CN113719379A - Rocket engine torch ignition control end control method and electronic equipment - Google Patents
Rocket engine torch ignition control end control method and electronic equipment Download PDFInfo
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- CN113719379A CN113719379A CN202111093605.6A CN202111093605A CN113719379A CN 113719379 A CN113719379 A CN 113719379A CN 202111093605 A CN202111093605 A CN 202111093605A CN 113719379 A CN113719379 A CN 113719379A
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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
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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Abstract
The embodiment of the invention provides a control method of a rocket engine torch ignition control end and electronic equipment, wherein the control method of the rocket engine torch ignition control end comprises the following steps: in response to the interrupt signal, the ignition control end suspends the execution of the main program and sets an interrupt identifier; the ignition control end executes time sequence operation according to the data bound by the time sequence parameters; after the ignition control end finishes the sequential operation, setting an interruption identifier; the ignition control terminal continues to execute the main routine. The invention adopts an interrupt mode to realize the time sequence operation control, has high priority of the time sequence operation and prevents resources from being occupied by other tasks. The ignition operation performance of the engine torch is more accurate, and the purpose of high-precision control of various indexes of torch ignition of the liquid rocket variable-thrust electric engine is achieved.
Description
Technical Field
The invention relates to the technical field of liquid carrier rocket propulsion systems, in particular to a control method for a rocket engine torch ignition control end and electronic equipment.
Background
No substantive research and engineering realization of the application of the electric pump device on the liquid rocket is available in China, the gas turbine pump device is adopted by the domestic in-service liquid rocket engine and used for a propellant supply system, and the torch ignition test scenes of the variable thrust electric engine suitable for the liquid rocket are also in a laboratory. In a traditional engine system, the ignition of an engine torch is generally designed based on Microsoft platforms such as VC and VS, an operating system is used for scheduling and executing the completion of operations such as instruction issuing and control, time sequence data and data interpretation, and all actions are integrated on the same software to complete the action control of corresponding time nodes. The software developed by the microsoft system ecology has a plurality of defects, such as insufficient control time precision, poor real-time performance and poor reliability, and the portability is poor due to high binding of the microsoft ecology.
Disclosure of Invention
In order to solve at least one of the above technical problems, embodiments of the present invention provide a method for controlling a flare ignition control end of a rocket engine and an electronic device, where a priority of a time sequence operation is high, and resources are prevented from being occupied by other tasks.
In one aspect, an embodiment of the present invention provides a control method for a rocket engine torch ignition control end, including:
in response to the interrupt signal, the ignition control end suspends the execution of the main program and sets an interrupt identifier;
the ignition control end executes time sequence operation according to the data bound by the time sequence parameters;
the ignition control end finishes the time sequence operation and retreats the interrupt identifier;
and the ignition control end continuously executes the main program.
In another aspect, the present invention also provides a readable storage medium having executable instructions thereon, which when executed, cause a computer to perform the steps of the rocket engine torch ignition control end control method described in any one of the preceding claims.
In another aspect, the present invention also provides an electronic device, which includes a processor and a memory, where the memory stores computer program instructions adapted to be executed by the processor, and the computer program instructions, when executed by the processor, implement the steps in the rocket engine flare ignition control end control method described in any one of the above.
The control method of the rocket engine torch ignition control end of the embodiment of the invention adopts an interruption mode to realize time sequence operation control, has high priority of time sequence operation, and prevents resources from being occupied by other tasks. The ignition operation performance of the engine torch is more accurate, and the purpose of high-precision control of various indexes of torch ignition of the liquid rocket variable-thrust electric engine is achieved.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the embodiments of the invention.
FIG. 1 is a schematic flow chart illustrating a method for controlling a flare ignition control end of a rocket engine according to an embodiment of the present invention;
FIG. 2 is another exemplary flow chart of a rocket engine flare ignition control end control method according to an embodiment of the present disclosure;
FIG. 3 is a schematic flow chart illustrating a method for controlling a flare ignition control end of a rocket engine according to an embodiment of the present invention;
FIG. 4 is a schematic overall flow chart of a control method for a flare ignition control end of a rocket engine according to an embodiment of the present invention;
fig. 5 is a schematic diagram of an exemplary structure of the electronic device of the present invention.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and the following description. It should be understood that the detailed description and specific examples, while indicating the embodiments of the invention, are given by way of illustration only. It should be noted that, for convenience of description, only the portions related to the embodiments of the present invention are shown in the drawings.
It should be noted that, in the embodiments of the present invention, features in the embodiments may be combined with each other without conflict. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
It should be noted that, the step numbers in the text are only for convenience of explanation of the specific embodiments, and do not serve to limit the execution sequence of the steps.
The method provided by the embodiment of the present invention can be executed by a relevant processor, and the following description takes the processor as an execution subject as an example. The execution subject can be adjusted according to the specific case, such as a server, an electronic device, a computer, and the like.
The embodiment of the invention provides a control method for a torch ignition control end of a rocket engine, which is suitable for a torch ignition scene of a variable-thrust electric engine of a liquid rocket.
In one aspect of the embodiments of the present invention, referring to fig. 1, a method for controlling a torch ignition control end of a rocket engine is provided, including:
and S11, responding to the interrupt signal, the ignition control end suspends the execution of the main program and sets the interrupt identifier.
And S12, the ignition control terminal executes the time sequence operation according to the data bound by the time sequence parameters. The data bound by the time sequence parameters comprises time sequence operation needing to be executed by an ignition control end, the time sequence operation relates to the operation of an ignition control time sequence, the ignition control time sequence is bound according to the time sequence parameters after receiving a timing signal, appointed valve operation is carried out at corresponding time, the requirements on control precision and reliability are high, the time sequence operation control is realized by adopting an interruption mode, the priority of the time sequence operation is high, and resources are prevented from being occupied by other tasks.
And S13, the ignition control end finishes the sequential operation and sets back the interrupt identifier.
And S14, the ignition control end continues to execute the main program.
The control method of the rocket engine torch ignition control end of the embodiment of the invention adopts an interruption mode to realize time sequence operation control, has high priority of time sequence operation, avoids the risk of occupation of CPU resource time slices, and prevents the resources from being occupied by other tasks. The ignition operation performance of the engine torch is more accurate, the aim of carrying out high-precision control on various indexes of torch ignition of the liquid rocket variable-thrust electric engine is fulfilled, and the time precision can reach the ms precision level.
In one implementation of the embodiment of the present invention, referring to fig. 2, the step of S12, the ignition control end performing the timing operation according to the data bound by the timing parameter, includes:
and the ignition control end detects whether the timing signal is received or not, and if the timing signal is not received, the ignition control end continues waiting for the timing signal. In the aerospace activity, the measurement data and events acquired and recorded by each measurement and control station must have the same strict and uniform time standard to be analyzed and processed, so that the application value is realized. The time signal is also used for controlling a program instrument to complete the ignition of the rocket and the missile and enable the instrument to work according to the program. The standardized time system equipment has the functions of time difference measurement, delay correction, leap second, leap year, time setting, fault alarm and the like, has high reliability and stability, is distributed in each large measurement and control station, and provides a unified time frequency signal format for the measurement and control equipment, namely a time system signal.
Responding to the timing signal, the ignition control end executes the periodic issuing of the timing data, the periodic issuing of the timing data relates to real-time data processing, after the timing signal is received, the periodic issuing of the real-time periodic 10ms timing data such as torch state, valve state, sensor data and the like is carried out every 10ms period, and the method comprises the following steps:
framing the issued time sequence data; and when the issued time sequence data are framed, the ignition control end numbers all the time sequence data.
Optionally, the time-series data is periodic 10ms time-series data. The timing data includes at least one of torch status, valve status, and sensor data.
In the process of issuing the periodic real-time data, in order to prevent data loss caused by factors such as bus interference, Bit overturn and the like from being difficult to interpret, when data are issued for framing, all periodic time sequence data are numbered, and the problem that the conventional engine torch ignition real-time drawing data are lost and difficult to check can be solved. That is to say, the problem that real-time data is lost and difficult to check is solved by numbering time series data through framing, and the interpretation efficiency is improved.
The problem that data are lost and difficult to investigate can be solved by numbering the time sequence data, correspondingly, if the numbers are arranged in sequence, the difficulty of cracking the data is easily reduced, the data are easily stolen, and if the numbers are arranged in non-sequence, the reduction effect on the difficulty of real-time data loss and investigation is limited. Therefore, in an optional embodiment, during the process of numbering the sequential data, a third data group is generated according to the first data group which is not repeated and out of order and the second data group which is not repeated and in order, the sequential data is numbered by using the data in the third data group, the ignition control device checks the sequential data lost by the stream according to the third data group and the first data group, wherein optionally, each data in the third data group is the sum of the data in the corresponding second data group and the second data, when the ignition control device checks the sequential data lost by the stream according to the third data group and the first data group, the third data group can be obtained according to the numbered sequential data, the second data group is obtained by subtracting the first data group from the third data group, and the lost sequential data is determined according to whether the data lost in the second data group or not. Illustratively, the first data group is [3, 5, 1], the second data group is [1, 2, 3], then, the third data group is [4, 7, 4], since the time series data is numbered by the third data group, the third data group is [4, 7, 4] can be obtained according to the number of the time series data, and then, according to the first data group [3, 5, 1], the second data group [1, 2, 3] can be obtained by calculation, and since the second data group is sequential data, the lost data in the second data group can be rapidly judged. The first data group is stored in advance, and when the time series data is illegally acquired, the third data group is out of order, so that the actual order of the time series data cannot be known under the condition that the first data group is not known, and an illegal acquirer is difficult to decode and restore the time series data according to the number, thereby improving the safety. In one implementation of the embodiment of the invention, referring to fig. 3, the rocket engine torch ignition control end control method further includes:
and the ignition control end detects whether the binding instruction is a time sequence parameter binding instruction, wherein the time sequence parameter binding instruction comprises time sequence parameter binding data.
And responding to the time sequence parameter binding instruction, and detecting whether a timing signal is received by the ignition control end.
In one implementation manner of the embodiment of the invention, if the ignition control end detects that the time sequence parameter binding instruction is not the time sequence parameter binding instruction, the control instruction is executed; and replying the terminal instruction end software response message.
Optionally, the performing, by the ignition control end, the time sequence operation according to the data bound by the time sequence parameter includes:
and the ignition control end detects whether the timing signal is received or not, and if the timing signal is not received, the ignition control end continues waiting for the timing signal.
And responding to the timing signal, and executing a periodic real-time control process by the ignition control end.
The ignition control end detects whether the periodic real-time control process is finished or not;
if the control is finished, otherwise, the periodic real-time control process is continuously executed.
Referring to fig. 4, a preferred example of a complete control flow is given below to understand the control method of the present invention.
After the system is started, the ignition control end receives a control command of the command end.
Checking whether the frame format is correct, and if not, directly ending the whole control flow.
If the frame format is correct, the instruction type is judged.
If the time sequence binding instruction is not the time sequence binding instruction, executing the control instruction; and continuing to execute the reply terminal instruction end software response message.
If the order is a time sequence binding order, waiting for a time sequence signal; detecting whether a timing signal is received or not, and if not, continuing to wait; if a timing signal is received, a periodic real-time control process is performed.
Detecting whether the control period is finished;
if the control period is over, the whole control flow is ended, otherwise, the periodic real-time control process is continuously executed.
In summary, the control method for the rocket engine torch ignition control end in the embodiment of the invention has the following advantages:
1. the time sequence operation control is realized by adopting an interruption mode, the priority of the time sequence operation is high, the risk that a CPU resource time slice is occupied is avoided, and the resource is prevented from being occupied by other tasks. The ignition operation performance of the engine torch is more accurate, the aim of carrying out high-precision control on various indexes of torch ignition of the liquid rocket variable-thrust electric engine is fulfilled, and the time precision can reach the ms precision level.
2. All the periodic time sequence data are numbered, so that the problem that the conventional engine torch ignition real-time drawing data are lost and difficult to check can be solved. That is to say, the problem that real-time data is lost and difficult to check is solved by numbering time series data through framing, and the interpretation efficiency is improved.
In yet another aspect of the embodiments of the present invention, there is also provided a readable storage medium having executable instructions thereon that, when executed, cause a computer to perform the steps in the rocket engine flare ignition control end control method of any one of the preceding claims.
In another aspect of the embodiment of the present invention, an electronic device is further provided, and the exemplary structure of the electronic device shown in fig. 5 includes a communication interface 1000, a memory 2000 and a processor 3000. The communication interface 1000 is used for communicating with an external device to perform data interactive transmission. The memory 2000 has stored therein a computer program that is executable on the processor 3000. The number of the memory 2000 and the processor 3000 may be one or more.
If the communication interface 1000, the memory 2000 and the processor 3000 are implemented independently, the communication interface 1000, the memory 2000 and the processor 3000 may be connected to each other through a bus to complete communication therebetween. The bus may be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus, an Extended Industry Standard Architecture (EISA) bus, or the like. The bus may be divided into an address bus, a data bus, a control bus, etc. For ease of illustration, only one thick line is shown, but this does not represent only one bus or one type of bus.
Optionally, in a specific implementation, if the communication interface 1000, the memory 2000, and the processor 3000 are integrated on a chip, the communication interface 1000, the memory 2000, and the processor 3000 may complete communication with each other through an internal interface.
The processor is used for executing one or more steps of the control method of the rocket engine torch ignition control end in any embodiment. The processor may be a Central Processing Unit (CPU), or may be other general-purpose processor, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other programmable logic device, a discrete gate or transistor logic device, a discrete hardware component, or the like. Wherein a general purpose processor may be a microprocessor or the processor may be any conventional processor or the like. Preferably, a multi-core based digital signal processor, such as multi-core digital signal processor FT-Q6713J/500R, is used, the time accuracy can reach the ms accuracy level.
The memory has stored therein computer program instructions adapted to be executed by the processor, the computer program instructions, when executed by the processor, performing one or more steps of the rocket engine flare ignition control end control method of any of the above embodiments.
The Memory may be a Read-Only Memory (ROM) or other type of static storage device that can store static information and instructions, a Random Access Memory (RAM) or other type of dynamic storage device that can store information and instructions, an Electrically Erasable Programmable Read-Only Memory (EEPROM), a Compact Disc Read-Only Memory (CD-ROM) or other optical Disc storage, optical Disc storage (including Compact Disc, laser Disc, optical Disc, digital versatile Disc, blu-ray Disc, etc.), magnetic disk storage media or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and that can be accessed by a computer, but is not limited to these. The memory may be self-contained and coupled to the processor via a communication bus. The memory may also be integral to the processor.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the embodiments of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise. Meanwhile, in the description of the embodiments of the present invention, unless explicitly specified or limited otherwise, the terms "connected" and "connected" should be interpreted broadly, for example, as being fixedly connected, detachably connected, or integrally connected; the connection can be mechanical connection or electrical connection; may be directly connected or indirectly connected through an intermediate. Specific meanings of the above terms in the embodiments of the present invention can be understood by those of ordinary skill in the art according to specific situations.
It should be understood by those skilled in the art that the foregoing embodiments are merely for illustrating the embodiments of the present invention clearly and are not intended to limit the scope of the embodiments of the present invention. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are within the scope of the embodiments of the invention.
Claims (10)
1. A control method for a rocket engine torch ignition control end is characterized by comprising the following steps:
in response to the interrupt signal, the ignition control end suspends the execution of the main program and sets an interrupt identifier;
the ignition control end executes time sequence operation according to the data bound by the time sequence parameters;
the ignition control end finishes the time sequence operation and retreats the interrupt identifier;
and the ignition control end continuously executes the main program.
2. A rocket engine torch ignition control end control method according to claim 1, wherein said ignition control end executing timing operations according to the data bound by timing parameters comprises:
the ignition control end detects whether a timing signal is received or not;
responding to the timing system signal, the ignition control end executes the periodical issuing of the time sequence data, and the periodical issuing of the time sequence data comprises the following steps: and when the issued time sequence data are framed, the ignition control end numbers all the time sequence data.
3. A rocket engine torch ignition control end control method according to claim 2, wherein said timing data is periodic 10ms timing data.
4. A rocket engine torch ignition control end control method as recited in claim 2, wherein said timing data includes at least one of torch status, valve status, and sensor data.
5. A rocket engine torch ignition control end control method as recited in claim 2, further comprising:
the ignition control end detects whether the time sequence parameter binding instruction is a time sequence parameter binding instruction, and the time sequence parameter binding instruction comprises time sequence parameter binding data;
and responding to the time sequence parameter binding instruction, and detecting whether a timing signal is received by the ignition control end.
6. A rocket engine torch ignition control end control method according to claim 5, characterized in that said ignition control end detects whether it is a time sequence parameter binding command;
if not, executing the control instruction; and replying the terminal instruction end software response message.
7. A rocket engine torch ignition control end control method according to claim 1, wherein said ignition control end executing timing operations according to the data bound by timing parameters comprises:
the ignition control end detects whether a timing signal is received or not;
responding to the timing signal, and executing a periodic real-time control process by the ignition control end;
the ignition control end detects whether the control period is finished or not;
and if the control period is finished, ending the whole control flow, otherwise, continuously executing the periodic real-time control process.
8. A readable storage medium having executable instructions thereon that, when executed, cause a computer to perform the steps in the rocket engine flare ignition control end control method of any one of claims 1-7.
9. An electronic device, characterized in that the device comprises a processor and a memory, in which computer program instructions adapted to be executed by the processor are stored, which computer program instructions, when executed by the processor, perform the steps in the rocket engine flare ignition control end control method according to any one of claims 1-7.
10. The electronic device of claim 9, wherein the processor is a multi-core digital signal processor.
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