CN110529292B - Rocket engine ground ignition test system, method, terminal device and medium - Google Patents
Rocket engine ground ignition test system, method, terminal device and medium Download PDFInfo
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- CN110529292B CN110529292B CN201910778438.5A CN201910778438A CN110529292B CN 110529292 B CN110529292 B CN 110529292B CN 201910778438 A CN201910778438 A CN 201910778438A CN 110529292 B CN110529292 B CN 110529292B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The application discloses a rocket engine ground ignition test system, a rocket engine ground ignition test method, terminal equipment and a medium. The test system comprises an ignition test tool, a comprehensive control machine for simulating control equipment on the rocket, a comprehensive control unit in signal connection with the comprehensive control machine through an embedded cable, and measurement and control equipment for acquiring signals; the ignition test tool comprises an L-shaped test bench, a thrust trolley positioned on the test bench and an elevated slide rail arranged on the test bench; the engine for testing is fixed on the thrust trolley; the separation system for testing is arranged on the rear skirt of the engine; the separation system is connected with the slide rail on the elevated slide rail in a sliding way; the comprehensive control machine is in signal connection with the engine and the separation system through a comprehensive control cable, and the control time sequence of a control program configured on the comprehensive control machine is consistent with the control time sequence of a rocket to be applied by the engine; the application increases the test coverage of the test, and can be further applied to the engine ignition test.
Description
Technical Field
The present disclosure relates generally to the field of rocket ignition testing techniques, and more particularly to a rocket engine ground ignition testing system, method, terminal device, and medium.
Background
In the existing solid engine ground ignition test method for rocket launching, test products are divided into two parts: 1. an engine system comprising an ignition engine and a disconnect system; the ignition engine is used as a main test object, the main purpose of the test is to obtain relevant performance indexes, and the separation system mainly verifies the separation time sequence of the engine; 2. a ground product comprises a control system and a test system. The control system generally adopts a special program to control the engine and the separation system to work, and the test system is mainly used for collecting the performance data of the engine.
In the current test method, a ground control system generally adopts a general program to control the work of an engine system on a time sequence control device, and only tests and verifies the performance parameters and the work separation time sequence of the engine; when the engine is applied to the launching of the rocket to be applied, the condition of engine failure caused by inconsistent working time sequence and testing still occurs, and the operation of the whole rocket is influenced.
Disclosure of Invention
In view of the above-mentioned deficiencies or inadequacies in the prior art, it would be desirable to provide a rocket engine ground ignition testing system, method, terminal device, and storage medium.
In a first aspect, the application provides a rocket engine ground ignition test system, which comprises an ignition test tool, a comprehensive control machine for simulating control equipment on a rocket, a comprehensive control unit in signal connection with the comprehensive control machine through a pre-buried cable, and measurement and control equipment for acquiring signals;
the ignition test tool comprises an L-shaped test bench, a thrust trolley positioned on the test bench and an elevated slide rail arranged on the test bench; an engine for testing is fixed on the thrust trolley; a separation system for testing is mounted on the rear skirt of the engine; the separation system is slidably arranged on the overhead sliding rail;
the comprehensive control machine is in signal connection with the engine and the separation system through a comprehensive control cable, and the control time sequence of a control program on the comprehensive control machine is consistent with the control time sequence of a rocket to be applied by the engine;
the integrated control machine is configured for sequentially controlling the separation system to ignite and separate and controlling the engine to ignite after receiving an ignition instruction sent by the integrated control unit according to the control program;
and the measurement and control equipment is in signal connection with a sensor in the engine.
According to the technical scheme provided by the embodiment of the application, the front end of the engine is connected with a thrust adapter bracket; a thrust sensor is arranged between the thrust adapter rack and the vertical side wall of the test board; and the thrust sensor is in signal connection with the measurement and control equipment.
According to the technical scheme provided by the embodiment of the application, the separation system comprises a tail section fixed on a rear skirt of the engine and a sliding trolley fixedly connected with the tail section; the sliding trolley is connected with the elevated slide rail in a sliding manner.
According to the technical scheme provided by the embodiment of the application, a junction box is arranged between the comprehensive control machine and the comprehensive control unit.
In a second aspect, the present application provides a testing method of the rocket engine ground ignition testing system as described above, comprising the steps of:
the comprehensive control machine receives an ignition instruction sent by the comprehensive control unit through the embedded cable;
the comprehensive control machine sends out a control instruction according to the control time sequence of the rocket to be applied by the engine, and the comprehensive control machine specifically comprises the following steps:
the comprehensive control machine sends a separation ignition instruction to the separation system,
the comprehensive control machine sends a cable connector disconnection instruction to the separation system,
the comprehensive control machine sends an ignition instruction to the engine and simultaneously sends a timing signal to the comprehensive control unit; the measurement and control equipment collects signals of sensors in the engine.
In a third aspect, the present application provides a terminal device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the steps of the testing method of the rocket engine ground ignition testing system.
In a fourth aspect, the present application provides a computer readable storage medium having a computer program which, when executed by a processor, performs the steps of the testing method of the rocket engine ground ignition testing system described above.
According to the technical scheme, in the ignition test of the engine, a special comprehensive control machine is arranged for the engine needing the ignition test, and a control program with the consistent control time sequence of rockets to be applied by the engine is configured on the comprehensive control machine; therefore, in the experimental stage, the ground control system is controlled by the whole rocket original state electrical system, the states of the whole rocket comprehensive control machine, the cable network state, the correctness of the control program and the like can be further examined on the basis of examining the performance parameters of the engine and the working separation time sequence, and the test coverage of the test is improved; the test method has wide application range, and can be further applied to tests such as engine ignition-gas rudder combined test, engine ignition-flexible nozzle combined test and the like.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
FIG. 1 is a schematic block diagram of a first embodiment of the present application;
FIG. 2 is a schematic structural diagram of an ignition test fixture in a first embodiment of the present application;
FIG. 3 is a flow chart of a second embodiment of the present application;
fig. 4 is a schematic block diagram of a third embodiment of the present application.
Reference numbers in the figures:
10. an ignition test tool; 20. a comprehensive control machine; 30. a comprehensive control unit; 31. a first control power supply; 40. an engine; 50. a separation system; 11. a test bench; 12. a thrust trolley; 60. A composite control cable; 41. a thrust adapter bracket; 42. a thrust sensor; 51. a tail section; 52. A sliding trolley; 53. fixing the tool; 54. a guide wheel; 21. a second control power supply; 32. pre-burying a cable; 55. an overhead sliding rail; 80. and (5) measurement and control equipment.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
Please refer to fig. 1, which is a schematic block diagram of a rocket engine ground ignition test system in a first embodiment of the present application, the system includes an ignition test tool 10, a comprehensive control machine 20 for simulating control devices on a rocket, and a comprehensive control unit 30 in signal connection with the comprehensive control machine 20 through an embedded cable 32, the comprehensive control unit 30 simulates a ground control end in a measurement and control chamber for rocket launching, and a first control power supply 31 for supplying power to the comprehensive control unit 30 is arranged in the measurement and control chamber; the measurement and control chamber is also provided with measurement and control equipment 80, the measurement and control equipment 80 is equipment for acquiring signals in an engine ignition test, which is not described herein, and signals of each sensor in the engine are merged into the embedded cable 32 through cables and then are connected with the measurement and control equipment 80; the comprehensive control machine 20 is arranged in a test room and close to a test site, and a second control power supply 21 for supplying power to the comprehensive control machine is arranged in the test room;
as shown in fig. 2, the ignition test tool 10 includes an L-shaped test platform 11, a thrust trolley 12 located on the test platform 11, and an overhead rail 55 disposed on the test platform 11; an engine 40 for testing is fixed on the thrust trolley 12; a separation system 50 for testing is mounted on the rear skirt of the engine 40; the separation system is slidably connected to the overhead slide 55;
the integrated control machine 20 is in signal connection with the engine 40 and the separation system 50 through an integrated control cable 60, and the control sequence of the control program on the integrated control machine 20 is consistent with the control sequence of the rocket to be applied by the engine 40.
The integrated control machine 20 is configured to, after receiving an ignition instruction sent by the integrated control unit according to the control program, sequentially control the separation system 50 to ignite and separate and control the engine 40 to ignite, and after receiving the ignition instruction, the integrated control machine not only sends a control instruction to the engine 40 and the separation system 50 through an integrated control cable, but also has the same function as that of an arrow, which is not described in detail.
As shown in fig. 2, a thrust adapter 41 is connected to the front end of the engine 40; a thrust sensor 42 is arranged between the thrust adapter bracket 41 and the vertical side wall of the test bench 11; the thrust sensor 42 is in signal connection with the measurement and control device 80 and is used for sensing the pressure generated in the ignition of the engine.
As shown in fig. 2, in the present embodiment, the separation system 50 includes a tail section 51 fixed on the rear skirt of the engine 40, and a sliding trolley 52 fixedly connected to the tail section 51; a fixing tool 53 is arranged on the side wall of the sliding trolley 52, and a guide wheel 54 is installed at the bottom of the fixing tool 53; the guide wheels 54 are slidably connected to the overhead rail 55. The elevated slide rails 55 and the sliding trolley can ensure that the separated parts of the tail section after being exploded can be orderly moved out along the elevated slide rails 55 without flying in disorder. The separation system 50 adopts a special tool, can simulate the separation working condition and ensures the validity of the separation work check.
The test system can also replace a part connected with the rear skirt of the engine so as to be suitable for different test purposes, such as the tests of engine ignition-gas rudder combined test run and engine ignition-flexible spray pipe combined test run, and the like, so that the test device is wide in application.
In this embodiment, the patch box 70 is disposed on the embedded cable 32, so as to ensure the stability of signal transmission between the integrated control machine and the integrated control unit, and provide a plug-in adaptor for different connection ports of the integrated control machine and the integrated control unit.
Example two
Fig. 3 is a flowchart of a second embodiment of the present application, and the present embodiment is based on the testing method of the rocket engine ground ignition testing system in the first embodiment, and includes the following steps, the default subject of the following steps is the integrated control machine:
s10, the comprehensive control machine receives an ignition instruction sent by the comprehensive control unit through the embedded cable;
sending a control command according to a control time sequence of a rocket to be applied by the engine, which specifically comprises the following steps:
s20, the integrated control machine sends a separation ignition instruction to the separation system, and after the separation system 50 receives the separation ignition instruction, the separation initiating explosive devices in the tail section are ignited, and the tail section 51 is exploded;
s30, the comprehensive control machine sends out a cable plug connector disconnection instruction to the separation system; the cable connector disconnection instruction is sent out after the separation ignition instruction is sent out, and after the separation system receives the signal, the separation section on the separation system is disconnected with the connector on the cable which is left to be partially connected;
s40, the comprehensive control machine sends an ignition instruction to the engine and simultaneously sends a timing signal to a comprehensive control unit; the measurement and control equipment collects signals of sensors in the engine. The timing signal and the ignition instruction are sent out simultaneously, so that the comprehensive control unit can be ensured to effectively monitor various parameters of the engine after ignition, and the time uniformity of ignition test data and ignition test actions is ensured. The engine is ignited after receiving an ignition instruction, and the exploded separation system is far away from the engine along the slide rail under the action of engine jet flow to complete separation and keep away from the working range of the engine.
In the process, the integrated control machine is ignited completely according to the working time sequence of the engine on the rocket, so that the test process of the engine is completely consistent with the actual working process of the engine, and the effectiveness of the test is ensured.
According to the technical scheme, the engine is completely matched with the working time sequence of the rocket working with the engine in the performance test stage, and the validity of the test result is guaranteed.
Example three:
the present embodiment provides a terminal device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above-mentioned un-buried-point socket data processing method when executing the computer program. As shown in fig. 4, the terminal device is, for example, a computer, and the computer system 500 includes a Central Processing Unit (CPU)501 that can perform various appropriate actions and processes according to a program stored in a Read Only Memory (ROM)502 or a program loaded from a storage section into a Random Access Memory (RAM) 503. In the RAM503, various programs and data necessary for system operation are also stored. The CPU501, ROM502, and RAM503 are connected to each other via a bus 504. An input/output (I/O) interface 505 is also connected to bus 504.
The following components are connected to the I/O interface 505: an input portion 506 including a keyboard, a mouse, and the like; an output section including a display such as a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, and a speaker; a storage portion 508 including a hard disk and the like; and a communication section 509 including a network interface card such as a LAN card, a modem, or the like. The communication section 509 performs communication processing via a network such as the internet. The drives are also connected to the I/O interface 505 as needed. A removable medium 511 such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, or the like is mounted on the drive 510 as necessary, so that a computer program read out therefrom is mounted into the storage section 508 as necessary.
In particular, according to an embodiment of the present invention, the processes described above with reference to the flowcharts of fig. 1 to 2 may be implemented as computer software programs. For example, an embodiment of the invention includes a computer program product comprising a computer program embodied on a computer-readable medium, the computer program comprising program code for performing the method illustrated in the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network via the communication section, and/or installed from a removable medium. The above-described functions defined in the system of the present application are executed when the computer program is executed by the Central Processing Unit (CPU) 501.
It should be noted that the computer readable medium shown in the present invention can be a computer readable signal medium or a computer readable storage medium or any combination of the two. A computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples of the computer readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the present invention, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present invention, however, a computer readable signal medium may include a propagated data signal with computer readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated data signal may take many forms, including, but not limited to, electro-magnetic, optical, or any suitable combination thereof. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, fiber optic cable, RF, etc., or any suitable combination of the foregoing.
The flowchart and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams or flowchart illustration, and combinations of blocks in the block diagrams or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The units described in the embodiments of the present invention may be implemented by software, or may be implemented by hardware, and the described units may also be disposed in a processor. Wherein the names of the elements do not in some way constitute a limitation on the elements themselves. The described units or modules may also be provided in a processor, and may be described as: a processor comprises a first generation module, an acquisition module, a search module, a second generation module and a merging module. The names of these units or modules do not in some cases form a limitation to the units or modules themselves, for example, the input module may also be described as "an acquisition module for acquiring a plurality of instances to be detected in the base table".
As another aspect, the present application also provides a computer-readable medium, which may be contained in the electronic device described in the above embodiments; or may exist separately without being assembled into the electronic device. The computer readable medium carries one or more programs which, when executed by an electronic device, cause the electronic device to implement the un-buried-point interpolation data processing method as described in the above embodiments.
For example, the electronic device may implement the following as shown in fig. 3: s10, receiving an ignition instruction sent by the integrated control unit through the embedded cable; sending a control command according to a control time sequence of a rocket to be applied by the engine, which specifically comprises the following steps: s20, sending a separating ignition instruction to the separating system; s30, starting a cable connector disconnection command to the separation system; s40, sending an ignition command and a timing signal to the engine; s50, receiving signals of the engine and the separation system in real time through the integrated control cable.
It should be noted that although in the above detailed description several modules or units of the device for action execution are mentioned, such a division is not mandatory. Indeed, the features and functionality of two or more modules or units described above may be embodied in one module or unit, according to embodiments of the present disclosure. Conversely, the features and functions of one module or unit described above may be further divided into embodiments by a plurality of modules or units.
Moreover, although the steps of the methods of the present disclosure are depicted in the drawings in a particular order, this does not require or imply that the steps must be performed in this particular order, or that all of the depicted steps must be performed, to achieve desirable results. Additionally or alternatively, certain steps may be omitted, multiple steps combined into one step execution, and/or one step broken down into multiple step executions, etc.
Through the above description of the embodiments, those skilled in the art will readily understand that the exemplary embodiments described herein may be implemented by software, or by software in combination with necessary hardware.
The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts of the present invention. The foregoing is only a preferred embodiment of the present invention, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present invention, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention using its spirit and scope, as defined by the claims, may be directed to other uses and embodiments.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (7)
1. A rocket engine ground ignition test system is characterized by comprising an ignition test tool, a comprehensive control machine for simulating control equipment on a rocket, a comprehensive control unit in signal connection with the comprehensive control machine through a pre-buried cable, and measurement and control equipment for acquiring signals;
the ignition test tool comprises an L-shaped test bench, a thrust trolley positioned on the test bench and an elevated slide rail arranged on the test bench; an engine for testing is fixed on the thrust trolley; a separation system for testing is fixed on the rear skirt of the engine; the separation system is slidably arranged on the overhead sliding rail;
the comprehensive control machine is connected with the engine and the separation system through a comprehensive control cable, and the control time sequence of a control program configured on the comprehensive control machine is consistent with the control time sequence of a rocket to be applied by the engine;
the integrated control machine is configured for sequentially controlling the separation system to ignite and separate and controlling the engine to ignite after receiving an ignition instruction sent by the integrated control unit according to the control program;
and the measurement and control equipment is in signal connection with a sensor in the engine.
2. A rocket engine ground ignition test system as recited in claim 1, wherein a thrust adapter is attached to said engine front end; a thrust sensor is arranged between the thrust adapter rack and the vertical side wall of the test board; and the thrust sensor is in signal connection with the measurement and control equipment.
3. A rocket engine ground ignition test system as recited in claim 1, wherein said decoupling system comprises a tail section secured to a rear skirt of said engine, a skid cart fixedly attached to said tail section; the sliding trolley is connected with the elevated slide rail in a sliding manner.
4. A rocket engine ground ignition test system according to any one of claims 1-3, characterized in that an adapter box is arranged between said comprehensive control machine and said comprehensive control unit.
5. A testing method using the rocket engine ground ignition testing system of any one of claims 1 to 4, characterized by comprising the steps of:
the comprehensive control machine receives an ignition instruction sent by the comprehensive control unit through the embedded cable;
the comprehensive control machine sends out a control instruction according to the control time sequence of the rocket to be applied by the engine, and the comprehensive control machine specifically comprises the following steps:
the comprehensive control machine sends a separation ignition instruction to the separation system,
the comprehensive control machine sends a cable connector disconnection instruction to the separation system,
the comprehensive control machine sends an ignition instruction to the engine and simultaneously sends a timing signal to the comprehensive control unit; the measurement and control equipment collects signals of sensors in the engine.
6. A terminal device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor when executing the computer program performs the steps of the testing method of the rocket engine ground ignition testing system recited in claim 5.
7. A computer-readable storage medium, having a computer program stored thereon, wherein the computer program, when executed by a processor, performs the steps of the testing method of the rocket engine ground ignition testing system recited in claim 5.
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| CN201910778438.5A CN110529292B (en) | 2019-08-22 | 2019-08-22 | Rocket engine ground ignition test system, method, terminal device and medium |
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| CN111520256B (en) * | 2020-04-26 | 2021-01-29 | 江苏深蓝航天有限公司 | Rocket engine comprehensive control method |
| CN111441878A (en) * | 2020-05-06 | 2020-07-24 | 航天建筑设计研究院有限公司 | Engine test bed and engine test assembly |
| CN111653151B (en) * | 2020-06-30 | 2022-05-06 | 四川深蓝未来航天科技有限公司 | Rocket launching experience system and rocket launching experience method |
| CN111765018B (en) * | 2020-07-07 | 2021-09-14 | 江苏深蓝航天有限公司 | Rocket engine torch ignition control method |
| CN112555053B (en) * | 2020-11-12 | 2022-02-08 | 蓝箭航天空间科技股份有限公司 | Test time sequence control method and control system for rocket engine |
| CN113945402B (en) * | 2021-08-30 | 2023-06-06 | 北京宇航系统工程研究所 | Ground test system of gas-driven separation device |
| CN114563192A (en) * | 2022-02-10 | 2022-05-31 | 宁波天擎航天科技有限公司 | Solid rocket engine ground test bench and temperature control method |
| CN115111976B (en) * | 2022-08-26 | 2022-11-18 | 北京星河动力装备科技有限公司 | Test run device of carrier rocket and test run method and system thereof |
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