Rocket erection frame rapid fallback realization system

Abstract

The present application provides a system for realizing the rapid backward tilting of a rocket erection frame, which includes an erection cylinder and a hydraulic system. The erection cylinder is arranged on the ground on one side of the launch pad, the lower hinge point of the erection cylinder is connected to the ground, and the upper hinge point is connected to the erection frame; the hydraulic system is connected to the erection cylinder, and is used to control the extension and retraction of the erection cylinder, so that the erection cylinder drives the erection frame to tilt backward rapidly relative to the rocket when the rocket is ignited at zero seconds. The present application can make the erection frame tilt backward rapidly and reliably when the rocket erection frame is heavy, has a large moment of inertia, and requires a large backward tilting angular velocity, so as to avoid the rocket take-off drift space and ensure the safe take-off of the rocket.

Description

Technical Field

[0001] The present application belongs to the field of aerospace, and specifically relates to a system for realizing the rapid backward collapse of a rocket erection frame. Background Art

[0002] In recent years, with the rapid development of communication, navigation and meteorological technology, especially the booming commercial aerospace in recent years, people's demand for launch vehicles has become increasingly strong. Launch vehicles often adopt the "three horizontal and one vertical" test and launch mode, which is a rocket test and launch mode of horizontal assembly, horizontal testing, horizontal transportation, and finally erection and launch on the launch pad. It requires the connector to be able to fall off in zero seconds. Therefore, after the rocket is transported to the launch pad and erected to a vertical state, at the moment of zero-second ignition of the rocket, the erection frame must quickly move away from the rocket to avoid the space where the rocket takes off and drifts. This is a very important link in the entire rocket launch process and determines the success or failure of the launch mission. Due to the heavy weight of the erection frame, the moment of inertia is large, and the angular velocity required for the backward fall is large, the realization of the rapid backward fall of the erection frame has a high design difficulty. In addition, the environmental conditions during rocket launch are harsh, which poses a higher challenge to how to ensure the reliability of the rapid backward fall of the erection frame; and there is no application case of liquid rocket launchers in the prior art that achieves rapid backward fall at zero-second ignition of the rocket. Therefore, there is an urgent need to design a driving and control method that can ensure the rapid backward collapse of the erection frame to meet the requirements of the rocket's "three horizontal and one vertical" test and launch mode. Summary of the invention

[0003] In order to overcome the problems existing in the related art at least to a certain extent, the present application provides a system for realizing the rapid backward collapse of a rocket erection frame.

[0004] According to an embodiment of the present application, a system for realizing rapid backward collapse of a rocket erection frame is provided, which includes an erection cylinder and a hydraulic system. The erection cylinder is arranged on the ground on one side of a launch pad, a lower hinge point of the erection cylinder is connected to the ground, and an upper hinge point thereof is connected to the erection frame; the hydraulic system is connected to the erection cylinder, and is used to control the extension and retraction of the erection cylinder, so that the erection cylinder drives the erection frame to rapidly collapse backward relative to the rocket when the rocket is ignited at zero seconds.

[0005] In the above-mentioned rocket erection frame rapid backward fall realization system, the hydraulic system includes an energy storage subsystem, a cylinder small cavity control subsystem, a cylinder large cavity control subsystem and a hydraulic lock control subsystem;

[0006] The energy storage subsystem is connected to the hydraulic oil inlet and the cylinder small cavity control subsystem, and the energy storage subsystem is used to provide pressure for the cylinder small cavity control subsystem through hydraulic oil; the cylinder small cavity control subsystem is connected to the small cavity of the erecting cylinder, and is used to control the retraction of the erecting cylinder; the cylinder large cavity control subsystem is connected to the large cavity of the erecting cylinder, and is used to control the extension of the erecting cylinder; the hydraulic lock control subsystem is connected to the small cavity hydraulic lock in the cylinder small cavity control subsystem and the large cavity hydraulic lock in the cylinder large cavity control subsystem, and is used to control the on and off of the small cavity hydraulic lock and the large cavity hydraulic lock.

[0007] Further, the energy storage subsystem includes an oil charging valve, an accumulator group and a first oil drain valve;

[0008] The inlet of the oil charging valve is connected to the hydraulic oil inlet, and the outlet is connected to the oil inlet of the accumulator group and the B port of the first oil discharge valve; the A port of the first oil discharge valve is connected to the oil cylinder small cavity control subsystem.

[0009] Furthermore, the energy storage subsystem also includes a pressure relay, a manual oil drain valve and an electric oil drain valve; the pressure relay, the manual oil drain valve and the electric oil drain valve are all arranged on the pipeline of the oil inlet of the accumulator group; the opposite end of the manual oil drain valve and the accumulator group connection end and the opposite end of the electric oil drain valve and the accumulator group connection end are both connected to the oil return port.

[0010] Furthermore, a safety valve is provided on the pipeline of the oil inlet of the accumulator group, and the safety valve is used to ensure the safety of the oil pressure filled in the accumulator group.

[0011] Furthermore, the oil cylinder small chamber control subsystem includes a first small chamber control valve and a small chamber hydraulic lock; the B oil port of the first small chamber control valve is connected to the A port of the first oil drain valve, and its A oil port is connected to the oil inlet of the small chamber hydraulic lock, and the oil outlet of the small chamber hydraulic lock is connected to the small chamber of the erecting cylinder.

[0012] Furthermore, the oil cylinder large cavity control subsystem includes a first proportional pressure valve, a first large cavity control valve and a large cavity hydraulic lock; the B port of the first proportional pressure valve is connected to the oil return port, and its A port is connected to the A oil port of the first large cavity control valve, the B oil port of the first large cavity control valve is connected to the oil inlet of the large cavity hydraulic lock, and the oil outlet of the large cavity hydraulic lock is connected to the large cavity of the erecting cylinder.

[0013] Furthermore, the hydraulic lock control subsystem includes a first unlocking valve and a shuttle valve, one end of the first unlocking valve is connected to the control oil port, and the other end thereof is connected to the small chamber hydraulic lock and the large chamber hydraulic lock through the shuttle valve to control the on and off of the small chamber hydraulic lock and the large chamber hydraulic lock.

[0014] Furthermore, a small cavity unlocking pressure sensor is arranged on the pipeline connecting the shuttle valve and the small cavity hydraulic lock, and the small cavity unlocking pressure sensor is used to detect the unlocking action of the small cavity hydraulic lock; a large cavity unlocking pressure sensor is arranged on the pipeline connecting the shuttle valve and the large cavity hydraulic lock, and the large cavity unlocking pressure sensor is used to detect the unlocking action of the large cavity hydraulic lock.

[0015] Furthermore, a small cavity pressure sensor is provided on the pipeline connecting the small cavity hydraulic lock and the small cavity of the erecting cylinder, and the small cavity pressure sensor is used to detect the small cavity pressure of the erecting cylinder in real time; a large cavity pressure sensor is provided on the pipeline connecting the large cavity hydraulic lock and the large cavity of the erecting cylinder, and the large cavity pressure sensor is used to detect the large cavity pressure of the erecting cylinder in real time.

[0016] According to the above-mentioned specific implementation methods of the present application, it can be known that at least the following beneficial effects are achieved: the rocket erection frame rapid backward tilting realization system provided by the present application, when the rocket erection frame is heavy, has a large moment of inertia, and requires a large backward tilting angular velocity, the hydraulic system controls the extension and retraction of the erection cylinder to drive the erection frame to quickly tilt backward relative to the rocket when the rocket is ignited at zero seconds, thereby avoiding the rocket's takeoff drift space and meeting the launch requirement of zero-second detachment of the energy filling connector; improving the reliability of the rocket's pre-launch filling system and optimizing the overall requirements of the rocket's full system test and launch mode, which is of decisive significance for improving the reliability of rocket launches under the "three horizontal and one vertical test and launch mode".

[0017] The rocket erection frame rapid backward collapse realization system provided in the embodiment of the present application adopts the accumulator group to discharge oil, which can meet the small chamber flow requirement of the erection frame for rapid backward collapse, and has high reliability; the proportional pressure valve is adopted to establish the large chamber back pressure of the erection cylinder, which can ensure the large chamber pressure in the deceleration stage of the erection frame, and has good control stability, avoiding damage to the erection cylinder caused by overpressure; the oil discharge valve, the small chamber control valve and the large chamber control valve all adopt two-way cartridge valves, which can discharge oil from the accumulator and control the large and small chambers of the erection cylinder, and have less leakage; the reliability of the hydraulic system in zero-second action can be ensured by multiple redundant backup valve components.

[0018] 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

[0019] 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.

[0020] Figure 1A schematic diagram of the application of a system for realizing rapid backward collapse of a rocket erection frame provided in an embodiment of the present application in the erection of a launch vehicle.

[0021] Figure 2 A schematic diagram of a system for realizing rapid backward collapse of a rocket erection frame provided in an embodiment of the present application.

[0022] Figure 3 A state diagram of a rocket igniting and rapidly falling back a rocket erection frame at zero seconds in a method for realizing the rapid falling back of a rocket erection frame provided in an embodiment of the present application.

[0023] Figure 4 A state diagram of a rocket erection frame stopping its dumping after the rocket flies away from an interference risk area in a method for realizing rapid dumping of a rocket erection frame provided in an embodiment of the present application.

[0024] Figure 5 This is one of the valve port pressure curve graphs of a proportional pressure valve in a method for realizing rapid backward collapse of a rocket erection frame provided in an embodiment of the present application; wherein the horizontal axis represents time in seconds, and the vertical axis represents the valve port pressure of the proportional pressure valve in MPa.

[0025] Figure 6 The second valve port pressure curve diagram of the proportional pressure valve in the method for realizing the rapid backward collapse of a rocket erection frame provided in an embodiment of the present application; wherein the horizontal axis represents time in seconds, and the vertical axis represents the valve port pressure of the proportional pressure valve in MPa.

[0026] Description of reference numerals:

[0027] 10. Launch pad; 20. Rotation axis; 30. Erection frame; 40. Launch vehicle; 50. Energy refueling connector;

[0028] 1. Lift the oil cylinder;

[0029] 2. Hydraulic system;

[0030] 21. Energy storage subsystem; 211. Oil charging valve; 212. Accumulator group; 213. First oil drain valve; 214. Pressure relay; 215. Manual oil drain valve; 216. Electric oil drain valve; 217. Safety valve; 218. Second oil drain valve;

[0031] 22. Oil cylinder small cavity control subsystem; 221. First small cavity control valve; 222. Small cavity hydraulic lock; 223. Small cavity unlocking pressure sensor; 224. Small cavity pressure sensor; 225. Second small cavity control valve; 226. First pressure measuring joint;

[0032] 23. Oil cylinder large cavity control subsystem; 231. First proportional pressure valve; 232. First large cavity control valve; 233. Large cavity hydraulic lock; 234. Large cavity unlocking pressure sensor; 235. Large cavity pressure sensor; 236. Second large cavity control valve; 237. Second proportional pressure valve; 238. Second pressure measuring joint;

[0033] 24. Hydraulic lock control subsystem; 241. First unlocking valve; 242. Shuttle valve; 243. Second unlocking valve. DETAILED DESCRIPTION

[0034] 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.

[0035] 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.

[0036] 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.

[0037] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0038] As used herein, "and / or" includes any or all combinations of the items described.

[0039] As used herein, “plurality” includes “two” and “more than two”; as used herein, “plurality groups” includes “two groups” and “more than two groups”.

[0040] 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.

[0041] like Figure 1 As shown, the rocket launch station is provided with a launch platform 10, and a rotating shaft 20 is provided on the launch platform 10. The rotating shaft 20 is used to connect the bottom end of the erection frame 30, and the erection frame 30 can rotate around the rotating shaft 20. After the carrier rocket 40 is transported to the launch station, the carrier rocket 40 can be erected to a vertical state by the erection frame 30.

[0042] like Figure 1 As shown, the present application provides a system for realizing rapid backward tilting of a rocket erection frame, which includes an erection cylinder 1 and a hydraulic system 2, wherein the erection cylinder 1 is arranged on the ground on one side of a launch pad 10, the lower hinge point of the erection cylinder 1 is connected to the ground, and the upper hinge point thereof is connected to the erection frame 30. The hydraulic system 2 is connected to the erection cylinder 1, and is used to control the extension and retraction of the erection cylinder 1, so that the erection cylinder 1 drives the erection frame 30 to tilt backward rapidly relative to the rocket when the rocket is ignited at zero seconds, avoiding the take-off drift space of the rocket, and ensuring the safe take-off of the rocket.

[0043] In a specific embodiment, Figure 2 As shown, the hydraulic system 2 includes an energy storage subsystem 21 , a cylinder small cavity control subsystem 22 , a cylinder large cavity control subsystem 23 and a hydraulic lock control subsystem 24 .

[0044] Among them, the energy storage subsystem 21 is connected to the hydraulic oil inlet and the cylinder small cavity control subsystem 22, and the energy storage subsystem 21 is used to provide pressure for the cylinder small cavity control subsystem 22 through hydraulic oil; the cylinder small cavity control subsystem 22 is connected to the small cavity of the erecting cylinder 1, and is used to control the retraction of the erecting cylinder 1; the cylinder large cavity control subsystem 23 is connected to the large cavity of the erecting cylinder 1, and is used to control the extension of the erecting cylinder 1; the hydraulic lock control subsystem 24 is connected to the small cavity hydraulic lock 222 in the cylinder small cavity control subsystem 22 and the large cavity hydraulic lock 233 in the cylinder large cavity control subsystem 23, and is used to control the on and off of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233.

[0045] In a specific embodiment, the energy storage subsystem 21 includes an accumulator group 212 , a first oil discharge valve 213 and an oil charging valve 211 .

[0046] The inlet of the oil charging valve 211 is connected to the hydraulic oil inlet port P, and the outlet thereof is connected to the oil inlet port of the accumulator group 212 and the port B of the first oil drain valve 213 .

[0047] When the power is off, the A port and the B port of the first oil drain valve 213 are blocked; the oil filling valve 211 is connected after power is supplied, and the oil flowing in from the hydraulic oil inlet P can enter the accumulator group 212 and the first oil drain valve 213 respectively through the oil filling valve 211.

[0048] The energy storage subsystem 21 further includes a pressure relay 214, a manual oil drain valve 215 and an electric oil drain valve 216. The pressure relay 214, the manual oil drain valve 215 and the electric oil drain valve 216 are all arranged on the pipeline of the oil inlet of the accumulator group 212. The end opposite to the connection end of the manual oil drain valve 215 and the end opposite to the connection end of the accumulator group 212 are both connected to the oil return port T.

[0049] The pressure relay 214 is used to detect the pressure of the oil inlet of the accumulator group 212. When the pressure of the oil inlet of the accumulator group 212 detected by the pressure relay 214 is greater than the preset pressure threshold, the charging valve 211 is powered off, and the oil is sealed between the accumulator group 212 and the first oil drain valve 213. When the oil needs to be drained, the manual oil drain valve 215 and the electric oil drain valve 216 of the accumulator group 212 can be opened to drain the oil in the accumulator group 212 to the oil return port T.

[0050] In addition, a safety valve 217 is provided on the pipeline of the oil inlet of the accumulator group 212 , and the safety valve 217 is used to ensure the safety of the oil pressure in the accumulator group 212 .

[0051] In a specific embodiment, the oil cylinder small cavity control subsystem 22 includes a first small cavity control valve 221 and a small cavity hydraulic lock 222. The B oil port of the first small cavity control valve 221 is connected to the A port of the first oil release valve 213, and its A oil port is connected to the oil inlet of the small cavity hydraulic lock 222 through a pipeline, and the oil outlet PB of the small cavity hydraulic lock 222 is connected to the small cavity of the erecting oil cylinder 1 through a hose and a small cavity pipeline, and the erecting oil cylinder 1 can be controlled to retract after the oil circuit is connected.

[0052] In a specific embodiment, the oil cylinder large cavity control subsystem 23 includes a first proportional pressure valve 231, a first large cavity control valve 232 and a large cavity hydraulic lock 233. The B port of the first proportional pressure valve 231 is connected to the oil return port T through a pipeline, and its A port is connected to the A port of the first large cavity control valve 232. The B port of the first large cavity control valve 232 is connected to the oil inlet of the large cavity hydraulic lock 233, and the oil outlet PA of the large cavity hydraulic lock 233 is connected to the large cavity of the erecting oil cylinder 1 through a hose and a large cavity pipeline. Among them, the first proportional pressure valve 231 provides back pressure for the large cavity of the erecting oil cylinder 1, which plays a role in deceleration during the backward falling process of the erecting frame 30.

[0053] In a specific embodiment, the hydraulic lock control subsystem 24 includes a first unlocking valve 241 and a shuttle valve 242. One end of the first unlocking valve 241 is connected to the control oil port X, and the other end thereof is connected to the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 through the shuttle valve 242 to control the on and off of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233. The small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 are both externally controlled and externally discharged hydraulic locks, and the unlocking actions of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 are both controlled by the first unlocking valve 241.

[0054] In addition, a small cavity unlocking pressure sensor 223 is provided on the pipeline connecting the shuttle valve 242 and the small cavity hydraulic lock 222, and the small cavity unlocking pressure sensor 223 is used to detect the unlocking action of the small cavity hydraulic lock 222. A large cavity unlocking pressure sensor 234 is provided on the pipeline connecting the shuttle valve 242 and the large cavity hydraulic lock 233, and the large cavity unlocking pressure sensor 234 is used to detect the unlocking action of the large cavity hydraulic lock 233.

[0055] A small cavity pressure sensor 224 is provided on the pipeline connecting the small cavity hydraulic lock 222 and the small cavity of the erecting oil cylinder 1. The small cavity pressure sensor 224 is used to detect the pressure of the small cavity of the erecting oil cylinder 1 in real time. A large cavity pressure sensor 235 is provided on the pipeline connecting the large cavity hydraulic lock 233 and the large cavity of the erecting oil cylinder 1. The large cavity pressure sensor 235 is used to detect the pressure of the large cavity of the erecting oil cylinder 1 in real time.

[0056] In order to ensure the reliability of the rapid backward collapse of the erecting frame 30, a backup second oil drain valve 218 is provided for the first oil drain valve 213, and the first oil drain valve 213 is connected in parallel with the second oil drain valve 218; a backup second small chamber control valve 225 is provided for the first small chamber control valve 221, and the first small chamber control valve 221 is connected in parallel with the second small chamber control valve 225; a backup second large chamber control valve 236 is provided for the first large chamber control valve 232, and the first large chamber control valve 232 is connected in parallel with the second large chamber control valve 236; a backup second proportional pressure valve 237 is provided for the first proportional pressure valve 231, and the first proportional pressure valve 231 is connected in parallel with the second proportional pressure valve 237; a backup second unlocking valve 243 is provided for the first unlocking valve 241, and the first unlocking valve 241 is connected in parallel with the second unlocking valve 243; through these redundant backup settings, it is possible to avoid affecting the execution of the rapid backward collapse of the erecting frame 30 due to the failure of a single valve action.

[0057] In order to facilitate the measurement of the pressure of the small chamber and the large chamber of the erecting cylinder 1, pressure measuring joints are provided on the pipeline connecting the small chamber hydraulic lock 222 and the small chamber of the erecting cylinder 1 and on the pipeline connecting the large chamber hydraulic lock 233 and the large chamber of the erecting cylinder 1.

[0058] In a specific embodiment, the accumulator group 212 includes five 100-liter accumulators and one backup 100-liter accumulator. To ensure that the small chamber of the erecting cylinder 1 has sufficient pressure during the back-up process, the initial charging pressure of the accumulator can be set to 21 MPa, and the pressure of the system for rapid back-up can be set to 25 MPa.

[0059] In the rocket erection frame rapid backward fall realization system provided by the present application, the accumulator group 212 discharges oil to meet the small chamber flow requirements of the erection frame 30 for rapid backward fall, and has high reliability; the proportional pressure valve is used to establish the large chamber back pressure of the erection cylinder 1, which can ensure the large chamber pressure during the deceleration stage of the erection frame 30, and has good control stability to avoid damage to the erection cylinder 1 caused by overpressure; the discharge valve, small chamber control valve and large chamber control valve all use two-way cartridge valves, which can discharge oil from the accumulator and control the large and small chambers of the erection cylinder 1, and have less leakage. Multiple redundant backup valves can ensure the reliability of the hydraulic system 2 in zero-second action.

[0060] The rocket erection frame rapid backward fall realization system provided in the present application can realize the rapid backward fall of the erection frame 30 after the rocket is ignited at zero seconds, avoid the drift space of the rocket takeoff, and ensure the safety of the rocket takeoff; at the same time, the present application can realize the launch mode of the liquid rocket energy filling connector 50 falling off at zero seconds, thereby maximally guaranteeing and optimizing the overall launch requirements of the rocket and improving the reliability of the rocket launch.

[0061] Based on a rocket erection frame rapid backward realization system provided in the present application, the present application also provides a rocket erection frame rapid backward realization method, which comprises the following steps:

[0062] S1, such as Figure 1 As shown, a vertical cylinder 1 is arranged on the ground at one side of the launching platform 10 , the lower hinge point of the vertical cylinder 1 is connected to the ground, and the upper hinge point is connected to the vertical frame 30 .

[0063] Specifically, the erecting oil cylinder 1 adopts a multi-stage cylinder, and its oil intake mode is large-chamber oil intake and small-chamber rod head oil intake.

[0064] S2. Before the rocket is launched, the rocket is erected to a vertical state under the action of the erection frame 30, and the erection cylinder 1 is controlled to retract, so that the erection frame 30 tilts horizontally by a first preset angle, so that the erection frame 30 is separated from the rocket by a preset distance. At this time, the energy filling connector 50 can be connected to the hard pipe on the erection frame 30 through a hose, so as to realize the small flow replenishment of the energy system in the last stage before the rocket is launched.

[0065] Specifically, 5 minutes before the rocket is launched, the erecting frame 30 can be tilted 5° toward the horizontal direction, that is, the first preset angle is 5°, and the erecting frame 30 is tilted to an angle of 85° with the horizontal direction.

[0066] S3, such as Figure 3 As shown, when the rocket is ignited at zero second, the erection cylinder 1 is controlled to continue to retract, so as to drive the erection frame 30 to continue to tilt in the horizontal direction. At the same time, the rocket flies away from the launching platform 10, and the energy filling connector 50 is disconnected from the rocket under the dual effects of the rocket taking off and the erection frame 30 tilting away from the rocket, thereby achieving zero-second detachment.

[0067] S4, such as Figure 4 As shown, after the rocket flies away from the interference risk area, the erection cylinder 1 is controlled to extend, so that the erection frame 30 tilts horizontally to a second preset angle under the action of two opposite direction forces provided by the erection cylinder 1 and then stops tilting. The erection cylinder 1 does not exceed its third-stage shift point, thereby avoiding the impact caused by the cylinder shift.

[0068] Specifically, the second preset angle may be 30°, that is, the erecting frame 30 is tilted to an angle of 60° with the horizontal direction.

[0069] It should be noted that, in step S2, the first preset angle and the second preset angle are both angles between the axis of the length direction of the erecting frame 30 and the vertical direction.

[0070] The method for realizing rapid backward tilting of a rocket erection frame provided in the present application is to make the erection frame 30 tilt in the horizontal direction at a first preset angle, and then continue to tilt backward quickly when the rocket is ignited at zero seconds, until the tilting stops after tilting in the horizontal direction at a second preset angle. This can avoid the take-off drift space of the rocket and meet the launch requirement of the energy filling connector falling off at 50 seconds. It can also improve the reliability of the rocket's pre-launch filling system and optimize the overall requirements of the rocket's full system test and launch mode, which is of decisive significance for improving the reliability of rocket launches under the "three horizontal and one vertical test and launch mode".

[0071] In the above steps S3 and S4, Figure 2 As shown, the retraction and extension of the erecting cylinder 1 are controlled by the hydraulic system 2. The hydraulic system 2 includes an energy storage subsystem 21, a cylinder small cavity control subsystem 22, a cylinder large cavity control subsystem 23 and a hydraulic lock control subsystem 24.

[0072] Among them, the energy storage subsystem 21 is connected to the hydraulic oil inlet P and the cylinder small cavity control subsystem 22, and the energy storage subsystem 21 is used to provide pressure for the cylinder small cavity control subsystem 22 through hydraulic oil; the cylinder small cavity control subsystem 22 is connected to the small cavity of the erecting cylinder 1, and is used to control the retraction of the erecting cylinder 1; the cylinder large cavity control subsystem 23 is connected to the large cavity of the erecting cylinder 1, and is used to control the extension of the erecting cylinder 1; the hydraulic lock control subsystem 24 is connected to the small cavity hydraulic lock 222 in the cylinder small cavity control subsystem 22 and the large cavity hydraulic lock 233 in the cylinder large cavity control subsystem 23, and is used to control the on and off of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233.

[0073] In a specific embodiment, the energy storage subsystem 21 includes an oil charging valve 211 , an accumulator group 212 and a first oil drain valve 213 .

[0074] The inlet of the oil charging valve 211 is connected to the hydraulic oil inlet port P, and the outlet thereof is connected to the oil inlet port of the accumulator group 212 and the port B of the first oil drain valve 213 .

[0075] When the power is off, the A port and the B port of the first oil drain valve 213 are blocked; the oil filling valve 211 is connected after power is supplied, and the oil flowing in from the hydraulic oil inlet P can enter the accumulator group 212 and the first oil drain valve 213 respectively through the oil filling valve 211.

[0076] The energy storage subsystem 21 further includes a pressure relay 214, a manual oil drain valve 215 and an electric oil drain valve 216. The pressure relay 214, the manual oil drain valve 215 and the electric oil drain valve 216 are all arranged on the pipeline of the oil inlet of the accumulator group 212. The end opposite to the connection end of the manual oil drain valve 215 and the end opposite to the connection end of the accumulator group 212 are both connected to the oil return port T.

[0077] The pressure relay 214 is used to detect the pressure of the oil inlet of the accumulator group 212. When the pressure of the oil inlet of the accumulator group 212 detected by the pressure relay 214 is greater than the preset pressure threshold, the charging valve 211 is powered off, and the oil is sealed between the accumulator group 212 and the first oil drain valve 213. When the oil needs to be drained, the manual oil drain valve 215 and the electric oil drain valve 216 of the accumulator group 212 can be opened to drain the oil in the accumulator group 212 to the oil return port T.

[0078] In addition, a safety valve 217 is provided on the pipeline of the oil inlet of the accumulator group 212 , and the safety valve 217 is used to ensure the safety of the oil pressure in the accumulator group 212 .

[0079] In a specific embodiment, the oil cylinder small cavity control subsystem 22 includes a first small cavity control valve 221 and a small cavity hydraulic lock 222. The B oil port of the first small cavity control valve 221 is connected to the A port of the first oil release valve 213, and its A oil port is connected to the oil inlet of the small cavity hydraulic lock 222 through a pipeline, and the oil outlet PB of the small cavity hydraulic lock 222 is connected to the small cavity of the erecting oil cylinder 1 through a hose and a small cavity pipeline, and the erecting oil cylinder 1 can be controlled to retract after the oil circuit is connected.

[0080] In a specific embodiment, the oil cylinder large cavity control subsystem 23 includes a first proportional pressure valve 231, a first large cavity control valve 232 and a large cavity hydraulic lock 233. The B port of the first proportional pressure valve 231 is connected to the oil return port T through a pipeline, and its A port is connected to the A port of the first large cavity control valve 232. The B port of the first large cavity control valve 232 is connected to the oil inlet of the large cavity hydraulic lock 233, and the oil outlet PA of the large cavity hydraulic lock 233 is connected to the large cavity of the erecting oil cylinder 1 through a hose and a large cavity pipeline. Among them, the first proportional pressure valve 231 provides back pressure for the large cavity of the erecting oil cylinder 1, which plays a deceleration role in the backward falling process of the erecting frame 30.

[0081] In a specific embodiment, the hydraulic lock control subsystem 24 includes a first unlocking valve 241 and a shuttle valve 242. One end of the first unlocking valve 241 is connected to the control oil port X, and the other end thereof is connected to the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 through the shuttle valve 242 to control the on and off of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233. The small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 are both externally controlled and externally discharged hydraulic locks. The unlocking actions of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 are both controlled by the first unlocking valve 241, and the first unlocking valve 241 simultaneously controls the unlocking actions of the small cavity hydraulic lock 222 and the large cavity hydraulic lock 233 through the shuttle valve 242.

[0082] In addition, a small cavity unlocking pressure sensor 223 is provided on the pipeline connecting the shuttle valve 242 and the small cavity hydraulic lock 222, and the small cavity unlocking pressure sensor 223 is used to detect the unlocking action of the small cavity hydraulic lock 222. A large cavity unlocking pressure sensor 234 is provided on the pipeline connecting the shuttle valve 242 and the large cavity hydraulic lock 233, and the large cavity unlocking pressure sensor 234 is used to detect the unlocking action of the large cavity hydraulic lock 233.

[0083] A small cavity pressure sensor 224 is provided on the pipeline connecting the small cavity hydraulic lock 222 and the small cavity of the erecting oil cylinder 1. The small cavity pressure sensor 224 is used to detect the pressure of the small cavity of the erecting oil cylinder 1 in real time. A large cavity pressure sensor 235 is provided on the pipeline connecting the large cavity hydraulic lock 233 and the large cavity of the erecting oil cylinder 1. The large cavity pressure sensor 235 is used to detect the pressure of the large cavity of the erecting oil cylinder 1 in real time.

[0084] In order to ensure the reliability of the rapid backward collapse of the erecting frame 30, a backup second oil drain valve 218 is provided for the first oil drain valve 213, and the first oil drain valve 213 is connected in parallel with the second oil drain valve 218; a backup second small chamber control valve 225 is provided for the first small chamber control valve 221, and the first small chamber control valve 221 is connected in parallel with the second small chamber control valve 225; a backup second large chamber control valve 236 is provided for the first large chamber control valve 232, and the first large chamber control valve 232 is connected in parallel with the second large chamber control valve 236; a backup second proportional pressure valve 237 is provided for the first proportional pressure valve 231, and the first proportional pressure valve 231 is connected in parallel with the second proportional pressure valve 237; a backup second unlocking valve 243 is provided for the first unlocking valve 241, and the first unlocking valve 241 is connected in parallel with the second unlocking valve 243; through these redundant backup settings, it is possible to avoid affecting the execution of the rapid backward collapse of the erecting frame 30 due to the failure of a single valve action.

[0085] The above-mentioned first oil release valve 213, second oil release valve 218, small chamber hydraulic lock 222, large chamber hydraulic lock 233, first small chamber control valve 221, second small chamber control valve 225, first large chamber control valve 232, second large chamber control valve 236, first proportional pressure valve 231 and second proportional pressure valve 237 are all connected to the oil drain port L.

[0086] In order to facilitate the measurement of the pressure in the small chamber and the large chamber of the erecting cylinder 1, a first pressure measuring joint 226 is provided on the pipeline connecting the small chamber hydraulic lock 222 and the small chamber of the erecting cylinder 1, and a second pressure measuring joint 238 is provided on the pipeline connecting the large chamber hydraulic lock 233 and the large chamber of the erecting cylinder 1.

[0087] In a specific embodiment, the accumulator group 212 includes five 100-liter accumulators and one backup 100-liter accumulator. To ensure that the small chamber of the erecting cylinder 1 has sufficient pressure during the back-up process, the initial charging pressure of the accumulator can be set to 21 MPa, and the pressure of the system for rapid back-up can be set to 25 MPa.

[0088] Based on the specific structure of the hydraulic system 2, an accumulator filling step and a pre-firing preparation step are further provided between step S2 and step S3.

[0089] The specific process of the accumulator filling step is as follows:

[0090] like Figure 2 As shown, the first oil discharge valve 213 is in a power-off closed state, the oil filling valve 211 is powered on and opened, and the oil enters through the hydraulic oil inlet P and continues to enter the accumulator group 212 through the oil filling valve 211. When the pressure at the oil inlet of the accumulator group 212 reaches the preset pressure threshold of the pressure relay 214, the pressure relay 214 sends a signal, and the oil filling valve 211 is powered off and disconnected, so that the oil is sealed between the accumulator group 212 and the first oil discharge valve 213.

[0091] If the pressure drops due to leakage and the reduced pressure exceeds the preset threshold value of the pressure relay 214, the pressure relay 214 continues to send a signal, the oil filling valve 211 continues to open, and the oil continues to be filled through the hydraulic oil inlet P to the preset pressure threshold of the pressure relay 214, so that the pressure of the accumulator group 212 is always maintained above the first preset pressure value, ready for use when the rocket is ignited and launched at zero seconds.

[0092] Specifically, the preset pressure threshold of the pressure relay 214 can be set to 25.2MPa, and the preset threshold value of the pressure relay 214 can be set to 0.2MPa, so that the pressure of the accumulator group 212 can always be maintained above 25MPa. Once the pressure of the accumulator group 212 is lower than 25MPa, it means that the reduced pressure exceeds the preset threshold value of 0.2MPa of the pressure relay 214, and at this time, the oil filling valve 211 needs to be opened to continue filling.

[0093] The specific process of the pre-shooting preparation steps is as follows:

[0094] At t1 time before the rocket is ignited, the first unlocking valve 241 is energized, the unlocking oil circuit is opened, and when the pressures detected by the small chamber unlocking pressure sensor 223 and the large chamber unlocking pressure sensor 234 both reach or exceed the second preset pressure value, it is confirmed that the unlocking is completed, and the first oil release valve 213 and the first small chamber control valve 221 are energized at the same time. At this time, the oil pressure acts on the small chamber of the erecting cylinder 1 through the accumulator group 212, the first oil release valve 213, the first small chamber control valve 221 and the small chamber hydraulic lock 222. Since the first large chamber control valve 232 is in a power-off closed state, at this time, the oil acts on the large chamber of the erecting cylinder 1 through the small chamber of the erecting cylinder 1, and the erecting cylinder 1 is in a standby state.

[0095] Among them, t1 can be set to 10s, and the second preset pressure value can be set to 15MPa.

[0096] In the above step S3, when the rocket is ignited at zero seconds, the specific process of controlling the erection cylinder 1 to continue to retract so as to drive the erection frame 30 to continue to tilt in the horizontal direction is as follows:

[0097] When the rocket ignites at zero seconds, a leave-station signal is issued.

[0098] At t2 time before the first proportional pressure valve 231 receives the off-stage signal, the valve port pressure of the first proportional pressure valve 231 is set to a minimum pressure value, wherein the minimum pressure value can be set to 1 MPa.

[0099] The first large-chamber control valve 232 is controlled to open rapidly.

[0100] During this process, since the pressure value of the large chamber of the erecting cylinder 1 is relatively low, the erecting cylinder 1 shrinks rapidly under the pressure of its small chamber, driving the erecting frame 30 to fall back quickly to move away from the rocket, so that the rocket can fly away from the launch pad 10.

[0101] In the above step S4, after the rocket flies away from the interference risk area, the erection cylinder 1 is controlled to extend so that the erection frame 30 tilts horizontally at a second preset angle under the action of two opposite direction forces provided by the erection cylinder 1 and then stops tilting. The specific process is:

[0102] like Figure 3 As shown, after time t3, the rocket flies away from the interference risk area, and the valve port pressure of the first proportional pressure valve 231 is controlled to gradually increase from the minimum pressure value to a stable pressure value.

[0103] During the process of gradually increasing the pressure at the valve port of the first proportional pressure valve 231, the pressure at the large chamber of the erecting cylinder 1 gradually increases. In the initial stage, due to the large inertia of the erecting frame 30, in order to avoid impact, the pressure at the large chamber of the erecting cylinder 1 cannot be too high, so it is necessary to control the pressure at the valve port of the first proportional pressure valve 231 to increase slowly.

[0104] After testing and verifying the matching, the following Figure 5 or Figure 6 The valve port pressure curve of the proportional pressure valve shown can ensure that the erecting frame 30 stops at an angle of about 60° with the horizontal direction without exceeding the third-stage shift point of the erecting cylinder 1, thereby avoiding the impact caused by the cylinder shift.

[0105] Figure 5 The function form of the valve port pressure curve of the proportional pressure valve shown is specifically:

[0106]

[0107] Figure 6 The function form of the valve port pressure curve of the proportional pressure valve shown can be a logarithmic function with a base greater than 1 or a power function with an exponent greater than 0 and less than 1 in the interval [2,7]; the valve port pressure of the proportional pressure valve is a constant value of 1MPa in the interval [0,2); the valve port pressure of the proportional pressure valve is a constant value of 20MPa in the interval (7,+∞).

[0108] The method for realizing rapid backward collapse of a rocket erection frame provided in the present application uses the accumulator group 212 to discharge oil, which can meet the small-chamber flow requirement for rapid backward collapse of the erection frame 30, and has high reliability; a proportional pressure valve is used to establish the large-chamber back pressure of the erection cylinder 1, which can ensure the large-chamber pressure of the erection frame 30 during the deceleration stage, and has good control stability, avoiding damage to the erection cylinder 1 caused by overpressure; the oil discharge valve, the small-chamber control valve and the large-chamber control valve all use two-way cartridge valves, and the two-way cartridge valves can discharge oil from the accumulator and control the large and small chambers of the erection cylinder 1, and have less leakage.

[0109] A backup second oil drain valve 218 is provided for the first oil drain valve 213, a backup second small chamber control valve 225 is provided for the first small chamber control valve 221, a backup second large chamber control valve 236 is provided for the first large chamber control valve 232, a backup second proportional pressure valve 237 is provided for the first proportional pressure valve 231, and a backup second unlocking valve 243 is provided for the first unlocking valve 241. Multiple redundant backup valve components can ensure the reliability of the hydraulic system 2 in zero-second operation.

[0110] The method for realizing the rapid backward fall of the rocket erection frame provided in the present application can realize the rapid backward fall of the erection frame 30 after the rocket is ignited at zero seconds, avoid the drifting space of the rocket takeoff, and ensure the safety of the rocket takeoff; at the same time, the present application can realize the launch mode of the liquid rocket energy filling connector 50 falling off at zero seconds, and maximize the guarantee and optimization of the overall launch requirements of the rocket, and improve the reliability of the rocket launch. This method for realizing the rapid backward fall of the erection frame 30 after the rocket is ignited at zero seconds is the first of its kind in China and abroad, and has a pioneering significance for improving the diversity and flexibility of my country's rocket launch mode. At the same time, it can lay a technical foundation for the development of other types of rockets and realize the launch mode of the connector falling off at zero seconds, and provide a strong guarantee for the long-term development of commercial aerospace.

[0111] It should be noted that the system for realizing the rapid backward collapse of the rocket erection frame provided in the above-mentioned embodiment and the method embodiment for realizing the rapid backward collapse of the rocket erection frame belong to the same concept, and the specific implementation process is detailed in the method embodiment, which will not be repeated here.

[0112] 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. A system for realizing rapid backward collapse of a rocket erection frame, characterized in that: It comprises an erecting oil cylinder and a hydraulic system. The erecting oil cylinder is arranged on the ground at one side of the launch platform. The lower hinge point of the erecting oil cylinder is connected to the ground, and the upper hinge point is connected to the erecting frame. A rotating shaft is arranged on the launch platform, and the rotating shaft is used to connect the bottom end of the erecting frame. The erecting frame can rotate around the rotating shaft. The hydraulic system is connected to the erecting oil cylinder, and is used to control the extension and retraction of the erecting oil cylinder, so that the erecting oil cylinder drives the erecting frame to quickly tilt backward relative to the rocket when the rocket is ignited at zero seconds. The hydraulic system includes an energy storage subsystem, a cylinder small cavity control subsystem, a cylinder large cavity control subsystem and a hydraulic lock control subsystem; The energy storage subsystem is connected to the hydraulic oil inlet and the oil cylinder small cavity control subsystem, and the energy storage subsystem is used to provide pressure to the oil cylinder small cavity control subsystem through hydraulic oil; the oil cylinder small cavity control subsystem is connected to the small cavity of the erecting oil cylinder, and is used to control the retraction of the erecting oil cylinder; The oil cylinder large cavity control subsystem is connected to the large cavity of the erecting oil cylinder, and is used to control the extension of the erecting oil cylinder; The hydraulic lock control subsystem is connected to the small-cavity hydraulic lock in the oil cylinder small-cavity control subsystem and the large-cavity hydraulic lock in the oil cylinder large-cavity control subsystem, and is used to control the on and off of the small-cavity hydraulic lock and the large-cavity hydraulic lock.

2. The rocket erection frame rapid fallback realization system according to claim 1, characterized in that: The energy storage subsystem includes an oil charging valve, an accumulator group and a first oil discharge valve; The inlet of the oil charging valve is connected to the hydraulic oil inlet, and the outlet is connected to the oil inlet of the accumulator group and the B port of the first oil discharge valve; the A port of the first oil discharge valve is connected to the oil cylinder small cavity control subsystem.

3. The rocket erection frame rapid fallback realization system according to claim 2, characterized in that: The energy storage subsystem also includes a pressure relay, a manual oil drain valve and an electric oil drain valve; the pressure relay, the manual oil drain valve and the electric oil drain valve are all arranged on the pipeline of the oil inlet of the accumulator group; the opposite end of the manual oil drain valve and the connection end of the accumulator group and the opposite end of the electric oil drain valve and the connection end of the accumulator group are both connected to the oil return port.

4. The rocket erection frame rapid fallback realization system according to claim 2, characterized in that: A safety valve is also provided on the pipeline of the oil inlet of the accumulator group, and the safety valve is used to ensure the safety of the oil pressure filled in the accumulator group.

5. The rocket erection frame rapid fallback realization system according to claim 2, characterized in that: The oil cylinder small chamber control subsystem includes a first small chamber control valve and a small chamber hydraulic lock; the B oil port of the first small chamber control valve is connected to the A port of the first oil release valve, and its A oil port is connected to the oil inlet of the small chamber hydraulic lock, and the oil outlet of the small chamber hydraulic lock is connected to the small chamber of the erecting cylinder.

6. The rocket erection frame rapid fallback realization system according to claim 2, characterized in that: The oil cylinder large cavity control subsystem includes a first proportional pressure valve, a first large cavity control valve and a large cavity hydraulic lock; the B port of the first proportional pressure valve is connected to the oil return port, and its A port is connected to the A oil port of the first large cavity control valve, the B oil port of the first large cavity control valve is connected to the oil inlet of the large cavity hydraulic lock, and the oil outlet of the large cavity hydraulic lock is connected to the large cavity of the erecting cylinder.

7. The rocket erection frame rapid fallback realization system according to claim 6, characterized in that: The hydraulic lock control subsystem includes a first unlocking valve and a shuttle valve, one end of the first unlocking valve is connected to the control oil port, and the other end of the first unlocking valve is connected to the small cavity hydraulic lock and the large cavity hydraulic lock through the shuttle valve to control the on and off of the small cavity hydraulic lock and the large cavity hydraulic lock.

8. The rocket erection frame rapid fallback realization system according to claim 7, characterized in that: A small cavity unlocking pressure sensor is arranged on the pipeline connecting the shuttle valve and the small cavity hydraulic lock, and the small cavity unlocking pressure sensor is used to detect the unlocking action of the small cavity hydraulic lock; a large cavity unlocking pressure sensor is arranged on the pipeline connecting the shuttle valve and the large cavity hydraulic lock, and the large cavity unlocking pressure sensor is used to detect the unlocking action of the large cavity hydraulic lock.

9. The rocket erection frame rapid fallback realization system according to claim 8, characterized in that: A small cavity pressure sensor is arranged on the pipeline connecting the small cavity hydraulic lock and the small cavity of the erecting cylinder, and the small cavity pressure sensor is used to detect the small cavity pressure of the erecting cylinder in real time; a large cavity pressure sensor is arranged on the pipeline connecting the large cavity hydraulic lock and the large cavity of the erecting cylinder, and the large cavity pressure sensor is used to detect the large cavity pressure of the erecting cylinder in real time.

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