A large capacity data self-recording airplane emergency life-locating overload starting device

Abstract

The application discloses an airplane emergency lifesaving positioning overload starting device with large-capacity data self-recording, which comprises a three-axis overload sensor, a power supply circuit board, two redundancy control boards and a data storage board, the three-axis overload sensor is connected with the input ends of the two redundancy control boards and the data storage board respectively, and the power supply circuit board is connected with the three-axis overload sensor, the two redundancy control boards and the data storage board respectively. The application can safely and reliably output starting signals when an airplane emergency accident occurs, improve the search and rescue means of the positioning system, and can record the overload data of the whole flight of the airplane in real time, which is an important basis for the airplane flight and the overload data analysis afterwards.

Description

Technical Field

[0001] The invention relates to an aircraft emergency life-saving positioning overload starting device with large-capacity data self-recording. Background Art

[0002] Foreign airborne emergency locator transmitters (ELTs) are equipped with an overload activation switch, which automatically triggers the ELT based on overload conditions in the event of an emergency crash. Existing domestic helicopter satellite emergency locator systems offer manual, water-immersion, and overload activation, with the overload activation method being uniaxial. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide an aircraft emergency life-saving positioning overload starting device with large-capacity data self-recording in response to the above-mentioned defects in the prior art, so as to achieve the safe and reliable output of the starting signal when an emergency accident occurs in the aircraft, improve the search and rescue means of the positioning system, and at the same time record the overload data of the aircraft throughout the flight in real time, which is an important basis for the analysis of the aircraft flight and subsequent overload data.

[0004] The technical solution adopted by the present invention to solve the above technical problems is:

[0005] An aircraft emergency life-saving positioning overload starting device with large-capacity data self-recording includes a three-axis overload sensor, a power supply circuit board, two redundancy control boards and a data storage board. The three-axis overload sensor is respectively connected to the input ends of the two redundancy control boards and the data storage board, and the power supply circuit board is respectively connected to the three-axis overload sensor, the two redundancy control boards and the data storage board.

[0006] According to the above technical solution, the three-axis overload sensor is a three-redundant overload sensor.

[0007] According to the above technical solution, the large-capacity data self-recording aircraft emergency life-saving positioning overload starting device also includes a box body, in which the three-axis overload sensor, power circuit board, two redundancy control boards and data storage board are all fixedly arranged.

[0008] According to the above technical solution, the output ends of the two redundancy control boards are both connected to the overload starting device.

[0009] According to the above technical solution, the redundancy control board includes a sampling processor, a filter, an AD conversion module and an operation controller which are connected in sequence.

[0010] According to the above technical solution, the filter is an IIR filter.

[0011] According to the above technical solution, the sampling processor is a DSP sampling processor.

[0012] According to the above technical solution, an identification validity judgment module is connected between the sampling processor and the filter.

[0013] The present invention has the following beneficial effects:

[0014] This device provides an overload-based activation input source for the lifesaving positioning system, monitors the aircraft's three-axis, six-directional overload, and uses two redundant control panels to safely control and output the activation output signal of the dual-redundancy control monitoring technology. This allows for safe and reliable output of activation signals in the event of an aircraft emergency. In the event of an emergency crash, forced landing, or other such incident, overload conditions can promptly trigger the emergency positioning system and initiate overload emergency measures, improving the positioning system's search and rescue capabilities. It also records overload data throughout the flight in real time, providing an important basis for flight and post-incident overload data analysis. This device is a new domestic activation device for emergency positioning transmitters based on aircraft overload signals and equipped with large-capacity data self-recording. Based on equipment requirements, by binding activation conditions, it can be expanded to overload monitoring for other emergency positioning and rescue systems, as well as applications in automotive collision avoidance systems, demonstrating promising application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of a large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to an embodiment of the present invention;

[0016] Figure 2 This is a flowchart of the work flow of the large-capacity data self-recording aircraft emergency life-saving positioning overload starting device in an embodiment of the present invention;

[0017] In the figure, 1-three-axis overload sensor, 2-redundancy control B board, 3-redundancy control A board, 4-power supply circuit board, 5-data storage board, 6-box body. DETAILED DESCRIPTION

[0018] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0019] Reference Figures 1 and 2 As shown, in one embodiment of the present invention, a large-capacity data self-recording aircraft emergency life-saving positioning overload starting device includes a three-axis overload sensor, a power supply circuit board, two redundancy control boards, and a data storage board. The three-axis overload sensor is respectively connected to the input ends of the two redundancy control boards and the data storage board, and the power supply circuit board is respectively connected to the three-axis overload sensor, the two redundancy control boards, and the data storage board.

[0020] Furthermore, the power supply circuit board supplies power to the three-axis overload sensor, two redundancy control boards and the data storage board. The three-axis overload sensor collects the acceleration values ​​of the single components of the X, Y and Z axes and transmits the collected signals to the two redundancy control boards at the same time. The output ends of the two redundancy control boards are connected to the overload starting device. Only when the two redundancy control boards determine that they are in an overload state based on the collected signals and output them to the overload starting device, the overload starting device will be activated.

[0021] Furthermore, the two redundancy control boards are respectively a redundancy control board A and a redundancy control board B.

[0022] Furthermore, the triaxial overload sensor is a triple-redundant overload sensor.

[0023] Furthermore, the large-capacity data self-recording aircraft emergency life-saving positioning overload starting device also includes a box body, and the three-axis overload sensor, the power circuit board, the two redundancy control boards and the data storage board are all fixedly arranged in the box body.

[0024] Furthermore, the output terminals of the two redundancy control boards are both connected to the overload starting device.

[0025] Furthermore, the redundancy control board includes a sampling processor, a filter, an AD conversion module and an operation controller which are connected in sequence.

[0026] Furthermore, the filter is an IIR filter.

[0027] Furthermore, the sampling processor is a DSP sampling processor.

[0028] Furthermore, an identification validity judgment module is connected between the sampling processor and the filter.

[0029] Further, the device is composed of three-redundancy three-axis overload sensor, power circuit board, redundancy control A board, redundancy control B board, data storage board, box body assembly and the like. Military overload sensor is used as control input source, to sense external acceleration signal, to convert into electric signal and input control board and data storage board assembly; overload signal monitoring and processing technology is used, to collect and filter signal in control circuit assembly; sensor three-redundancy signal processing technology is used, to realize effectiveness discrimination of redundancy sensor signal; two-redundancy control boards are used, to realize safety control and output of two-redundancy control monitoring technology starting output signal; overload starting threshold and starting pulse width condition judgment technology is used, to realize judgment of crash, forced landing and the like; the application has special data data storage board, can realize 4-channel overload sensor acquisition at 1KHz sampling rate, and record data, realizes data download according to requirement, provides data reserve for airplane flight data and event data analysis. The starting output signal of the application reports overload starting information to positioning system through communication combined with signal of hardware signal redundancy, improves system safety, realizes safe and reliable output starting signal when airplane emergency occurs.

[0030] Working principle of the application:

[0031] After the product is powered on, the power circuit board completes power filtering, power conversion and isolation, provides power for the sensor, redundancy control board and data storage board, the three-redundancy overload sensor senses three-redundancy three-axis overload in real time, the double-redundancy control board collects three-redundancy three-axis overload data, judges redundancy signal effectiveness of overload signal, redundancy voting, sensor signal filtering and starting condition monitoring, when overload signal value meets starting threshold and pulse width condition, immediately outputs starting signal; the redundancy control board performs self-checking during overload signal monitoring, and communicates with emergency positioning system to report overload data and self-checking state in time. The data storage board collects three-axis overload sensor in real time, and stores in data storage.

[0032] The implementation process of the application includes the following steps:

[0033] Step 1, three-axis acceleration sensor senses X, Y, Z three-axis single component acceleration value, to provide overload signal judgment input source.

[0034] Step 2, DSP sampling is performed on overload sensor signal.

[0035] Step 3, effectiveness discrimination is performed by using sensor signal range.

[0036] Step 4, effective overload signal digital IIR filter filtering is performed, to filter out signal higher than installation position vibration frequency in sampling signal, to obtain low-frequency overload signal.

[0037] Step 5: Calculate the actual physical values ​​of the three-axis accelerations based on the conversion relationship between the actual physical dimension and AD conversion.

[0038] Step 6: The three axial component accelerations are synthesized into a vector sum acceleration according to the synthetic vector sum operation method.

[0039] Step 7: When the synthesized acceleration signal is greater than the initial startup threshold, the software counter starts timing. If the counter continues timing to reach the startup pulse width, it is determined that the startup pulse width condition is met, and the signal output can be started. If the synthesized acceleration signal appears to be less than the initial startup threshold during the counting, the counter stops timing and returns to zero, and the signal output is not started.

[0040] By starting the logic judgment method of the threshold and pulse width combination, when the crash signal arrives, only the continuous pulse width acceleration signal that reaches the threshold or above is determined to have met the trigger condition.

[0041] Step 8: When the start pulse width condition is reached and the threshold judgment condition is satisfied, the start signal output is started.

[0042] This overload start method uses a three-axis vector sum overload signal algorithm based on energy principles. This algorithm uses a vector sum algorithm to calculate the vector value of the three-axis overload signal and determine whether the overload start condition has been met. The following strategy is employed: a three-axis accelerometer senses the acceleration values ​​of the X, Y, and Z axes in real time and outputs analog three-axis sensor values. These values ​​are then converted into effective acceleration values ​​of the three axes through AD acquisition, sensor signal validity determination, low-pass digital filtering, and physical quantity transformation by a processor. These three-axis acceleration values ​​are then processed through a vector synthesis algorithm to generate a composite acceleration value. This composite acceleration signal is then compared with the given overload start condition. When the composite acceleration start condition is met, a start signal is output.

[0043] The present invention proposes an overload activation method based on the vector sum of three-axis overload signals. This technology enables timely triggering of the emergency positioning system by monitoring the three-axis composite overload conditions in the event of an emergency crash, forced landing, or other complex environmental incidents involving any force direction, thereby further improving the overload trigger envelope for aircraft emergency life-saving positioning. The energy-based three-axis vector sum overload activation method is applied to the second-generation overload activation device of the aircraft emergency life-saving positioning system. This method can also be applied to other energy-based signal processing and design, automotive collision avoidance, and other triggering systems, and has excellent application prospects.

[0044] The above are only preferred embodiments of the present invention, and certainly cannot be used to limit the scope of rights of the present invention. Therefore, equivalent changes made according to the scope of the patent application of the present invention still fall within the scope of protection of the present invention.

Claims

1. A large-capacity data self-recording aircraft emergency life-saving positioning overload starting device, characterized in that: It includes a three-axis overload sensor, a power supply circuit board, two redundancy control boards and a data storage board. The three-axis overload sensor is connected to the input ends of the two redundancy control boards and the data storage board respectively. The power supply circuit board is connected to the three-axis overload sensor, the two redundancy control boards and the data storage board respectively. The three-axis overload sensor collects the acceleration values ​​of the single components of the X, Y, and Z axes and transmits the collected signals to the two redundancy control boards at the same time. The output ends of the two redundancy control boards are connected to the overload start device. The overload start device will only be activated when the two redundancy control boards determine that the overload state is in effect based on the collected signals and output them to the overload start device. The signal processing flow of the redundancy control board includes the following steps: Step 1: The three-axis overload sensor senses the acceleration values ​​of the single components of the X, Y, and Z axes and provides an overload signal to determine the input source; Step 2: Perform DSP sampling on the three-axis overload sensor signals; Step 3: Use the range of the three-axis overload sensor signal to determine the validity; Step 4: Filter out the signal with a higher vibration frequency than the installation position in the sampling signal to obtain a low-frequency overload signal; Step 5: Calculate the actual physical values ​​of the three-axis accelerations based on the conversion relationship between the actual physical dimension and AD conversion; Step 6: The three axial components of acceleration are combined into a vector sum acceleration according to the combined vector sum calculation method; Step 7: When the synthesized acceleration signal is greater than the initial startup threshold, the software counter starts timing. If the counter continues timing to reach the startup pulse width, it is determined that the startup pulse width condition is met, and the signal output can be started. If the synthesized acceleration signal appears to be less than the initial startup threshold during the counting, the counter stops timing and returns to zero, and the signal output is not started. By starting the logic judgment method of the initial threshold and pulse width combination, when the crash signal arrives, only the continuous pulse width acceleration signal that reaches the threshold or above is considered to have met the trigger condition; Step 8: When the start pulse width condition is reached and the threshold judgment condition is satisfied, the start signal output is started; The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device also includes a box body, a three-axis overload sensor, a power supply circuit board, two redundancy control boards and a data storage board are all fixedly arranged in the box body; Two redundant control boards are used to realize the safe control and output of the output signal of the dual-redundancy control monitoring technology. The overload starting threshold and starting pulse width condition judgment technology are used to realize the judgment of the collision and forced landing accident status. It is equipped with a dedicated data storage board to realize data collection and data recording by the three-axis overload sensor, and data download is realized according to demand, providing data reserves for aircraft flight data and event data analysis.

2. The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to claim 1 is characterized in that: The triaxial overload sensor is a triple-redundant overload sensor.

3. The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to claim 1 is characterized in that: The redundancy control board includes a sampling processor, a filter and an operation controller which are connected in sequence.

4. The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to claim 3 is characterized in that: The filter is an IIR filter.

5. The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to claim 3 is characterized in that: The sampling processor is a DSP sampling processor.

6. The large-capacity data self-recording aircraft emergency life-saving positioning overload starting device according to claim 5 is characterized in that: An identification validity judgment module is connected between the sampling processor and the filter.

Images