CN111806704B - Helicopter aerial separated emergency flight data recording system - Google Patents
Helicopter aerial separated emergency flight data recording system Download PDFInfo
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- CN111806704B CN111806704B CN202010715266.XA CN202010715266A CN111806704B CN 111806704 B CN111806704 B CN 111806704B CN 202010715266 A CN202010715266 A CN 202010715266A CN 111806704 B CN111806704 B CN 111806704B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/18—Flotation gear
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/20—Releasing of crash position indicators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0065—Black boxes, devices automatically broadcasting distress signals
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Abstract
The invention discloses an air separation type emergency flight data recording system of a helicopter. The system comprises: an emergency state analysis system, an ejection system and a buffering/floating system; the emergency state analysis system is used for judging whether the helicopter is in an emergency state or not and controlling the launching system to start when the helicopter is in the emergency state; the ejection system is used for ejecting the buffering/floating system from the helicopter; the buffering/floating system comprises: a radio transceiver, an electromechanical module, and an airbag wrapped outside the electromechanical module; the electromechanical module comprises a flight data recorder and a gas generator, and the gas generator generates gas for filling the air bag under the control of the flight data recorder; and the radio transceiver is electrically connected with the flight data recorder and broadcasts the positioning signal. The intelligent airplane has the advantages of being intelligently and quickly separated from an airplane, strong in high-altitude falling resistance, capable of floating on the water surface after falling, and easy to search and rescue.
Description
Technical Field
The invention relates to the technical field of helicopter emergency, in particular to an air separation type emergency flight data recording system for a helicopter.
Background
With the development of domestic and foreign civil aviation industry, helicopter crash accidents caused by mechanical failure and other reasons are increasing day by day. Currently, in order to record the accident occurrence process, investigate the accident occurrence reason and improve aviation safety, higher requirements are put forward on Flight Data Recorders (FDRs). Traditional FDR fixes inside the helicopter, and when the helicopter crashed, traditional FDR relied on the structure protection inside data storage equipment that shocks resistance of self, and after the helicopter crashed, traditional FDR relied on the inside data storage equipment of waterproof construction protection, relies on the beacon to fix a position for the search and rescue team under water.
However, the lift limit of a civil helicopter is generally 2000-4000 meters, the lift limit of a military helicopter can reach 6000 meters, if the helicopter has mechanical faults (engine parking and the like) at high altitude, the helicopter can fall at a high speed, at the moment, the impact-resistant structure of the traditional FDR can be damaged to different degrees, if the helicopter falls into the sea, the wreckage of the helicopter can sink into the deep sea, and according to the maritime air disaster rescue practice, the traditional FDR has the problems that the deep sea is not easy to retrieve, underwater signal interference, the battery endurance time is limited and the like, so that the search and rescue cost is increased rapidly.
Disclosure of Invention
The invention aims to provide a helicopter aerial separation type emergency flight data recording system which is strong in high-altitude falling resistance and easy to search and rescue.
In order to achieve the purpose, the invention provides the following scheme:
an airborne disconnect-type emergency flight data recording system for a helicopter, comprising: an emergency state analysis system, an ejection system and a buffering/floating system;
the emergency state analysis system is used for judging whether the helicopter is in an emergency state or not and controlling the ejection system to start when the helicopter is in the emergency state;
the ejection system is used for ejecting the buffering/floating system from the helicopter;
the buffering/floatation system, comprising: a radio transceiver, an electromechanical module, and a bladder wrapped outside the electromechanical module; the electromechanical module comprises a flight data recorder and a gas generator, a gas output port of the gas generator is communicated with a gas input port of the airbag, and the gas generator generates gas for inflating the airbag under the control of the flight data recorder; the radio transceiver is electrically connected with the flight data recorder and is used for broadcasting positioning signals and transmitting flight data under the control of the flight data recorder.
Optionally, the ejection system includes: the ejection device comprises a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston and a propellant; the ejection cylinder is arranged on the ejection cylinder base, the propellant, the piston and the buffering/floating system are sequentially distributed in the ejection cylinder from the bottom of the ejection cylinder to an outlet, 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 to react.
Optionally, the flight data recorder is connected to the helicopter electronic device through a cable, and the flight data is backed up from the electronic device to the flight data recorder through the cable.
Optionally, the cable includes first cable, second cable and third cable, install first joint on the base, install the second joint on the piston, the one end of first cable with electronic equipment connects, the other end of first cable with the one end of first joint is connected, the other end of first joint with the one end of second cable is connected, the other end of second cable with the one end of second joint is connected, the other end of second joint with third cable junction, the other end of third cable with the flight data recorder is connected.
Optionally, the helicopter air separation type emergency flight data recording system further includes an ejection attitude control device, the ejection system is installed on the ejection attitude control device, the ejection attitude control device obtains helicopter flight attitude information from the emergency state analysis system, and a control motor of the ejection attitude control device adjusts an ejection angle according to the attitude information.
Optionally, 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 base comprises a base and a straight rod fixedly connected with one side of the base; the pulley connecting rod device comprises two pulleys connected by a first connecting rod and a second connecting rod pivoted with the first connecting rod; the ejection system is arranged in the base of the ejection system mounting seat, the ejection system mounting seat is rotatably connected with the support, the straight rod is inserted into a gap between the two pulleys, and the control motor is connected with the second connecting rod of the pulley connecting rod device and used for driving the second connecting rod to swing.
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 ignites under the control of the flight data recorder to initiate the reaction of the chemical reaction raw material.
Optionally, an air passage and a one-way valve are arranged in the electromechanical module, and air generated by the gas generator enters the airbag through the air passage and the one-way valve.
Optionally, a protective shell is wrapped outside the flight data recorder, and a damping material is arranged between the flight data recorder and the protective shell.
Optionally, the radio transceiver is located outside the space enclosed by the airbag and is connected to the flight data recorder through the third cable.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the invention provides a helicopter air separation type emergency flight data recording system which comprises an emergency state analysis system, an ejection system and a buffering/floating system. The buffering/floating system is after separating with the helicopter, and gas generator wherein produces gas, inflates to the gasbag of parcel outside, and at the descending in-process, the gasbag has played the effect that the buffering descends, if fall into the aquatic, the gasbag can also play the effect that makes the device float on the surface of water. The arrangement mode avoids the crash of the flight data recorder along with the helicopter, greatly reduces the impact overload when the flight data recorder collides with the ground (or the water surface) through the buffering of the air bag, and simultaneously, the recorder can float on the water surface under the action of the air bag when the recorder falls into the water surface. In addition, the helicopter aerial separating type emergency flight data recording system provided by the invention is also provided with a radio transceiver, which can broadcast a positioning signal to the outside, is easy for the outside to find and search and rescue, and can remotely and wirelessly transmit flight data for a search and rescue team.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural diagram of an aerial separation type emergency flight data recording system of a helicopter according to an embodiment of the present invention;
FIG. 2 is a side view of an installation location of a helicopter airborne split emergency flight data recording system provided by an embodiment of the present invention;
FIG. 3 is a top view of a further installation location of a helicopter airborne split emergency flight data recording system provided in accordance with an embodiment of the present invention;
fig. 4 is a cross-sectional view of the main components of an ejection system provided by an embodiment of the present invention;
fig. 5 is a schematic structural diagram of an ejection attitude control device according to an embodiment of the present invention;
FIG. 6 is a schematic structural diagram of a buffering/floating system provided in accordance with an embodiment of the present invention;
FIG. 7 is a schematic structural view of an airbag provided in accordance with an embodiment of the present invention;
FIG. 8 is a cross-sectional view of the major components of a bumper/floatation system provided in accordance with an embodiment of the present invention;
FIG. 9 is a schematic diagram of a model in a numerical simulation of an airbag crash in an embodiment of the invention;
FIG. 10(a) is a perspective view of the interior of the bladder at the point where the bladder begins to deform in accordance with the particular example of the present invention; FIG. 10(b) is an external view of the airbag at the moment of the onset of deformation of the airbag in the particular example of the invention; FIG. 10(c) is a perspective view of the interior of the airbag at the time of maximum deformation of the airbag in an embodiment of the present invention; FIG. 10(d) is an external view of the airbag at the time of maximum deformation of the airbag in the embodiment of the present invention.
1. An emergency analysis system, 2, an ejection system, 3, a buffering/floating system, 4, a nose mounting location, 5, a belly mounting location, 6, a tail mounting location, 7, a first body side mounting location, 8, a second body side mounting location, 9, a piston, 10, an ejection cartridge, 11, an ejection cartridge cover, 12, a propellant, 13, a first ignition plug, 14, an ejection cartridge base, 15, helicopter onboard electronics, 16, a first cable, 17, a first connector, 18, a second cable, 19, a second connector, 20, a third cable, 21, an ejection cartridge cover lock, 22, a spring, 23, a base, 24, a support, 25, a shaft, 26, a helicopter internal mounting point, 27, a straight rod, 28, a pulley linkage, 29, a control motor, 30, an electromechanical module, 31, an airbag, 32, a radio transceiver, 33, a flight data recorder, 34. damping material 35, protective shell 36, base 37, chemical reaction raw material 38, gas generator 39, second ignition plug 40, one-way valve 41, air bag charging port 42 and ground.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Fig. 1 is a schematic structural diagram of a helicopter air separation type emergency flight data recording system according to an embodiment of the present invention, and referring to fig. 1, the helicopter air separation type emergency flight data recording system according to the embodiment includes: an emergency analysis system 1, an ejection system 2 and a buffering/floatation system 3. The emergency state analysis system 1 is used for judging whether the helicopter is in an emergency state or not, and controlling the ejection system 2 to start when the helicopter is in the emergency state. And an ejection system 2 for ejecting the cushioning/floatation system 3 from the helicopter. The buffering/floating system 3 includes: a radio transceiver, an electromechanical module, and an airbag wrapped outside the electromechanical module; the electromechanical module comprises a flight data recorder and a gas generator, a gas output port of the gas generator is communicated with a gas input port of the air bag, and the gas generator generates gas for filling the air bag under the control of the flight data recorder; and the radio transceiver is electrically connected with the flight data recorder and is used for broadcasting the positioning signal and transmitting the flight data under the control of the flight data recorder.
In this embodiment, the emergency state analysis system 1 may include its own sensors for acceleration, altitude, and the like, and also includes data interfaces for a helicopter emergency floating system, a ground proximity warning system, and a helicopter flight control system, and after comprehensively analyzing data, the emergency state analysis system is responsible for determining whether the helicopter is in an emergency state. When the helicopter is in an emergency state, the ejection system 2 is started. At this time, the emergency state analysis system 1 controls the ejection system 2 to eject the buffering/floating system 3 from the helicopter. When the buffering/floating system 3 is ejected out of the fuselage, the flight data recorder controls the gas generator to generate gas, and the gas fills the air bag of the buffering/floating system quickly. When the buffering/floating system 3 falls into the water (or falls into the ground), the air bag can not only effectively reduce the impact, but also provide enough buoyancy for the buffering/floating system 3 so as to float on the water surface when falling into the water. After the bumper/floatation system is dropped (or dropped), the radio transceiver begins broadcasting a locating signal. When the search and rescue aircraft sends an instruction to the radio transceiver, the radio transceiver uploads the data in the data recorder to the search and rescue aircraft.
It should be noted that, according to the difference of helicopter models, the difference of operating (or using) units, and the difference of relevant laws (or industrial regulations) of operating (or using) places (or countries), the present invention can use one or more of the following judgment logics to judge whether the helicopter is in an emergency state. If a plurality of judgment logics are used, a user can optionally meet one judgment logic, namely, the helicopter is considered to be in an emergency state, or simultaneously meet a plurality of judgment logics, and then the helicopter is considered to be in the emergency state. The following is the judgment logic of the emergency analysis system:
1) if the helicopter emergency floating system is started, the helicopter is considered to be in an emergency state. In the judgment logic, the helicopter emergency floating system can be selected to be started and then immediately judged to be in the emergency state according to the specific situation of the user, or the helicopter emergency floating system is started for a period of time and then judged to be in the emergency state (the delay time can be adjusted according to the specific situation of the user).
2) If the helicopter is close to the ground, the helicopter is considered to be in an emergency state. In the judgment logic, according to the specific situation of the user, the helicopter is selected to be in the emergency state immediately after the ground proximity alarm, or the helicopter is not cancelled after the ground proximity alarm is given for a period of time, and the helicopter is judged to be in the emergency state (the delay time can be adjusted according to the specific situation of the user).
3) Each model of helicopter has a flight envelope (or flight parameters) recommended by the design or production unit. Such as: maximum flying height, maximum flying speed, maximum fuselage deflection angle and speed, etc. These parameters characterize, among other things, the range of flight and the limitations of use of the helicopter. If the emergency analysis system detects that the flight data exceeds the limit range of the parameters or does not return to the limit range after exceeding the limit range for a period of time, the helicopter is judged to be in an emergency state (the delay time length can be adjusted according to the specific situation of a user). It should be noted 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 fig. 2 and 3, the helicopter air separation type emergency flight data recording system provided by the invention can be installed at the positions of the head, the belly, the tail, the side surface of the body and the like of a helicopter according to the specific conditions of different types of helicopters.
As an alternative embodiment, the user may set the starting height of the ejection system 2 according to factors such as the flight environment of the helicopter and the type of task to be performed. The ejection system 2 automatically judges the current height of the helicopter through the height sensor and the received height data of the helicopter. If the launch height of the launch system 2 is set, the bumper/floatation system 3 is only launched out of the fuselage if the helicopter is lowered (or dropped) below the set height.
As an alternative embodiment, the ejection system 2 comprises: the ejection device comprises a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston and a propellant; the ejection cylinder is arranged on a base of the ejection cylinder, propellant, a piston and a buffering/floating system are sequentially distributed in the ejection cylinder from the bottom of the ejection cylinder to an outlet, the piston is coaxial with the ejection cylinder, and a first ignition plug is ignited under the control of the emergency state analysis system to initiate propellant reaction.
The ejection system 2 may be specifically configured as shown in fig. 4, in which one end of the ejection cylinder 10 is connected to the ejection cylinder base 14 through a screw, and the other end of the ejection cylinder 10 is connected to the ejection cylinder cover 11 through a spring 22. The shooting pot lid lock 21 is fixed to the shooting pot 10. When the ejection system 2 is in standby, one end of the ejection cartridge cover 11 is locked by the ejection cartridge cover lock 21. The piston 9 is placed inside the shooting pot 10 and the lower stopping point of the piston 9 moving in the shooting pot 10 is the end of the shooting pot base 14. The first ignition plug 13 is fixed on the base 14 of the shooting pot, one end of the first ignition plug 13 extends out of the base 14 of the shooting pot, the other end of the first ignition plug extends into the base 14 of the shooting pot and is embedded into the propellant 12, and the propellant 12 is fixed inside the base 14 of the shooting pot. After the ejection system 2 is started, the first ignition plug 13 initiates chemical reaction of the propellant 12, a large amount of gas is rapidly released, high pressure is generated behind the piston 9, and the piston 9 is pushed to move forwards. At the same time the ejection cartridge cover lock 21 is opened, the ejection cartridge cover 11 is opened under the action of the spring 22, and the damping/floating system 3 is then ejected out of the body.
In this embodiment, the flight data recorder is connected to the helicopter electronics via a cable, and the flight data is backed up from the electronics (i.e., the flight control computer on the helicopter) via the cable to the flight data recorder when the aircraft is in an emergency. The specific setting mode can be as follows: as shown in fig. 4, the onboard helicopter electronics 15 are connected to a first connector 17 by a first cable 16, the first connector 17 is connected to a second connector 19 by a second cable 18, and the second connector 19 is connected to the flight data recorder by a third cable 20. Both the first connector 17 and the second connector 19 can be used for transmitting data. A first connector 17 is threadably (or otherwise) secured to the shooting pot base 14 and a second connector 19 is threadably (or otherwise) secured to the piston 9. When the piston 9 moves to the outlet of the ejection cartridge mount 14, the second cable 18 is straightened out, thereby preventing the piston 9 from being ejected out of the body. The third cable 20 is simply connected to the second connector 19 by means of a plug, so that after the damping/floating system 3 is ejected from the fuselage, the third cable 20 is quickly straightened and then, under the action of the inertia of the damping/floating system 3, the plug at the end of the third cable 20 is pulled out of the second connector 19, so that the damping/floating system 3 is completely detached from the helicopter.
As an implementation manner, the helicopter air separation type emergency flight data recording system provided in this embodiment further includes an ejection attitude control device, where the ejection attitude control device is configured to adjust and control an attitude of the ejection system. As shown in fig. 5, the ejection attitude control means includes a support 24, an ejection system mount, a pulley link 28, and a control motor 29. The ejection system mounting base comprises a base 23 and a straight rod 27 fixedly connected with one side of the base 23, and the ejection system 2 is mounted in the base 23. The pulley linkage 28 includes two pulleys connected by a first link, and a second link pivotally connected to the first link. The catapult system mounting seat is rotatably connected with the support 24, the straight rod 27 is inserted into a gap between two pulleys (the size of the gap is equivalent to the diameter of the straight rod 27), the pulley connecting rod device 28 is fixed on a control motor 29, and the control motor 29 is fixed on an internal mounting point of the helicopter. The control motor 29 receives information such as the flight attitude of the helicopter and the like transmitted by the emergency state analysis system, and the attitude of the ejection attitude control device is rapidly changed by adjusting the swing angle of the pulley and link device 28, so that the ejection angle is changed, and the ejection of high altitude to the rotor wing and low altitude to the ground can be avoided. The ejection attitude control device is fixed on an internal mounting point 26 of the helicopter through a support 24. The support 24 has a shaft 25 so that the ejection attitude control means can rotate about the shaft 25. This shaft 25 can also be a ball or cardan shaft, allowing a greater freedom of rotation of the ejection attitude control device.
The ejection cylinder base 14 of the ejection system 2 may be fixed to the base 23 of the ejection attitude control device by a screw (or by other means such as welding). As can be seen from fig. 4, the ejection cartridge base 14 is connected with a first connector 17, and the first connector 17 and the first cable 16 can protrude from the hole (at a in fig. 5) of the ejection attitude control device.
In this embodiment, as an implementation manner, the gas generator includes a second ignition plug and a chemical reaction material for generating gas, the second ignition plug is electrically connected with the flight data recorder, and the second ignition plug is ignited under the control of the flight data recorder to initiate the reaction of the chemical reaction material. The electromechanical module is provided with a gas channel and a one-way valve, and 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 material 37 is stored in the gas generator 38, the second ignition plug 39 is fixed to the top of the gas generator 38, one end of the second ignition plug 39 is embedded in the chemical reaction material 37, and the other end is connected to the flight data recorder 33. The gas outlet of the gas generator 38 is fixed to the base 36 by means of a screw, and the gas outlet of the gas generator 38 communicates with a gas delivery channel inside the base 36, which is obtained by drilling a hole in the base 36, instead of an embedded pipe. A check valve 40 is also mounted on the base 36, and the other end of the gas delivery passage has an outlet communicating with the check valve 40. The check valve 40 is connected to the airbag inflation port 41. When the bumper/float system 3 is ejected from the fuselage, the second igniter plug 39 initiates a chemical reaction of the chemically reactive material 37, rapidly releasing a large amount of gas. This gas enters the bladder 31 through the one-way valve 40. The protective housing 35 of the flight data recorder 33 is mounted on a base 36, and the flight data recorder 33 is connected to the third cable 20. The third cable 20 passes through the protective housing 35 and the base 36 and is connected to the second connector 19 of the ejector system 2. Between the flight data recorder 33 and the protective casing 35, a shock-absorbing material 34 is filled, 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 4 or more chambers, the electromechanical module 30 is enclosed in the airbag 31, each chamber of the airbag 31 has an inflation port 41, the inflation ports 41 are connected to the check valves 40, and each inflation port corresponds to 1 check valve. Each chamber of the air bag 31 is not communicated, and each chamber can individually provide the buffering/floating system 3 with enough buoyancy to float on the water surface.
In this embodiment, referring to fig. 8, the radio transceiver 32 is located outside the space enclosed by the air bag, specifically, the radio transceiver 32 may be installed on the third cable 20, and the radio transceiver 32 may broadcast the positioning signal and upload the flight data after the buffering/floating system 3 falls into water (or land).
During a fall of the bumper/float system 3, the transceiver 32 acts as a counterweight to adjust the center of gravity of the bumper/float system 3 below the pneumatic center. Thereby maintaining the bumper/float system 3 in an approximately vertically downward attitude during the fall. This nearly vertical drop attitude causes the bumper/float system 3 to fall to the ground (or water) with the air bag below the electromechanical module 30 first contacting the ground (or water surface). There is a thicker bladder below the electromechanical module 30 (i.e., H2> H1 in fig. 8). By this means, the cushion effect when falling down (or falling to the ground) can be enhanced by the limited gas in the air bag.
By increasing the length of the cable 20, or by increasing the weight of the transceiver 32. The distance between the gravity center and the pneumatic center of the buffering/floating system 3 can be increased, so that the stability of the buffering/floating system 3 during falling is increased, and the thicker side of the air bag faces the water surface or the ground when the buffering/floating system 3 falls into water (or falls into the ground).
The effect of the helicopter airborne separate emergency flight data recording system provided by the invention is verified in a specific verification example mode as follows:
the total mass of the buffer/floating system 3 is about 1.6kg, the volume of the air bag 31 is about 90L, and the frontal area of the air bag 31 is about 0.478m when the air bag falls2About 143g of sodium azide was required as the chemical reaction raw material 37. The aerodynamic coefficient of the cylindrical airbag 31 falling at a constant speed is calculated by a numerical simulation method and is about 0.18. From equation (1), the final drop velocity of the buffering/floating system 3 can be calculated to be 17.4 m/s. If the height of the bumper/float system 3 is low when it is ejected from the fuselage, its final drop velocity will be less than 17.4 m/s.
Where m is the total mass of the bumper/floatation system 3, g is the acceleration of gravity, and ρ is the ambient air density (1.2 kg/m)3) V is a buffering/floating system 3C is the aerodynamic coefficient of the cylindrical airbag 31 when it falls at a constant speed, and a is the frontal area of the airbag 31.
As shown in fig. 9 and 10, the air bag 31 is crushed and deformed during the crash of the buffering/floating system 3, and at the time when the deformation of the air bag 31 is maximum, the thicker air bag protection is still provided under the electromechanical module 30. During a crash, the maximum overload of the electromechanical module 30 is about 85g (i.e., 85 times acceleration due to gravity). When the airbag 31 falls into the water, the maximum overload of the electromechanical module 30 is less than the impact of the falling. According to civil aviation specifications such as C123a, the conventional FDR should be able to withstand a maximum overload of 3400 g. Comparing the helicopter emergency flight data recording system (HEEFDR) with the traditional FDR, the helicopter air separation type emergency flight data recording system provided by the invention can obviously reduce the falling impact of the recorder and can more effectively protect the flight data.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (7)
1. An aerial disconnect-type emergency flight data recording system of a helicopter, comprising: an emergency state analysis system, an ejection system and a buffering/floating system;
the emergency state analysis system is used for judging whether the helicopter is in an emergency state or not and controlling the ejection system to start when the helicopter is in the emergency state;
the ejection system is used for ejecting the buffering/floating system from the helicopter; the ejection system includes: the ejection device comprises a first ignition plug, an ejection cylinder base, an ejection cylinder, a piston and a propellant; the ejection cylinder is arranged on the ejection cylinder base, the propellant, the piston and the buffering/floating system are sequentially distributed in the ejection cylinder from the bottom of the ejection cylinder to an outlet, 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 to react; one end of the ejection barrel is connected with the ejection barrel base through threads, and the other end of the ejection barrel is connected with the ejection barrel cover through a spring; the ejection barrel cover lock is fixed on the ejection barrel; when the ejection system is in standby, one end of the ejection cylinder cover is locked by the ejection cylinder cover lock; the piston is arranged in the ejection barrel, and the lower stopping point of the piston moving in the ejection barrel is the tail end of the base of the ejection barrel; the first ignition plug is fixed on the ejection cylinder base, one end of the first ignition plug extends out of the ejection cylinder base, the other end of the first ignition plug extends into the ejection cylinder base and is embedded into a propellant, and the propellant is fixed inside the ejection cylinder base; after the ejection system is started, the first ignition plug initiates chemical reaction of the propellant to quickly release a large amount of gas, and high pressure is generated behind the piston to push the piston to move forwards; meanwhile, the ejection barrel cover lock is opened, the ejection barrel cover is opened under the action of the spring, and then the buffering/floating system is ejected out of the machine body;
the buffering/floatation system, comprising: a radio transceiver, an electromechanical module, and a bladder wrapped outside the electromechanical module; the electromechanical module comprises a flight data recorder and a gas generator, a gas output port of the gas generator is communicated with a gas input port of the airbag, and the gas generator generates gas for inflating the airbag under the control of the flight data recorder; the radio transceiver is electrically connected with the flight data recorder and is used for broadcasting positioning signals and transmitting flight data under the control of the flight data recorder;
the helicopter air separation type emergency flight data recording system also comprises an ejection attitude control device, the ejection attitude control device is used for adjusting and controlling the attitude of an ejection system, the ejection system is arranged on the ejection attitude control device, the ejection attitude control device obtains helicopter flight attitude information from an emergency state analysis system, and a control motor of the ejection attitude control device adjusts an ejection angle according to the attitude information; the ejection attitude control device comprises a support, an ejection system mounting seat, a pulley connecting rod device and a control motor; the ejection system mounting base comprises a base and a straight rod fixedly connected with one side of the base; the pulley connecting rod device comprises two pulleys connected by a first connecting rod and a second connecting rod pivoted with the first connecting rod; the ejection system is arranged in the base of the ejection system mounting seat, the ejection system mounting seat is rotatably connected with the support, the straight rod is inserted into a gap between the two pulleys, and the control motor is connected with the second connecting rod of the pulley connecting rod device and used for driving the second connecting rod to swing; the pulley connecting rod device is fixed on a control motor, and the control motor is fixed on an installation point in the helicopter; the control motor receives helicopter flight attitude information transmitted by the emergency state analysis system, and the attitude of the ejection attitude control device is quickly changed by adjusting the swing angle of the pulley and link device, so that the ejection angle is changed, and the high-altitude rotor wing and the low altitude ground ejection are avoided; the ejection attitude control device is fixed at an internal mounting point of the helicopter through a support; the support is provided with a shaft so that the ejection attitude control device can rotate around the shaft.
2. A helicopter airborne emergency flight data recorder system according to claim 1, wherein said flight data recorder is connected to helicopter electronics via a cable, and flight data is backed up from said electronics via said cable to said flight data recorder.
3. A helicopter aerial disconnect emergency flight data recording system as claimed in claim 2, wherein the cable comprises a first cable, a second cable and a third cable, a first connector is mounted on the base, a second connector is mounted on the piston, 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, the other end of the first connector 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; the wireless transceiver is arranged on the third cable, and plays a role of a counterweight in the falling process of the buffering/floating system, so that the gravity center of the buffering/floating system can be adjusted to be below the pneumatic center, the buffering/floating system can keep an approximately vertical downward posture in the falling process, and when the buffering/floating system falls down or falls into water, the air bag below the electromechanical module contacts the ground or the water surface firstly; the thicker air bag is arranged below the electromechanical module, and by the method, the buffer effect when the air bag falls into water or the ground can be enhanced by the limited air in the air bag; by increasing the length of the third cable or the weight of the radio transceiver, the distance between the gravity center and the pneumatic center of the buffering/floating system is increased, so that the stability of the buffering/floating system during falling is increased, and the thicker side of the air bag faces the water surface or the ground when the buffering/floating system falls into water or the ground.
4. A helicopter airborne emergency flight data recorder system according to claim 1, wherein said gas generator includes a second igniter plug and a chemically reactive material for generating gas, said second igniter plug being electrically connected to said flight data recorder, said second igniter plug being fired under control of said flight data recorder to initiate reaction of said chemically reactive material.
5. A helicopter airborne split emergency flight data recording system according to claim 1, wherein a gas passage and a one-way valve are provided in the electromechanical module, and gas generated by the gas generator enters the airbag through the gas passage and the one-way valve.
6. A helicopter airborne emergency flight data recorder system according to claim 1, wherein the flight data recorder is externally encased by a protective shell, and a shock absorbing material is disposed between the flight data recorder and the protective shell.
7. A helicopter airborne emergency flight data recorder system according to claim 3, wherein said radio transceiver, located outside the space enclosed by said envelope, is connected to said flight data recorder by said third cable.
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| CN202010715266.XA CN111806704B (en) | 2020-07-23 | 2020-07-23 | Helicopter aerial separated emergency flight data recording system |
| PCT/CN2021/085756 WO2022016908A1 (en) | 2020-07-23 | 2021-04-07 | Helicopter air separation type emergency flight data recording system |
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| CN202010715266.XA CN111806704B (en) | 2020-07-23 | 2020-07-23 | Helicopter aerial separated emergency flight data recording system |
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| CN111806704B (en) * | 2020-07-23 | 2021-10-12 | 南京航空航天大学 | Helicopter aerial separated emergency flight data recording system |
| CN114919739A (en) * | 2022-06-29 | 2022-08-19 | 海南艾锐奥科技有限公司 | Unmanned aerial vehicle drowning guiding and searching method |
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| US8670879B1 (en) * | 2010-04-21 | 2014-03-11 | Lockheed Martin Corporation | Automatically ejecting flight data recorder |
| CN104044748B (en) * | 2014-04-01 | 2016-09-14 | 柳州治业科技有限公司 | Aircraft black box position reporting and course line tracking |
| CN103950545B (en) * | 2014-04-01 | 2017-01-11 | 柳州治业科技有限公司 | Airplane black box position apprizing and route tracking system |
| CN104139859A (en) * | 2014-05-12 | 2014-11-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Water floating recorder catapulting method |
| CN104007451B (en) * | 2014-05-27 | 2016-06-08 | 曹宇 | Wrecked position record report device |
| WO2016141231A1 (en) * | 2015-03-05 | 2016-09-09 | Comac America Corporation | Emergency mechanical and communication systems and methods for aircraft |
| CN106347690B (en) * | 2016-09-01 | 2019-11-08 | 肇庆高新区异星科技有限公司 | A kind of black box control method and system |
| US9745071B1 (en) * | 2017-01-27 | 2017-08-29 | Comac America Corporation | Ejectable flight data recorder systems, methods, and devices |
| CN109094788A (en) * | 2018-10-10 | 2018-12-28 | 常州市小域智能科技有限公司 | A kind of unmanned aerial vehicle ejecting apparatus and system |
| CN111806704B (en) * | 2020-07-23 | 2021-10-12 | 南京航空航天大学 | Helicopter aerial separated emergency flight data recording system |
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