阅读说明：本技术 火箭发动机地面点火试验系统、方法、终端设备及介质 (Rocket engine ground firing system, method, terminal device and medium ) 是由 申力夫 陈伟 马超 舒畅 于 2019-08-22 设计创作，主要内容包括：本申请公开了一种火箭发动机地面点火试验系统、方法、终端设备及介质。其中试验系统,包括点火试验工装、用于模拟火箭上控制设备的综控机、通过预埋电缆与综控机信号连接的综合控制单元、用于采集信号的测控设备；点火试验工装包括L型测试台、位于测试台上的推力小车和设置在测试台上的高架滑轨；用于测试的发动机固定在推力小车上；用于测试的分离系统安装在发动机的后裙上；分离系统可滑动地与高架滑轨上的滑轨连接；综控机通过综合控制电缆与发动机和分离系统信号连接,综控机上配置有发动机所要应用的火箭的控制时序一致的控制程序；本申请增加了试验的测试覆盖性,可以进一步应用于发动机点火试验中。(This application discloses a kind of rocket engine ground firing system, method, terminal device and media.Wherein pilot system, the comprehensive control machine that equipment is controlled including fire trial tooling, on simulated rocket, comprehensively control unit, the measuring and controlling equipment for acquiring signal being connect by pre-buried cable with comprehensive control machine signal；Fire trial tooling includes L-type testboard, the thrust trolley on testboard and the high frame sliding track being arranged on testboard；Engine for test is fixed on thrust trolley；Separation system for test is mounted on the rear skirt of engine；Separation system is slideably connect with the sliding rail on high frame sliding track；Comprehensive control machine is connect by Separated-screening comprehensive control cable with engine and separation system signal, be configured on comprehensive control machine engine rocket to be applied the consistent control program of control sequential；The application increases the test coverage of test, can further apply in engine ignition test.)

1. a kind of rocket engine ground firing system, which is characterized in that including fire trial tooling, be used for simulated rocket The comprehensive control machine of upper control equipment, the comprehensively control unit being connect by pre-buried cable with the comprehensive control machine signal are believed for acquiring Number measuring and controlling equipment；

The fire trial tooling includes L-type testboard, the thrust trolley on testboard and the height being arranged on testboard Frame sliding track；Engine for test is fixed on the thrust trolley；Separation system for test is fixed on described start In the rear skirt of machine；The separation system is slidably disposed on the high frame sliding track；

The comprehensive control machine is connect by Separated-screening comprehensive control cable with the engine and separation system, is configured on the comprehensive control machine State engine rocket to be applied the consistent control program of control sequential；

The comprehensive control machine is configured to, according to the control program in the firing command for receiving the comprehensively control unit sending Afterwards, it successively controls the separation system separating ignition and controls the engine ignition；

The measuring and controlling equipment is connect with the in-engine sensor signal.

2. rocket engine ground firing system according to claim 1, which is characterized in that the motor head It is connected with thrust adapter frame；Thrust pickup is provided between the thrust adapter frame and the upright side walls of the testboard；Institute Thrust pickup is stated to connect with the measuring and controlling equipment signal.

3. rocket engine ground firing system according to claim 1, which is characterized in that the separation system packet Include the endpiece being fixed in the rear skirt of the engine, the sliding machine being fixedly connected with the endpiece；The sliding machine with The high frame sliding track slidable connection.

4. according to claim 1 to rocket engine ground firing system described in 3 any one, which is characterized in that institute It states and is provided with interconnecting device between comprehensive control machine and the comprehensively control unit.

5. a kind of test method using rocket engine ground firing system described in Claims 1-4 any one, Characterized by comprising the following steps:

Receive the firing command that the comprehensively control unit is sent by the pre-buried cable；

According to the engine rocket to be applied control sequential issue control instruction, specifically include:

Separation firing command is issued to the separation system,

Upper surface, which is issued, to the separation system divides plug-in split instruction,

Firing command is sent to the engine simultaneously and sends Timing Signal to the comprehensively control unit；It is adopted by measuring and controlling equipment Collect the signal of in-engine sensor.

6. a kind of terminal device, including memory, processor and storage are in the memory and can be on the processor The computer program of operation, which is characterized in that the processor is realized as claimed in claim 5 when executing the computer program The step of test method of rocket engine ground firing system.

7. a kind of computer readable storage medium, the computer readable storage medium has computer program, which is characterized in that institute State the test that rocket engine ground firing system as claimed in claim 5 is realized when computer program is executed by processor The step of method.

Technical field

The present disclosure relates generally to rocket firing experimental technique fields, and in particular to rocket engine ground firing system System, method, terminal device and medium.

Background technique

The product that is currently used for participating in the experiment in the solid engines ground firing method of rocket launching is divided into two parts: 1, Engine system, including igniter motor and separation system；As test main object, test main purpose is igniter motor Its related performance indicators is obtained, separation system mainly verifies engine separation timing；2, flooring product, including control system and survey Test system.Control system generally uses dedicated program control engine and separation system work, and test macro main function is to adopt Collect engine performance data.

Ground control system generally takes general program in timing control equipment to engine system in current test method System work is controlled, and the performance parameter and work separation timing just for engine carry out verification experimental verification；Work as engine application When it is by rocket launching to be applied, still will appear working sequence and test when it is inconsistent due to, out The case where existing power failure, influence the operation of the whole arrow of rocket.

Summary of the invention

In view of drawbacks described above in the prior art or deficiency, it is intended to provide a kind of rocket engine ground firing system System, method, terminal device and storage medium.

In a first aspect, the application provides a kind of rocket engine ground firing system, including fire trial tooling, use In the comprehensive control machine that equipment is controlled on simulated rocket, the comprehensively control unit being connect with the comprehensive control machine signal by pre-buried cable, For acquiring the measuring and controlling equipment of signal；

The fire trial tooling includes L-type testboard, the thrust trolley on testboard and is arranged on testboard High frame sliding track；Engine for test is fixed on the thrust trolley；Separation system for test is mounted on described In the rear skirt of engine；The separation system is slidably disposed on the high frame sliding track；

The comprehensive control machine is connect by Separated-screening comprehensive control cable with the engine and separation system signal, on the comprehensive control machine Configured with the engine rocket to be applied the consistent control program of control sequential；

The comprehensive control machine is configured to, according to the control program in the igniting for receiving the comprehensively control unit sending After instruction, successively controls the separation system separating ignition and control the engine ignition；

The measuring and controlling equipment is connect with the in-engine sensor signal.

According to technical solution provided by the embodiments of the present application, the motor head is connected with thrust adapter frame；It is described to push away Thrust pickup is provided between power adapter frame and the upright side walls of the testboard；The thrust pickup is set with the observing and controlling Standby signal connects.

According to technical solution provided by the embodiments of the present application, the separation system includes being fixed on the rear skirt of the engine On endpiece, the sliding machine that is fixedly connected with the endpiece；The sliding machine and the high frame sliding track slidable connection.

According to technical solution provided by the embodiments of the present application, it is provided between the comprehensive control machine and the comprehensively control unit Interconnecting device.

Second aspect, the application provide a kind of test method such as above-mentioned rocket engine ground firing system, The following steps are included:

Receive the firing command that the comprehensively control unit is sent by the pre-buried cable；

According to the engine rocket to be applied control sequential issue control instruction, specifically include:

Separation firing command is issued to the separation system,

Upper surface, which is issued, to the separation system divides plug-in split instruction,

Firing command is sent to the engine simultaneously and sends Timing Signal to the comprehensively control unit；It is set by observing and controlling The standby signal for acquiring in-engine sensor.

The third aspect, the application provide a kind of terminal device, including memory, processor and are stored in the memory In and the computer program that can run on the processor, which is characterized in that the processor executes the computer program The step of test method of for example above-mentioned rocket engine ground firing system of Shi Shixian.

Fourth aspect, the application provide a kind of computer readable storage medium, and the computer readable storage medium has meter Calculation machine program realizes the examination such as above-mentioned rocket engine ground firing system when the computer program is executed by processor The step of proved recipe method.

Technical solution provided by the present application, by making the engine of igniting test to needs in engine ignition is tested Be equipped with proprietary comprehensive control machine, on the comprehensive control machine configured with the engine rocket to be applied the consistent control of control sequential Program；Therefore in the experimental stage, ground control system is controlled using whole arrow original state electrical system, can be sent out in examination On the basis of motivation performance parameter and work separation timing, further examination includes the comprehensive control machine state of whole arrow, cable net state, control Program correctness processed etc. increases the test coverage of test；Test method has a wide range of application, and can further apply and start Machine igniting-jet vane joint test run is tested, in the test such as engine ignition-flexible joint nozzle joint test run.

Detailed description of the invention

By reading a detailed description of non-restrictive embodiments in the light of the attached drawings below, the application's is other Feature, objects and advantages will become more apparent upon:

Fig. 1 is the functional block diagram of the first embodiment of the application；

Fig. 2 is the structural schematic diagram of igniting test tool in the first embodiment of the application；

Fig. 3 is the flow chart of embodiment in the application second；

Fig. 4 is the functional block diagram of the third embodiment of the application.

Figure label:

10, fire trial tooling；20, comprehensive control machine；30, comprehensively control unit；31, the first control power supply；40, engine； 50, separation system；11, testboard；12, thrust trolley；60, Separated-screening comprehensive control cable；41, thrust adapter frame；42, thrust senses Device；51, endpiece；52, forward's connector analog part；53, fixing tool；54, directive wheel；21, the second control power supply；32, pre-buried cable； 55, high frame sliding track；80, measuring and controlling equipment.

Specific embodiment

The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched The specific embodiment stated is used only for explaining related invention, rather than the restriction to the invention.It also should be noted that in order to Convenient for description, part relevant to invention is illustrated only in attached drawing.

It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.