Data storage and use method of ejection lifesaving controller, computer equipment and medium

Abstract

The invention discloses a data storage and use method of an ejection lifesaving controller, computer equipment and a medium, and relates to the field of ejection lifesaving. The data storage and use method of the ejection lifesaving controller comprises the following steps: electrifying and self-checking the If power-on self-test is normal, whether an ejection signal exists or not is judged, no ejection signal is sent to a receiver, a sensor signal is collected, and periodic self-test is carried out; after the ejection signal is monitored, the authenticity of the ejection signal is judged, and the onboard signal is analyzed; after a differential pressure true value is calculated, the height is determined according to the static pressure true value, the chair-loaded ejection surface speed is calculated, and the true ejection surface speed is determined; determining delay time according to the static pressure real value and the real ejection surface speed, and loading a timer for delaying; after the time delay is finished, a chair-loaded static pressure storage DARM area is collected to determine whether a parachute opening condition is met or not, and a parachute opening instruction is output if the condition is met; and after a parachute opening instruction is output, DRAM data are transferred to an SRAM, and the data of the SRAM are written into an external EEPROM. The data storage and use method of the ejection lifesaving controller can ensure the safety and reliability of data and improve the ejection reliability.

Description

TECHNICAL FIELD

[0001] The application relates to the field of ejection rescue, in particular to an ejection rescue controller data storage use method, computer equipment and a medium. BACKGROUND

[0002] The controller of the ejection rescue system is an important part of the ejection rescue system. The main control chip of the controller of a certain ejection rescue system adopts DSP and is JS320F240, the capacity of the internal DRAM is 544 bytes, in the external extended memory, the capacity of the external EEPROM is 64K bytes, and the capacity of the external SRAM is 64K bytes; after the controller is powered on, the on-board signals need to be received, the power-on self-checking collection, the periodic self-checking collection and the cyclic collection of the external sensor signals, due to the limited capacity of the storage, the data storage in the DRAM, the external SRAM or the EEPROM needs to be properly considered to meet the ejection safety requirements, in addition, under the premise of ensuring the real-time of the ejection start signal, the storage positions of the received on-board signals, the self-checking and periodic self-checking collected sensor signals and the cyclic collected sensor data need to be reasonably distributed to ensure the ejection safety. SUMMARY

[0003] The application aims to provide an ejection rescue controller data storage use method, computer equipment and a medium, which can ensure data safety and reliability, and does not affect the delay output when the individual address of the storage space appears a check exception, and improve the ejection reliability.

[0004] The application is implemented in the following manner: The application provides an ejection rescue controller data storage use method, which comprises the following steps: The ejection rescue system controller performs power-on self-checking; The power-on self-checking is normally judged to have no ejection signal, the on-board signals are cyclically received, the sensor signals are collected and the periodic self-checking is performed; After the ejection signal is monitored, the authenticity of the ejection signal is judged and the on-board signals are analyzed; The total pressure of the air speed and the static pressure of the air speed are collected and processed to obtain a real difference pressure value, and the height is determined according to the real static pressure value; The real ejection table speed is determined according to the difference pressure real value and the height; The delay time is loaded in the timer according to the real static pressure value and the real ejection table speed; After the delay is ended, the chair-mounted static pressure is collected and stored in the DARM area, and the corresponding static pressure value of the preset parachute opening height is compared to determine whether the parachute opening condition is met, and the parachute opening instruction is output if the condition is met; After the parachute opening instruction is output, the data in the DRAM is transferred to the SRAM, and the data in the SRAM is written into the external EEPROM.

[0005] In some optional embodiments, when there is no ejection signal, the receiver receives the on-board signal, collects the sensor signals, and performs periodic self-checking. When there is no on-board signal during the periodic self-checking, the ejection signal and the on-board signal are monitored in sequence, and after 3-5 ms of waiting for the receiver signal, 2 ms of round-robin cycle detection is entered. After the self-checking sub-item detection of one round-robin cycle detection is completed, 16-20 ms of sensor signals of the total pressure and the static pressure of the airspeed are collected, and the above steps are repeated.

[0006] In some optional embodiments, when there is no ejection signal, the receiver receives the on-board signal, collects the sensor signals, and performs periodic self-checking. When there is no on-board signal during the periodic self-checking, the receiver receives the on-board signal, and after receiving one byte of data, the ejection signal is monitored. After receiving one frame of data of the on-board signal, the next frame of data is waited to be received. After the on-board signal is completed, 2 ms of round-robin cycle detection is entered. After the self-checking sub-item detection of one round-robin cycle detection is completed, 36-40 ms of sensor signals of the total pressure and the static pressure of the airspeed are collected, and the above steps are repeated.

[0007] In some optional embodiments, when the sensor signals of the total pressure and the static pressure of the airspeed are collected, the sampling rate is 4-6 Ks / s, and 1500-2000 sensor data are collected.

[0008] In some optional embodiments, when the on-board signal is analyzed, the received on-board signal is subjected to identification word, check sum, and valid word judgment. If there is an error, the calibrated airspeed valid word and the real static pressure valid word are invalid. Then, it is judged whether the calibrated airspeed and the real static pressure are within a preset range. If not, the on-board signal is invalid.

[0009] In some optional embodiments, when the collected total pressure and static pressure of the airspeed are processed and calculated, the total pressure and the static pressure of the airspeed collected before ejection are sorted in time sequence and subjected to FIR filtering, and then converted into pressure. The difference pressure real value is calculated by subtracting the static pressure of the airspeed from the total pressure of the airspeed.

[0010] In some optional embodiments, when the on-board signal is valid, the real static pressure value is equal to the on-board static pressure value. When the on-board signal is invalid, the real static pressure value is equal to the valid value of the static pressure of the airspeed.

[0011] In some optional embodiments, when the real ejection indicated speed is determined, if the on-board signal is valid, the real ejection indicated speed is equal to the calibrated airspeed of the on-board. If the on-board signal is invalid, the real ejection indicated speed is equal to the chair-mounted ejection indicated speed.

[0012] The application also provides a computer device, which comprises a memory, a processor, and a computer program stored in the memory and executable on the processor. The processor implements the steps of the above method when executing the computer program.

[0013] The application further provides a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the steps of the method.

[0014] The application has the beneficial effects that the ejection escape controller data storage use method, the computer device and the medium provided by the application can ensure data safety and reliability by distributing the on-board signals, the sensor signals collected at different time points and the result data to different storage spaces, and can ensure the reliability of ejection by storing the on-board signals and the total static pressure signals of airspeed used for time delay in different positions, without affecting the final time delay output when individual addresses of the storage spaces have check abnormality. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some of the embodiments of the application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor.

[0016] Figure 1 The flowchart of the ejection escape controller data storage use method provided by the embodiments of the application is shown in the figure. Figure 2 The external interface diagram of the ejection escape controller in the ejection escape controller data storage use method provided by the embodiments of the application is shown in the figure. Figure 3 The software timing control diagram in the ejection escape controller data storage use method provided by the embodiments of the application is shown in the figure. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solutions and advantages of the embodiments of the application more clear, the technical solutions in the embodiments of the application will be described clearly and completely in the following with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only some of the embodiments of the application, not all the embodiments.

[0018] Therefore, the following detailed description of the embodiments of the application provided in the drawings is not intended to limit the scope of the claimed application, but only represents selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments in the application without creative labor are within the scope of protection of the application.

[0019] The features and performance of the ejection escape controller data storage use method of the application will be further described in detail in the following with reference to the embodiments.

[0020] AsFigure 1 As shown in the figure, the embodiment of the application provides a data storage method of an ejection escape controller. The DRAM space of the controller is 544 bytes, the read-write rate is fast, and is used for storing the received on-board signal, the collected sensor signal of the power-on self-test, the collected sensor signal of the periodic self-test, and the total pressure value, the static pressure value and the chair-mounted static pressure value of the sensor calculated at the ejection moment. The SRAM space is 64K bytes, and is used for storing the cyclically collected total pressure AD value, the static pressure AD value, the AD value after filtering, and the total static pressure value converted from the AD value. After the ejection, the data needs to be recorded for the convenience of post-analysis, and can also be read after power-off. Therefore, the DRAM data and the SRAM data are all stored into the EEPROM after the ejection, and the SRAM and the EEPROM are selected through the chip selection signal. The external interface diagram of the controller in the embodiment of the application is shown in the figure. Figure 2 .

[0021] The data storage method of the ejection escape controller comprises the following steps: Step one, after the ejection escape system controller is powered on, the power-on self-test is performed, and the normal or abnormal judgment of each self-test item is performed. Step two, the power-on self-test normal judgment is performed on whether there is an ejection signal. If there is no ejection signal, the on-board signal is cyclically received, the sensor signal is collected, and the periodic self-test is performed. If there is no on-board signal, the ejection signal and the on-board signal are monitored in turn, after waiting for 4ms of the on-board signal, the 2ms of the round tour cycle detection is entered. After the detection of the self-test sub-item of one round tour cycle detection is completed, the sensor signal of the airspeed total pressure and the airspeed static pressure is collected for 18ms, and the above steps are repeated.

[0022] If there is an on-board signal, the on-board signal is received, the ejection signal is monitored after each byte of data is received, the next frame of data is waited for after one frame of data of the on-board signal is received, and after the on-board signal is received, the 2ms of the round tour cycle detection is entered. After the detection of the self-test sub-item of one round tour cycle detection is completed, the sensor signal of the airspeed total pressure and the airspeed static pressure is collected for 38ms, and the above steps are repeated.

[0023] Among them, when the sensor signal of the airspeed total pressure and the airspeed static pressure is collected, the sampling rate is 5Ks / s, and 1800 sensor data is collected for filtering correction.

[0024] The self-test of each round tour cycle requires that the self-test is completed in 2ms, the periodic self-test includes the timer, the DRAM and the SRAM, the SRAM space is larger, one page (7FH) is detected in each cycle, and the self-test timing sequence diagram of the round tour cycle is shown in the figure. Figure 3 .

[0025] Step three, after the ejection signal is monitored, the authenticity of the ejection signal is judged, and the on-board signal is analyzed; when the on-board signal is analyzed, the received on-board signal is judged for identification word, check sum, and valid word; if it is wrong, the calibrated airspeed valid word and the real static pressure valid word are set to invalid; then it is judged whether the calibrated airspeed and the real static pressure are within the preset range; if not, the on-board signal is considered invalid.

[0026] Step four, the airspeed total pressure and the airspeed static pressure collected before ejection are processed and calculated to obtain the real value of the differential pressure; when processing and calculating, the airspeed total pressure and the airspeed static pressure collected before ejection are sorted in time sequence and converted into pressure after FIR filtering; the real value of the differential pressure is calculated by subtracting the airspeed static pressure from the airspeed total pressure. The real value of the static pressure is obtained; when the on-board signal is valid, the real value of the static pressure is equal to the on-board static pressure value; when the on-board signal is invalid, the real value of the static pressure is equal to the airspeed static pressure valid value, that is, the minimum value of the airspeed static pressure after filtering; the current height is determined according to the real value of the static pressure according to HB6127.

[0027] Step five, the chair-mounted ejection table speed is calculated according to the real value of the differential pressure and the height, and the real ejection table speed is determined; when the real ejection table speed is determined, if the on-board signal is valid, the real ejection table speed is equal to the on-board calibrated airspeed; if the on-board signal is invalid, the real ejection table speed is equal to the chair-mounted ejection table speed.

[0028] Step six, the delay time is determined according to the real value of the static pressure and the real ejection table speed, and the timer is loaded for delay; Step seven, after the delay is over, the chair-mounted static pressure is collected and stored in the DARM area, and compared with the static pressure value corresponding to the preset parachute opening height (generally 7000m) to determine whether the parachute opening condition is met, and the parachute opening instruction is output if the condition is met. Step eight, after the parachute opening instruction is output, the data in the DRAM is transferred to the SRAM, and the data in the SRAM is written into the external EEPROM for subsequent analysis.

[0029] The ejection life controller data storage use method provided by the embodiment of the application can ensure data safety and reliability by distributing the on-board signal, the sensor signals collected at different times, and the final event result data to different storage spaces through an external expansion chip when the main control chip storage space of the controller is insufficient, and can greatly improve the reliability of ejection data preservation and ejection safety by storing the on-board signal and the airspeed total static pressure signal used for delay in different positions, and not affecting the final delay output when individual addresses of the storage space have check abnormality.

[0030] Embodiment 1 The ejection life controller data storage use method provided by the embodiment of the application includes the following steps: Step one, compile and link the code into the ejection seat controller according to the previous subject.

[0031] Step two, power on the controller, send the on-board signal through the serial port assistant, calibrate the airspeed to 800 km / h, the on-board static pressure value to 70.11 kPa / 3000 m, the preset parachute opening height to 7000 m, and the ejection controller to the current atmospheric environment. At this time, the power-on self-test is normal, the periodic self-test is normal, the system is in detection, there is no ejection signal, there is an on-board signal and signal reception, and the total static pressure value is collected. The controller connects the simulator to view the data storage location, and the on-board signal is stored in the DRAM area. The sensor power-on self-test, periodic self-test AD value and converted pressure value are also stored in the DRAM area.

[0032] Step three, power on the controller, send the on-board signal through the serial port assistant, calibrate the airspeed to 800 km / h, the on-board static pressure value to 70.11 kPa / 3000 m, the preset parachute opening height to 7000 m, and the pressure equipment to simulate the airspeed static pressure to 73.75 Kpa / 2600, the total airspeed pressure to 99.62 kPa. Power-on self-test, periodic self-test are normal, then ejection occurs. Step four, first determine the authenticity of the ejection signal, the ejection signal changes from physical closure to disconnection, and the ejection signal is true.

[0033] Step five, then analyze the on-board signal, the identification word, the checksum, and the valid word are correct, and the calibrated airspeed is within the range of 50-1600 km / h, the true static pressure is within the range of 1.172 kPa-107.478 kPa, and the on-board signal is valid.

[0034] Total static pressure data processing: Sort the total airspeed pressure and airspeed static pressure collected before ejection in time sequence, and perform FIR filtering. Convert it to pressure value according to the formula, and calculate the differential pressure true value as 25.87 kPa by subtracting the total airspeed pressure from the airspeed static pressure.

[0035] Get the true value of static pressure: the on-board signal is valid, the true value of static pressure = the on-board static pressure value = 70.11 kPa.

[0036] Determine the height state: determine the current height state according to the true value of static pressure, and determine it to be 3000 m according to HB6127.

[0037] Step six, determine the true ejection speed, calculate the chair-mounted ejection table speed to be 700 km / h according to the differential pressure true value Qc (25.87 kPa) and the height state (3000 m) according to HB6127, then determine the true ejection speed. Since the on-board signal is valid, the true ejection speed is equal to the calibrated airspeed on the board, which is 800 km / h.

[0038] Step seven, get the delay time and delay: according to the static pressure true value and the true ejection table speed, the delay time is 1.26s, and the timer is loaded for delay.

[0039] Step eight, output the parachute opening instruction: after the delay is over, the chair-mounted static pressure is collected, the chair-mounted static pressure is the current atmospheric pressure, which is lower than the preset parachute opening height (7000m), and meets the parachute opening instruction output condition, so the parachute opening instruction is output.

[0040] Step nine, data recording: after the parachute opening instruction is output, the data in the DRAM is first transferred to the SRAM, and finally the data in the SRAM is written into the external EEPROM, the calibration airspeed recorded in the EEPROM is 800 km / h, the on-board static pressure value is 70.11kPa, the preset parachute opening height is 7000m, the actual delay is 1.262s, the true ejection table speed is 800km / h, and the chair-mounted ejection table speed is 700km / h.

[0041] The embodiment of the application further provides a computer device, which comprises a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor implements the steps of the ejection escape controller data storage use method when executing the computer program.

[0042] The embodiment of the application further provides a computer readable storage medium, which stores a computer program, and the steps of the ejection escape controller data storage use method are implemented when the computer program is executed by a processor.

[0043] The above-described embodiments are part of the embodiments of the application, rather than all the embodiments. The detailed description of the embodiments of the application is not intended to limit the scope of the claimed application, but only represents selected embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those of ordinary skill in the art without creative labor are within the scope of protection of the application.

Claims

1. A method of data storage use for an ejection survival controller, characterized by, The method comprises the following steps: The ejection rescue system controller performs a power-on self-test; If no ejection signal is detected in the power-on self-test, the system cyclically receives signals from the receiver, collects sensor signals, and performs periodic self-tests; After detecting an ejection signal, the system determines the authenticity of the ejection signal and analyzes the signals from the aircraft; The system collects total airspeed pressure and static airspeed pressure, processes and calculates the real difference pressure value, determines the height based on the real static pressure value, and determines the real ejection table speed based on the real difference pressure value and the height; The system determines the delay time based on the real difference pressure value and the height, loads the timer, and delays; After the delay ends, the system collects the chair-mounted static pressure, stores it in the DARM area, compares it with the corresponding static pressure value of the preset parachute opening height, determines whether the parachute opening condition is met, and outputs the parachute opening instruction if the condition is met; After outputting the parachute opening instruction, the system transfers the data in the DRAM to the SRAM, and writes the data in the SRAM to the external EEPROM. If there is no aircraft signal during the cyclic reception of signals from the receiver, collection of sensor signals, and periodic self-tests, the system sequentially monitors the ejection signal and the aircraft signal, waits for 3-5 ms for the receiver to receive signals, enters a 2-ms round-trip cycle detection, collects 16-20 ms of sensor signals of total airspeed pressure and static airspeed pressure after completing the self-test sub-item detection of one round-trip cycle detection, and repeats the above steps.

2. The ejection survival controller data storage use method of claim 1, wherein, If there is an aircraft signal during the cyclic reception of signals from the receiver, collection of sensor signals, and periodic self-tests, the system receives signals from the receiver, monitors the ejection signal after receiving one byte of data, waits for the next frame of data after receiving one frame of aircraft signal data, enters a 2-ms round-trip cycle detection after completing the self-test sub-item detection of one round-trip cycle detection, collects 36-40 ms of sensor signals of total airspeed pressure and static airspeed pressure, and repeats the above steps.

3. The ejection survival controller data storage use method of claim 2, wherein, When collecting sensor signals of total airspeed pressure and static airspeed pressure, the sampling rate is 4-6 Ks / s, and 1500-2000 sensor data are collected.

4. The ejection survival controller data storage use method according to claim 2 or 3, characterized in that, When analyzing the aircraft signals, the system identifies the received aircraft signals, checks the checksum and valid word, and sets the calibrated airspeed valid word and the real static pressure valid word as invalid if there is an error.

5. The ejection survival controller data storage use method of claim 1, wherein, Subsequently, the system determines whether the calibrated airspeed and the real static pressure are within the preset range, and considers the aircraft signal as invalid if they are not within the preset range. When processing and calculating the collected total airspeed pressure and static airspeed pressure, the system sorts the cyclically collected total airspeed pressure and static airspeed pressure in time sequence, performs FIR filtering, converts the pressure, and calculates the real difference pressure value by subtracting the static airspeed pressure from the total airspeed pressure.

6. The ejection survival controller data storage use method of claim 1, wherein, When the aircraft signal is valid, the real static pressure value is equal to the aircraft static pressure value; when the aircraft signal is invalid, the real static pressure value is equal to the valid value of the static airspeed pressure.

7. The ejection survival controller data storage use method of claim 1, wherein, When determining the real ejection table speed, if the aircraft signal is valid, the real ejection table speed is equal to the calibrated airspeed of the aircraft; if the aircraft signal is invalid, the real ejection table speed is equal to the chair-mounted ejection table speed.

8. The ejection survival controller data storage use method of claim 1, wherein, 9. A computer device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the method of any one of claims 1 to 8. ​ 10. A computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of the method of any one of claims 1 to 8.

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