meets the inter-stage separation standard at the second preset temperature is verified through the pneumatic function test.

[0021] In some possible embodiments, the pneumatic function test comprises:

[0022] The unlocking mechanism is unlocked, the fixed pull rod is disconnected with the second mass body, and the inter-stage separation push rod drives the second mass body to move.

[0023] acquiring, by a force sensor and a displacement sensor on the stage separation push rod, force versus time data and displacement versus time data of the stage separation push rod;

[0024] obtaining a stage separation speed according to the displacement versus time data;

[0025] calculating a stage separation energy according to the stage separation speed and a mass of the second mass body;

[0026] verifying whether the stage separation push rod can reach a stage separation standard at different temperatures according to the stage separation energy.

[0027] In some possible implementation manners, the method further includes:

[0028] acquiring, by an air pressure sensor on the stage separation push rod, air pressure versus time data of the stage separation push rod, and when an air pressure value of the stage separation push rod reaches a preset air pressure threshold, the electromagnetic valve timing controller controls the second electromagnetic valve to open, and the stage separation push rod is supplemented with gas by the second gas cylinder.

[0029] In some possible implementation manners, before the stage separation command of the carrier rocket is received, the method further includes:

[0030] filling the stage separation push rod, the first gas cylinder and the second gas cylinder with gas by a gas distribution platform.

[0031] In a third aspect, an embodiment of the present application provides a stage separation force and thermal environment identification level test device, and the device includes:

[0032] a mechanical environment identification unit, configured to perform a vibration test on a stage separation push rod arranged on a vibration test table by using a stage separation working condition in rocket flight, and to verify whether the stage separation push rod can meet a mechanical environment in the process of rocket flight;

[0033] a stage separation push rod heating unit, configured to continuously heat the stage separation push rod to a first preset temperature and keep the stage separation push rod at the first preset temperature for a first preset time when the stage separation push rod meets the mechanical environment in the process of rocket flight;

[0034] a first aerodynamic function test unit, configured to perform an aerodynamic function test on the stage separation test system in any one of the first aspect, and to verify whether the stage separation push rod meets a stage separation standard at the first preset temperature through the aerodynamic function test;

[0035] a stage separation push rod cooling unit, configured to continuously cool the stage separation push rod to a second preset temperature and keep the stage separation push rod at the second preset temperature for a second preset time when the stage separation push rod meets the stage separation standard at the first preset temperature;

[0036] The second pneumatic function test unit is used to perform a pneumatic function test through the interstage separation test system of any one of the first aspect, and whether the interstage separation push rod meets the interstage separation standard at the second preset temperature is verified through the pneumatic function test.

[0037] The technical scheme has the beneficial effects that:

[0038] The interstage separation test system, the force-thermal environment identification level test method and the device provided by the embodiment of the present application have the beneficial effects that: When the interstage separation push rod meets the interstage separation standard at the first preset temperature, the interstage separation push rod is continuously cooled to a second preset temperature and kept for a second preset time, and then a pneumatic function test is performed through the interstage separation test system to verify whether the interstage separation push rod meets the interstage separation standard at the first preset temperature. The embodiment of the present application can completely simulate the force and thermal environment on the rocket, and can complete the interstage separation test under the condition of simulating the force and thermal environment on the rocket. BRIEF DESCRIPTION OF DRAWINGS

[0039] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0040] Figure 1A is a structural schematic diagram of a launch vehicle interstage separation test system according to an embodiment of the present application;

[0041] Figure 1B is a schematic diagram of an interstage separation push rod connected to the first mass body and the second mass body through an adapter tool according to an embodiment of the present application;

[0042] Figure 1C is a structural schematic diagram of another launch vehicle interstage separation test system according to an embodiment of the present application;

[0043] Figure 2 is a flowchart of a launch vehicle interstage force-thermal environment identification level test method according to an embodiment of the present application;

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

[0045] Figure 4 is a structural block diagram of a stage separation force thermal environment identification magnitude test device according to an embodiment of the present application.

[0046] Figure 5 is a function 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 or all of these specific details. The description of the embodiments is merely illustrative of the present application and is not intended to limit the present application, as is apparent to one of ordinary skill in the art. In the following 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 or all of these specific details. In other instances, well-known structures and functions have not been described in detail in order to not obscure the present application. Also, the description is not to be considered limiting in scope, as the scope of the present application is defined by the appended claims and their equivalents. In addition, features described herein can be incorporated in any suitable manner in one or more embodiments.

[0048] Terminology:

[0049] Embodiments of the present application provide a new test method with improved ground stage cold separation test efficiency, test safety and test accuracy. Embodiments of the present application simulate the separation body and the stage section to simulate the real separation condition; design the track and the track carriage to eliminate the friction; use dry ice tank refrigeration and electric heating band heating to simulate the environment on the rocket; and completely simulate the force and thermal environment on the rocket to test the stage separation push rod.

[0050] Embodiment One

[0051] Figure 1A is a structural schematic diagram of a launch vehicle stage separation test system according to an embodiment of the present application, as shown in Figure 1AAs shown, the separation system comprises: a first mass body 1 for simulating the upper stage and a second mass body 2 for simulating the lower stage; an inter-stage fixed rod 3, one end of the inter-stage fixed rod 3 is connected with the first mass body 1, and the other end is connected with the second mass body 2 through an unlocking mechanism 4; an inter-stage separation push rod 5, one end of the inter-stage separation push rod 5 is connected with the first mass body 1, and the other end is connected with the second mass body 2 through a movable connection; a push force sensor 6 and a displacement sensor 7, both of which are arranged on the inter-stage separation push rod 5, are used to collect the push force and displacement data of the inter-stage separation push rod 5 and transmit them to a data acquisition device A, and the collected data is saved and convenient for subsequent processing through the data acquisition device A and other terminal devices.

[0052] Figure 1B It is a schematic view of an inter-stage separation push rod connected with the first mass body and the second mass body through an adapter tool according to an embodiment of the present application, as shown in Figure 1B As shown, in some embodiments, the inter-stage separation push rod 5 can be connected with both the first mass body 1 and the second mass body 2 through an adapter tool, wherein the adapter tool comprises a push force dispersion seat 8 and a buffer pad 9, the first end of the inter-stage separation push rod 5 is connected to the first mass body 1 through the push force dispersion seat 8, and the push force dispersion seat 8 is used to disperse the push force of the inter-stage separation push rod 5 acting on the first mass body 1, the second end of the inter-stage separation push rod 5 is connected with the second mass body 2 through a buffer pad 9, the buffer pad 9 is made of soft material, and the real state of the simulated rocket is simulated through the soft material buffer to protect the structure of the position where the inter-stage separation push rod 5 contacts the second mass body 2 from being damaged. In addition, the number of inter-stage separation fixed rods 3 can be determined according to actual conditions, for example, three, and the three inter-stage separation fixed rods 3 are distributed in a triangular form, and the inter-stage separation push rod 5 is located at the center of the triangular row formed by the three inter-stage separation fixed rods to maintain the balance of the system, and a unlocking mechanism 4 is connected between each inter-stage separation fixed rod 5 and the second mass body 2. In FIG. 1, two inter-stage separation fixed rods 3 are shown, and the other inter-stage separation push rod 5 is blocked. The push force sensor 6 and the displacement sensor 7 are arranged on the inter-stage separation push rod 5, which are used to measure the push force and displacement on the inter-stage separation push rod 5, wherein the displacement of the inter-stage separation push rod 5 is also the displacement of the second mass body 2, and is transmitted to the data acquisition device for subsequent data analysis.

[0053] In the actual launch process of the launch vehicle of this embodiment, the mass of the upper stage separation body is much larger than that of the lower stage separation body. Therefore, in this embodiment, the first mass body 1 can be an object such as a fixed wall, and the second mass body 2 can be a railcar with a certain mass. The railcar is filled with a sufficient amount of mass (e.g., the railcar is loaded with 30t of sand) to simulate the mass of the lower stage separation body. In addition, the end of the track near the first mass body 1 can be raised to create a certain slope between the first mass body 1 and the second mass body 2. For example, wedge steel can be used to raise the end near the first mass body 1. The advantages of using wedge steel to raise the near end of the track to form a downhill slope mainly include: easy height adjustment, as wedge steel can be cut or stacked as needed to easily adjust the height of the track; good stability, as wedge steel has high strength and rigidity, providing stable support and ensuring the stability of the track; and simple installation, as wedge steel can usually fit tightly with the track structure, simplifying the installation process. The interstage separation fixing rod 3 is connected between the fixed wall and the railcar. The railcar is fixed by the interstage separation fixing rod 3. Since the gas pressure of the interstage separation push rod 5 is as high as tens of megapascals, in order to prevent high-pressure gas leakage and injury during the test, the entire test system can be isolated by two partition walls on the side, so that the relevant tooling during the test is placed inside the partition walls, such as the interstage separation push rod 5 and the interstage separation fixing rod 3.

[0054] Figure 1C This is a schematic diagram of another launch vehicle stage separation test system according to an embodiment of the present invention, as shown below. Figure 1C As shown, in some embodiments, the separation test system further includes: a first gas cylinder 10, a second gas cylinder 11, a solenoid valve timing controller 12, and a pressure sensor 13; when the unlocking mechanism is a pneumatic unlocking mechanism, the first gas cylinder 10 is connected to the unlocking mechanism 4, and a first solenoid valve 14 is provided between the first gas cylinder 10 and the unlocking mechanism 4; the second gas cylinder 11 is connected to the interstage separation push rod 5, and a second solenoid valve 15 is provided between the second gas cylinder 11 and the interstage separation push rod 5; the solenoid valve timing controller 12 is used to control the opening and closing of the first solenoid valve 14 and the second solenoid valve 15; the pressure sensor 13 is used to collect the air pressure on the interstage separation push rod 5 and obtain the air pressure value on the interstage separation push rod 5 in real time.

[0055] In this embodiment, after the interstage separation push rod 5 is pushed out, the internal volume increases and the air pressure decreases. Therefore, the second solenoid valve 15 needs to be opened and closed intermittently by the solenoid valve timing controller 12 to inflate the interstage separation push rod 5.

[0056] As shown in Figure 1, in some embodiments, the separation test system further includes: a gas distribution platform 16 and a blocking mechanism 17. The gas distribution platform 16 supplies gas to the interstage separation push rod 5, the first gas cylinder 10 and the second gas cylinder 11 through a gas filling hose. The blocking mechanism 17 is connected to the second mass body 2 and is used to block the second mass body 2 pushed out by the interstage separation push rod 5.

[0057] Since the energy of the entire system in this embodiment comes from high-pressure gas, the first gas cylinder 10, the second gas cylinder 11 and the interstage separation push rod 5 need to be filled with gas through the gas distribution platform 16 at the beginning to provide initial energy. The two sides of the second mass body 2 are equipped with blocking mechanisms, such as large mass objects like stone discs, which are connected to the two sides of the second mass body 2 to block the second mass body 2 pushed out by the interstage separation push rod 5, so as to facilitate the withdrawal and reset after the test.

[0058] In this embodiment, since both the interstage separation fixing rod 3 and the interstage separation push rod 5 are suspended, to reduce the bending moment load generated by their own weight, a support frame can be used to support the interstage separation fixing rod 3 and the interstage separation push rod 5 near the unlocking mechanism. After the unlocking mechanism 4 is unlocked, the interstage separation fixing rod 3 is disconnected from the second mass body 2, and then supported by the support frame. In addition, a crane and a trolley can be prepared outside the partition wall for resetting the corresponding tooling after the test, so that it can be used repeatedly in subsequent tests. In this embodiment, before the test begins, the interstage separation push rod 5, the first gas cylinder 10, and the second gas cylinder 11 are filled with gas through the gas distribution platform 16 (after the interstage separation push rod 5 is filled with gas, it will gradually generate thrust until the gas pressure reaches the predetermined value and the thrust gradually stabilizes). After the test is ready to begin, the railcar releases the brake, the first solenoid valve of the unlocking mechanism 4 unlocks, the interstage separation fixing rod 3 is disconnected from the second mass body 2, the interstage separation push rod 5 starts to work, and the thrust sensor 6 and displacement sensor 7 start to collect data. After a period of time, the second solenoid valve 15 for replenishing gas to the interstage separation push rod 5 opens, and the second gas cylinder 11 of the interstage separation push rod 5 starts to replenish gas to the interstage separation push rod 5. After the interstage separation push rod 5 and the railcar stabilize, the data collection stops, and the test is completed.

[0059] In this embodiment of the invention, the railcar can be a large truck, engineering vehicle or other modified mobile heavy vehicle, the fixed wall can be replaced by a fixed steel component, the interstage separation push rod 5 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.

[0060] The interstage separation system of the launch vehicle provided in this embodiment of the invention can effectively eliminate or reduce the friction of the separated parts during the separation process, and can also control the deceleration and repositioning of the separated parts.

[0061] Example 2

[0062] Figure 2 This is a flowchart of a test method for determining the magnitude of interstage separation force and thermal environment according to an embodiment of the present invention, as shown below. Figure 2 As shown, the method includes the following steps:

[0063] Step S11: Vibration test is performed on the interstage separation push rod 5 set on the vibration test bench using the interstage working conditions during rocket flight to verify whether the interstage separation push rod 5 can meet the mechanical environment during rocket flight.

[0064] Among them, the interstage working conditions during rocket flight include the mechanical environment during rocket startup, that is, the vibration generated during startup. This step uses a vibration test bench to verify whether the interstage separation push rod 5 can adapt to the vibration generated by interstage separation under this vibration environment.

[0065] Step S12: When the interstage separation push rod 5 meets the mechanical environment during rocket flight, the interstage separation push rod 5 is continuously heated to a first preset temperature and maintained for a first preset time.

[0066] Step S13: Perform a pneumatic function test using the interstage separation test system to verify whether the interstage separation push rod 5 meets the interstage separation standard at the first preset temperature.

[0067] Step S14: When the interstage separation push rod 5 meets the interstage separation standard at the first preset temperature, the interstage separation push rod 5 is continuously cooled to the second preset temperature and maintained for the second preset time.

[0068] Step S15: Perform a pneumatic function test using the interstage separation test system to verify whether the interstage separation push rod 5 meets the interstage separation standard at the second preset temperature.

[0069] Specifically, a vibration test bench is a testing device used to simulate the effects of real vibration environments in a laboratory. In this embodiment, the mechanical environment during rocket launch is simulated. The vibration test involves exciting the sample on the vibration bench using different input signals. Vibration tests are mainly divided into sinusoidal vibration and random vibration. Because the physical processes of the two are different, there is no strict equivalence between them. Therefore, when selecting a test method, a severity level conversion from sinusoidal to random should not be performed. This embodiment verifies the correctness of the SSP design by determining whether the interstage separation push rod 5 can meet the mechanical environment requirements during rocket flight.

[0070] In this embodiment, the temperature range of the rocket is -40 to 60 degrees Celsius. Therefore, the interstage separation push rod 5 needs to adapt to the extreme temperature range of this range while maintaining its basic function, i.e., successfully completing one interstage separation. During the heating process of the interstage separation push rod 5, an electric heating tape can be used to wrap the interstage separation push rod 5, and it can be sealed with a mold. A displacement sensor is placed inside, and the interstage separation push rod 5 is continuously heated and kept at about 60°C (first preset temperature) for 2 hours (first preset time). When the temperature reaches 60 degrees Celsius and is maintained for 2 hours, it is basically stable. At this time, a pneumatic function test is performed in a high-temperature environment to verify whether the interstage separation push rod 5 meets the interstage separation standard at 60 degrees Celsius. Similarly, after the SSP meets the high-temperature environment in the thermal environment, an aluminum plate can be used to customize an aluminum groove for the SSP. An appropriate amount of dry ice is added to the aluminum groove and it is sealed with a mold. The interstage separation push rod 5 is continuously cooled and kept at about -40°C (second preset temperature) for 2 hours (second preset time). Then, after the minimum temperature stabilizes at about 40 degrees Celsius, a pneumatic function separation test is performed in a low-temperature environment. In addition, the embodiments of the present invention can be tested under high temperature environment or low temperature environment first.

[0071] The embodiments of the present invention can completely simulate the force and thermal environment on the arrow, and can complete the interstage separation test under the simulated force and thermal environment on the arrow.

[0072] Figure 3 This is a flowchart of a pneumatic function testing method according to an embodiment of the present invention, such as... Figure 3 As shown, this pneumatic function testing method is based on the aforementioned pneumatic separation system, and the method includes the following steps:

[0073] Step S21: Unlock the unlocking mechanism 4, disconnect the interstage separation fixing rod 3 from the second mass body 2, and the interstage separation push rod 5 pushes the second mass body 2 to move. In this embodiment, after receiving the interstage separation command of the launch vehicle, the unlocking mechanism 4 is unlocked to disconnect the interstage separation fixing rod 3 from the second mass body 2.

[0074] In this embodiment, the interstage separation process is divided into two steps. First, the unlocking mechanism 4 needs to be unlocked, and then the separation energy is provided through the interstage separation push rod 5. Traditional domestic separation energy sources are mostly positive and negative thrust rockets (pyrotechnic components are the separation energy source), while a few models use thermal separation (the separation energy source is the high-temperature exhaust gas flow from the upper-stage engine). Unlike traditional domestic separation energy sources, the interstage separation push rod 5 in this embodiment is powered by air pressure, making it easier to control the separation force.

[0075] Step S22: The thrust and time data and displacement and time data of the interstage separation push rod 5 are collected by the thrust sensor 6 and displacement sensor 7 on the interstage separation push rod 5.

[0076] Step S23: Obtain the interstage separation velocity based on displacement and time data.

[0077] In this embodiment, the interstage separation displacement is a design specification, the interstage separation time is obtained by the sensor based on the interstage separation displacement, and the interstage separation velocity can be obtained by taking the first derivative of the displacement-time curve. Before the test, the entire separation process will be simulated using simulation software to obtain the separation time, thrust, and velocity. After obtaining the test data, the data will be compared, and the simulation model will be corrected based on the comparison results.

[0078] Step S24: Calculate the interstage separation energy based on the interstage separation velocity and the mass of the second mass body 2;

[0079] In this embodiment, the interstage separation energy can be calculated using the formula E = (m * v) 2 E is obtained as ) / 2, where E is the interstage separation energy, m is the mass of the second mass body 2, and v is the interstage separation velocity.

[0080] Step S25: Verify, based on the interstage separation energy, whether the thrust of the interstage separation push rod 5 at different temperatures can meet the interstage separation standard.

[0081] This embodiment verifies whether the interstage separation energy meets the requirements through computer simulation and ground testing. Simulation helps predict various situations during the separation process, while ground testing provides actual verification. The simulation model is then modified after verification. For example, if the rocket has already flown, flight data can be analyzed to verify whether the interstage separation pusher 5 separates as expected at different temperatures. Alternatively, the calculated interstage separation energy E can be compared with the design standards and safety margins. If the calculated energy is greater than or equal to the energy required by the design standards and safety margins, the rocket is considered to have met the interstage separation standards. If the energy is insufficient, the separation mechanism or rocket design needs to be re-evaluated to ensure successful separation. The safety margin refers to the safety margin typically designed in actual engineering to ensure reliable separation under various conditions, including extreme conditions.

[0082] 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 the launch vehicle, thereby verifying whether the interstage separation push rod 5 can meet the requirements of the first and second stage separation process. At the same time, the structural stability, coordination and safety of the interstage separation push rod 5 can be observed to verify whether the existing design meets the interstage separation standard. In addition, the deceleration and resetting of the separated body can be controlled after separation to repeat the test and improve the utilization rate of the system.

[0083] In some embodiments, the method further includes: collecting air pressure and time data on the interstage separation push rod 5 using sensors on the push rod 5; when the air pressure value of the interstage separation push rod 5 reaches a preset air pressure threshold, the solenoid valve timing controller 12 controls the second solenoid valve 15 to open, and replenishes the interstage separation push rod 5 with gas through the second gas cylinder 11. In this embodiment, after the interstage separation push rod 5 is pushed out, the internal volume increases and the air pressure decreases, so the second solenoid valve 15 needs to be opened and closed intermittently by the solenoid valve timing controller to inflate the interstage separation push rod 5, so as to maintain sufficient thrust of the interstage separation push rod 5 to simulate interstage separation.

[0084] In some embodiments, before receiving instructions from the launch vehicle, the process further includes: inflating the interstage separation push rod 5, the first gas cylinder 10, and the second gas cylinder 11 via the gas distribution platform 16; checking the safety of the test site; checking whether the data acquisition device is working properly; and recording the separation process via a camera.

[0085] Since the energy of the entire system in this embodiment comes from high-pressure gas, it is necessary to initially fill the first gas cylinder 10, the second gas cylinder 11, and the interstage separation push rod 5 with gas through the gas distribution platform 16 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 interstage separation fixing rod 3 and interstage separation push rod 5, along with other supporting fixtures, can be reinstalled. The air pipes, cables, sensors, high-speed camera, etc., can be checked for damage for subsequent tests.

[0086] Example 3

[0087] Figure 4 This is a structural block diagram of a test device for determining the magnitude of interstage separation force and thermal environment according to an embodiment of the present invention, as shown below. Figure 4 As shown, the device 100 includes:

[0088] The mechanical environment assessment unit 110 is used to conduct vibration tests on the interstage separation push rod 5 set on the vibration test bench using the interstage working conditions during rocket flight, to verify whether the interstage separation push rod 5 can meet the mechanical environment during rocket flight.

[0089] The interstage separation heating unit 120 is used to continuously heat the interstage separation push rod 5 to a first preset temperature and maintain it for a first preset time when the interstage separation push rod 5 meets the mechanical environment during rocket flight.

[0090] The first pneumatic function test unit 130 is used to conduct pneumatic function tests through the interstage separation test system, and to verify whether the interstage separation push rod 5 meets the interstage separation standard at the first preset temperature through the pneumatic function test.

[0091] The interstage separation cooling unit 140 is used to continuously cool the interstage separation push rod 5 to a second preset temperature and maintain it for a second preset time when the first preset temperature meets the interstage separation standard.

[0092] The second pneumatic function test unit 150 conducts pneumatic function tests through the interstage separation test system, and verifies whether the interstage separation push rod 5 meets the interstage separation standard at the second preset temperature through the pneumatic function test.

[0093] Among them, the interstage working conditions during rocket flight include the mechanical environment during rocket startup, that is, the vibration generated during startup. This step uses a vibration test bench to verify whether the interstage separation push rod 5 can adapt to the vibration generated by interstage separation under this vibration environment.

[0094] Specifically, in this embodiment, the mechanical environment assessment unit 110 simulates the mechanical environment during rocket launch using a vibration test bench to conduct mechanical tests on the interstage separation pusher 5. The vibration test bench is a test device used to simulate the effects of a real vibration environment in a laboratory. The vibration test involves exciting the sample on the vibration bench using different input signals. Vibration tests are mainly divided into sinusoidal and random vibrations. Since the physical processes of the two are different, there is no strict equivalence between them. Therefore, when selecting the test method, it is crucial to avoid converting the severity level from sinusoidal to random. This embodiment verifies the correctness of the SSP design by assessing whether the interstage separation pusher 5 can meet the mechanical environment requirements during rocket flight.

[0095] In this embodiment, the temperature range of the rocket is -40 to 60 degrees Celsius. Therefore, the interstage separation push rod 5 needs to adapt to the extreme temperature range of this range while maintaining its basic function, i.e., successfully completing one interstage separation. During the heating process of the interstage separation push rod 5, the interstage separation heating unit 120 can use an electric heating tape to wrap the interstage separation push rod 5, seal it with a mold, insert a displacement sensor, and continuously heat and maintain the interstage separation push rod 5 at about 60°C (first preset temperature) for 2 hours (first preset time). When the temperature reaches 60 degrees Celsius and is maintained for 2 hours, it basically stabilizes. At this time, the first aerodynamic function test unit 130 verifies whether the interstage separation push rod 5 is fully functional at 60 degrees Celsius through a pneumatic function test of the interstage separation test system in a high-temperature environment. Similarly, to meet the standard for interstage separation, after the interstage separation push rod 5 meets the high-temperature environment requirement in the thermal environment, the interstage separation cooling unit 140 can use aluminum sheets to customize an aluminum groove for the interstage separation push rod 5, add an appropriate amount of dry ice to the aluminum groove, and seal it with a mold to continuously cool the interstage separation push rod 5 and maintain it at approximately -40°C (second preset temperature) for about 2 hours (second preset time). Then, after the minimum temperature stabilizes at approximately 40°C, the second pneumatic function test unit 150 conducts a pneumatic function separation test again in a low-temperature environment through the interstage separation test system. In addition, the embodiments of the present invention can conduct tests in either a high-temperature environment or a low-temperature environment first.

[0096] It should be noted that the interstage separation heating unit 120 and interstage separation cooling unit 140 in this embodiment are not limited to the manner provided in this embodiment. For example, the interstage separation heating unit 120 can also take the following forms:

[0097] Heating is achieved by using an electric heating wire: the electric heating wire can be embedded inside the pneumatic push rod or wrapped around its surface, and heat is generated by passing electricity through it.

[0098] Microwave heating: Using a microwave generator to heat the pneumatic actuator locally or entirely results in fast and uniform heating.

[0099] Infrared heating: The pneumatic actuator is heated by infrared radiation. The infrared heater can emit infrared rays in a specific direction to achieve rapid and efficient heating.

[0100] Induction heating: Heating is achieved by generating eddy currents in the pneumatic actuator through electromagnetic induction. This method is suitable for pneumatic actuators made of metal. Heat pipe technology: Heat is transferred from one end of the pneumatic actuator to the part requiring heating by circulating a working fluid within the heat pipe. Chemical heating element: Heat is generated using a chemical reaction and can be used as a disposable heating element.

[0101] In addition to dry ice bath cooling, the interstage separation cooling unit 140 can also be cooled by the following methods:

[0102] Liquid nitrogen cooling: Liquid nitrogen, as a cryogenic refrigerant, can effectively and rapidly cool the pneumatic actuator. Semiconductor cooling: Utilizing the thermoelectric effect of semiconductor materials, cooling is achieved through direct current. This method has no moving parts, making it quieter and more reliable. Eddy current cooling: Utilizing the thermal separation effect generated by eddy current tubes to cool the pneumatic actuator.

[0103] Coolant circulation: A specific coolant is used, and a circulation system delivers the coolant to the parts of the pneumatic actuator that require cooling. Heat pipe cooling: In contrast to heating, heat pipes are used to rapidly conduct and dissipate heat from the pneumatic actuator.

[0104] Phase change materials are used: the pneumatic push rod is cooled by utilizing the property of certain substances to absorb or release heat during the phase change process.

[0105] Air cooling: Forced convection cooling of the pneumatic actuator is achieved using airflow generated by a fan or blower. Jet cooling: Coolant or gas is directly sprayed onto the surface of the pneumatic actuator through nozzles for rapid and efficient cooling. Heat exchanger cooling: A heat exchanger is used to exchange heat between the pneumatic actuator and the refrigerant, thus achieving a cooling effect.

[0106] The embodiments of the present invention can completely simulate the force and thermal environment on the arrow, and can complete the interstage separation test under the simulated force and thermal environment on the arrow.

[0107] If the integrated module / unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes in the methods of the above embodiments can also be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium, and when executed by a processor, it can implement the steps of the various method embodiments described above. The computer program includes computer program code, which can be in the form of source code, object code, executable files, or certain intermediate forms. The computer-readable medium can include: any entity or device capable of carrying the computer program code, recording media, USB flash drives, portable hard drives, magnetic disks, optical disks, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signals, telecommunication signals, and software distribution media, etc. Of course, there are other types of readable storage media, such as quantum memories, graphene memories, etc. It should be noted that the content contained in the computer-readable medium may be appropriately added to or subtracted from the content as required by the legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, the computer-readable medium may not include electrical carrier signals and telecommunication signals.

[0108] The following is for reference. Figure 5 It illustrates an electronic device suitable for implementing embodiments of the present disclosure.

[0109] The terminal devices in this disclosure may include, but are not limited to, mobile terminals such as mobile phones, laptops, digital broadcast receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), and in-vehicle terminals (such as in-vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Figure 5 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of the embodiments disclosed herein.

[0110] like Figure 5 As shown, the electronic device may include a processing unit (e.g., a central processing unit, a graphics processor, etc.) 501, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 502 or a program loaded from a storage device 508 into a random access memory (RAM) 503. The RAM 503 also stores various programs and data required for the operation of the electronic device. The processing unit 501, ROM 502, and RAM 503 are interconnected via a bus 504. An input / output (I / O) interface 505 is also connected to the bus 504.

[0111] Typically, the following devices can be connected to I / O interface 505: input devices 506 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 507 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 508 including, for example, magnetic tapes, hard disks, etc.; and communication devices 509. Communication device 509 allows electronic devices to communicate wirelessly or wiredly with other devices to exchange data. Although Figure 4 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown. More or fewer devices may be implemented or have alternatively.

[0112] In particular, according to embodiments of this disclosure, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this 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 shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 509, or installed from a storage device 508, or installed from a ROM 502. When the computer program is executed by the processing device 501, it performs the functions defined in the methods of embodiments of this disclosure.

[0113] It should be noted that the computer-readable medium described above in this disclosure can be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example,—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this disclosure, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or loaded onto an instruction execution system, apparatus, or device. In this disclosure, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or loaded thereon by an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical fibers, RF (radio frequency), etc., or any suitable combination thereof.

[0114] In some implementations, clients and servers may communicate using any currently known or future-developed network protocol such as HTTP (Hypertext Transfer Protocol) and may interconnect with digital data communication (e.g., communication networks) of any form or medium. Examples of communication networks include local area networks (“LANs”), wide area networks (“WANs”), the Internet (e.g., the Internet of Things), and end-to-end networks (e.g., ad-hoc networks), as well as any currently known or future-developed networks.

[0115] The aforementioned computer-readable medium may be included in the aforementioned electronic device; or it may exist independently and not assembled into the electronic device.

[0116] The aforementioned computer-readable medium carries one or more programs that, when executed by the electronic device, cause the electronic device to:

[0117] Vibration tests were conducted on the interstage separation push rod, which was installed on a vibration test bench, using the interstage conditions during rocket flight to verify whether the interstage separation push rod could meet the mechanical environment during rocket flight.

[0118] When the interstage separation push rod meets the mechanical environment during rocket flight, the interstage separation push rod is continuously heated to a first preset temperature and maintained for a first preset time;

[0119] Aerodynamic function tests were conducted using a launch vehicle stage separation test system to verify whether the stage separation push rod met the stage separation standard at the first preset temperature.

[0120] When the interstage separation push rod meets the interstage separation standard at the first preset temperature, the interstage separation push rod is continuously cooled to the second preset temperature and maintained for the second preset time.

[0121] A pneumatic function test is conducted using an interstage separation test system to verify whether the interstage separation push rod meets the interstage separation standard at the second preset temperature.

[0122] Computer program code for performing the operations of this disclosure can be written in one or more programming languages ​​or a combination thereof, including but not limited to object-oriented programming languages ​​such as Java, Smalltalk (an object-oriented programming language), and C++, as well as conventional procedural programming languages ​​such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0123] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0124] The units described in the embodiments of this disclosure can be implemented in software or hardware. The names of the units are not, in some cases, intended to limit the specific unit.

[0125] The functions described above in this document can be performed, at least in part, by one or more hardware logic components. For example, exemplary types of hardware logic components that can be used, without limitation, include: Field Programmable Gate Arrays (FPGAs), Application-Specific Integrated Circuits (ASICs), Application Standard Products (ASSPs), System-on-Chip (SoCs), Complex Programmable Logic Devices (CPLDs), and so on.

[0126] In the context of this disclosure, a machine-readable medium can be a tangible medium that may contain or store a program for use by or loaded with an instruction execution system, apparatus, or device. A machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can be, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0127] The above description is merely a preferred embodiment of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0128] Furthermore, while the operations are described in a specific order, this should not be construed as requiring these operations to be performed in the specific order shown or in a sequential order. In certain environments, multitasking and parallel processing may be advantageous. Similarly, while several specific implementation details are included in the above discussion, these should not be construed as limiting the scope of this disclosure. Certain features described in the context of individual embodiments may also be implemented in combination in a single embodiment. Conversely, various features described in the context of a single embodiment may also be implemented individually or in any suitable sub-combination in multiple embodiments.

[0129] Although the subject matter has been described using language specific to structural features and / or methodological logic, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or actions described above. Rather, the specific features and actions described above are merely illustrative examples of implementing the claims.

Claims

1. A test method for determining the magnitude of interstage separation force and thermal environment, characterized in that, The method is applied to a launch vehicle interstage separation test system, the launch vehicle interstage separation test system comprising: The first mass body used to simulate the upper stage and the second mass body used to simulate the lower stage; An interstage fixing rod, one end of which is connected to the first mass body, and the other end of which is connected to the second mass body via an unlocking mechanism; An interstage separation push rod, one end of which is fixedly connected to the first mass body, and the other end of which is movably connected to the second mass body; Both the thrust sensor and the displacement sensor are mounted on the interstage separation push rod, and are used to collect the thrust and time data and displacement and time data of the interstage separation push rod; The test method includes: Vibration tests were conducted on the interstage separation push rod, which was installed on a vibration test bench, using the interstage conditions during rocket flight to verify whether the interstage separation push rod could meet the mechanical environment during rocket flight. When the interstage separation push rod meets the mechanical environment during rocket flight, the interstage separation push rod is continuously heated to a first preset temperature and maintained for a first preset time; Aerodynamic function tests are conducted using the launch vehicle interstage separation test system to verify whether the interstage separation push rod meets the interstage separation standard at the first preset temperature. When the interstage separation push rod meets the interstage separation standard at the first preset temperature, the interstage separation push rod is continuously cooled to the second preset temperature and maintained for the second preset time. The interstage separation test system is used to conduct pneumatic function tests to verify whether the interstage separation push rod meets the interstage separation standard at the second preset temperature.

2. The method for determining the magnitude of mechanical and thermal environment according to claim 1, characterized in that, The pneumatic function test includes: The unlocking mechanism disconnects the fixed pull rod from the second mass body, and the interstage separation push rod pushes the second mass body to move. The thrust and time data and displacement and time data of the interstage separation push rod are collected by the thrust sensor and displacement sensor on the interstage separation push rod; The interstage separation velocity is obtained based on the displacement and time data; The interstage separation energy is calculated based on the interstage separation velocity and the mass of the second mass body. The interstage separation energy is used to verify whether the thrust of the interstage separation pusher can meet the interstage separation standard at different temperatures.

3. The test method for determining the magnitude of the interstage separation force and thermal environment according to claim 1, characterized in that, The launch vehicle stage separation test system also includes: a first gas cylinder, a second gas cylinder, a solenoid valve timing controller, and a pressure sensor; The first gas cylinder is connected to the unlocking mechanism, and a first solenoid valve is provided between the first gas cylinder and the second gas cylinder. The second gas cylinder is connected to the interstage separation push rod, and a second solenoid valve is provided between the second gas cylinder and the interstage separation push rod; The solenoid valve timing controller is used to control the switching of the first solenoid valve and the second solenoid valve; The pressure sensor is used to collect the air pressure on the interstage separation push rod and obtain the air pressure value on the interstage separation push rod in real time.

4. The method for determining the magnitude of mechanical and thermal environment according to claim 3, characterized in that, The method further includes: The pressure sensor on the interstage separation push rod collects the pressure and time data of the interstage separation push rod. When the pressure value of the interstage separation push rod reaches the preset pressure threshold, the second solenoid valve is controlled to open, and gas is replenished to the interstage separation push rod through the second gas cylinder.

5. The test method for determining the magnitude of interstage separation force and thermal environment according to claim 3, characterized in that, The launch vehicle stage separation test system also includes: The gas distribution platform is used to supply gas to the interstage separation push rod, the first gas cylinder, and the second gas cylinder; the blocking mechanism is connected to the second mass body and is used to block the second mass body pushed out by the interstage separation push rod.

6. The method for determining the magnitude of mechanical and thermal environment according to claim 5, characterized in that, The method further includes: The interstage separation push rod, the first gas cylinder, and the second gas cylinder are filled with gas through the gas distribution platform.

7. A test apparatus for determining the magnitude of interstage separation force and thermal environment, characterized in that, The device includes: The mechanical environment assessment unit is used to conduct vibration tests on the interstage separation push rod set on the vibration test bench using the interstage working conditions during rocket flight, and to verify whether the interstage separation push rod can meet the mechanical environment during rocket flight. The interstage separation push rod heating unit is used to continuously heat the interstage separation push rod to a first preset temperature and maintain it for a first preset time when the interstage separation push rod meets the mechanical environment during rocket flight. The first aerodynamic function test unit is used to conduct aerodynamic function tests through the launch vehicle interstage separation test system according to any one of claims 1-6, and to verify whether the interstage separation push rod meets the interstage separation standard at the first preset temperature through the aerodynamic function test. The interstage separation push rod cooling unit is used to continuously cool the interstage separation push rod to a second preset temperature and maintain it for a second preset time when the interstage separation push rod meets the interstage separation standard at the first preset temperature. The second aerodynamic function test unit conducts aerodynamic function tests using the launch vehicle interstage separation test system described in any one of claims 1-6, and verifies whether the interstage separation push rod meets the interstage separation standard at the second preset temperature through the aerodynamic function test.

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