Aerodynamic separation device with thrust real-time monitoring and buffering function

Abstract

The application provides a kind of pneumatic separation device with thrust real-time monitoring and buffering function, can measure the separation force of pneumatic separation device in the flight process of launch vehicle, especially at the moment of first and second stage separation, real-time monitoring of thrust data can comprehensively reflect the load change in the flight process of launch vehicle, so as to provide technical reference for reusable rocket. At the same time, aiming at the separation impact problem of launch vehicle interstage pneumatic separation, the exhaust damping hole impact reduction and physical impact reduction scheme are designed, so as to optimize the thrust load of pneumatic separation device in the working process, improve the reliability of product. In the physical impact reduction scheme, two ways of non-metallic rubber pad impact reduction and steel honeycomb impact reduction are proposed according to the thrust size, and the combination scheme of the above three schemes can also be used.

Description

Technical Field

[0001] This invention relates to a pneumatic separation device that can be used for interstage separation of launch vehicles, belonging to the field of interstage separation technology for launch vehicles. Background Technology

[0002] Traditional rocket stage separation includes two modes: hot separation and cold separation. Hot separation uses the second-stage engine ignition as the power source to separate the second stage from the first stage. Cold separation refers to the mode where the second-stage engine ignites again after the first and second stages have separated. In cold separation, the first and second stages are separated by the ignition of a solid-propellant retrorockets (propellants) mounted on the first stage.

[0003] With the development of aerospace technology, especially the demand for reusable launch vehicle technology, interstage aerodynamic separation schemes using gas as a power source have become a new development trend. As the most critical product in the interstage aerodynamic separation of launch vehicles, the aerodynamic separation device directly affects the success or failure of interstage separation and directly determines the success or failure of satellite launch missions.

[0004] The interstage aerodynamic separation technology solves the problems of pyrotechnics not being able to ignite and being single-use in traditional retro-rocket separation schemes, offering significant technological advantages. However, this technology is still in its early stages of development in China, and detailed research has not been conducted on the thrust variation during aerodynamic separation or the impact at the end of separation, making it a blind spot in aerodynamic separation technology. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose an aerodynamic separation device with real-time thrust monitoring and buffering functions. This solves the problems of thrust monitoring during the interstage aerodynamic separation of launch vehicles and separation impact at the end of interstage aerodynamic separation. The thrust data obtained through measurement can comprehensively reflect the load situation during the flight of the launch vehicle, thereby providing a technical reference for reusable rocket technology. By reducing separation impact, the product margin is improved and the separation reliability is increased.

[0006] The technical solution adopted in this invention is as follows: A pneumatic separation device with real-time thrust monitoring and buffering function includes: a cylinder assembly 1, a thrust assembly 2, a thrust measurement module 3, and a buffering module 4; A portion of the thrust assembly 2 is placed in the cylinder of the cylinder assembly 1, and the other portion of the thrust assembly 2 holds the second stage of the launch vehicle. By filling the air inlet of the cylinder assembly 1 with high-pressure gas, the thrust assembly 2 extends with high thrust, pushing the first stage of the launch vehicle away from the second stage, thus achieving separation. The cylinder assembly 1 uses an adjustable exhaust damping orifice to reduce the separation impact. The thrust is monitored in real time by the thrust measurement module 3. The buffer module 4 is set between the thrust assembly 2 and the inner wall of the cylinder assembly 1. The cylinder decelerates and reduces impact at the end of the cylinder's operation.

[0007] Furthermore, the thrust assembly 2 includes a head and a rod connected to the head, the rod being located in the cylinder of the cylinder assembly 1; The head includes a thrust structure 2-1 and a thrust outer sleeve structure 2-2; the thrust structure 2-1 is a hollow metal structure used to transmit thrust, and it is fixedly connected to the rod; the thrust outer sleeve structure 2-2 is made of a non-metallic material with elasticity, and is fitted onto the thrust structure 2-1 by the elastic force of the non-metallic material.

[0008] Furthermore, the inner surface of the thrust outer casing structure 2-2 has the same dimensions as the outer surface of the thrust structure 2-1.

[0009] Furthermore, the cylinder assembly 1 includes a cylinder 1-1, an exhaust damping hole plug 1-2, and a front end cover 1-3; The front end cover 1-3 is installed at the end of the cylinder 1-1. The space between the rod of the thrust assembly 2 and the inner wall of the cylinder 1-1 is the rod cavity. The front end cover 1-3 is provided with an exhaust damping hole, which is connected to the rod cavity. The exhaust damping hole is opened or closed through the exhaust damping hole plug 1-2. In the closed state, when the cylinder is actuated, the gas in the rod chamber is compressed, forming a large resistance to slow down the cylinder's actuation speed; in the open state, the gas in the rod chamber is discharged as the cylinder actuates, thus forming a certain resistance to achieve damped deceleration. Different deceleration effects can be achieved by designing the size or number of exhaust damping holes.

[0010] Furthermore, the number of exhaust damping holes is 1 to 3, with a diameter of 5 mm.

[0011] Furthermore, the thrust measurement module 3 includes a thin-film sensor 3-1 and a data transmission cable 3-2; The thin-film sensor 3-1 is nestled between the thrust structure 2-1 and the thrust outer sleeve structure 2-2. The thin-film sensor 3-1 adopts the shape-following design of the thrust structure 2-1, and at least four pieces are evenly arranged in the circumference to uniformly collect the circumferential thrust of the thrust structure 2-1. The data transmission cable 3-2 connects to the thin-film sensor 3-1.

[0012] Furthermore, the thrust measurement module 3 measures the magnitude and uniformity of the thrust of the aerodynamic separation device in real time during the thrust process, and realizes thrust detection during rocket flight. The thrust measurement module 3 has two usage modes. The first mode is to detect the thrust on the ground through a ground measurement system, which includes a data acquisition device 3-3 and a data processing device 3-4. The data acquisition device 3-3 is connected to the thin-film sensor 3-1 through a data transmission cable 3-2, and transmits the acquired thrust to the data processing device 3-4. The second mode is to connect the data transmission cable 3-2 to the launch vehicle measurement system during the launch vehicle flight phase to detect the thrust data of the launch vehicle during flight in real time.

[0013] Furthermore, during the flight phase of the launch vehicle, the data transmission cable 3-2 needs to be reserved with the length required for the cylinder assembly's actuation stroke, and is wound in the form of a reel. The reel is fixed to the front end of the cylinder and rotates along the cylinder to the rocket body, and then runs along the rocket body to the measurement system interface.

[0014] Furthermore, the buffer module 4 is made of non-metallic rubber or metal honeycomb.

[0015] Furthermore, cylinder assembly 1 is fixedly installed on the first stage of the launch vehicle. When the first and second stages separate, cylinder assembly 1 separates together with the first stage.

[0016] The beneficial effects of this invention compared to the prior art are as follows: (1) The present invention provides an aerodynamic separation device with real-time thrust monitoring and buffering function. By adding a thrust measurement module to the thrust assembly, the separation force of the aerodynamic separation device during the flight of the launch vehicle, especially at the first and second stage separation, can be measured in real time. This enables the detection of separation force during the flight of the rocket. Real-time monitoring of separation force data can comprehensively reflect the load changes during the flight of the launch vehicle, thereby providing technical reference for reusable rockets.

[0017] (2) This invention proposes two working modes for thrust detection: ground measurement and flight test measurement, so as to realize the separation force monitoring of the first and second stages of the launch vehicle under static and dynamic conditions.

[0018] (3) This invention considers impact reduction design from two aspects, proposing two schemes: impact reduction based on exhaust damping holes and physical impact reduction, thereby optimizing the thrust load of the pneumatic separation device during operation and improving product reliability. In the physical impact reduction scheme, two methods are proposed for impact reduction: non-metallic rubber pads and steel honeycomb, depending on the thrust magnitude. A combination of the above three schemes can also be used. This invention can implement different buffering methods or different combinations of buffering methods for different applications.

[0019] (4) During the separation process between launch stages, the separation force acting on the thrust assembly comprehensively reflects the influence of the launch vehicle's mass, center of mass position, and overall attitude. By monitoring the separation force between stages, in addition to ensuring the reliable separation of the first and second stages, it is of reference significance for studying the overall stability of the rocket. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in this invention patent or prior art, the drawings used in the description of the embodiments or prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention patent. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the pneumatic separation device of the present invention; Figure 2 This is a schematic diagram of the cylinder assembly structure; Figure 3 Diagrams showing the exhaust effect of different damping orifices; Figure 4 This is a schematic diagram of the thrust assembly structure; Figure 5 This is a schematic diagram of the mounting structure of a thin-film sensor on a thrust assembly. Figure 6 This is a schematic diagram of the overall structure of the separation device; Explanation of markings in the diagram: 1: Cylinder assembly; 1-1: Cylinder; 1-2: Exhaust damping hole plug; 1-3: Front end cover; 2: Thrust assembly; 2-1: Thrust structure; 2-2: Thrust jacket structure; 3: Thrust measurement module; 3-1: Thin-film sensor; 3-2: Data transmission cable; 3-3: Data acquisition equipment; 3-4: Data processing equipment; 4: Buffer module.

[0022] Specific implementation methods Interstage aerodynamic separation technology is a crucial component of reusable rockets. By replacing traditional pyrotechnic separation techniques, it solves undetectable and unmeasurable aerospace engineering problems and offers the advantage of low cost, meeting the needs of commercial spaceflight. Research on interstage aerodynamic separation technology in China is still in its early stages. Issues such as aerodynamic thrust variations and aerodynamic separation impacts have not yet been addressed. To ensure the reliability of interstage aerodynamic separation, this invention proposes an aerodynamic separation device with real-time thrust monitoring and buffering functions. This device provides guidance for studying aerodynamic thrust variations during the separation of the first and second stages of a launch vehicle and has practical engineering significance for reducing aerodynamic separation impacts and improving the reliability of first and second stage separation.

[0023] Specifically, such as Figure 1 and Figure 6 As shown, the present invention proposes a pneumatic separation device with real-time thrust monitoring and buffering functions, comprising: a cylinder assembly 1, a thrust assembly 2, a thrust measurement module 3, and a buffering module 4; A portion of the thrust assembly 2 (i.e., the rod) is placed in the cylinder of the cylinder assembly 1, and the other portion of the thrust assembly 2 (i.e., the head) presses against the second stage of the launch vehicle. By filling the air inlet of the cylinder assembly 1 with high-pressure gas, the thrust assembly 2 extends with high thrust, pushing the first stage of the launch vehicle away from the second stage, thus achieving separation. The cylinder assembly 1 uses adjustable exhaust damping to reduce the separation impact. The thrust is monitored in real time by the thrust measurement module 3. The buffer module 4 is set between the thrust assembly 2 and the inner wall of the cylinder assembly 1. The cylinder decelerates and reduces impact at the end of the cylinder's operation.

[0024] The cylinder assembly 1 is fixedly installed on the first stage of the launch vehicle. When the first and second stages separate, the cylinder assembly 1 separates together with the first stage.

[0025] This invention uses a thrust measurement module to measure the separation force of the aerodynamic separation device in real time during the flight of a launch vehicle, especially at the first and second stage separation. Real-time monitoring of thrust data can comprehensively reflect the load changes during the flight of the launch vehicle, thereby providing technical reference for reusable rockets.

[0026] like Figure 1 and Figure 2 As shown, the thrust assembly 2 includes a head and a rod connected to the head, the rod being located in the cylinder of the cylinder assembly 1; like Figure 4 As shown, the head includes a thrust structure 2-1 and a thrust outer sleeve structure 2-2; the thrust structure 2-1 is a hollow metal structure used to transmit thrust, and it is fixedly connected to the rod; the thrust outer sleeve structure 2-2 is made of a non-metallic material with elasticity, and is fitted onto the thrust structure 2-1 by the elastic force of the non-metallic material.

[0027] Furthermore, the inner surface of the thrust outer casing structure 2-2 has the same dimensions as the outer surface of the thrust structure 2-1.

[0028] The lower part of the cylinder also includes a rodless chamber, which is separated from the piston, rod, and rod chamber by the piston. When the cylinder is filled with air, the rodless chamber is filled with air, which in turn pushes the piston and the thrust assembly 2 to move upward and compress the gas in the rod chamber.

[0029] like Figure 2As shown, the cylinder assembly 1 includes a cylinder 1-1, an exhaust damping hole plug 1-2, and a front end cover 1-3; the front end cover 1-3 is installed at the end of the cylinder 1-1, and the space between the rod of the thrust assembly 2 and the inner wall of the cylinder 1-1 is the rod cavity; the front end cover 1-3 is provided with an exhaust damping hole, which communicates with the rod cavity, and the exhaust damping hole is opened or closed through the exhaust damping hole plug 1-2; In the closed state, when the cylinder is actuated, the gas in the rod chamber is compressed, forming a large resistance to slow down the cylinder's actuation speed; in the open state, the gas in the rod chamber is discharged as the cylinder actuates, thus forming a certain resistance to achieve damped deceleration. Different deceleration effects can be achieved by designing the size or number of exhaust damping holes.

[0030] Preferably, the number of exhaust damping holes is 1 to 3, and the diameter is 5 mm.

[0031] like Figure 5 As shown, the thrust measurement module 3 includes a thin-film sensor 3-1 and a data transmission cable 3-2; the thin-film sensor 3-1 is nestled between the thrust structure 2-1 and the thrust outer sleeve structure 2-2, and the thin-film sensor 3-1 adopts a contour-following design of the outer surface of the thrust structure 2-1, with no less than four sensors evenly arranged circumferentially to uniformly collect the circumferential thrust of the thrust structure 2-1; the data transmission cable 3-2 connects to the thin-film sensor 3-1.

[0032] The thrust measurement module 3 measures the magnitude and uniformity of thrust from the aerodynamic separation device in real time during the thrust process, and also detects thrust during rocket flight. The thrust measurement module 3 has two usage modes. The first mode is to detect thrust on the ground through a ground measurement system, which includes a data acquisition device 3-3 and a data processing device 3-4. The data acquisition device 3-3 is connected to the thin-film sensor 3-1 via a data transmission cable 3-2, and transmits the acquired thrust to the data processing device 3-4. The second mode is to connect the data transmission cable 3-2 to the launch vehicle measurement system during the launch vehicle flight phase to detect thrust data in real time during the launch vehicle flight.

[0033] During the flight phase of the launch vehicle, the data transmission cable 3-2 needs to be reserved with the length required for the cylinder assembly's actuation stroke, and is wound in the form of a reel. The reel is fixed to the front end of the cylinder and rotates along the cylinder to the rocket body, and then runs along the rocket body to the measurement system interface.

[0034] Preferably, the buffer module 4 is made of non-metallic rubber or metal honeycomb.

[0035] This invention addresses the separation impact problem during aerodynamic separation between stages of a launch vehicle by designing exhaust damping and physical impact reduction schemes. These schemes optimize the thrust load on the aerodynamic separation device during operation and improve product reliability. The physical impact reduction scheme proposes two methods for impact reduction based on thrust magnitude: non-metallic rubber pads and steel honeycomb pads. A combination of these three methods can also be used.

[0036] Example: Figure 1 This invention provides a schematic diagram of the layout of a pneumatic separation device with real-time thrust monitoring and buffering functions. The pneumatic separation device consists of a cylinder assembly 1, a thrust assembly 2, a thrust measurement module 3, and a buffering module 4. Its application scenario is an inter-stage pneumatic separation system for launch vehicles. The external interfaces of the pneumatic separation device include the launch vehicle to be separated (second stage) matched with the thrust assembly 2, and the launch vehicle support body (first stage) fixedly connected to the cylinder assembly 1. Figure 1 The thrust measurement module 3 shown is illustrated using a ground-based measurement method. This thrust measurement module can also be connected to the launch vehicle measurement system.

[0037] Figure 2 This is a schematic diagram of the cylinder assembly structure. In cylinder assembly 1, the exhaust damping hole plugs 1-2 can be installed or removed as needed to achieve different buffering and impact reduction requirements; the size or number of exhaust damping holes can be designed according to the size of the front cover and the buffering and impact reduction requirements. See the example effect below. Figure 3 .

[0038] Figure 4 This is a schematic diagram of the thrust assembly structure. The thrust assembly 2 consists of a thrust structure 2-1 and a thrust jacket structure 2-2. Its function is to transmit thrust and to mount the thin-film sensor 3-1.

[0039] Figure 5 This is a schematic diagram of the installation structure of the thin-film sensor on the thrust assembly. The thrust measurement module 3 consists of a thin-film sensor 3-1 and a data transmission cable 3-2. Its function is to detect the magnitude and uniformity of the thrust of the piston rod. The thin-film sensor 3-1 is installed between the thrust structure 2-1 and the thrust outer casing structure 2-2. Four or eight thin-film sensors can be evenly arranged on the thrust structure 2-1. Therefore, the installation sequence of the thin-film sensor 3-1 is before the combination of the thrust structure 2-1 and the thrust outer casing structure 2-2. After installation, the connector of the data transmission cable 3-2 can be left unconnected. When thrust measurement is required, the connector of the data transmission cable 3-2 can be connected to the data acquisition device 3-3.

[0040] During the operation of cylinder assembly 1, thrust measurement module 3 can measure the magnitude of thrust transmitted from piston rod (i.e. rod). Through the arrangement of 4 or 8 thin-film sensors, it can not only measure the magnitude of the resultant thrust, but also measure the uniformity of thrust of thrust assembly 1.

[0041] Figure 1 In the thrust measurement module 3, data acquisition device 3-3 and data processing device 3-4 are used as a ground measurement system. During rocket flight, the entire launch vehicle measurement system can also be used for data acquisition and processing. In this case, the data transmission cable connector 3-2 needs to be connected to the launch vehicle measurement system. Figure 6 As shown.

[0042] The parts of this invention not described in detail are common knowledge to those skilled in the art.

Claims

1. A pneumatic separation device with real-time thrust monitoring and buffering functions, characterized in that, include: Cylinder assembly (1), thrust assembly (2), thrust measurement module (3) and buffer module (4); A portion of the thrust assembly (2) is placed in the cylinder of the cylinder assembly (1), and the other portion of the thrust assembly (2) holds the second stage of the launch vehicle. By filling the air inlet of the cylinder assembly (1) with high-pressure gas, the thrust assembly (2) extends with high thrust, pushing the first stage of the launch vehicle away from the second stage, thus achieving separation. The cylinder assembly (1) uses an adjustable exhaust damping hole to reduce the separation impact. The thrust is monitored in real time by the thrust measurement module (3). The buffer module (4) is set between the thrust assembly (2) and the cylinder wall of the cylinder assembly (1). The cylinder decelerates and reduces impact at the end of the cylinder operation by the buffer module (4).

2. The pneumatic separation device with real-time thrust monitoring and buffering function according to claim 1, characterized in that: The thrust assembly (2) includes a head and a rod connected to the head, the rod being located in the cylinder of the cylinder assembly (1); The head includes a thrust structure (2-1) and a thrust jacket structure (2-2); the thrust structure (2-1) is a hollow metal structure used to transmit thrust, and it is fixedly connected to the rod; the thrust jacket structure (2-2) is made of a non-metallic material with elasticity, and is fitted onto the thrust structure (2-1) by the elastic force of the non-metallic material.

3. The pneumatic separation device with real-time thrust monitoring and buffering function according to claim 2, characterized in that: The inner surface of the thrust jacket structure (2-2) has the same dimensions as the outer surface of the thrust structure (2-1).

4. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 2 or 3, characterized in that: The cylinder assembly (1) includes a cylinder (1-1), an exhaust damping hole plug (1-2), and a front end cover (1-3). The front cover (1-3) is installed at the end of the cylinder (1-1). The space between the rod of the thrust assembly (2) and the inner wall of the cylinder (1-1) is the rod cavity. The front cover (1-3) is provided with an exhaust damping hole, which is connected to the rod cavity. The exhaust damping hole is opened or closed through the exhaust damping hole plug (1-2). In the closed state, when the cylinder is actuated, the gas in the rod chamber is compressed, forming a large resistance to slow down the cylinder's actuation speed; in the open state, the gas in the rod chamber is discharged as the cylinder actuates, thus forming a certain resistance to achieve damped deceleration. Different deceleration effects can be achieved by designing the size or number of exhaust damping holes.

5. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 4, characterized in that: The number of exhaust damping holes is 1 to 3, with a diameter of 5 mm.

6. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 4, characterized in that: The thrust measurement module (3) includes a thin-film sensor (3-1) and a data transmission cable (3-2). The thin-film sensor (3-1) is nestled between the thrust structure (2-1) and the thrust outer sleeve structure (2-2). The thin-film sensor (3-1) adopts the shape-following design of the thrust structure (2-1) and is evenly arranged with no less than four pieces to uniformly collect the circumferential thrust of the thrust structure (2-1). The data transmission cable (3-2) connects to the thin-film sensor (3-1).

7. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 6, characterized in that: The thrust measurement module (3) measures the magnitude and uniformity of the thrust of the aerodynamic separation device in real time during the thrust process, and realizes thrust detection during rocket flight. The thrust measurement module (3) has two usage modes. The first mode is to detect the thrust on the ground through a ground measurement system. The ground measurement system includes a data acquisition device (3-3) and a data processing device (3-4). The data acquisition device (3-3) is connected to the thin-film sensor (3-1) through a data transmission cable (3-2) to transmit the collected thrust to the data processing device (3-4). The second mode is to connect the data transmission cable (3-2) to the launch vehicle measurement system during the launch vehicle flight phase to detect the thrust data during the launch vehicle flight process in real time.

8. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 7, characterized in that: During the flight phase of the launch vehicle, the data transmission cable (3-2) needs to be reserved with the length required for the cylinder assembly to actuate. It is wound in the form of a spool, which is fixed to the front end of the cylinder and rotates along the cylinder to the rocket body. Then it is wired along the rocket body to the measurement system interface.

9. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 7, characterized in that: The buffer module (4) is made of non-metallic rubber or metal honeycomb.

10. A pneumatic separation device with real-time thrust monitoring and buffering function according to claim 1, characterized in that: The cylinder assembly (1) is fixedly installed on the first stage of the launch vehicle. When the first and second stages separate, the cylinder assembly (1) separates together with the first stage.

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