Aerodynamic separation system for launch vehicle and launch vehicle

Abstract

The present application provides a pneumatic separation system for a launch vehicle and a launch vehicle, the pneumatic separation system comprising: at least one gas cylinder, a gas source output switch and at least one gas cylinder; the gas cylinder is connected to the gas cylinder through a gas charging pipeline, the gas source output switch is arranged on the gas charging pipeline to control the on-off of the gas charging pipeline; the gas cylinder is used to be filled with compressed gas with a preset pressure, and when the gas source output switch is turned on, the compressed gas pushes the to-be-separated structures of the launch vehicle to separate from each other through the pneumatic push rod in the gas cylinder after passing through the gas charging pipeline. When the present application is used in interstage separation, it can avoid the use of solid small rocket ignition to flush the plume of the separated substage body, which is conducive to the recovery and reuse of the separated substage body; it can directly perform performance testing, thereby avoiding the cost of increased production and ground ignition testing for the performance of pyrotechnics in flight tests; the principle is reliable, and it can provide energy for interstage separation, fairing separation and payload separation.

Description

Technical Field

[0001] The present application belongs to the field of launch vehicle technology, and specifically relates to an aerodynamic separation system for a launch vehicle and a launch vehicle. Background Art

[0002] With the continuous advancement of science and technology, launch vehicles as carriers are moving from the one-time use stage to the multiple reuse stage. In order to achieve multiple reuse of launch vehicles, it is necessary to recover the separated sub-stage bodies of launch vehicles.

[0003] For launch vehicles with reusable sub-stages, the adverse effects on the structure and attitude of the launch vehicle's sub-stages should be minimized during the entire flight mission while ensuring the safety and reliability of the launch vehicle's flight. In order to avoid the thermal impact of interstage separation on the sub-stages, the interstage separation of launch vehicles with reusable sub-stages adopts cold separation. At present, the impulse device used for cold separation of domestic launch vehicles is generally a small solid rocket.

[0004] The small solid rocket is fixed to the separation sub-stage body. During the separation process, the reverse thrust generated by the ignition of the small solid rocket causes the separation sub-stage body to separate from the upper stage body. Small solid rockets are pyrotechnics, and their energy is concentrated. During the separation process, the heat flow of the small solid rocket will seriously wash away the separation sub-stage body, which will seriously affect the reuse of the separation sub-stage body after recovery. In addition, although small solid rockets are widely used in domestic launch vehicles at this stage, they have the disadvantage that their performance cannot be directly tested. The performance of the products on the rocket can only be verified by increasing the production quantity of pyrotechnics in the same batch and then extracting a sufficient number of products for ground ignition tests. This type of consumable test is not only costly, but also still cannot directly test the performance of the upper rocket products. Moreover, pyrotechnics are all produced by professional manufacturers, and it is very difficult to reduce costs. Summary of the invention

[0005] In order to overcome the problems existing in the related art at least to a certain extent, the present application provides an aerodynamic separation system for a launch vehicle and a launch vehicle.

[0006] According to a first aspect of an embodiment of the present application, the present application provides an aerodynamic separation system for a launch vehicle, comprising:

[0007] At least one gas cylinder,

[0008] Gas source output switch,

[0009] at least one cylinder;

[0010] The gas cylinder is connected to the gas cylinder via a gas charging pipeline, and the gas source output switch is arranged on the gas charging pipeline to control the on and off of the gas charging pipeline;

[0011] The gas cylinder is used to be filled with compressed gas with a preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder pushes the to-be-separated structures of the launch vehicle to separate from each other through the pneumatic push rod in the cylinder after passing through the filling pipeline.

[0012] In the above-mentioned pneumatic separation system for a launch vehicle, a force transmission device is provided on the structure to be separated of the launch vehicle, and the pneumatic push rod in the cylinder pushes the force transmission device to separate the structures to be separated of the launch vehicle from each other.

[0013] In the above-mentioned pneumatic separation system for launch vehicles, the air source output switch adopts an electrically controlled switch, which is connected to an external control device through a control signal line.

[0014] In the above-mentioned pneumatic separation system for launch vehicles, a gas cylinder pressure detection gauge is also provided on the inflation pipeline connecting the gas cylinder and the gas source output switch, and the gas cylinder pressure detection gauge is used to detect the pressure of the compressed gas output by the gas cylinder.

[0015] The above-mentioned pneumatic separation system for a launch vehicle is provided with a charging and discharging port at one end of the charging pipeline connected to the gas cylinder, and a mechanical charging switch is provided on the charging and discharging port and the charging pipeline connected to the gas cylinder.

[0016] Furthermore, an interface is provided on the inflation pipeline connected to the mechanical inflation switch and the gas cylinder, and the gas cylinder is connected to the rocket body pressurization delivery system through the interface.

[0017] In the above-mentioned pneumatic separation system for launch vehicles, a first pressure detection gauge is provided at one end of the cylinder, and a second pressure detection gauge is provided at the other end; the first pressure detection gauge is used to detect the pressure of the cylinder inflation chamber, and the second pressure detection gauge is used to detect the pressure of the cylinder exhaust chamber.

[0018] The above-mentioned aerodynamic separation system for a launch vehicle is used in interstage separation, fairing separation or payload separation of a launch vehicle.

[0019] The above-mentioned pneumatic separation system for a launch vehicle provides energy for the interstage separation when used in the interstage separation of the launch vehicle; the gas cylinder is installed on the front bottom of the separation sub-stage rocket body or on the interstage section.

[0020] In the above-mentioned aerodynamic separation system for a launch vehicle, when there is only one interstage structure of a main nozzle configuration in the upper stage body, the cylinder is provided as one or more than two;

[0021] When there is one cylinder, the cylinder is arranged at the main nozzle of the engine in the upper stage body, the force transmission device adopts the main nozzle of the engine in the upper stage body, and the pneumatic push rod in the cylinder applies thrust to the main nozzle of the engine in the upper stage body, so that the upper stage body is separated from the separation sub-stage body;

[0022] When there are more than two cylinders, the more than two cylinders are used to be evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell; the force transmission device adopts a force transmission support, which is fixedly connected to the upper stage rocket body and close to the interstage separation surface; the pneumatic push rod in the cylinder applies thrust to the force transmission support, so that the upper stage rocket body is separated from the separation sub-stage rocket body.

[0023] Furthermore, when there are multiple interstage structures with main nozzle configurations in the upper stage body, the cylinders are provided in more than two, and the more than two cylinders are evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell; the force transmission device is fixedly connected to the upper stage body and is close to the interstage separation surface; the pneumatic push rod in the cylinder applies thrust to the force transmission device, so that the upper stage body is separated from the separation sub-stage body.

[0024] Furthermore, when the pneumatic separation system is used in the separation of the fairing, it provides energy for the separation of the fairing; the force transmission device adopts a force transmission support;

[0025] When the fairing is separated from the rocket body by an integrally pulled-out method, the pneumatic separation system is installed on the fairing, and the force transmission support is installed on the front end of the final stage rocket body of the launch vehicle; more than two cylinders are arranged on the lateral separation surface of the fairing; after the fairing separation surface is unlocked, the fairing is separated from the rocket body under the action of the pneumatic push rod;

[0026] When the fairing is separated from the rocket body by means of two half-fairings being split and thrown horizontally, a set of the pneumatic separation system is installed on each half-fairing, the installation axis of the cylinder is perpendicular to the longitudinal separation surface of the fairing, the pneumatic push rod points to the other half-fairing, and the force transmission support is arranged on the other half-fairing; after the fairing separation surface is unlocked, the two half-fairings move horizontally in a direction perpendicular to the fairing separation surface under the action of the pneumatic push rod, and finally separate from the rocket body;

[0027] When the fairing is separated from the rocket body by a two-half-fairing split-petal spinning and throwing method, a set of the pneumatic separation system is installed on each half-fairing, the installation axis of the cylinder is perpendicular to the lateral separation surface of the fairing, the pneumatic push rod points to the front end of the final-stage rocket body, and the force transmission support is arranged on the front end of the final-stage rocket body; after the fairing separation surface is unlocked, the two half-fairings rotate along their rotation axes with each other under the action of the pneumatic push rods, and finally separate from the rocket body.

[0028] Further, when the pneumatic separation system is used in payload separation, it provides energy for payload separation;

[0029] The pneumatic separation system is installed at the front end of the final stage body of the carrier rocket, and more than two cylinders are arranged on the separation surface of the payload; after the separation surface of the payload is unlocked, the payload is separated from the final stage body under the action of the pneumatic push rod.

[0030] According to a second aspect of an embodiment of the present application, the present application provides a launch vehicle, comprising the aerodynamic separation system described in any one of the above items, wherein the aerodynamic separation system is used for inter-stage separation and / or fairing separation and / or payload separation of the launch vehicle.

[0031] According to the above-mentioned specific implementation methods of the present application, it can be known that it has at least the following beneficial effects: the present application is used for the pneumatic separation system of a launch vehicle, by setting a gas cylinder, a gas source output switch and a gas cylinder, compressed gas is filled in the gas cylinder, the gas source output switch is turned on, and the gas cylinder generates thrust through the pneumatic push rod in the cylinder, which is the separation energy of the launch vehicle. The present application is used in the inter-stage separation process, which can avoid the plume scouring of the separation sub-stage rocket body by the ignition of a solid small rocket, and is conducive to the reuse of the separation sub-stage rocket body.

[0032] The pneumatic separation system used in the launch vehicle of the present application can avoid the disadvantage that the performance of pyrotechnic products cannot be directly tested, and can directly perform performance testing, thereby avoiding the cost of increased product production and ground ignition testing for conducting circumstantial testing of flight test product performance.

[0033] The pneumatic separation system for launch vehicles in this application has reliable principle, simple structure, good versatility, and can also be applied to the separation of launch vehicle fairings and payloads, which can play a positive role in the recovery and reuse of launch vehicles and the cost control of launch vehicles.

[0034] It should be understood that the above general description and the following specific embodiments are only exemplary and illustrative and do not limit the scope of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The attached drawings below are part of the specification of the present application, which illustrate embodiments of the present application. The attached drawings together with the description of the specification are used to explain the principles of the present application.

[0036] Figure 1 A structural schematic diagram of an aerodynamic separation system for a launch vehicle provided in an embodiment of the present application.

[0037] Figure 2 A schematic structural diagram of a pneumatic separation system for a launch vehicle in a single-cylinder state, showing a gas cylinder and a pneumatic push rod in an interstage separation structure.

[0038] Figure 3 A schematic structural diagram of a pneumatic separation system for a launch vehicle provided in an embodiment of the present application, in which a gas cylinder is installed on the front bottom of a separation sub-stage body in a single-cylinder state, wherein the flight direction of the launch vehicle is perpendicular to the paper plane.

[0039] Figure 4 A schematic structural diagram of a pneumatic separation system for a launch vehicle provided in an embodiment of the present application, in which a gas cylinder is installed on an interstage section in a single-cylinder state, wherein the flight direction of the launch vehicle is perpendicular to the paper plane.

[0040] Figure 5 One of the structural schematic diagrams of a pneumatic separation system for a launch vehicle provided in an embodiment of the present application, in which a gas cylinder and a pneumatic push rod are installed in an interstage structure in a multi-cylinder state, wherein the pneumatic push rod acts on a rocket body support.

[0041] Figure 6 The second structural schematic diagram of a pneumatic separation system for a launch vehicle provided in an embodiment of the present application, in which the gas cylinders and pneumatic push rods are installed in the interstage structure in a multi-cylinder state, wherein the pneumatic push rods act on the rocket body support.

[0042] Figure 7 A schematic diagram of the structural distribution of an aerodynamic separation system for a launch vehicle provided in an embodiment of the present application when applied to the horizontal separation of the fairing.

[0043] Figure 8 for Figure 7 One of the top views of the middle structure.

[0044] Fig. 9 for Figure 7 The second top view of the middle structure.

[0045] Fig.10 A schematic diagram of the state of the fairing being separated by horizontal throwing under the action of the pneumatic push rod in the cylinder provided in an embodiment of the present application.

[0046] Fig.11A schematic diagram of the structural distribution of an aerodynamic separation system for a launch vehicle provided in an embodiment of the present application when applied to the spin-and-throw separation of a fairing.

[0047] Fig.12 for Fig.11 Top view of part of the structure.

[0048] Fig.13 A schematic diagram of the state of the fairing being spun and separated under the action of the pneumatic push rod in the cylinder provided in an embodiment of the present application.

[0049] Description of reference numerals:

[0050] 1. Gas cylinder; 2. Gas source output switch; 3. Gas cylinder; 31. Cylinder push rod; 4. Inflation pipeline; 5. Nozzle front end pipeline; 6. Gas cylinder pressure test gauge; 7. Filling and discharging port; 8. Mechanical inflation switch; 9. Interface; 10. First pressure test gauge; 11. Second pressure test gauge; 12. Force transmission device; 13. Fixed bracket. DETAILED DESCRIPTION

[0051] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clearly understood, the spirit of the contents disclosed in the present application will be clearly explained with the accompanying drawings and detailed descriptions below. After understanding the embodiments of the contents of the present application, any technician in the relevant technical field can change and modify them according to the techniques taught by the contents of the present application without departing from the spirit and scope of the contents of the present application.

[0052] The exemplary embodiments and descriptions of the present application are used to explain the present application, but are not intended to limit the present application. In addition, elements / components with the same or similar reference numerals used in the drawings and embodiments are used to represent the same or similar parts.

[0053] The terms “first”, “second”, etc. used in this document do not particularly refer to an order or sequence, nor are they used to limit this application. They are only used to distinguish elements or operations described with the same technical terms.

[0054] The directional terms used in this document, such as up, down, left, right, front or back, etc., are only used to refer to the directions of the drawings. Therefore, the directional terms used are used to illustrate and not to limit the present invention.

[0055] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0056] As used herein, "and / or" includes any or all combinations of the items described.

[0057] As used herein, “plurality” includes “two” and “more than two”; as used herein, “plurality groups” includes “two groups” and “more than two groups”.

[0058] The terms "substantially" and "approximately" used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors do not change their essence. Generally speaking, the range of slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. Those skilled in the art should understand that the aforementioned values ​​can be adjusted according to actual needs and are not limited thereto.

[0059] Certain terms used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art regarding the description of the present application.

[0060] The pneumatic separation system for a launch vehicle of the present application comprises at least one gas bottle, a gas source output switch and at least one gas cylinder. The gas bottle is connected to the gas cylinder through a gas charging pipeline. The gas source output switch is arranged on the gas charging pipeline to control the on-off of the gas charging pipeline.

[0061] The gas cylinder is used to be filled with compressed gas with a preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder pushes the structures to be separated of the launch vehicle to be separated from each other after passing through the filling pipeline and the pneumatic push rod in the cylinder.

[0062] Specifically, a force transmission device is provided on the to-be-separated structure of the launch vehicle, and the force transmission device can be a force transmission support or a main nozzle of the engine that functions as the force transmission support.

[0063] When the pneumatic separation system is used in the interstage separation of a launch vehicle, a force transmission device is provided on the upper stage of the launch vehicle. The compressed gas stored in the gas cylinder enters the inflation chamber in the cylinder after passing through the inflation pipeline, pushing the pneumatic push rod in the cylinder to move, and the pneumatic push rod acts on the force transmission device. After the interstage connection is unlocked, the pneumatic push rod in the cylinder pushes the separation sub-stage body fixedly connected to the force transmission device to move, so that the upper stage body is separated from the separation sub-stage body; when the pneumatic push rod reaches its stroke and stops moving, a relative speed is generated between the upper stage body and the separation sub-stage body. The upper stage body and the separation sub-stage body continue to move until the interstage separation is completed, the force transmission device is launched with the upper stage body, and the pneumatic separation system returns to the ground with the separation sub-stage body.

[0064] During the launch preparation phase of the launch vehicle, compressed gas is filled into the gas cylinder to make the pressure in the gas cylinder reach a preset pressure. The compressed gas may be one or more of compressed air, nitrogen, helium and hydrogen.

[0065] During the flight of the launch vehicle, the gas source output switch is controlled to open, the air chamber of the cylinder is pressurized, and the pneumatic push rod pushes the force transmission device on the upper stage body to separate the upper stage body from the separation sub-stage body.

[0066] The pneumatic separation system for launch vehicles in the present application can replace pyrotechnics to provide separation energy for launch vehicles. During the separation process of the upper stage body and the separation sub-stage body in the launch vehicle, no damage to the separation sub-stage body such as ignition of pyrotechnics and thermal flow scouring will occur, and the separation impact is small, which is conducive to the recovery and reuse of the separation sub-stage body.

[0067] The working safety of the aerodynamic separation system used in the launch vehicle in the present application has the advantage of being directly tested, thus avoiding the inherent defect that the performance of pyrotechnics cannot be directly tested. It also avoids the need for consumable verification tests such as increasing the production quantity of the same batch of products and conducting large-scale random ignition inspections to verify the reliability of flight products, thereby effectively reducing costs.

[0068] The aerodynamic separation system for launch vehicles in this application has strong versatility and can provide energy for the lateral separation of the booster and the separation of the fairing (either horizontal or rotational throwing) by appropriately adjusting the structure.

[0069] The principle of the aerodynamic separation system used in the launch vehicle in the present application is reliable, the performance of each component is detectable, and the product cost is low, which is conducive to the recovery and reuse of the rocket body and helps to reduce costs.

[0070] The aerodynamic separation system of the present application for a launch vehicle is described in detail below in conjunction with specific embodiments.

[0071] Embodiment 1

[0072] like Figure 1 As shown, the pneumatic separation system for a launch vehicle provided in this embodiment includes at least one gas bottle 1, a gas source output switch 2 and at least one gas cylinder 3. Each gas bottle 1 is connected to a gas charging pipeline 4, and the gas bottle 1 is connected to one end of the gas source output switch 2 through the gas charging pipeline 4. The other end of the gas source output switch 2 is connected to each gas cylinder 3 through a nozzle front end pipeline 5. The pneumatic push rod 31 in the gas cylinder 3 is used in conjunction with the force transmission device 12.

[0073] Specifically, the gas source output switch 2 is an electrically controlled switch, which is connected to an external control device through a control signal line. During the flight of the launch vehicle, when it is necessary to provide a pneumatic separation impulse for the rocket body, the external control device sends a control signal to the gas source output switch 2 to control the opening of the gas source output switch 2 to pressurize the inflation chamber of the cylinder 3.

[0074] In this embodiment, a gas cylinder pressure detection meter 6 is also provided on the gas filling pipeline 4 connecting the gas cylinder 1 and the gas source output switch 2, and the gas cylinder pressure detection meter 6 is used to detect the pressure of the compressed gas output by the gas cylinder 1. The pressure detected by the gas cylinder pressure detection meter 6 can quantitatively analyze whether the system is normal. It is understandable that the gas cylinder pressure detection meter 6 can be connected to the gas cylinder pressure monitoring device through a cable.

[0075] In this embodiment, one end of the gas charging pipeline 4 connected to the gas cylinder 1 is provided with a charging and discharging port 7. A mechanical charging switch 8 is provided on the gas charging pipeline 4 connected to the gas charging and discharging port 7 and the gas cylinder 1. In the launch vehicle takeoff preparation stage, the mechanical charging switch 8 can be turned on to charge the gas cylinder 1 with compressed gas through the charging and discharging port 7.

[0076] In addition, an interface 9 can be provided on the gas charging pipeline 4 connecting the mechanical gas charging switch 8 and the gas cylinder 1, and the gas cylinder 1 is connected to the rocket body pressurization and delivery system through the interface 9, so that the gas source of the pneumatic separation system used in the launch vehicle and the rocket body pressurization and delivery system can be shared. When the gas cylinder 1 is connected to the rocket body pressurization and delivery system, in order to ensure the normal operation of the rocket body pressurization and delivery system, the type of compressed gas required to be filled in the gas cylinder 1 can be determined according to the gas type required by the rocket body pressurization and delivery system.

[0077] In this embodiment, a first pressure detection gauge 10 is provided at one end of the cylinder 3, and a second pressure detection gauge 11 is provided at the other end thereof. The first pressure detection gauge 10 is used to detect the pressure of the inflation chamber of the cylinder 3, and the second pressure detection gauge 11 is used to detect the pressure of the exhaust chamber of the cylinder 3. By providing the first pressure detection gauge 10 and the second pressure detection gauge 11, the pressure changes of the inflation chamber and the exhaust chamber of the cylinder 3 can be measured, so as to detect whether the working state of the cylinder 3 is normal. It can be understood that the first pressure detection gauge 10 and the second pressure detection gauge 11 can be connected to the pressure monitoring device of the cylinder 3 through a cable.

[0078] It can be understood that the size of the separation force can be determined based on the initial state before separation and the requirements of the separation process, thereby determining the cylinder diameter, charging pressure and other requirements of the cylinder 3, and then calculating the amount of gas used, determining the required volume of the gas cylinder 1 and the initial charging pressure of the gas cylinder 1.

[0079] The gas cylinder 1 and the charging pipeline 4 are connected by threads, and a seal is arranged at the connection to make it airtight. The gas cylinder 3 and the front end pipeline 5 of the nozzle are connected by threads or welding, and a seal is arranged at the connection when the thread connection is used to make it airtight.

[0080] During the final assembly and testing process of the pneumatic separation system for a launch vehicle in the present application, the gas cylinder 1 can be inflated before the separation surfaces are connected, the gas source output switch 2 can be turned on, and the cylinder 3 can be checked to see whether it is working normally. The pressure detected by the gas cylinder pressure detection gauge 6 can also be used to quantitatively analyze whether the system is working normally. In actual flight conditions, it can also be determined whether the system is working normally by analyzing the telemetered pressure signal.

[0081] The pneumatic separation system for the launch vehicle in the present application is equipped with a gas cylinder pressure detection gauge 6, a first pressure detection gauge 10 and a second pressure detection gauge 11. During the final assembly test or the actual flight of the launch vehicle, it can assist in quantitatively analyzing whether the pneumatic separation system for the launch vehicle is operating normally, thereby completely avoiding the inherent defect of pyrotechnics that cannot be directly tested for performance, and further avoiding the need for consumable verification tests such as increasing the production quantity of the same batch of products and conducting large-scale random ignition inspections to verify the reliability of flight products, thereby significantly reducing costs.

[0082] Embodiment 2

[0083] like Figures 2 to 6 As shown, the pneumatic separation system for a launch vehicle of the present application provides energy for the interstage separation when used in the interstage separation of the launch vehicle. The gas cylinder 1 is installed on the front bottom of the separation sub-stage body or on the interstage section.

[0084] For the interstage structure with only one main nozzle configuration in the upper stage body, more than two cylinders 3, i.e., a multi-cylinder state, can be used. More than two cylinders 3 are evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell. The force transmission device 12 is fixedly connected to the upper stage body and close to the interstage separation surface. The pneumatic push rod 31 in the cylinder 3 applies thrust to the force transmission device 12 to achieve the separation between the upper stage body and the separation sub-stage body. Among them, the force transmission device 12 is specifically a force transmission support, which is fixedly connected to the upper stage body and close to the interstage separation surface.

[0085] Of course, if Figure 2 As shown, for the interstage structure with only one main nozzle configuration in the upper stage body, one cylinder 3, i.e., a single cylinder state, can also be used. The cylinder 3 is arranged at the main nozzle of the engine in the upper stage body, and the pneumatic push rod 31 in the cylinder 3 applies thrust to the force transmission device 12 to achieve the separation between the upper stage body and the separation sub-stage body. Among them, the force transmission device 12 specifically adopts the main nozzle of the engine in the upper stage body, and the role of the main nozzle of the engine is equivalent to that of the force transmission support.

[0086] like Figure 3As shown, when the gas cylinder 1 is installed on the front bottom of the separation sub-stage body, the cylinder 3 is fixed by a fixing bracket 13 of a regular triangular pyramid structure. In this embodiment, the pneumatic separation system for the launch vehicle includes six gas cylinders 1, each of which is a group of two gas cylinders 1, divided into three groups. Two adjacent groups of gas cylinders 1 are used to be evenly arranged at intervals of 120° around the axis of the flight direction of the launch vehicle.

[0087] like Figure 4 As shown, when the gas cylinder 1 is installed on the interstage, the gas cylinder 3 is fixed by a fixing bracket 13 of a regular tetrahedral structure. In this embodiment, the pneumatic separation system for the launch vehicle includes eight gas cylinders 1, each of which is a group of two gas cylinders 1, divided into four groups. Each group of gas cylinders 1 is used to be evenly arranged at 90° intervals around the axis of the launch vehicle's flight direction.

[0088] like Figure 5 As shown, for the interstage structure with multiple main nozzle configurations in the upper stage body, more than two cylinders 3, i.e., a multi-cylinder state, can be used, and more than two cylinders 3 can be evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell. The force transmission device 12 is fixedly connected to the upper stage body and close to the interstage separation surface. The pneumatic push rod 31 in the cylinder 3 applies thrust to the force transmission device 12 to achieve the separation between the upper stage body and the separation sub-stage body. Among them, the force transmission device 12 specifically adopts a force transmission support, which is fixedly connected to the upper stage body and close to the interstage separation surface.

[0089] like Figure 6 As shown, the pneumatic separation system for the launch vehicle includes eight gas bottles 1 and four gas cylinders 3, and each group of two gas bottles 1 is divided into four groups. Two adjacent groups of gas bottles 1 are used to be evenly arranged at intervals of 90° around the axis of the launch vehicle's flight direction. The four gas cylinders 3 are all arranged on the interstage, and each cylinder 3 is used to be evenly arranged at intervals of 90° around the axis of the launch vehicle's flight direction, and a group of gas bottles 1 is arranged between two adjacent cylinders 3.

[0090] During the launch vehicle takeoff preparation stage, the gas cylinder 1 is filled with compressed gas to a required pressure through the gas filling and discharging port 7. The compressed gas may be one or more of compressed air, nitrogen, helium and the like.

[0091] When the launch vehicle performs interstage separation, the gas source output switch 2 is turned on, the air chamber of the cylinder 3 is pressurized, and the pneumatic push rod 31 pushes the force transmission device 12 on the upper stage body to separate the upper stage body from the separation sub-stage body. When the pneumatic push rod 31 reaches its stroke and stops moving, there is a relative speed between the upper stage body and the separation sub-stage body. The upper stage body and the separation sub-stage body continue to move until the interstage separation is completed, the force transmission device 12 is launched with the upper stage body, and the pneumatic separation system returns to the ground with the separation sub-stage body.

[0092] The aerodynamic separation system of the launch vehicle in the present application is used as the separation energy source of the launch vehicle. During the inter-stage separation process, it can avoid the plume scouring of the separation sub-stage rocket body by the ignition of the small solid rocket, which is conducive to the reuse of the separation sub-stage rocket body.

[0093] The aerodynamic separation system used in the launch vehicle of the present application itself has the effect of direct performance detection, which can avoid the disadvantage that the performance of pyrotechnics cannot be directly detected, thereby avoiding the cost of increased product production and ground ignition testing for conducting circumstantial testing of flight test product performance.

[0094] The pneumatic separation system for launch vehicles in this application has reliable principle, simple structure, good versatility, and can also be applied to the separation of launch vehicle fairings and payloads, which can play a positive role in the recovery and reuse of launch vehicles and the cost control of launch vehicles.

[0095] Embodiment 3

[0096] The pneumatic separation system for launch vehicles of the present application provides energy for the separation of the fairing when used in the separation of the fairing. Among them, the force transmission device 12 adopts a force transmission support.

[0097] When the fairing is separated from the body of the rocket by pulling out the fairing as a whole, the pneumatic separation system is installed on the fairing, and the force transmission support is installed on the front end of the final stage of the rocket. Two or more cylinders 3 are arranged on the lateral separation surface of the fairing. After receiving the separation signal and unlocking the separation surface of the fairing, the fairing is separated from the body of the rocket under the action of the pneumatic push rod 31, and its working principle is similar to the interstage separation process in the multi-cylinder 3 state. However, in order to ensure that the separated fairing does not collide with the body of the rocket, a side thrust rocket with delayed ignition needs to be installed on the fairing to push the fairing debris away from the trajectory of the rocket body.

[0098] like Figures 7-10 As shown, when the fairing is separated from the rocket body by means of two half-fairings split and thrown horizontally, a pneumatic separation system needs to be installed on each half-fairing, the installation axis of the cylinder 3 is perpendicular to the longitudinal separation surface of the fairing, the pneumatic push rod 31 points to the other half-fairing, and the force transmission support is arranged on the other half-fairing. After receiving the separation signal and unlocking the fairing separation surface, the two half-fairings move horizontally in a direction perpendicular to the fairing separation surface under the action of the pneumatic push rod 31, and finally separate from the rocket body.

[0099] like Figures 11 to 13As shown, when the fairing is separated from the arrow body by two half-fairings splitting and spinning, a pneumatic separation system needs to be installed on each half-fairing, the installation axis of the cylinder 3 is perpendicular to the horizontal separation surface of the fairing, the pneumatic push rod 31 points to the front end of the final arrow body, and the force transmission support is set on the front end of the final arrow body. After receiving the separation signal and unlocking the fairing separation surface, the two half-fairings rotate along their respective rotation axes under the action of the pneumatic push rod 31, and finally separate from the arrow body after unhooking.

[0100] Embodiment 4

[0101] The aerodynamic separation system of the present application for a launch vehicle provides energy for the separation of the payload when used in the separation of the payload.

[0102] The pneumatic separation system is installed at the front end of the final stage of the launch vehicle. Two or more cylinders 3 are set on the separation surface of the payload. After receiving the separation signal and unlocking the payload separation surface, the payload is separated from the final stage of the rocket under the action of the pneumatic push rod 31. Its working principle is similar to Figure 5 and 6 The interstage separation process for the multi-cylinder 3 state shown is similar.

[0103] In addition, the pneumatic separation system for the launch vehicle of the present application can also provide energy for the lateral separation of the booster by appropriate modification. In this working condition, the pneumatic separation system is installed on the booster, and the cylinder 3 is placed inside the binding connecting rod and its axis direction is perpendicular to the axis of the rocket body, and is pointed from the booster to the core stage rocket body. After receiving the separation signal, the booster is separated from the rocket body under the action of the pneumatic push rod 31.

[0104] Embodiment 5

[0105] The present application also provides a launch vehicle, which includes any of the above-mentioned aerodynamic separation systems for launch vehicles, and the aerodynamic separation system is used for inter-stage separation, fairing separation or payload separation of the launch vehicle.

[0106] The above description is only an illustrative specific implementation manner of the present application. Without departing from the concept and principle of the present application, any equivalent changes and modifications made by any technician in the field should fall within the scope of protection of the present application.

Claims

1. An aerodynamic separation system for a launch vehicle, characterized in that: include: At least one gas cylinder, Gas source output switch, at least one cylinder; The gas cylinder is connected to the gas cylinder through the gas charging pipeline, and the gas source output switch is arranged on the gas charging pipeline to control the on and off of the gas charging pipeline; the gas source output switch adopts an electrically controlled switch, which is connected to the external control device through a control signal line; The gas cylinder is used to be filled with compressed gas having a preset pressure, and when the gas source output switch is turned on, the compressed gas stored in the gas cylinder pushes the to-be-separated structures of the launch vehicle to separate from each other through the pneumatic push rod in the cylinder after passing through the gas charging pipeline; A gas cylinder pressure detection gauge is also provided on the gas filling pipeline connecting the gas cylinder and the gas source output switch, and the gas cylinder pressure detection gauge is used to detect the pressure of the compressed gas output by the gas cylinder; A first pressure detection gauge is provided at one end of the cylinder, and a second pressure detection gauge is provided at the other end; the first pressure detection gauge is used to detect the pressure of the cylinder charging chamber, and the second pressure detection gauge is used to detect the pressure of the cylinder exhaust chamber.

2. The aerodynamic separation system for a launch vehicle according to claim 1, characterized in that: A force transmission device is provided on the to-be-separated structure of the carrier rocket, and the pneumatic push rod in the cylinder pushes the force transmission device to separate the to-be-separated structures of the carrier rocket from each other.

3. The aerodynamic separation system for a launch vehicle according to claim 1, characterized in that: One end of the inflation pipeline connected to the gas cylinder is provided with a charging and discharging port, and a mechanical inflation switch is provided on the inflation pipeline connected to the charging and discharging port and the gas cylinder.

4. The aerodynamic separation system for a launch vehicle according to claim 3, characterized in that: An interface is provided on the inflation pipeline connected with the mechanical inflation switch and the gas cylinder, and the gas cylinder is connected with the rocket body pressurization delivery system through the interface.

5. The aerodynamic separation system for a launch vehicle according to claim 2, characterized in that: The aerodynamic separation system is used in the interstage separation, fairing separation or payload separation of a launch vehicle.

6. The aerodynamic separation system for a launch vehicle according to claim 5, characterized in that: When the pneumatic separation system is used in the interstage separation of a launch vehicle, it provides energy for the interstage separation; the gas cylinder is installed on the front bottom of the separation sub-stage rocket body or on the interstage section.

7. The aerodynamic separation system for a launch vehicle according to claim 6, characterized in that: When there is only one interstage structure of a main nozzle configuration in the upper stage body, the cylinder is provided as one or more than two; When there is one cylinder, the cylinder is arranged at the main nozzle of the engine in the upper stage body, the force transmission device adopts the main nozzle of the engine in the upper stage body, and the pneumatic push rod in the cylinder applies thrust to the main nozzle of the engine in the upper stage body, so that the upper stage body is separated from the separation sub-stage body; When there are more than two cylinders, the more than two cylinders are used to be evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell; the force transmission device adopts a force transmission support, which is fixedly connected to the upper stage rocket body and close to the interstage separation surface; the pneumatic push rod in the cylinder applies thrust to the force transmission support, so that the upper stage rocket body is separated from the separation sub-stage rocket body.

8. The aerodynamic separation system for a launch vehicle according to claim 7, characterized in that: When there are multiple interstage structures with main nozzle configurations in the upper stage body, the cylinders are arranged in number of more than two, and the more than two cylinders are evenly distributed on the interstage separation surface between the interstage section and the upper stage rear short shell; the force transmission device is fixedly connected to the upper stage body and is close to the interstage separation surface; the pneumatic push rod in the cylinder applies thrust to the force transmission device, so that the upper stage body is separated from the separation sub-stage body.

9. The aerodynamic separation system for a launch vehicle according to claim 5, characterized in that: When the pneumatic separation system is used in the separation of the fairing, it provides energy for the separation of the fairing; the force transmission device adopts a force transmission support; When the fairing is separated from the rocket body by an integrally pulled-out method, the pneumatic separation system is installed on the fairing, and the force transmission support is installed on the front end of the final stage rocket body of the launch vehicle; more than two cylinders are arranged on the lateral separation surface of the fairing; after the fairing separation surface is unlocked, the fairing is separated from the rocket body under the action of the pneumatic push rod; When the fairing is separated from the rocket body by means of two half-fairings being split and thrown horizontally, a set of the pneumatic separation system is installed on each half-fairing, the installation axis of the cylinder is perpendicular to the longitudinal separation surface of the fairing, the pneumatic push rod points to the other half-fairing, and the force transmission support is arranged on the other half-fairing; after the fairing separation surface is unlocked, the two half-fairings move horizontally in a direction perpendicular to the fairing separation surface under the action of the pneumatic push rod, and finally separate from the rocket body; When the fairing is separated from the rocket body by a two-half-fairing split-petal spinning and throwing method, a set of the pneumatic separation system is installed on each half-fairing, the installation axis of the cylinder is perpendicular to the lateral separation surface of the fairing, the pneumatic push rod points to the front end of the final-stage rocket body, and the force transmission support is arranged on the front end of the final-stage rocket body; after the fairing separation surface is unlocked, the two half-fairings rotate along their rotation axes with each other under the action of the pneumatic push rods, and finally separate from the rocket body.

10. The aerodynamic separation system for a launch vehicle according to claim 5, characterized in that: When the pneumatic separation system is used in payload separation, it provides energy for payload separation; The pneumatic separation system is installed at the front end of the final stage body of the carrier rocket, and more than two cylinders are arranged on the separation surface of the payload; after the separation surface of the payload is unlocked, the payload is separated from the final stage body under the action of the pneumatic push rod.

11. A launch vehicle, characterized in that: It comprises the aerodynamic separation system as described in any one of claims 1 to 10, and the aerodynamic separation system is used in the interstage separation and / or fairing separation and / or payload separation of the launch vehicle.

Images