CN114992001A - Control method and control circuit of aircraft engine safety mechanism - Google Patents
Control method and control circuit of aircraft engine safety mechanism Download PDFInfo
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- CN114992001A CN114992001A CN202210576614.9A CN202210576614A CN114992001A CN 114992001 A CN114992001 A CN 114992001A CN 202210576614 A CN202210576614 A CN 202210576614A CN 114992001 A CN114992001 A CN 114992001A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 116
- 238000000034 method Methods 0.000 title claims abstract description 28
- 238000006243 chemical reaction Methods 0.000 claims abstract description 47
- 238000001514 detection method Methods 0.000 claims abstract description 11
- 230000009471 action Effects 0.000 claims abstract description 7
- 230000003111 delayed effect Effects 0.000 claims abstract description 6
- 239000007787 solid Substances 0.000 claims description 13
- 230000007704 transition Effects 0.000 claims description 4
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- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
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- 230000008569 process Effects 0.000 abstract description 8
- 238000012360 testing method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000012544 monitoring process Methods 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003990 capacitor Substances 0.000 description 1
- 238000004590 computer program Methods 0.000 description 1
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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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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Safety Devices In Control Systems (AREA)
Abstract
The invention discloses a control method of an aircraft engine safety mechanism, which comprises the following steps: receiving control information and judging the state of a safety mechanism; when the state is judged to be the first state, the MCU sends a first electromagnetic pin power distribution command and a second electromagnetic pin power distribution command firstly, the first solid-state relay and the second solid-state relay are used for distributing power for the electromagnetic pin action electromagnet, after the first time is delayed, a second state control command is sent out again to control the solid-state motor control module to execute the state conversion of the safety mechanism, and the second time is delayed; and after delaying the second time, judging the state of the safety mechanism again, if the state is the second state, sending out the state conversion success information of the safety mechanism, and if the state is the first state, sending out the state conversion fault alarm information of the safety mechanism. The method introduces a safety mechanism state detection process, not only meets the application requirement of safety mechanism state conversion, but also can detect the safety mechanism state and diagnose faults in real time, and the used circuit has simple and reliable composition form and lower cost.
Description
Technical Field
The invention relates to the technical field of aircraft launching control, in particular to a control method and a control circuit of an aircraft engine safety mechanism.
Background
With the development of rocket engine technology and the requirement for reliability and safety of launching, more and more rocket engines for aerospace, transportation and testing require the use of engine safety mechanisms to increase the safety of the rocket engines in use. In the process of final assembly test and system test, the engine safety mechanism is in a safe state, the possibility of accidental ignition of the engine caused by misoperation and the like can be physically isolated, and the safety of personnel, sites and space vehicles is ensured. When the ignition is formally fired, the safety mechanism of the engine is in a working state, so that a reliable ignition channel of the engine can be ensured, and the normal use is met.
The engine safety mechanism belongs to electromechanical products, the conversion between the safety state and the working state needs to be carried out according to strict time sequence control and state detection procedures, and related circuits in the prior art need to use a large number of electromagnetic relays to realize the switching between the operation and the safety state of the engine safety mechanism, so that the circuit composition is complex, the cost is high due to the large number of electromagnetic relays, and meanwhile, the fault state of the safety mechanism cannot be diagnosed.
Disclosure of Invention
Aiming at least one defect or improvement requirement in the prior art, the invention provides a control method and a control circuit of an aircraft engine safety mechanism, which are used for solving the technical problems of how to realize the state conversion of the aircraft engine safety mechanism, and simultaneously realize the real-time monitoring on the state conversion success or failure alarm on the state conversion of the safety mechanism.
To achieve the above object, according to a first aspect of the present invention, there is provided a control method of an aircraft engine safety mechanism, comprising the steps of:
receiving control information and judging the state of the safety mechanism;
when the state of the safety mechanism is judged to be a first state, the MCU sends a first electromagnetic pin power distribution command and a second electromagnetic pin power distribution command firstly, the first solid-state relay and the second solid-state relay are used for distributing power for the electromagnetic pin action electromagnet, after the first time is delayed, a second state control command is sent out again to control the solid-state motor control module to execute the state conversion of the safety mechanism, and the second time is delayed;
and after delaying the second time, judging the state of the safety mechanism again, if the state is the second state, sending out the state conversion success information of the safety mechanism, and if the state is the first state, sending out the state conversion fault alarm information of the safety mechanism.
Further, if the first state is a working state, the second state is a safe state, or if the first state is a safe state, the second state is a working state.
Further, the first time is 50ms ± 10 ms.
Further, the second time is 800ms ± 100 ms.
Further, the first solid state relay and the second solid state relay are model number PVG 612A.
According to a second aspect of the invention, there is provided a control circuit for an aircraft engine safety mechanism, comprising an MCU, an electromagnetic pin control circuit, a safety mechanism state transition control circuit and a safety mechanism state detection circuit;
the electromagnetic pin control circuit comprising a first solid-state relay and a second solid-state relay distributes power for the electromagnetic pin action electromagnet through a first electromagnetic pin power distribution command and a second electromagnetic pin power distribution command which are sent by the MCU through the first solid-state relay and the second solid-state relay;
the safety mechanism state conversion control circuit comprising a solid-state motor control module controls the solid-state motor control module to execute state conversion of the safety mechanism through a state conversion control instruction sent by the MCU;
the safety mechanism state detection circuit comprising an optical coupling acquisition circuit is used for judging the state of the safety mechanism and judging whether the state conversion of the safety mechanism is successful or not.
Further, the control circuit further comprises a state information feedback module;
the state information feedback module sends out the state switching success information of the safety mechanism when judging that the state switching of the safety mechanism is successful; and when the state conversion of the safety mechanism fails, sending out state conversion fault alarm information of the safety mechanism.
Further, the state transition of the safety mechanism is specifically as follows:
the operating state of the safety mechanism is converted into the safety state or the safety state of the safety mechanism is converted into the operating state.
Further, the first solid state relay and the second solid state relay are model number PVG 612A.
In general, compared with the prior art, the above technical solutions conceived by the present invention can achieve the following beneficial effects:
(1) according to the invention, by introducing the safety mechanism state detection process, whether the safety mechanism has a state conversion fault can be judged, and the health state monitoring of the safety mechanism state conversion process is realized by the MCU. The method of the invention can meet the application requirement of the state conversion of the engine safety mechanism, can detect the state of the engine safety mechanism in real time and diagnose the state conversion fault, and can effectively improve the operation safety of the control circuit.
(2) The control circuit for realizing the aircraft engine safety mechanism based on the solid-state relay and the solid-state motor control module is simple in circuit composition, low in cost and high in working reliability.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic circuit diagram of a control circuit for implementing a rocket engine safety mechanism based on a solid-state relay and a solid-state motor control module according to an embodiment of the present invention;
fig. 2 is an operational flow diagram of a method for implementing control of a rocket engine safety mechanism based on a solid-state relay and a solid-state motor control module according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The terms "first," "second," or "third," and the like in the description, claims, or the foregoing drawings of the present application, are used for distinguishing between different objects and not for describing a particular order. Furthermore, the terms "comprising" and "having," as well as any variations thereof, are intended to cover non-exclusive inclusions. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those steps or elements but may alternatively include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
As shown in fig. 1, in an embodiment, taking an aircraft such as a rocket as an example, a control circuit for implementing a rocket engine safety mechanism based on a solid-state relay and a solid-state motor control module specifically includes the following components: MCU, electromagnetism round pin control circuit, safety mechanism state conversion control circuit and safety mechanism state detection circuit.
The electromagnetic pin control circuit controls the solid-state relays K1 and K2 to realize that K1 and K2 are respectively connected with resistors R1 and R2 in series by IO1 (first electromagnetic pin power distribution command) and IO2 (second electromagnetic pin power distribution command) of the MCU. The output end of the solid-state relay controls the on-off of the power supply + MC and the power supply-MC to the M _ DCX + and the M _ DCX-respectively, and the M _ DCX + and the M _ DCX-are connected to the electromagnetic pin control end of the safety mechanism. Preferably, the solid-state relays K1 and K2 are model PVG 612A.
The safety mechanism state conversion control circuit controls the solid state motor control module K3 to execute the state conversion of the safety mechanism through IO3 (transfer safety state control command) and IO4 (transfer working state control command) of the MCU. The state transition of the safety mechanism is specifically as follows: the operating state of the safety mechanism is converted into the safety state or the safety state of the safety mechanism is converted into the operating state.
The power supply of the solid-state motor control module K3 is + MC, -MC, the output signals of the solid-state motor control module K3 are M _ ZZ and M _ FZ, and the M _ ZZ and M _ FZ are connected to the conversion control end of the safety mechanism.
The safety mechanism state detection circuit is used for detecting the safety state and the working state of the safety mechanism through an optocoupler B1, and the optocoupler acquisition circuit is composed of an optocoupler B1, resistors R3-R8, capacitors C1-C4 and diodes V1-V2. The MCU collects KR1 and KR2 signals to judge whether the safety mechanism is in a safety state or a working state. The safety mechanism state detection circuit is also used for further judging whether the state conversion of the safety mechanism is successful or not based on the state judgment result of the safety mechanism.
The control circuit of the rocket engine safety mechanism also comprises a state information feedback module; the state information feedback module sends out the state conversion success information of the safety mechanism when judging that the state conversion of the safety mechanism is successful; and when the state conversion failure of the safety mechanism is judged, state conversion fault alarm information of the safety mechanism is sent.
With reference to fig. 1 and fig. 2, another embodiment of the present invention provides a method for implementing a control of a rocket engine safety mechanism based on a solid-state relay and a solid-state motor control module, which specifically includes the following steps:
(1) firstly, the MCU receives the control information and tests and judges the state of the safety mechanism. The optical coupling acquisition circuit acquires a position state signal of the safety mechanism and judges whether the safety mechanism is in a safety state or a working state.
(2) If the safety mechanism is in a working state, an MCU (microprogrammed control Unit) sends out an electromagnetic pin power distribution command IO1 and an IO2, and power distribution is performed on an electromagnetic pin action electromagnet through solid relays K1 and K2, preferably, after the time delay of 50ms +/-10 ms, a safety state switching control command IO3 is sent out to control a solid state motor control module K3 to switch the working state into the safety state, preferably, after the time delay of 800ms +/-100 ms, the MCU tests to judge whether the state of the safety mechanism is switched successfully or not. If the safety mechanism is in the safe state, the conversion is successful, and the information that the state of the safety mechanism is converted successfully is sent; if the safety mechanism is in the working state, the state conversion fault of the safety mechanism occurs, and the state conversion fault alarm information of the safety mechanism is sent out. The safety state control command IO3 is cancelled, and the MCU cancels the electromagnetic pin control command IO1 and IO 2. Through the operation, the safety mechanism is switched from the working state to the safety state, and an alarm is given in time when a state switching fault occurs.
If the safety mechanism is in a safe state, an MCU (microprogrammed control Unit) sends out an electromagnetic pin control command IO1 and an IO2, and power is distributed to an electromagnetic pin action electromagnet through solid relays K1 and K2, preferably, after delaying 50ms +/-10 ms, a work state control command IO4 is sent out again to control a solid state motor control module K3 to execute conversion from the safe state to the work state, preferably, after delaying 800ms +/-100 ms, the MCU tests to judge whether the state of the safety mechanism is converted successfully or not. If the safety mechanism is in the working state, the switching is successful, and the state switching success information of the safety mechanism is sent; if the safety mechanism is in the safety state, the state conversion fault of the safety mechanism occurs, and state conversion fault alarm information of the safety mechanism is sent out. The control command IO4 of the transfer work state is cancelled, and the MCU cancels the control commands IO1 and IO2 of the electromagnetic pin. Through the operation, the safety mechanism is converted from the safety state to the working state, and the alarm is given in time when the state conversion fault occurs.
By the method and the process, the state monitoring and the state switching of the rocket engine safety mechanism can be realized by the MCU control, and the fault detection in the state switching process can be realized. In the application of an actual system, the problem and hidden danger of the fault of the safety mechanism can be conveniently and timely found, and the safety of rocket test flow operation is improved.
The flowchart or block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present disclosure. 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. 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.
Those skilled in the art will appreciate that various combinations and/or combinations of features recited in the various embodiments and/or claims of the present disclosure can be made, even if such combinations or combinations are not expressly recited in the present disclosure. In particular, various combinations and/or combinations of the features recited in the various embodiments and/or claims of the present disclosure may be made without departing from the spirit or teaching of the present disclosure, and all such combinations and/or combinations are within the scope of the present disclosure.
While the disclosure has been shown and described with reference to certain exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure as defined by the appended claims and their equivalents. Accordingly, the scope of the present disclosure should not be limited to the above-described embodiments, but should be defined not only by the appended claims, but also by equivalents thereof.
Claims (9)
1. A method of controlling an aircraft engine safety mechanism, comprising the steps of:
receiving control information and judging the state of the safety mechanism;
when the state of the safety mechanism is judged to be a first state, the MCU sends a first electromagnetic pin power distribution command and a second electromagnetic pin power distribution command firstly, the first solid-state relay and the second solid-state relay are used for distributing power for the electromagnetic pin action electromagnet, after the first time is delayed, a second state control command is sent out again to control the solid-state motor control module to execute the state conversion of the safety mechanism, and the second time is delayed;
and after delaying the second time, judging the state of the safety mechanism again, if the state is the second state, sending out the state conversion success information of the safety mechanism, and if the state is the first state, sending out the state conversion fault alarm information of the safety mechanism.
2. The control method according to claim 1, wherein the first state is an operating state and the second state is a safe state or the first state is a safe state and the second state is an operating state.
3. The control method of claim 1, wherein the first time is 50ms ± 10 ms.
4. The control method according to claim 1, characterized in that the second time is 800ms ± 100 ms.
5. The control method of claim 1, wherein the first solid state relay and the second solid state relay are of the PVG612A model number.
6. A control circuit of an aircraft engine safety mechanism is characterized by comprising an MCU, an electromagnetic pin control circuit, a safety mechanism state conversion control circuit and a safety mechanism state detection circuit;
the electromagnetic pin control circuit comprising a first solid-state relay and a second solid-state relay distributes power for the electromagnetic pin action electromagnet through a first electromagnetic pin power distribution command and a second electromagnetic pin power distribution command which are sent by the MCU through the first solid-state relay and the second solid-state relay;
the safety mechanism state conversion control circuit comprising a solid-state motor control module controls the solid-state motor control module to execute state conversion of the safety mechanism through a state conversion control instruction sent by the MCU;
the safety mechanism state detection circuit comprising an optical coupling acquisition circuit is used for judging the state of the safety mechanism and judging whether the state conversion of the safety mechanism is successful or not.
7. The control circuit of claim 6, wherein the control circuit further comprises a state information feedback module;
the state information feedback module sends out the state switching success information of the safety mechanism when judging that the state switching of the safety mechanism is successful; and when the state conversion of the safety mechanism fails, sending out state conversion fault alarm information of the safety mechanism.
8. The control circuit according to claim 6, wherein the state transition of the safety mechanism is in particular:
the operating state of the safety mechanism is converted into the safety state or the safety state of the safety mechanism is converted into the operating state.
9. The control circuit of claim 6, wherein the first solid state relay and the second solid state relay are model number PVG 612A.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210576614.9A CN114992001A (en) | 2022-05-25 | 2022-05-25 | Control method and control circuit of aircraft engine safety mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210576614.9A CN114992001A (en) | 2022-05-25 | 2022-05-25 | Control method and control circuit of aircraft engine safety mechanism |
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| CN202210576614.9A Pending CN114992001A (en) | 2022-05-25 | 2022-05-25 | Control method and control circuit of aircraft engine safety mechanism |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3713708C1 (en) * | 1987-04-24 | 1996-08-22 | Diehl Gmbh & Co | Adaptive detection of signals |
| CN105422315A (en) * | 2015-11-27 | 2016-03-23 | 湖北三江航天红峰控制有限公司 | Solid rocket engine safety mechanism control circuit and control method |
| CN206206012U (en) * | 2016-11-28 | 2017-05-31 | 西安航天动力测控技术研究所 | A kind of Iganition control system for being applied to Solid Rocket Motor Ground Test |
| CN109854414A (en) * | 2018-12-11 | 2019-06-07 | 西安航天动力测控技术研究所 | A kind of safety ignition mechanism unit tester |
| CN112130543A (en) * | 2020-07-21 | 2020-12-25 | 上海宇航系统工程研究所 | Carrier rocket electrical system based on FC-AE-1553 high-speed bus |
-
2022
- 2022-05-25 CN CN202210576614.9A patent/CN114992001A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3713708C1 (en) * | 1987-04-24 | 1996-08-22 | Diehl Gmbh & Co | Adaptive detection of signals |
| CN105422315A (en) * | 2015-11-27 | 2016-03-23 | 湖北三江航天红峰控制有限公司 | Solid rocket engine safety mechanism control circuit and control method |
| CN206206012U (en) * | 2016-11-28 | 2017-05-31 | 西安航天动力测控技术研究所 | A kind of Iganition control system for being applied to Solid Rocket Motor Ground Test |
| CN109854414A (en) * | 2018-12-11 | 2019-06-07 | 西安航天动力测控技术研究所 | A kind of safety ignition mechanism unit tester |
| CN112130543A (en) * | 2020-07-21 | 2020-12-25 | 上海宇航系统工程研究所 | Carrier rocket electrical system based on FC-AE-1553 high-speed bus |
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