CN117806598A - Software safety design method and system for ejection life-saving device to instruct ejection function - Google Patents
Software safety design method and system for ejection life-saving device to instruct ejection function Download PDFInfo
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Abstract
The invention discloses a software security design method and a system for an ejection life-saving device to instruct an ejection function, comprising the following steps: setting seat position information and ejection mode information; setting the seat position information and the ejection mode information to safe states; setting 4 reference seat instruction ejection states according to the seat position information and the ejection mode information; when the non-reference seat instruction ejection state is identified, determining a corresponding reference seat instruction ejection state according to the current seat position information; judging the ejection mode information after judging the seat position information, and locking the ejection state of the seat instruction; when the seats are ejected, the time delay of the ejection of the seats of the front cabin and the rear cabin is set according to the speed, the height, the pitch angle and the roll angle of the double-seat aircraft. The invention can accurately identify the current state of the ejection lifesaving device and set delay time, thereby ensuring that the lifesaving failure caused by the position identification error does not occur and achieving the optimal ejection lifesaving efficiency.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a software security design method and system for an ejection life-saving device to instruct an ejection function.
Background
The certain type ejection life-saving device realizes double-seat instruction ejection, multi-parameter continuous feeling, redundant emergency ejection starting judgment and multi-mode/multi-mode emergency ejection life-saving program control by combining a mode of combining mechanical/gas control and electric control with an instruction ejection system.
According to the design requirement of the double-assembled seat, the seats are arranged in the front cabin and the rear cabin and are designed in an isomorphic mode, after the seats are electrified, the electronic program controller recognizes the seat position information and the ejection mode information according to the ejection mode control board to perform ejection control of single/double seats so as to control the front and rear seats to be separated from the cabin respectively, and collision caused by simultaneous cabin outlet is avoided. The instruction ejection function is a key function of the double-seat ejection life-saving device, and if the identification is wrong, single-seat ejection delay or collision during double-seat ejection can be caused to cause life-saving failure; meanwhile, the original instruction ejection control system is hardware control, delay control is carried out according to fixed time, and delay time control cannot be set according to different speeds, pitching and rolling states, so that the lifesaving effect cannot be optimal when the lifesaving device is ejected by two seats.
Disclosure of Invention
The invention aims to provide a software safety design method for an instruction ejection function of an ejection life-saving device, which is characterized in that through the safety design of the instruction ejection function, software can accurately identify the current state of the ejection life-saving device and intelligently set delay time through comprehensively judging the position information of a seat, the ejection mode information and the working state of an aircraft, thereby ensuring that the life-saving failure caused by position identification errors does not occur and achieving the optimal ejection life-saving efficiency.
In order to solve the technical problems, the technical scheme of the invention is as follows: the software safety design method for the ejection function of the ejection life-saving device instruction comprises the following steps:
setting seat position information and ejection mode information for representing ejection state in software; the seat position information is used for indicating that the seat is positioned in the front cabin or the rear cabin; the ejection mode information is used for representing double ejection or single ejection, namely ejection of seats of a front cabin and a rear cabin in the double-seat aircraft, ejection of one of two seats of the front cabin or the rear cabin in the double-seat aircraft or ejection of a seat in the single-seat aircraft;
setting the seat position information and the ejection mode information to safe states;
setting 4 reference seat instruction ejection states according to the seat position information and the ejection mode information to respectively represent ejection of a front cabin seat, ejection of seats of a front cabin and a rear cabin in the double-seat aircraft, ejection of the seats of the rear cabin and ejection of the seats in the single-seat aircraft; alarming when the software identifies a non-reference seat instruction ejection state, determining a corresponding reference seat instruction ejection state according to the current seat position information, and writing the seat position information and ejection mode information corresponding to the determined reference seat instruction ejection state into a memory;
judging the ejection mode information after judging the seat position information, and locking the ejection state of the seat instruction according to the seat position information locked after the judgment and the ejection mode information;
in the same flight frame, locking is carried out after the seat position information is identified, and no change occurs in the power-on period of the aircraft;
when the aircraft is on the ground or the flying speed is greater than a preset value, locking the ejection state of the seat command; when the aircraft is in the air or the flying speed is smaller than a preset value, periodically collecting ejection mode information again, judging the seat position information and the ejection mode information in sequence again, and locking the ejection state of the seat instruction again;
when the seats are ejected, the time delay of the ejection of the seats of the front cabin and the rear cabin is set according to the speed, the height, the pitch angle and the roll angle of the double-seat aircraft.
After the seat position information and the ejection mode information corresponding to the determined ejection state of the reference seat instruction are written into the memory, the method further comprises the following steps: and confirming the seat position information and the ejection mode information written into the memory, and re-writing once if a writing error occurs.
After the seat position information and the ejection mode information corresponding to the determined ejection state of the reference seat instruction are written into the memory, the method further comprises the following steps: the method comprises the steps of customizing two storage addresses in a memory, namely a main storage address and a backup address, when the aircraft is powered down and powered up again, reading seat position information and ejection mode information of the previous period from the main storage address of the memory, and if a reading error occurs, reading from the backup address again; when ejection occurs, track divergence is executed according to the read ejection state of the seat command, and if ejection does not occur, the seat position information and ejection mode information are identified again.
The method for judging the seat position information comprises the following steps: collecting seat position information, stopping collecting if the seat position information obtained by continuously collecting for 3 times is consistent, and locking the seat position information obtained by collecting; if the seat position information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, taking the seat position information and ejection mode information written in a memory as the ejection state of the seat instruction, locking, and exiting judgment.
The method for judging the ejection mode information comprises the following steps: after seat position information with consistent continuous 3 acquisition results is obtained, acquiring ejection mode information, stopping acquisition if the seat position information obtained by continuous 3 acquisition is consistent, and locking the acquired ejection mode information; if ejection mode information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, locking the ejection mode information written in the memory, and exiting judgment.
The specific method for setting the time delay of the ejection of the seats of the front cabin and the rear cabin according to the speed, the pitch angle and the roll angle of the aircraft comprises the following steps:
when the seat is ejected, the delay time of the ejection of the front seat when the ejection of the double seat is generated is set according to the speed, the height, the pitch angle and the roll angle of the aircraft and whether the data source is effective or not, wherein the delay time of the ejection of the front seat when the ejection of the double seat is generated comprises short, medium and long time delays, the data source is judged to be effective when the data state bit of the data source is 1, the data source is judged to be ineffective when the data state bit of the data source is 0, and the delay time of the short, medium and long time delays is respectively 0.4s, 0.45s and 0.5s;
when the data source is invalid, and the aircraft is in a high-speed state, adopting short time delay, otherwise adopting medium time delay, wherein when the calibrated airspeed of the aircraft is greater than 600km/h, the aircraft is judged to be in the high-speed state;
when the data source is effective, and the aircraft is in the high-altitude area, adopting short time delay, otherwise adopting medium time delay, and when the absolute altitude of the aircraft is greater than 4000m, considering that the aircraft is in the high-altitude area; adopting short time delay when the aircraft is at high speed, otherwise, continuing to judge the pitch angle; adopting short time delay when the pitch angle is larger than 60 degrees, otherwise, continuing to judge the roll angle; a medium time delay is used when the roll angle exceeds 120 ° or between 40 ° and 80 °, a long time delay is used when the roll angle is between 80 ° and 120 °, otherwise a short time delay is used.
The system is arranged in the aircraft, and when the aircraft is in ejection, the software safety design method for the ejection function of the ejection lifesaving device is called.
After the seat position information and the ejection mode information corresponding to the determined ejection state of the reference seat instruction are written into the memory, the method further comprises the following steps:
confirming the seat position information and the ejection mode information written into the memory, and re-writing once if a writing error occurs;
two storage addresses are customized in the memory, namely a main storage address and a backup address, and when the aircraft is powered down and powered up again, the main storage address of the slave memory is defined; when ejection occurs, track divergence is executed according to the read ejection state of the seat command, and if ejection does not occur, the seat position information and ejection mode information are identified again.
The method for judging the seat position information comprises the following steps: collecting seat position information, stopping collecting if the seat position information obtained by continuously collecting for 3 times is consistent, and locking the seat position information obtained by collecting; if the seat position information with consistent continuous 3 acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, taking the seat position information and ejection mode information written in a memory as the ejection state of the seat instruction, locking, and exiting judgment;
the method for judging the ejection mode information comprises the following steps: after seat position information with consistent continuous 3 acquisition results is obtained, acquiring ejection mode information, stopping acquisition if the seat position information obtained by continuous 3 acquisition is consistent, and locking the acquired ejection mode information; if ejection mode information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, locking the ejection mode information written in the memory, and exiting judgment.
The specific method for setting the time delay of the ejection of the seats of the front cabin and the rear cabin according to the speed, the pitch angle and the roll angle of the aircraft comprises the following steps:
when the seat is ejected, the delay time of the ejection of the front seat when the ejection of the double seat is generated is set according to the speed, the height, the pitch angle and the roll angle of the aircraft and whether the data source is effective or not, wherein the delay time of the ejection of the front seat when the ejection of the double seat is generated comprises short, medium and long time delays, the data source is judged to be effective when the data state bit of the data source is 1, the data source is judged to be ineffective when the data state bit of the data source is 0, and the delay time of the short, medium and long time delays is respectively 0.4s, 0.45s and 0.5s;
when the data source is invalid, and the aircraft is in a high-speed state, adopting short time delay, otherwise adopting medium time delay, wherein when the calibrated airspeed of the aircraft is greater than 600km/h, the aircraft is judged to be in the high-speed state;
when the data source is effective, and the aircraft is in the high-altitude area, adopting short time delay, otherwise adopting medium time delay, and when the absolute altitude of the aircraft is greater than 4000m, considering that the aircraft is in the high-altitude area; adopting short time delay when the aircraft is at high speed, otherwise, continuing to judge the pitch angle; adopting short time delay when the pitch angle is larger than 60 degrees, otherwise, continuing to judge the roll angle; a medium time delay is used when the roll angle exceeds 120 ° or between 40 ° and 80 °, a long time delay is used when the roll angle is between 80 ° and 120 °, otherwise a short time delay is used.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, through the safety design of the ejection function, the software can accurately identify the current state of the ejection lifesaving device and intelligently set delay time through comprehensively judging the seat position information, the ejection mode information and the working state of the aircraft, so that the lifesaving failure caused by the position identification error is avoided, and the optimal ejection lifesaving efficiency is achieved.
Drawings
Fig. 1 is a schematic flow chart of an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention. In addition, the technical features of the embodiments of the present invention described below may be combined with each other as long as they do not collide with each other.
The technical scheme of the invention is as follows: a software security design method for a catapulting life-saving device to instruct a catapulting function, as shown in fig. 1, comprising:
1) The ejection state is composed of seat position information and ejection mode information, the seat position information indicates whether the seat is positioned in a front cabin or a rear cabin, the ejection mode information indicates whether double ejection or single ejection is performed, each ejection state is composed of two homologous switch signals, and software sets 4 variable identifications;
2) The software sets the seat position information and the ejection mode information to be in a safe state, so that abnormal identification is ensured not to occur;
3) The software sets four reference seat instruction ejection states of a front seat single bullet, a front seat double bullet, a rear seat and a single seat according to the seat position information and the ejection mode information, alarms the situation that the four reference states are not identified, and locks one instruction ejection state according to the current seat position information;
4) The software confirms the seat position information and the ejection mode information written into the memory, and if the writing is wrong, the software is written once again;
5) When the whole aircraft is powered down and powered up again, the seat position information and the ejection mode information are read from the memory, and if the reading is wrong, the seat position information and the ejection mode information are read again from the backup address; when ejection occurs, track divergence is executed according to the read ejection state of the instruction, and if the ejection is not performed, seat position information and ejection mode information are identified again;
6) When the ejection state of the instruction is judged, firstly, the seat position signal is judged, and then the ejection mode is judged:
a) Collecting the seat position signals, stopping collecting if the state is consistent for 3 times, stopping collecting after continuously collecting for 6 times if the state is not consistent for 3 times, setting the seat position signals and the ejection mode signals to be in the state of a memory, and exiting the instruction ejection control signal detection function;
b) After the correct acquisition and processing of the seat position signals are finished, the ejection mode signals are periodically acquired, the acquisition is stopped when the state is consistent for 3 times continuously acquired in each period, the acquisition is stopped after the state is continuously acquired for 6 times if the state is not consistent for 3 times continuously, the seat position signals are set to be in the current latest state, the ejection mode signals are in the state in a memory, and the instruction ejection control signals are judged and locked according to the combination of the acquired seat position signals and the ejection mode signals.
7) Based on the flight working condition, the positions of pilots in the same flight frame are fixed, so that the seats are immediately locked after the position information is identified, and the same power-on period is not changed;
8) Based on the flight condition, the ejection mode signal may be changed according to the pilot requirement when the ground, so that the ejection control signal is locked when the ground or the flight speed is greater than a certain value; if the 'air' or the flying speed is smaller than a certain value, periodically collecting the ejection mode signal again, and judging the instruction ejection control signal according to the logic;
9) According to the state of the data source, different speeds, heights, pitching and rolling states in the data source and whether the data source is effective or not, the time delay time (the time delay time is divided into three types of medium, short and long) of the front chair ejection during double ejection is intelligently set during ejection, so that optimal life-saving control can be executed during double ejection: when the data state bit of the data source is 1, the data source is judged to be valid, and when the data state bit of the data source is 0, the data source is judged to be invalid, and the short, medium and long time delays are respectively 0.4s, 0.45s and 0.5s; when the data source is invalid, and the aircraft is in a high-speed state, adopting short time delay, otherwise adopting medium time delay, wherein when the calibrated airspeed of the aircraft is greater than 600km/h, the aircraft is judged to be in the high-speed state; when the data source is effective, and the aircraft is in the high-altitude area, adopting short time delay, otherwise adopting medium time delay, and when the absolute altitude of the aircraft is greater than 4000m, considering that the aircraft is in the high-altitude area; adopting short time delay when the aircraft is at high speed, otherwise, continuing to judge the pitch angle; adopting short time delay when the pitch angle is larger than 60 degrees, otherwise, continuing to judge the roll angle; a medium time delay is used when the roll angle exceeds 120 ° or between 40 ° and 80 °, a long time delay is used when the roll angle is between 80 ° and 120 °, otherwise a short time delay is used.
The code and introduction of the design method are as follows:
initializing the instruction ejection state of the seat into a determined state, and ensuring that the instruction ejection state is not a random state when the software works abnormally.
1) Safety design for reading seat position information and ejection mode information from memory
2) Safety design for continuous acquisition of seat position signals
3) Security design for continuous acquisition of ejection mode signals
4) Safety design for writing seat position signal and ejection mode signal states to memory
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5) Safety design for locking and unlocking a seat position signal and an ejection mode signal
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It will be readily appreciated by those skilled in the art that the foregoing description is merely a preferred embodiment of the invention and is not intended to limit the invention, but any modifications, equivalents, improvements or alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The software safety design method for the ejection function of the ejection life-saving device is characterized by comprising the following steps:
setting seat position information and ejection mode information for representing ejection state in software; the seat position information is used for indicating that the seat is positioned in the front cabin or the rear cabin; the ejection mode information is used for representing double ejection or single ejection, namely ejection of seats of a front cabin and a rear cabin in the double-seat aircraft, ejection of one of two seats of the front cabin or the rear cabin in the double-seat aircraft or ejection of a seat in the single-seat aircraft;
setting the seat position information and the ejection mode information to safe states;
setting 4 reference seat instruction ejection states according to the seat position information and the ejection mode information to respectively represent ejection of a front cabin seat, ejection of seats of a front cabin and a rear cabin in the double-seat aircraft, ejection of the seats of the rear cabin and ejection of the seats in the single-seat aircraft; alarming when the software identifies a non-reference seat instruction ejection state, determining a corresponding reference seat instruction ejection state according to the current seat position information, and writing the seat position information and ejection mode information corresponding to the determined reference seat instruction ejection state into a memory;
judging the ejection mode information after judging the seat position information, and locking the ejection state of the seat instruction according to the seat position information locked after the judgment and the ejection mode information;
in the same flight frame, locking is carried out after the seat position information is identified, and no change occurs in the power-on period of the aircraft;
when the aircraft is on the ground or the flying speed is greater than a preset value, locking the ejection state of the seat command; when the aircraft is in the air or the flying speed is smaller than a preset value, periodically collecting ejection mode information again, judging the seat position information and the ejection mode information in sequence again, and locking the ejection state of the seat instruction again;
when the seats are ejected, the time delay of the ejection of the seats of the front cabin and the rear cabin is set according to the speed, the height, the pitch angle and the roll angle of the double-seat aircraft.
2. The software security design method for the ejection life saving device instruction ejection function according to claim 1, wherein after the seat position information and the ejection mode information corresponding to the determined reference seat instruction ejection state are written into the memory, further comprising the steps of: and confirming the seat position information and the ejection mode information written into the memory, and re-writing once if a writing error occurs.
3. The software security design method for the ejection life saving device instruction ejection function according to claim 1, wherein after the seat position information and the ejection mode information corresponding to the determined reference seat instruction ejection state are written into the memory, further comprising the steps of: the method comprises the steps of customizing two storage addresses in a memory, namely a main storage address and a backup address, when the aircraft is powered down and powered up again, reading seat position information and ejection mode information of the previous period from the main storage address of the memory, and if a reading error occurs, reading from the backup address again; when ejection occurs, track divergence is executed according to the read ejection state of the seat command, and if ejection does not occur, the seat position information and ejection mode information are identified again.
4. The software security design method for an ejection life saving device to instruct an ejection function according to claim 1, wherein the method for judging the seat position information is: collecting seat position information, stopping collecting if the seat position information obtained by continuously collecting for 3 times is consistent, and locking the seat position information obtained by collecting; if the seat position information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, taking the seat position information and ejection mode information written in a memory as the ejection state of the seat instruction, locking, and exiting judgment.
5. The software security design method for an ejection life saving device to instruct an ejection function according to claim 4, wherein the method for judging ejection mode information is: after seat position information with consistent continuous 3 acquisition results is obtained, acquiring ejection mode information, stopping acquisition if the seat position information obtained by continuous 3 acquisition is consistent, and locking the acquired ejection mode information; if ejection mode information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, locking the ejection mode information written in the memory, and exiting judgment.
6. The software safety design method for the ejection life saving device to instruct the ejection function according to claim 1, wherein the specific method for setting the delay time of the ejection of the seats of the front cabin and the rear cabin according to the speed, the pitch angle and the roll angle of the aircraft is as follows:
when the seat is ejected, the delay time of the ejection of the front seat when the ejection of the double seat is generated is set according to the speed, the height, the pitch angle and the roll angle of the aircraft and whether the data source is effective or not, wherein the delay time of the ejection of the front seat when the ejection of the double seat is generated comprises short, medium and long time delays, the data source is judged to be effective when the data state bit of the data source is 1, the data source is judged to be ineffective when the data state bit of the data source is 0, and the delay time of the short, medium and long time delays is respectively 0.4s, 0.45s and 0.5s;
when the data source is invalid, and the aircraft is in a high-speed state, adopting short time delay, otherwise adopting medium time delay, wherein when the calibrated airspeed of the aircraft is greater than 600km/h, the aircraft is judged to be in the high-speed state;
when the data source is effective, and the aircraft is in the high-altitude area, adopting short time delay, otherwise adopting medium time delay, and when the absolute altitude of the aircraft is greater than 4000m, considering that the aircraft is in the high-altitude area; adopting short time delay when the aircraft is at high speed, otherwise, continuing to judge the pitch angle; adopting short time delay when the pitch angle is larger than 60 degrees, otherwise, continuing to judge the roll angle; a medium time delay is used when the roll angle exceeds 120 ° or between 40 ° and 80 °, a long time delay is used when the roll angle is between 80 ° and 120 °, otherwise a short time delay is used.
7. A system for instructing an ejection function of an ejection lifesaving device, wherein the system is arranged in an aircraft, and when the aircraft is ejected, the software security design method for instructing the ejection function of the ejection lifesaving device according to claim 1 is called.
8. The system of claim 7, further comprising the steps of, after writing the seat position information and the ejection mode information corresponding to the determined reference seat command ejection state to the memory:
confirming the seat position information and the ejection mode information written into the memory, and re-writing once if a writing error occurs;
two storage addresses are customized in the memory, namely a main storage address and a backup address, and when the aircraft is powered down and powered up again, the main storage address of the slave memory is defined; when ejection occurs, track divergence is executed according to the read ejection state of the seat command, and if ejection does not occur, the seat position information and ejection mode information are identified again.
9. The system of claim 7, wherein the system further comprises a controller configured to control the controller,
the method for judging the seat position information comprises the following steps: collecting seat position information, stopping collecting if the seat position information obtained by continuously collecting for 3 times is consistent, and locking the seat position information obtained by collecting; if the seat position information with consistent continuous 3 acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, taking the seat position information and ejection mode information written in a memory as the ejection state of the seat instruction, locking, and exiting judgment;
the method for judging the ejection mode information comprises the following steps: after seat position information with consistent continuous 3 acquisition results is obtained, acquiring ejection mode information, stopping acquisition if the seat position information obtained by continuous 3 acquisition is consistent, and locking the acquired ejection mode information; if ejection mode information with consistent continuous 3-time acquisition results cannot be obtained, stopping acquisition after 6 continuous acquisition, locking the ejection mode information written in the memory, and exiting judgment.
10. The system of claim 7, wherein the specific method for setting the delay time of the ejection of the seats of the front cabin and the rear cabin according to the speed, the pitch angle and the roll angle of the aircraft is as follows:
when the seat is ejected, the delay time of the ejection of the front seat when the ejection of the double seat is generated is set according to the speed, the height, the pitch angle and the roll angle of the aircraft and whether the data source is effective or not, wherein the delay time of the ejection of the front seat when the ejection of the double seat is generated comprises short, medium and long time delays, the data source is judged to be effective when the data state bit of the data source is 1, the data source is judged to be ineffective when the data state bit of the data source is 0, and the delay time of the short, medium and long time delays is respectively 0.4s, 0.45s and 0.5s;
when the data source is invalid, and the aircraft is in a high-speed state, adopting short time delay, otherwise adopting medium time delay, wherein when the calibrated airspeed of the aircraft is greater than 600km/h, the aircraft is judged to be in the high-speed state;
when the data source is effective, and the aircraft is in the high-altitude area, adopting short time delay, otherwise adopting medium time delay, and when the absolute altitude of the aircraft is greater than 4000m, considering that the aircraft is in the high-altitude area; adopting short time delay when the aircraft is at high speed, otherwise, continuing to judge the pitch angle; adopting short time delay when the pitch angle is larger than 60 degrees, otherwise, continuing to judge the roll angle; when the roll angle exceeds 120 DEG or 40 DEG
A medium time delay is used when the roll angle is between 80 and 120 degrees, a long time delay is used when the roll angle is between 80 and 120 degrees,
otherwise, a short time delay is used.
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| CN202311797803.XA CN117806598A (en) | 2023-12-25 | 2023-12-25 | Software safety design method and system for ejection life-saving device to instruct ejection function |
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| CN202311797803.XA CN117806598A (en) | 2023-12-25 | 2023-12-25 | Software safety design method and system for ejection life-saving device to instruct ejection function |
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