阅读说明：本技术 一种火箭发动机火炬点火控制方法 (Rocket engine torch ignition control method ) 是由 不公告发明人 于 2020-07-07 设计创作，主要内容包括：本公开提供了一种火箭发动机火炬点火控制方法,包括如下步骤：系统初始化；综合控制端系统接收终端指令端系统下发的指令；检测到时统信号时,综合控制端系统在固定的控制周期内执行周期性实时控制至控制周期结束；当接收到非周期性指令时,综合控制端系统执行非周期性指令,并将执行结果返回给终端指令端系统。本公开所述的火箭发动机火炬点火控制方法,由终端指令端系统与综合控制端系统共同控制,终端指令端系统采用的Qt平台,综合控制端系统运行于数字信号处理器上。可以解决传统发动机火炬点火时间控制精度不足、实时绘图数据丢失难排查、可移植性差的问题。(The present disclosure provides a rocket engine torch ignition control method, which comprises the following steps: initializing a system; the comprehensive control end system receives an instruction issued by the terminal instruction end system; when a timing signal is detected, the comprehensive control end system executes periodic real-time control in a fixed control period until the control period is finished; and when the aperiodic command is received, the comprehensive control end system executes the aperiodic command and returns the execution result to the terminal command end system. The rocket engine torch ignition control method disclosed by the disclosure is controlled by a terminal instruction end system and a comprehensive control end system together, wherein the terminal instruction end system adopts a Qt platform, and the comprehensive control end system runs on a digital signal processor. The method can solve the problems of insufficient control precision of the torch ignition time of the traditional engine, difficult investigation of loss of real-time drawing data and poor transportability.)

1. A rocket engine torch ignition control method is characterized in that: the method comprises the following steps:

initializing a system;

the comprehensive control end system receives an instruction issued by a terminal instruction end system, wherein the instruction is an instruction with a correct frame format;

the comprehensive control end system judges the type of the received instruction, wherein the type of the instruction comprises a time sequence binding instruction and a non-periodic instruction;

when a time sequence binding instruction is received, comprehensively controlling a terminal system to wait for a time sequence signal; when a timing system signal is detected, the comprehensive control end system executes periodic real-time control in a fixed control period until the control period is finished;

when receiving the non-periodic instruction, the integrated control end system executes the non-periodic instruction and returns an execution result to the terminal instruction end system;

the terminal instruction end system is a control terminal system for displaying an interface and agrees with a communication protocol with the comprehensive control end system; the terminal instruction end system issues an agreed communication protocol, the comprehensive control end system completes the execution of the protocol function, and the terminal instruction end system displays the protocol execution result on a display interface;

the comprehensive control end system runs on the digital signal processor;

the terminal instruction end system is developed based on a Qt platform.

2. A rocket engine torch ignition control method as recited in claim 1, wherein:

the comprehensive control end system comprises an aperiodic instruction processing module, a torch ignition control time sequence module and a periodic data issuing module:

the aperiodic command processing module: receiving an aperiodic command, binding time sequence parameters according to the aperiodic command, or checking an engine sensor and a valve, and returning a result of whether the execution of the aperiodic command is successful to a terminal command end system;

the torch ignition control sequence module is characterized in that: after receiving the timing signal, switching on the interrupt, entering a fixed control period operation mode according to the timing parameters bound by the terminal instruction end system before ignition, and executing periodic real-time control at the timing parameter point;

the periodic data issuing module: after receiving the timing signal, periodically issuing the traffic data in a fixed control period, and returning a characteristic data result to the terminal instruction end system; the characteristic data includes engine pump controller speed data, engine sensor status, valve status, flare status, time consuming information.

3. A rocket engine torch ignition control method as recited in claim 2, wherein:

the comprehensive control end system runs on a digital signal processor, and more than one inner core is arranged in the digital signal processor.

4. A rocket engine torch ignition control method as recited in claim 3, wherein:

the comprehensive control end system runs on a digital signal processor, the digital signal processor is FT-Q6713J/500R, and 4 cores with dominant frequencies of 500MHz are built in the digital signal processor.

5. A rocket engine torch ignition control method as recited in claim 1, wherein:

the terminal instruction end system comprises a non-periodic instruction control module and a real-time periodic time sequence data receiving and processing module;

the aperiodic instruction control module issues an aperiodic instruction before a timing signal, wherein the aperiodic instruction comprises an engine sensor, a valve initialization check and test, and a binding time sequence parameter;

the real-time periodic time sequence data receiving and processing module receives an instruction execution result and characteristic data returned by the comprehensive control end system, wherein the instruction execution result is the result of whether the non-periodic instruction execution is successful, and the characteristic data comprises the rotating speed data of an engine pump controller, the state of an engine sensor, the state of a valve, the state of a torch and time consumption information.

6. A rocket engine torch ignition control method according to claim 5, characterized in that:

the terminal instruction end system generates a software configuration item by configuring an XML file and tests the software configuration item; when configuring the XML file, constructing according to the multilevel tree structure design; the tree structure configuration takes an electric motor display control terminal control system as a top level menu item, comprises more than 1 test menu and comprises more than 1 configuration item test under each test menu.

7. A rocket engine torch ignition control method as recited in claim 1, wherein:

the fixed control period is 5ms-20 ms.

8. A rocket engine torch ignition control method as recited in claim 7, wherein: the fixed control period is 5ms-20 ms.

9. A rocket engine torch ignition control method as recited in claim 8, wherein: the fixed control period is 10 ms.

10. A rocket engine torch ignition control method as recited in claim 1, wherein: the time system signal is a direct current 28V high-level pulse lasting for more than 100 ms.

Technical Field

The disclosure belongs to the technical field of engines, and particularly relates to a rocket engine torch ignition control method.

Background

At present, in-service liquid rocket engines in China all adopt a gas turbine pump device for a propellant supply system, substantive research and engineering realization of application of an electric pump device on a liquid rocket are not available in China, and torch ignition scenes of variable thrust electric engines suitable for the liquid rocket are also in laboratories.

In a traditional rocket system, the ignition of an engine torch is generally designed based on a Windows platform to complete the action control of a corresponding time node. The development environment is mostly the microsoft system ecological development software used, such as VC, VS and other software, although it has good operability and graphic development capability, its reliability is poor, control accuracy is not enough, and it is highly bound with microsoft ecology, which easily causes repeated development of software, and wastes manpower, material resources and financial resources.

Disclosure of Invention

To address at least one of the above technical problems, the present disclosure provides a rocket engine torch ignition control method.

The technical scheme of the disclosure is as follows:

a rocket engine torch ignition control method comprises the following steps:

initializing a system;

the comprehensive control end system receives an instruction issued by a terminal instruction end system, wherein the instruction is an instruction with a correct frame format;

the comprehensive control end system judges the type of the received instruction, wherein the type of the instruction comprises a time sequence binding instruction and a non-periodic instruction;

when a time sequence binding instruction is received, comprehensively controlling a terminal system to wait for a time sequence signal; when a timing system signal is detected, the comprehensive control end system executes periodic real-time control in a fixed control period until the control period is finished;

when receiving the non-periodic instruction, the integrated control end system executes the non-periodic instruction and returns an execution result to the terminal instruction end system;

the terminal instruction end system is a control terminal system for displaying an interface and agrees with a communication protocol with the comprehensive control end system; the terminal instruction end system issues an agreed communication protocol, the comprehensive control end system completes the execution of the protocol function, and the terminal instruction end system displays the protocol execution result on a display interface;

the comprehensive control end system runs on the digital signal processor;

the terminal instruction end system is developed based on a Qt platform.

Further, the comprehensive control end system comprises an aperiodic command processing module, a torch ignition control time sequence module and a periodic data issuing module:

the aperiodic command processing module: receiving an aperiodic command, binding time sequence parameters according to the aperiodic command, or checking an engine sensor and a valve, and returning a result of whether the execution of the aperiodic command is successful to a terminal command end system;

the torch ignition control sequence module is characterized in that: after receiving the timing signal, switching on the interrupt, entering a fixed control period operation mode according to the timing parameters bound by the terminal instruction end system before ignition, and executing periodic real-time control at the timing parameter point;

the periodic data issuing module: after receiving the timing signal, periodically issuing the traffic data in a fixed control period, and returning a characteristic data result to the terminal instruction end system; the characteristic data includes engine pump controller speed data, engine sensor status, valve status, flare status, time consuming information.

Furthermore, the integrated control end system runs on a digital signal processor, and more than one inner core is arranged in the digital signal processor.

Furthermore, the digital signal processor is FT-Q6713J/500R, and 4 cores with main frequency of 500MHz are built in the digital signal processor.

Furthermore, the terminal instruction end system comprises a non-periodic instruction control module and a real-time periodic time sequence data receiving and processing module;

the aperiodic instruction control module issues an aperiodic instruction before a timing signal, wherein the aperiodic instruction comprises an engine sensor, a valve initialization check and test, and a binding time sequence parameter;

the real-time periodic time sequence data receiving and processing module receives an instruction execution result and characteristic data returned by the comprehensive control end system, wherein the instruction execution result is the result of whether the non-periodic instruction execution is successful, and the characteristic data comprises the rotating speed data of an engine pump controller, the state of an engine sensor, the state of a valve, the state of a torch and time consumption information.

Furthermore, the terminal instruction end system generates a software configuration item by configuring an XML file and tests the software configuration item; when configuring the XML file, constructing according to the multilevel tree structure design; the tree structure configuration takes an electric motor display control terminal control system as a top level menu item, comprises more than 1 test menu and comprises more than 1 configuration item test under each test menu.

Further, the fixed control period is 5ms-20 ms.

Further, the fixed control period is 10 ms.

Further, the timing signal is a dc 28V high-level pulse lasting for more than 100 ms.

The method is used for instruction control of torch ignition of the liquid rocket variable thrust electric engine and real-time issuing of torch data, and is an important basis for success or failure of torch ignition of the variable thrust electric engine. The advantages are that:

1. the comprehensive control end system runs on the DSP, replaces the traditional Windows ecological software, has high reliability and high time control precision, can process the receiving and processing of large-scale data transmission, and can achieve the us precision level; and the portability of the system is strong, and the problem of waste of manpower, material resources and financial resources caused by repeated development of traditional engine control software is avoided.

2. When the comprehensive control end system issues the real-time periodic time sequence data, all the periodic time sequence data are numbered through framing of the data, so that if the data are lost, the data can be easily tracked and intuitively reflected to the terminal instruction end system; in order to visually see the data loss phenomenon, the terminal command end system takes the serial number of the data as an X axis and the state data as a Y axis for analysis and display during drawing. If the data number is lost, the graph can lose the data point, and the problem of data loss can be reflected very intuitively.

3. The rocket engine display control terminal control system is developed based on Qt, the Qt has strong portability, allows component programming, is designed and developed through a low coupling idea, and has better reusability, maintainability and expandability; the lightweight XML technology is used for replacing the traditional heavyweight database technology, and the software configuration items are generated by configuring the XML, so that the system is high in practicability, flexible and convenient.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.

FIG. 1 is a schematic flow chart illustrating the operation of one embodiment of the rocket engine integrated control according to the present disclosure.

Fig. 2 is a block diagram of a terminal command end system according to the present disclosure.

Fig. 3 is a block diagram of an integrated control end system according to the present disclosure.

Detailed Description

The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.