Adaptive flight recorder distress detection and ejection control method and system

Abstract

The present application relates to the field of civil aircraft avionics technology, and provides a kind of self-adapting flight recorder distress detection and eject control method and system, the method comprises: the flight parameter of real-time acquisition aircraft, real-time to the load and the environment that aircraft is subjected to are perceived, distress detection, risk level adjustment, flight recorder ejection point determination, flight recorder ejection determination.The system includes flight parameter acquisition module, sensor module, distress detection module, risk level adjustment module, ejection point area calculation module and ejection determination module.The present application is detected by being in distress scene, risk level adjustment is carried out, combined with sensor detection result, and point area calculation is carried out, and comprehensive judgment can be realized when aircraft encounters accident, recorder pops out in time, saves flight data for accident investigation, and reduces the damage to ground personnel and building.

Description

Technical Field

[0001] This invention relates to the field of avionics technology for civil aircraft, and in particular to an adaptive flight recorder distress detection and ejection control method and system. Background Technology

[0002] The 2009 Air France AF447 and 2014 Malaysia Airlines MH370 accidents caused a global uproar, highlighting the limitations of current air navigation systems in promptly identifying and locating distressed aircraft, leading to delays or even the inability to recover flight data recorders from the affected aircraft. Member states of the International Civil Aviation Organization (ICAO) and the global industry began systematically advancing aircraft tracking and monitoring efforts, and promoting the development of automatic ejector flight data recorder (AEVR) technology.

[0003] After the recorder is ejected, it will have a certain speed upon landing, so the damage to the ground needs to be assessed. Summary of the Invention

[0004] The purpose of this invention is to overcome at least one of the shortcomings of the prior art and provide an adaptive flight recorder distress detection and ejection control method and system, which can automatically eject the recorder in the event of an aircraft crash, save flight data for accident investigation, and assess the landing point after the recorder is ejected. When the landing point is located in water or mountainous areas with few people and basic buildings, the damage caused to the ground after the recorder is ejected is reduced.

[0005] The present invention adopts the following technical solution:

[0006] On one hand, the present invention provides an adaptive flight recorder distress detection and ejection control method, comprising:

[0007] S1. Obtain the aircraft's flight parameters in real time;

[0008] S2. Real-time perception of the load on the aircraft and its environment.

[0009] S3. Distress Detection: Based on the real-time flight parameters obtained in step S1 and the real-time aircraft load and environment obtained in step S2, determine whether the aircraft is in distress.

[0010] S4. Risk Level Adjustment: When the aircraft is in distress, the current risk level is adjusted according to different distress scenarios and flight stages. Different risk levels correspond to different risk level thresholds. When the risk level threshold is exceeded, the aircraft distress alarm result is output.

[0011] S5. Flight recorder ejection landing point determination: After step S3 outputs the aircraft emergency alarm result, the landing point area of ​​the flight recorder after ejection is calculated based on real-time flight parameters.

[0012] S6. Flight recorder ejection judgment: Based on the classification of the landing area obtained in step S5, determine whether to eject the flight recorder.

[0013] In addition to any of the possible implementations described above, another implementation is provided in which the flight parameters in step S1 include, but are not limited to, flight phase, altitude, speed, engine parameters, heading angle, and alarm information.

[0014] In addition to any of the possible implementations described above, a further implementation is provided in which, in step S2, sensors are used to perceive the load borne by the aircraft and its environment.

[0015] In addition to any of the possible implementations described above, another implementation is provided in which, in step S4, the risk is relatively low when the aircraft is on the ground, which is the first risk level.

[0016] When the aircraft is in the cruise phase, there is a certain risk, which is classified as the second risk level.

[0017] The risk level is level 3 when the aircraft is in one of the stages of takeoff, climb, approach, or landing.

[0018] When an aircraft is in distress, the risk is the highest, classified as the fourth risk level.

[0019] Different risk levels have different risk level thresholds, which are the sensor measurements that meet the ejection conditions at that risk level. The risk level thresholds are determined based on aircraft design values, standard clauses, and flight statistics.

[0020] In addition to any of the possible implementations described above, another implementation is provided in which, in step S5, by acquiring flight parameters including but not limited to altitude, speed, and heading angle, the speed, angle, and other states of the recorder after ejection are calculated in real time, the landing position after ejection is calculated in combination with aerodynamics, and the landing area of ​​the recorder is calculated in combination with terrain data.

[0021] In addition to any of the possible implementations described above, another implementation is provided, in step S6,

[0022] If the landing area after ejection is in an area with few people and buildings, and the flight recorder will cause little damage to the ground after landing, then it is determined to eject the flight recorder.

[0023] If the landing area after ejection is located in a densely populated area with many buildings, and the flight recorder would cause significant damage to the ground upon landing, then it will be determined not to eject the flight recorder.

[0024] In addition to any of the possible implementations described above, another implementation is provided in which the sparsely populated and sparsely built areas include water bodies, mountainous areas, and open areas of towns; and the sparsely populated and sparsely built areas include cities with high population or infrastructure density.

[0025] On the other hand, the present invention also provides an adaptive flight recorder distress detection and ejection control system, the system comprising a flight parameter acquisition module, a sensor module, a distress detection module, a risk level adjustment module, an ejection landing area calculation module, and an ejection judgment module:

[0026] The flight parameter acquisition module is used to acquire aircraft flight parameters in real time;

[0027] The sensor module is used to perceive the load on the aircraft and the environment in real time.

[0028] The distress detection module determines whether the aircraft is in distress based on the flight parameters, the load the aircraft is bearing, and the environment it is in, and outputs the distress detection result.

[0029] The risk level adjustment module receives detection results from the distress detection module and adjusts the current risk level of the aircraft according to different distress scenarios and flight stages. Different risk levels correspond to different sensor thresholds. The module also receives detection results from the sensor module and outputs the results to the ejection judgment module when the sensor detection results exceed the current risk level threshold.

[0030] The ejection landing area calculation module calculates the landing area after the recorder is ejected in real time using real-time flight parameters.

[0031] The ejection judgment module receives the results from the risk level adjustment module and the ejection landing area calculation module and makes a comprehensive judgment. When it simultaneously receives signals that the sensor exceeds the current risk level threshold and the ejection landing area meets the ejection requirements, it sends an ejection separation command to the ejection separation mechanism to complete the ejection separation process of the ejectable flight recorder.

[0032] In addition to any of the possible implementations described above, another implementation is provided in which the ejection judgment module acquires flight parameters including but not limited to altitude, speed, and heading angle, calculates the speed, angle, and other states of the recorder after ejection in real time, calculates the landing position after ejection in combination with aerodynamics, and calculates whether the landing area of ​​the recorder is a water area, a mountainous area, or an area with low population density in combination with terrain data, and outputs the results to the ejection judgment module.

[0033] On the other hand, the present invention also provides an aircraft equipped with the aforementioned adaptive flight recorder distress detection and ejection control system.

[0034] The beneficial effects of this invention are as follows: By detecting distress scenarios and adjusting risk levels, and combining sensor detection results with landing area calculations, this invention makes a comprehensive judgment, enabling the recorder to pop out in time when an aircraft encounters an accident, saving flight data for accident investigation, and reducing damage to ground personnel and buildings. Attached Figure Description

[0035] Figure 1 The diagram shown is a flowchart of an adaptive flight recorder distress detection and ejection control method according to an embodiment of the present invention.

[0036] Figure 2 The diagram shown is a structural schematic of an adaptive flight recorder distress detection and ejection control system according to an embodiment of the present invention. Detailed Implementation

[0037] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be considered in isolation, but can be combined with each other to achieve better technical effects.

[0038] like Figure 1 As shown in the figure, an adaptive flight recorder distress detection and ejection control method according to an embodiment of the present invention includes:

[0039] S1. Obtain the aircraft's flight parameters in real time;

[0040] S2. Real-time perception of the load on the aircraft and its environment.

[0041] S3. Distress Detection: Based on the real-time flight parameters obtained in step S1 and the real-time aircraft load and environment obtained in step S2, determine whether the aircraft is in distress.

[0042] S4. Risk Level Adjustment: When the aircraft is in distress, the current risk level is adjusted according to different distress scenarios and flight stages. Different risk levels correspond to different risk level thresholds. When the risk level threshold is exceeded, the aircraft distress alarm result is output.

[0043] S5. Flight recorder ejection landing point determination: After step S3 outputs the aircraft emergency alarm result, the landing point area of ​​the flight recorder after ejection is calculated based on real-time flight parameters.

[0044] S6. Flight recorder ejection judgment: Based on the classification of the landing area obtained in step S5, determine whether to eject the flight recorder.

[0045] In one specific embodiment, in step S1, the flight parameters include, but are not limited to, flight phase, altitude, speed, engine parameters, heading angle, alarm information, etc.

[0046] In one specific embodiment, in step S2, sensors are set up to sense the load on the aircraft and the environment in which it is located.

[0047] In one specific embodiment, in step S4, when the aircraft is on the ground, the risk is relatively small, which is the first risk level;

[0048] When the aircraft is in the cruise phase, there is a certain risk, which is classified as the second risk level.

[0049] The risk level is level 3 when the aircraft is in one of the stages of takeoff, climb, approach, or landing.

[0050] When an aircraft is in distress, the risk is the highest, classified as the fourth risk level.

[0051] Different risk levels have different risk level thresholds, which are the sensor measurements that meet the ejection conditions at that risk level. The risk level thresholds are determined based on aircraft design values, standard clauses, and flight statistics.

[0052] In one specific embodiment, in step S6,

[0053] If the landing area after ejection is in an area with few people and buildings, and the flight recorder will cause little damage to the ground after landing, then it is determined to eject the flight recorder.

[0054] If the landing area after ejection is located in a densely populated area with many buildings, and the flight recorder would cause significant damage to the ground upon landing, then it will be determined not to eject the flight recorder.

[0055] In one specific embodiment, the areas with sparse population and buildings include water bodies, mountainous areas, and open areas of towns; the areas with sparse population and buildings include cities with high population or infrastructure density.

[0056] like Figure 2 As shown in the figure, an adaptive flight recorder distress detection and ejection control system according to an embodiment of the present invention includes a flight parameter acquisition module, a sensor module, a distress detection module, a risk level adjustment module, an ejection landing area calculation module, and an ejection judgment module:

[0057] The flight parameter acquisition module is used to acquire aircraft flight parameters in real time;

[0058] The sensor module is used to perceive the load on the aircraft and the environment in real time.

[0059] The distress detection module determines whether the aircraft is in distress based on the flight parameters, the load the aircraft is bearing, and the environment it is in, and outputs the distress detection result.

[0060] The risk level adjustment module receives detection results from the distress detection module and adjusts the current risk level of the aircraft according to different distress scenarios and flight stages. Different risk levels correspond to different sensor thresholds. The module also receives detection results from the sensor module and outputs the results to the ejection judgment module when the sensor detection results exceed the current risk level threshold.

[0061] The ejection landing area calculation module calculates the landing area after the recorder is ejected in real time using real-time flight parameters.

[0062] The ejection judgment module receives the results from the risk level adjustment module and the ejection landing area calculation module and makes a comprehensive judgment. When it simultaneously receives signals that the sensor exceeds the current risk level threshold and the ejection landing area meets the ejection requirements, it sends an ejection separation command to the ejection separation mechanism to complete the ejection separation process of the ejectable flight recorder.

[0063] In one specific embodiment, the ejection judgment module acquires flight parameters including but not limited to altitude, speed, and heading angle, performs real-time calculations on the speed, angle, and other states of the recorder after ejection, calculates the landing position after ejection based on aerodynamics, and calculates whether the landing area of ​​the recorder is a water area, a mountainous area, or an area with low population density based on terrain data, and outputs the results to the ejection judgment module.

[0064] An embodiment of the present invention provides an aircraft equipped with the aforementioned adaptive flight recorder distress detection and ejection control system.

[0065] The adaptive flight recorder distress detection and ejection control method and device provided by this invention can automatically eject the recorder during an aircraft crash, save flight data for accident investigation, and assess the landing point after ejection. When the landing point is located in water or mountainous areas with few people and basic buildings, the damage caused to the ground after the recorder is ejected is reduced.

[0066] While several embodiments of the present invention have been provided herein, those skilled in the art should understand that modifications can be made to these embodiments without departing from the spirit of the invention. The above embodiments are merely exemplary and should not be construed as limiting the scope of the invention.

Claims

1. An adaptive flight recorder distress detection and ejection control method, characterized in that, The method comprises: S1, acquiring flight parameters of the aircraft in real time; S2, sensing the load borne by the aircraft and the environment in which the aircraft is located in real time; S3, distress detection: judging whether the aircraft is in a distress state according to the real-time flight parameters obtained in step S1 and the real-time load borne by the aircraft and the environment in which the aircraft is located obtained in step S2; S4, risk level adjustment: when the aircraft is in a distress state, adjusting the current risk level according to different distress scenarios and flight stages, different risk levels corresponding to different risk level thresholds; when the risk level threshold is exceeded, outputting an aircraft distress alarm result; S5, flight recorder ejection point judgment: after the aircraft distress alarm result is output in step S4, calculating the landing point area of the flight recorder after ejection according to the real-time flight parameters; S6, flight recorder ejection judgment: determining whether to eject the flight recorder according to the classification of the landing point area obtained in step S5.

2. The adaptive flight recorder distress detection and ejection control method of claim 1, wherein, In step S1, the flight parameters include flight stage, height, speed, engine parameters, heading angle, and alarm information.

3. The adaptive flight recorder distress detection and ejection control method of claim 1, wherein, In step S2, the load borne by the aircraft and the environment in which the aircraft is located are sensed by setting sensors.

4. The adaptive flight recorder distress detection and ejection control method of claim 1, wherein, In step S4, when the aircraft is on the ground, the risk is small, and the first risk level is set; when the aircraft is in the cruising stage, there is a certain risk, and the second risk level is set; when the aircraft is in one of the take-off, climbing, approach and landing stages, there is a high risk, and the third risk level is set; when the aircraft is in a distress state, the risk is the highest, and the fourth risk level is set.

5. The adaptive flight recorder distress detection and ejection control method of claim 4, wherein, Different risk levels are set with different risk level thresholds, the risk level threshold is the sensor measurement value corresponding to the risk level that meets the ejection condition; the risk level threshold is determined according to the aircraft design value, standard clauses and flight flight statistical data.

6. The adaptive flight recorder distress detection and ejection control method of claim 1, wherein, In step S6, when the landing point area after ejection is in an area with few people and buildings, the flight recorder causes little damage to the ground after landing, and the flight recorder is determined to be ejected; when the landing point area after ejection is in an area with many people and buildings, the flight recorder causes great damage to the ground after landing, and the flight recorder is determined not to be ejected.

7. The adaptive flight recorder distress detection and ejection control method of claim 6, wherein, The area with few people and buildings includes water area, mountainous area and open area of town; the area with many people and buildings includes city with high population or infrastructure density.

8. An adaptive flight recorder distress detection and ejection control system, characterized by, The system is used to implement the method of any one of claims 1-7, and the system comprises a flight parameter acquisition module, a sensor module, a distress detection module, a risk level adjustment module, an ejection point area calculation module and an ejection judgment module: The flight parameter acquisition module is used to acquire flight parameters of the aircraft in real time; The sensor module is used to sense the load borne by the aircraft and the environment in which the aircraft is located in real time; The distress detection module judges whether the aircraft is in a distress state according to the flight parameters, the load borne by the aircraft and the environment in which the aircraft is located, and outputs a distress detection result; The risk level adjustment module receives the detection result from the distress detection module, adjusts the current risk level of the aircraft according to different distress scenarios and flight stages, and different risk levels correspond to different sensor thresholds. Receiving the detection result from the sensor module, when the sensor detection result exceeds the threshold of the current risk level, output the result to the ejection judgment module; The ejection landing area calculation module calculates the landing area of the recorder after ejection through real-time flight parameters; The ejection judgment module receives the results from the risk level adjustment module and the ejection landing area calculation module for comprehensive judgment, when receiving the signals that the sensor exceeds the threshold of the current risk level and the ejection landing area meets the ejection condition at the same time, sends the ejection separation command to the ejection separation mechanism, and completes the ejection separation process of the ejectable flight recorder.

9. The adaptive flight recorder distress detection and ejection control system of claim 8, wherein, The ejection judgment module calculates the speed and angle state of the flight recorder after ejection in real time by obtaining the flight parameters, calculates the landing position after ejection combined with aerodynamics, determines whether the landing area of the flight recorder is water area, mountainous area, or area with small population density combined with terrain data, and outputs the result to the ejection judgment module.

10. An aircraft, characterized in that The aircraft is provided with the adaptive flight recorder distress detection and ejection control system according to any one of claims 8-9.

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