WO2022016908A1

WO2022016908A1 - Helicopter air separation type emergency flight data recording system

Info

Publication number: WO2022016908A1
Application number: PCT/CN2021/085756
Authority: WO
Inventors: 孙智; 孙建红
Original assignee: 南京航空航天大学
Priority date: 2020-07-23
Filing date: 2021-04-07
Publication date: 2022-01-27
Also published as: CN111806704B; CN111806704A

Abstract

A helicopter air separation type emergency flight data recording system, comprising: an emergency state analysis system, an ejection system and a cushioning/floating system, wherein the emergency state analysis system is used for determining whether a helicopter is in an emergency state, and controlling the ejection system to be started when the helicopter is in the emergency state; the ejection system is used for ejecting the cushioning/floating system out from the helicopter; and the cushioning/floating system comprises: a radio transceiver, an electromechanical module and an air bag wrapping the electromechanical module, the electromechanical module comprises a flight data recorder and a gas generator, the gas generator generates, under the control of the flight data recorder, gas for inflating the air bag, and the radio transceiver is electrically connected to the flight data recorder and broadcasts a positioning signal. The system has the advantage of realizing intelligent and quick separation from an airplane, a strong capability in terms of high-altitude falling resistance, and floating on the surface of the water after falling into water, and easy search and rescue.

Description

A helicopter air-separated emergency flight data recording system

technical field

The invention relates to the technical field of helicopter emergency, in particular to a helicopter air-separated emergency flight data recording system.

Background technique

With the development of the civil aviation industry at home and abroad, the number of helicopter crashes due to mechanical failures and other reasons is increasing. At present, in order to record the accident process, investigate the cause of the accident, and improve aviation safety, higher requirements are placed on the flight data recorder (FDR). The traditional FDR is fixed inside the helicopter. When the helicopter crashes, the traditional FDR relies on its own impact-resistant structure to protect the internal data storage device. After the helicopter falls into the water, the traditional FDR relies on the waterproof structure to protect the internal data storage device, and relies on the underwater beacon Search and rescue team positioning.

However, the ceiling of civil helicopters is generally 2000-4000 meters, and the ceiling of military helicopters can reach 6000 meters. If the helicopter has a mechanical failure (engine stop, etc.) at high altitude, it will fall at a higher speed. At this time, the impact resistance of traditional FDR The structure will also be damaged to varying degrees. If the helicopter falls into the sea, its wreckage may sink into the deep sea. According to the practice of maritime air disaster rescue, the traditional FDR has problems such as difficult recovery in the deep sea, underwater signal interference, and limited battery life. Salvage costs skyrocketed.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a helicopter air-separated emergency flight data recording system with strong anti-falling ability and easy search and rescue.

For achieving the above object, the present invention provides the following scheme:

A helicopter air-separated emergency flight data recording system, comprising: an emergency state analysis system, an ejection system and a buffer/floating system;

The emergency state analysis system is used to judge whether the helicopter is in an emergency state, and when the helicopter is in an emergency state, control the launch of the ejection system;

the ejection system for ejecting the buffer/float system from the helicopter;

The buffering/floating system includes: a radio transceiver, an electromechanical module, and an airbag wrapped outside the electromechanical module; the electromechanical module includes a flight data recorder and a gas generator, and the gas output port of the gas generator is connected to the airbag. The gas input port of the airbag is communicated, and the gas generator generates gas for filling the airbag under the control of the flight data recorder; the radio transceiver is electrically connected with the flight data recorder, and uses Positioning signals are broadcast and flight data is transmitted under the control of the flight data recorder.

Optionally, the ejection system includes: a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston and a propellant; the ejection cylinder is installed on the ejection cylinder base, and the ejection cylinder is installed in the ejection cylinder by the ejection cylinder. The propellant, the piston and the buffer/floating system are distributed in sequence from the bottom to the outlet, the piston is coaxial with the ejection cylinder, and the first ignition plug is under the control of the emergency state analysis system Ignition initiates the propellant reaction.

Optionally, the flight data recorder is connected to the helicopter electronic device through a cable, and flight data is backed up from the electronic device to the flight data recorder through the cable.

Optionally, the cable includes a first cable, a second cable and a third cable, a first connector is installed on the base, a second connector is installed on the piston, and one end of the first cable is connected to the Electronic equipment is connected, the other end of the first cable is connected to one end of the first connector, the other end of the first connector is connected to one end of the second cable, and the other end of the second cable is connected to the One end of the second connector is connected, the other end of the second connector is connected to the third cable, and the other end of the third cable is connected to the flight data recorder.

Optionally, the helicopter air-separated emergency flight data recording system further includes an ejection attitude control device, the ejection system is installed on the ejection attitude control device, and the ejection attitude control device obtains the helicopter from the emergency state analysis system. flight attitude information, the control motor of the launch attitude control device adjusts the ejection angle according to the attitude information.

Optionally, the ejection attitude control device includes a support, an ejection system mounting seat, a pulley link device and a control motor; the ejection system mounting seat includes a base and a straight rod fixedly connected to one side of the base; the The pulley link device includes two pulleys connected by a first link, and a second link pivotally connected with the first link; the ejection system is installed in the base of the ejection system mounting seat, so The ejection system mounting base is rotatably connected with the support, the straight rod is inserted into the gap between two pulleys, and the control motor is connected with the second link of the pulley link device for driving the pulley The second link swings.

Optionally, the gas generator includes a second ignition plug and a chemical reaction raw material for generating gas, the second ignition plug is electrically connected to the flight data recorder, and the second ignition plug is used in the flight. Ignition under the control of the data logger initiates the reaction of the chemical reaction feedstock.

Optionally, a gas channel and a one-way valve are provided in the electromechanical module, and the gas generated by the gas generator enters the air bag through the gas channel and the one-way valve.

Optionally, the flight data recorder is covered with a protective shell outside, and a shock absorbing material is provided between the flight data recorder and the protective shell.

Optionally, the radio transceiver, located outside the space enclosed by the airbag, is connected to the flight data recorder through the third cable.

According to the specific embodiment provided by the present invention, the present invention discloses the following technical effects: the helicopter air-separated emergency flight data recording system provided by the present invention includes an emergency state analysis system, an ejection system and a buffer/floating system. When the emergency state analysis system determines When the helicopter is currently in an emergency, the control ejection system ejects the buffer/float system from the helicopter and separates it from the helicopter. After the buffer/float system is separated from the helicopter, the gas generator in it generates gas to inflate the air bag wrapped outside. During the landing process, the air bag plays a role in buffering the landing. If it falls into the water, the air bag can also play a role in making The device floats on the water. The above setting method avoids the crash of the flight data recorder with the helicopter, and the impact overload when the flight data recorder collides with the ground (or water surface) is greatly reduced by the buffering of the airbag. When falling into the water, the recorder can be floated on the water. In addition, the helicopter air-separated emergency flight data recording system provided by the present invention is also provided with a radio transceiver, which can broadcast positioning signals to the outside world, which is easy for the outside world to discover and search and rescue, and at the same time, it can also remotely wirelessly transmit flight data for the search and rescue team.

Description of drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings required in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some of the present invention. In the embodiments, for those of ordinary skill in the art, other drawings can also be obtained according to these drawings without any creative effort.

1 is a schematic structural diagram of a helicopter air-separated emergency flight data recording system provided by an embodiment of the present invention;

2 is a side view of an installation position of a helicopter air-separated emergency flight data recording system provided by an embodiment of the present invention;

3 is a top view of another installation location of a helicopter air-separated emergency flight data recording system provided by an embodiment of the present invention;

4 is a cross-sectional view of main components of an ejection system provided by an embodiment of the present invention;

5 is a schematic structural diagram of an ejection attitude control device provided by an embodiment of the present invention;

FIG. 6 is a schematic structural diagram of a buffering/floating system provided by an embodiment of the present invention;

7 is a schematic structural diagram of an airbag provided by an embodiment of the present invention;

8 is a cross-sectional view of the main components of the buffer/float system provided by an embodiment of the present invention;

9 is a schematic diagram of a model in the numerical simulation of the airbag falling to the ground in a specific example of the present invention;

Fig. 10(a) is a perspective view of the inside of the airbag at the moment when the airbag starts to deform in a specific example of the present invention; Fig. 10(b) is an external view of the airbag at the moment when the airbag starts to deform in the specific example of the present invention; Fig. 10(c) is a specific example of the present invention. The internal perspective view of the airbag at the time of maximum deformation of the airbag in the example; FIG. 10(d) is an external view of the airbag at the time of maximum deformation of the airbag in the specific example of the present invention.

1. Emergency analysis system, 2. Ejection system, 3. Cushioning/floating system, 4. Nose installation position, 5. Aircraft belly installation position, 6. Tail installation position, 7. Installation position on the side of the first fuselage, 8. Installation position on the side of the second fuselage, 9. Piston, 10, Ejection barrel, 11, Ejection barrel cover, 12, Propellant, 13, First ignition plug, 14, Ejection barrel base, 15, Helicopter airborne Electronics, 16, first cable, 17, first connector, 18, second cable, 19, second connector, 20, third cable, 21, ejector barrel lid lock, 22, spring, 23, base, 24 , Support, 25, Shaft, 26, Helicopter interior mounting point, 27, Straight rod, 28, Pulley linkage, 29, Control motor, 30, Electromechanical module, 31, Airbag, 32, Radio transceiver, 33, Flight Data logger, 34, Damping material, 35, Protective casing, 36, Base, 37, Chemical reaction material, 38, Gas generator, 39, Second ignition plug, 40, Check valve, 41, Airbag inflation port , 42, the ground.

detailed description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In order to make the above objects, features and advantages of the present invention more clearly understood, the present invention will be described in further detail below with reference to the accompanying drawings and specific embodiments.

FIG. 1 is a schematic structural diagram of a helicopter air-separated emergency flight data recording system provided by an embodiment of the present invention. Referring to FIG. 1 , the helicopter air-separated emergency flight data recording system provided by this embodiment includes: an emergency state analysis system 1, an ejection system 2 and cushioning/floating system 3. Among them, the emergency state analysis system 1 is used to judge whether the helicopter is in an emergency state, and when the helicopter is in an emergency state, it controls the ejection system 2 to start. Ejection system 2, used to eject the buffer/float system 3 from the helicopter. The buffer/float system 3 includes: a radio transceiver, an electromechanical module, and an airbag wrapped outside the electromechanical module; the electromechanical module includes a flight data recorder and a gas generator, and the gas output port of the gas generator communicates with the gas input port of the airbag, and the gas The generator generates gas for filling the airbag under the control of the flight data recorder; the radio transceiver is electrically connected to the flight data recorder for broadcasting positioning signals and transmitting flight data under the control of the flight data recorder.

In this embodiment, the emergency state analysis system 1 may have its own sensors such as acceleration and altitude, as well as data interfaces for the helicopter emergency flotation system, the ground proximity warning system and the helicopter flight control system. After comprehensively analyzing the data, the emergency state analysis The system is responsible for judging whether the helicopter is in an emergency state. When the helicopter is in an emergency state, the ejection system 2 is activated. At this time, the emergency analysis system 1 will control the ejection system 2 to eject the buffer/float system 3 from the helicopter. When the buffer/float system 3 is ejected from the fuselage, the flight data recorder controls the gas generator to generate gas, and the gas will quickly fill the airbag of the buffer/float system. When the buffering/floating system 3 falls into water (or falls to the ground), the airbag can not only effectively reduce the impact, but also provide sufficient buoyancy for the buffering/floating system 3 to float on the water surface when the water falls. After the buffer/float system falls into the water (or the ground), the radio transceiver starts broadcasting a positioning signal. When the search and rescue aircraft sends commands to the radio transceiver, the radio transceiver uploads the data from the data logger to the search and rescue aircraft.

It should be noted that the present invention may use one or more of the following according to different helicopter types, different operating (or using) units, and different relevant laws (or industry regulations, etc.) in the location (or country) of operation (or use) The judgment logic judges whether the helicopter is in an emergency state. If multiple judgment logics are used, the user can choose to satisfy one judgment logic that the helicopter is in an emergency state, or satisfy several judgment logics at the same time to consider that the helicopter is in an emergency state. The following is the judgment logic of the emergency state analysis system:

1) If the helicopter emergency flotation system is activated, the helicopter is considered to be in an emergency state. In this judgment logic, according to the specific situation of the user, the helicopter can be selected to judge that the helicopter is in an emergency state immediately after the helicopter emergency flotation system is activated, or to judge that the helicopter is in an emergency state after the helicopter emergency flotation system is activated for a period of time (the delay time can be determined according to the user's specific situation). situation adjustment).

2) If the helicopter is alerted to the ground, then the helicopter is considered to be in an emergency state. In the judgment logic, according to the specific situation of the user, the helicopter can be judged in an emergency state immediately after the helicopter is in an emergency state, or the helicopter is in an emergency state after a period of time when the helicopter is in an emergency state. User specific adjustment).

3) Each type of helicopter has a flight envelope (or flight parameters) recommended by the design or production unit. For example: maximum flight altitude, maximum flight speed, maximum deflection angle and speed of the fuselage, etc. These parameters characterize the flight range and usage constraints of the helicopter. If the emergency state analysis system detects that the flight data exceeds the limit range of the above parameters, or does not return to the limit range after exceeding the limit range for a period of time, it will determine that the helicopter is in an emergency state (the delay time can be adjusted according to the user's specific situation). It should be pointed out that, according to the specific situation of the user and the specific situation of the helicopter model, the user can set the limit range of the flight parameters by himself.

As shown in Figures 2 and 3, according to the specific conditions of different models, the helicopter air-separated emergency flight data recording system provided by the present invention can be installed on the nose, belly, tail and side of the fuselage of the helicopter.

As an optional implementation manner, the user can set the startup height of the ejection system 2 according to factors such as the helicopter flight environment and the type of tasks to be performed. The ejection system 2 independently judges the current helicopter altitude through its own altitude sensor and the received helicopter altitude data. If the ejection system 2 activation altitude is set, the buffer/float system 3 is ejected from the fuselage only when the helicopter descends (or falls) below the set altitude.

As an optional embodiment, the ejection system 2 includes: a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston, and a propellant; the ejection cylinder is installed on the ejection cylinder base, and the ejection cylinder extends from the ejection cylinder bottom to the ejection cylinder base. The outlet is sequentially distributed with propellant, piston and buffer/floating system, the piston is coaxial with the ejection cylinder, and the first ignition plug is ignited under the control of the emergency state analysis system to trigger the propellant reaction.

The specific structure of the ejection system 2 can be shown in FIG. 4 , one end of the ejection cylinder 10 is connected with the ejection cylinder base 14 by threads, and the other end of the ejection cylinder 10 is connected with the ejection cylinder cover 11 through the spring 22 . The ejector barrel cover lock 21 is fixed on the ejector barrel 10 . When the ejection system 2 is in standby, one end of the ejection barrel cover 11 is locked by the ejection barrel cover lock 21 . The piston 9 is placed inside the ejection barrel 10 , and the lower stop point for the movement of the piston 9 in the ejection barrel 10 is the end of the ejection barrel base 14 . The first ignition plug 13 is fixed on the ejection cylinder base 14, one end of the first ignition plug 13 protrudes from the ejection cylinder base 14, and the other end penetrates into the ejection cylinder base 14 and is embedded in the propellant 12, and the propellant 12 is fixed in the ejection cylinder base 14. The interior of the ejector base 14. After the ejection system 2 is activated, the first ignition plug 13 triggers the chemical reaction of the propellant 12, rapidly releases a large amount of gas, and generates high pressure behind the piston 9 to push the piston 9 to move forward. At the same time, the ejection cylinder cover lock 21 is opened, and under the action of the spring 22, the ejection cylinder cover 11 is opened, and then the buffer/float system 3 is ejected from the fuselage.

In this embodiment, the flight data recorder is connected to the helicopter electronic equipment through a cable. When the aircraft is in an emergency, the flight data is backed up from the electronic equipment (ie, the flight control computer on the helicopter) to the flight control computer through the cable. in the data logger. The specific setting method can be as follows: as shown in FIG. 4 , the helicopter onboard electronic equipment 15 is connected to the first connector 17 through the first cable 16, and the second cable 18 is connected between the first connector 17 and the second connector 19, The connection between the second connector 19 and the flight data recorder is via a third cable 20 . Both the first connector 17 and the second connector 19 described above can be used to transmit data. The first joint 17 is fixed on the ejection barrel base 14 by threads (or other means), and the second joint 19 is fixed on the piston 9 by threads (or other means). When the piston 9 is moved to the outlet of the ejector base 14, the second cable 18 is straightened, preventing the piston 9 from being ejected from the fuselage. The third cable 20 and the second connector 19 are simply plug-in connection. After the buffer/float system 3 pops out of the fuselage, the third cable 20 is quickly straightened, and then under the inertia of the buffer/float system 3, The plug at one end of the third cable 20 is pulled out from the second connector 19, and the buffer/float system 3 is completely separated from the helicopter at this time.

As an implementation manner, the helicopter air-separated emergency flight data recording system provided in this embodiment further includes an ejection attitude control device, and the ejection attitude control device is used to adjust and control the attitude of the ejection system. As shown in FIG. 5 , the ejection attitude control device includes a support 24 , an ejection system mounting seat, a pulley link device 28 and a control motor 29 . The ejection system mounting seat includes a base 23 and a straight rod 27 fixedly connected to one side of the base 23 , and the ejection system 2 is installed in the base 23 . The pulley link device 28 includes two pulleys connected by a first link, and a second link pivotally connected with the first link. The ejection system mounting base is rotatably connected with the support 24, the straight rod 27 is inserted into the gap between the two pulleys (the size of the gap is equivalent to the diameter of the straight rod 27), the pulley link device 28 is fixed on the control motor 29, and the control motor 29 Fastened to the mounting point inside the helicopter. The control motor 29 receives the helicopter flight attitude and other information transmitted by the emergency state analysis system, and quickly changes the attitude of the ejection attitude control device by adjusting the swing angle of the pulley link device 28, thereby changing the ejection angle, which can avoid the high-altitude rotor and the low-altitude to the ground. catapult. The ejection attitude control device is fixed to the interior mounting point 26 of the helicopter by means of the support 24 . A shaft 25 is provided on the support 24 so that the ejection attitude control device can be rotated about the shaft 25 . The shaft 25 can also be a rolling ball, or a universal shaft, so that the ejection attitude control device can have a greater degree of rotational freedom.

Wherein, the ejection cylinder base 14 of the ejection system 2 can be fixed on the base 23 of the ejection attitude control device by means of threads (or welding or other means). As can be seen from FIG. 4 , the ejection cylinder base 14 is connected with a first connector 17 , and the first connector 17 and the first cable 16 can protrude from the hole (A in FIG. 5 ) of the ejection attitude control device.

In this embodiment, as an implementation, the gas generator includes a second ignition plug and a chemical reaction raw material for generating gas, the second ignition plug is electrically connected to the flight data recorder, and the second ignition plug is in the flight data recorder. Ignition under the control of the device initiates the reaction of the chemical reaction raw materials. The electromechanical module is provided with a gas channel and a one-way valve, and the gas generated by the gas generator enters the air bag through the gas channel and the one-way valve. Specifically, as shown in FIG. 6 , the chemical reaction raw material 37 is stored in the gas generator 38 , the second ignition plug 39 is fixed on the top of the gas generator 38 , and one end of the second ignition plug 39 is embedded in the chemical reaction raw material 37 , The other end is connected to the flight data recorder 33 . The air outlet of the gas generator 38 is fixed on the base 36 by threads, and the air outlet of the gas generator 38 is communicated with the air transport channel inside the base 36, which is obtained by drilling holes on the base 36 instead of Buried pipeline. The one-way valve 40 is also installed on the base 36 , and the other end outlet of the gas delivery channel is communicated with the one-way valve 40 . The one-way valve 40 is connected to the airbag inflation port 41 . When the buffer/float system 3 is ejected from the fuselage, the second ignition plug 39 triggers the chemical reaction of the chemical reaction raw material 37, and releases a large amount of gas rapidly. These gases enter the air bag 31 through the one-way valve 40 . The protective casing 35 of the flight data recorder 33 is mounted on the base 36 , and the flight data recorder 33 is connected to the third cable 20 . The third cable 20 passes through the protective casing 35 and the base 36 and is connected to the second connector 19 of the ejection system 2 . A shock absorbing material 34 is filled between the flight data recorder 33 and the protective casing 35, which has a low density and does not absorb water, and can provide a certain buoyancy.

As shown in FIG. 7 , the airbag 31 has four or more chambers, the electromechanical module 30 is wrapped in the airbag 31 , each chamber of the airbag 31 has an inflation port 41 , and the inflation port 41 is connected to the one-way valve 40 . Each inflation port corresponds to a one-way valve. Each chamber of the airbag 31 is disconnected, and each chamber alone can provide sufficient buoyancy for the cushioning/floating system 3 to float on the water.

In this embodiment, referring to FIG. 8 , the radio transceiver 32 is located outside the space enclosed by the airbag. Specifically, the radio transceiver 32 can be installed on the third cable 20 , and the radio transceiver 32 can be buffered/floated. After the system 3 falls into the water (or the ground), it broadcasts positioning signals and uploads flight data.

When the buffer/float system 3 falls, the radio transceiver 32 acts as a counterweight, which can adjust the center of gravity of the buffer/float system 3 to be below the aerodynamic center. Therefore, the buffer/float system 3 maintains an approximately vertical downward posture during the fall. This approximately vertical falling posture makes the airbag below the electromechanical module 30 contact the ground (or water surface) first when the buffer/floating system 3 falls to the ground (or to the water). Therefore, there is a thicker airbag below the electromechanical module 30 (ie, in FIG. 8 , H2 > H1 ). In this way, the limited gas in the airbag can be used to enhance the cushioning effect when falling into water (or falling to the ground).

By increasing the length of the cable 20, or by increasing the weight of the radio transceiver 32. The distance between the center of gravity and the aerodynamic center of the cushioning/floating system 3 can be increased, thereby increasing the stability of the cushioning/floating system 3 when it falls, ensuring that when the cushioning/floating system 3 falls into the water (or the ground), the thicker side of the airbag faces the water surface or the ground .

The effect of the helicopter air-separated emergency flight data recording system provided by the present invention is verified below by means of a specific verification example:

The total mass of the buffer/floating system 3 is about 1.6kg, the volume of the airbag 31 is about 90L, the windward area of the airbag 31 is about 0.478m ² when falling, and about 143g of sodium azide is needed as the chemical reaction raw material 37 . Using the method of numerical simulation, the aerodynamic coefficient of the cylindrical airbag 31 when falling at a constant speed is calculated, which is about 0.18. According to formula (1), the final falling speed of the buffer/float system 3 can be calculated to be 17.4 m/s. If the buffer/float system 3 is ejected from the fuselage at a low height, its final fall speed will be less than 17.4m/s.

where m is the total mass of the buffering/floating system 3, g is the acceleration of gravity, ρ is the ambient air density (1.2kg/m ³ ), v is the final falling speed of the buffering/floating system 3, and C is when the cylindrical airbag 31 is falling at a constant speed The aerodynamic coefficient, A, is the windward area of the airbag 31 .

As shown in FIG. 9 and FIG. 10 , when the buffer/floating system 3 falls to the ground, the airbag 31 is squeezed and deformed. At the moment when the airbag 31 is deformed the most, there is still a thick airbag under the electromechanical module 30 for protection. In the process of falling to the ground, the maximum overload of the electromechanical module 30 is about 85g (ie, 85 times the gravitational acceleration). When the airbag 31 falls into the water, the maximum overload of the electromechanical module 30 is smaller than the impact of falling to the ground. According to civil aviation regulations such as C123a, the traditional FDR should be able to withstand the maximum overload of 3400g. Comparing the helicopter emergency flight data recording system (HEEFDR) with the traditional FDR, it can be seen that the helicopter air-separated emergency flight data recording system provided by the present invention significantly reduces the impact of the recorder on the ground, and can more effectively protect the flight data.

The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments can be referred to each other.

In this paper, specific examples are used to illustrate the principles and implementations of the present invention. The descriptions of the above embodiments are only used to help understand the methods and core ideas of the present invention; meanwhile, for those skilled in the art, according to the present invention There will be changes in the specific implementation and application scope. In conclusion, the contents of this specification should not be construed as limiting the present invention.

Claims

A helicopter air-separated emergency flight data recording system is characterized by comprising: an emergency state analysis system, an ejection system and a buffer/floating system;

The emergency state analysis system is used to judge whether the helicopter is in an emergency state, and when the helicopter is in an emergency state, control the launch of the ejection system;

the ejection system for ejecting the buffer/float system from the helicopter;

The buffering/floating system includes: a radio transceiver, an electromechanical module, and an airbag wrapped outside the electromechanical module; the electromechanical module includes a flight data recorder and a gas generator, and the gas output port of the gas generator is connected to the airbag. The gas input port of the airbag is communicated, and the gas generator generates gas for filling the airbag under the control of the flight data recorder; the radio transceiver is electrically connected with the flight data recorder, and uses Positioning signals are broadcast and flight data is transmitted under the control of the flight data recorder.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the ejection system comprises: a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston and a propellant; the ejection cylinder is installed On the base of the ejection cylinder, the propellant, the piston and the buffer/floating system are sequentially distributed in the ejection cylinder from the bottom of the ejection cylinder to the outlet, and the piston is coaxial with the ejection cylinder, The first glow plug ignites under the control of the emergency analysis system to initiate the propellant reaction.
The helicopter air-separated emergency flight data recording system according to claim 1 or 2, wherein the flight data recorder is connected with the helicopter electronic equipment through a cable, and the flight data is backed up from the electronic equipment to the helicopter via the cable. in the flight data recorder.
The helicopter air-separated emergency flight data recording system according to claim 3, wherein the cable comprises a first cable, a second cable and a third cable, a first connector is installed on the base, and the piston A second connector is installed thereon, one end of the first cable is connected to the electronic device, the other end of the first cable is connected to one end of the first connector, and the other end of the first connector is connected to the One end of the second cable is connected to one end of the second cable, the other end of the second cable is connected to one end of the second connector, the other end of the second connector is connected to the third cable, and the other end of the third cable is connected to The flight data recorder is connected.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the helicopter air-separated emergency flight data recording system further comprises an ejection attitude control device, and the ejection system is installed in the ejection attitude control device. On the device, the shooting attitude control device obtains the helicopter flight attitude information from the emergency state analysis system, and the control motor of the shooting attitude control device adjusts the ejection angle according to the attitude information.
The helicopter air-separated emergency flight data recording system according to claim 5, wherein the ejection attitude control device comprises a support, an ejection system mounting seat, a pulley link device and a control motor; the ejection system mounting seat It includes a base and a straight rod fixedly connected with one side of the base; the pulley link device includes two pulleys connected by a first link, and a second link pivotally connected with the first link; the The ejection system is installed in the base of the ejection system installation seat, the ejection system installation seat is rotatably connected with the support, the straight rod is inserted into the gap between the two pulleys, and the control motor is connected to the pulley. The second link of the link device is connected for driving the second link to swing.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the gas generator comprises a second ignition plug and a chemical reaction raw material for generating gas, the second ignition plug and the The flight data recorder is electrically connected, and the second ignition plug is ignited under the control of the flight data recorder to cause the chemical reaction raw material to react.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the electromechanical module is provided with a gas channel and a one-way valve, and the gas generated by the gas generator passes through the gas channel and the one-way valve. into the air bag to the valve.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the flight data recorder is externally covered with a protective shell, and a protective shell is provided between the flight data recorder and the protective shell. shock material.
The helicopter air-separated emergency flight data recording system according to claim 1, wherein the radio transceiver is located outside the space enclosed by the airbag, and communicates with the flight data recording through the third cable. device connection.