WO2018041253A1 - Procédé et système de commande de boîte noire - Google Patents

Procédé et système de commande de boîte noire Download PDF

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Publication number
WO2018041253A1
WO2018041253A1 PCT/CN2017/100287 CN2017100287W WO2018041253A1 WO 2018041253 A1 WO2018041253 A1 WO 2018041253A1 CN 2017100287 W CN2017100287 W CN 2017100287W WO 2018041253 A1 WO2018041253 A1 WO 2018041253A1
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WO
WIPO (PCT)
Prior art keywords
black box
aircraft
signal
trigger circuit
control system
Prior art date
Application number
PCT/CN2017/100287
Other languages
English (en)
Chinese (zh)
Inventor
梁泰然
Original Assignee
梁泰然
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from CN201610805054.4A external-priority patent/CN106477045B/zh
Priority claimed from CN201610805107.2A external-priority patent/CN106347690B/zh
Priority claimed from CN201610805098.7A external-priority patent/CN106314796A/zh
Application filed by 梁泰然 filed Critical 梁泰然
Publication of WO2018041253A1 publication Critical patent/WO2018041253A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B27/00—Arrangement of ship-based loading or unloading equipment for cargo or passengers
    • B63B27/26—Arrangement of ship-based loading or unloading equipment for cargo or passengers of devices with throwing action
    • 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
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • 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
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
    • B64D1/12—Releasing
    • 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
    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C5/00—Registering or indicating the working of vehicles

Definitions

  • the present invention relates to the field of aerospace technology, and in particular to a black box control method and system.
  • the black box mounted on the plane will follow the plane and fall into the unknown area.
  • the audio data of the aircraft cockpit is only stored in the black box. Only after the plane falls, the ground personnel can download the data.
  • the black box search will be much more difficult than the plane crash on land.
  • the traditional satellite positioning technology can only roughly determine the scope of the crash. However, because the transmission time interval of the positioning signal is long, the determined range is too large, and the ground conditions that crash after the crash are complicated, which ultimately makes it impossible or difficult to search. The black box of the wrecked plane.
  • an object of embodiments of the present invention is to provide a black box control method and system capable of ejecting an internal black box when a plane crashes, so that the black box is in the vicinity of the plane crash; the black box receives the crash information of the plane. And sent to the rescue center system in real time, the rescue center system can quickly determine the location of the crash according to the crash information, and then quickly find the black box of the crashed aircraft.
  • an embodiment of the present invention provides a black box control method, including:
  • the flight data including an impact signal, a runaway signal, and a stall signal
  • the flight state determination module determines YES, the first black box set on the aircraft is ejected to the aircraft.
  • the flight data may also be a height signal.
  • the embodiment of the present invention provides a first possible implementation manner of the first aspect, wherein when the flight state determination module determines to be YES, the first black box set on the aircraft is popped up. After the aircraft, it also includes:
  • the second flight state determination module determines YES, the second black box set on the aircraft is ejected from the aircraft.
  • the embodiment of the present invention provides a second possible implementation manner of the first aspect, wherein when the flight state determination module determines to be YES, the first black box set on the aircraft is popped up. After the aircraft, it also includes:
  • an embodiment of the present invention provides a black box control system, including a first flight state detection module, a first flight state determination module, and a first ejection module:
  • a first flight state detecting module configured to acquire current flight data of the aircraft, where the flight data includes an impact signal, a runaway signal, and a stall signal;
  • a first flight state determining module configured to determine, according to the flight data, whether the aircraft is in a dangerous state at a current time
  • the first ejection module is configured to pop the first black box set on the aircraft when the first flight state determination module determines to be YES.
  • the embodiment of the present invention provides a first possible implementation manner of the second aspect, further comprising: a second flight state detecting module, a second flight state determining module, and a second ejection module;
  • a second flight state detecting module configured to acquire a current altitude signal of the aircraft
  • a second flight state determining module configured to determine, according to the height signal, whether the aircraft is in a state of impending ground fall at a current time
  • a second ejection module configured to: when the second flight state determination module determines to be YES, eject the second black box set on the aircraft to the aircraft.
  • an embodiment of the present invention provides a second possible implementation manner of the second aspect, further comprising: a pop-up structure used by the first black box, characterized in that: a cabin disposed on the aircraft, and The aircraft ejects a push-out portion electrically connected to the trigger circuit, the push-out portion includes a push rod; the cabin is a hollow cavity having an opening at one end;
  • the push rod is located inside the cabin, and is configured to perform a ejection motion toward a direction in which the opening of the cabin is located after receiving a trigger signal of the aircraft pop-up trigger circuit to eject the first black box aircraft.
  • the embodiment of the present invention provides a third possible implementation manner of the second aspect, wherein the pushing portion further includes a fixed lock and a motor for driving the fixed lock,
  • the push rod is provided with a card slot, and the fixed lock protrudes into the card slot to limit Positioning the putter;
  • the motor is electrically connected to the trigger circuit, and is configured to drive the fixed lock to protrude from the card slot after receiving a trigger signal of the aircraft pop-up trigger circuit, so that the push rod faces the cabin
  • the ejection movement is performed in the direction in which the opening is located, and the first black box is ejected into the aircraft.
  • the embodiment of the present invention provides a fourth possible implementation of the second aspect, wherein the fixed lock is annular.
  • the embodiment of the present invention provides a fifth possible implementation manner of the second aspect, wherein the pushing portion further includes a first ejector, and the first ejector is used Produces thrust for a long time.
  • an embodiment of the present invention provides a sixth possible implementation of the second aspect, wherein the ejecting portion further includes a second ejector.
  • the embodiment of the present invention provides a seventh possible implementation manner of the second aspect, further comprising: a housing and a card lock carrying the black box;
  • the latch is configured to provide a clamping force to the outer casing of the black box so that the outer casing is fixed on the cabin by the clamping force;
  • the thrust is greater than the clamping force.
  • the embodiment of the present invention provides the eighth possible implementation manner of the second aspect, further comprising: a baffle disposed at the opening of the cabin;
  • One end of the baffle is rotatably coupled to an edge of the push-out port end.
  • the embodiment of the present invention provides the ninth possible implementation manner of the second aspect, further comprising a lower board and a moving board disposed at the opening of the cabin;
  • a through hole is formed in a center of the lower plate to form an opening of the cabin
  • the lower plate is annular, and the inner wall is provided with a telescopic groove
  • the moving plate is slidably coupled to the telescopic slot and reciprocable along the telescopic slot to close or open the opening of the pod.
  • a black box control method and system provided by an embodiment of the present invention mainly includes acquiring current flight data of an aircraft, the flight data includes an impact signal, a runaway signal, and a stall signal; determining whether the aircraft is in a dangerous state according to flight data; when the first flight When the state determination module determines that it is YES, the first black box set on the aircraft is ejected into the aircraft.
  • the invention provides a black box control method and system, which can eject an internal black box when a plane crashes, so that the black box is in the vicinity of the plane crash; the black box receives the crash information of the plane and sends it to the rescue center system in real time.
  • the rescue center system can quickly determine the location of the crash based on the crash information, and then quickly find the black box of the crashed aircraft.
  • FIG. 1 is a schematic diagram of a black box control method provided by an embodiment of the present invention.
  • FIG. 2 is a schematic diagram showing a preferred scheme of a black box control method according to an embodiment of the present invention
  • FIG. 3 is a schematic diagram showing another preferred scheme of a black box control method according to an embodiment of the present invention.
  • FIG. 4 is a schematic structural diagram of a black box control system according to an embodiment of the present invention.
  • FIG. 5 is a schematic structural diagram of a black box signal transmitting and receiving apparatus in a black box control method according to an embodiment of the present invention
  • FIG. 6 is a schematic structural diagram of a pop-up structure used by a black box in a black box control system according to an embodiment of the present invention
  • FIG. 7 is a schematic diagram showing a state before a pop-up structure used by a black box in a black box control system according to an embodiment of the present invention
  • FIG. 8 is a schematic diagram showing a state in which a pop-up structure used by a black box in a black box control system is subjected to a ejection motion according to an embodiment of the present invention
  • FIG. 9 is a schematic diagram showing a state after a pop-up structure used by a black box in a black box control system according to an embodiment of the present invention.
  • FIG. 10 is a schematic view showing a state in which a pop-up structure used by another black box provided by an embodiment of the present invention is subjected to a ejection motion
  • FIG. 11 is a schematic diagram showing a state in which a pop-up structure used by another black box provided by an embodiment of the present invention is subjected to a ejection motion
  • FIG. 12 is a schematic structural diagram of a housing structure used for carrying a black box in a black box control system according to an embodiment of the present invention.
  • FIG. 13 is a schematic diagram showing a state of a shell structure used for carrying a black box in a black box control system according to an embodiment of the present invention
  • FIG. 14 is a schematic diagram showing a state of operation of a housing structure expansion device for carrying a black box in a black box control system according to an embodiment of the present invention
  • FIG. 15 is a block diagram showing the operation of a shell structure floating device used for carrying a black box in a black box control system according to an embodiment of the present invention.
  • FIG. 16 is a schematic structural view showing a structure of an ejection structure cabin having only one baffle in a black box controlled by a black box control system according to an embodiment of the present invention
  • FIG. 17 is a schematic structural view showing a structure of an ejection structure cabin having a plurality of baffles in a black box controlled by a black box control system according to an embodiment of the present invention
  • FIG. 18 is a schematic structural view showing a moving plate of an ejection structure cabin opening used in a black box in a black box control system according to an embodiment of the present invention.
  • FIG. 19 is a schematic structural view showing a floating air cushion in a carrier used for carrying a black box in a black box control system according to an embodiment of the present invention
  • FIG. 20 is a schematic structural diagram of a connector used for carrying a black box in a black box control system according to an embodiment of the present invention
  • 21 is a schematic structural diagram of a floating device used for carrying a black box in a black box control system according to an embodiment of the present invention.
  • the black box mounted on the plane will follow the plane and fall into the unknown area.
  • the audio data of the aircraft cockpit is only stored in the black box. Only after the plane falls, the ground personnel can download the data.
  • the black box search will be much more difficult than the plane crash on land.
  • the traditional satellite positioning technology can only roughly determine the scope of the crash. However, because the transmission time interval of the positioning signal is long, the determined range is too large, and the ground conditions that crash after the crash are complicated, which ultimately makes it impossible or difficult to search. The black box of the wrecked plane.
  • a black box control method provided by an embodiment of the present invention includes steps S110-S150.
  • Step S110 Acquire current flight data of the aircraft, where the flight data includes an impact signal, a runaway signal, a stall signal, or one of the signals.
  • Step S120 determining, according to the flight data, whether the aircraft is in a dangerous state at the current time
  • Step S130 when the first flight state determination module determines that it is YES, the first black box set on the aircraft is ejected into the aircraft.
  • the invention provides a first flight state detecting module 10, a first flight state determining module 11 and a first catapult module 12 on the aircraft.
  • the first flight detection module disposed on the aircraft monitors its flight condition in real time, and when the first flight state detection module 10 acquires the current flight data, it is electrically connected to the first flight state detection module 10.
  • the first flight state determination module 11 determines, based on the flight data, whether the aircraft is in a dangerous state at the current time.
  • the first ejection module 12 ejects the first black box set on the aircraft.
  • the risk of flying risk is various, may impact, or may be due to loss of control or stall, which eventually leads to the crash of the aircraft. Therefore, the above flight data includes impact signals, runaway signals and stall signals, but not limited to impact signals, runaway signals and stall signals. .
  • the flight data may also be a height signal
  • the first flight state determination module determines YES
  • the first black box set on the aircraft is ejected from the aircraft.
  • steps S140-S160 are further included. Obtain the current altitude signal of the aircraft;
  • Step S140 acquiring a current altitude signal of the aircraft
  • Step S150 determining, according to the altitude signal, whether the aircraft is in a state of impending groundfall at the current time
  • Step S160 when the second flight state determination module determines that it is YES, the second black box set on the aircraft is ejected into the aircraft.
  • the second flight state detecting module on the aircraft acquires the current altitude signal of the aircraft
  • the second flight state detecting module includes a GPS positioning unit and a calculating unit
  • the GPS positioning unit acquires the current position information
  • the calculating unit Calculate the current altitude based on the current location information Height, and then calculate the ejection height according to the aircraft model.
  • the second flight state detecting module may also be a radio height detecting module, and the current height from the ground or the water surface may be acquired by the radio height detecting module. It should be emphasized here that different models of aircraft have different performances, and their corresponding trigger ejection heights are different.
  • the second flight state judging module judges whether the current moment is in a state of falling to the ground according to the altitude signal.
  • the second ejecting module ejects the second black box pre-set on the aircraft. For example, after the GPS positioning unit acquires the current location information, the calculation unit calculates the current altitude according to the current location information, and compares the altitude with a preset ejection altitude of 100 meters, when the calculated altitude is less than or equal to 100 meters.
  • the judgment result of the second flight state determination module is YES.
  • the current height to judge whether the black box is popped up, it can avoid premature or too high pop-up, which causes the position of the black box to be too far from the plane crash and reduces the search efficiency of the search and rescue personnel. It can also avoid the black box damage caused by the too late or too low pop-up.
  • the aircraft was brought into a complex location, increasing the difficulty for rescuers to find black boxes. Ejecting at a suitable height can also make the flight of the aircraft safer or reduce the impact of airflow on the aircraft during the black box ejection process, or make the impact more predictable.
  • the second flight state detecting module, the second flight state determining module and the second catapult module are only a preferred embodiment of the present invention, and the second black box that is ejected has the same function as the first black box, and after the plane crashes, the phase Looking for a black box, looking for two black boxes increases the efficiency of search and rescue personnel. Similarly, the installation of multiple (ejected) black boxes on the aircraft, which pops up in sequence during the crash, also increases the efficiency of the search and rescue personnel. It is also within the scope of the present invention to provide a plurality of black boxes.
  • steps S141 to S161 are further included.
  • Step S141 acquiring a crash signal
  • Step S151 acquiring a crash signal
  • step S161 the crash signal is sent to the rescue center system.
  • the black box signal receiving module 20 inside the black box can acquire the crash signal, that is, can continuously record the position and flight condition of the plane crash, for example, the crash signal includes the crash location, the impact force, the impact angle, and the like.
  • the crash signal includes the escape ladder, whether the life raft is opened or used, Various signals such as breakage and breakage of various parts of the aircraft; if the aircraft is still in flight (sliding) when the black box is ejected, the crash signal includes remaining fuel condition, current flight altitude, flight speed, and angle of attack.
  • the black box signal storage module 21 inside the black box can store the crash signal described above into the local memory.
  • the signal transmitting module inside the black box can send the crash signal to the rescue center system in real time, and the rescuer can remotely obtain the information stored in the black box.
  • the process of a plane crash does not require a lot of time to search for and recycle the black box and then obtain the information stored in it.
  • Rescuers can quickly determine the location of the crash based on the information received in real time, and arrive at the crash site and rescue operations in the first place, saving valuable search and rescue time. Further, after the black box is ejected, the black box continues to receive information about the aircraft before the aircraft flies away from the effective communication range to provide the rescuer with the latest information and conditions.
  • a black box control system provided by an embodiment of the present invention includes: a first flight state detecting module 10, a first flight state determining module 11 and a first Ejection module 12;
  • the first flight state detecting module 10 is configured to acquire current flight data of the aircraft, and the flight data includes an impact signal, a runaway signal, and a stall signal;
  • the first flight state determining module 11 is configured to determine, according to the flight data, whether the aircraft is in a dangerous state at the current time;
  • the first ejection module 12 is configured to eject the first black box set on the aircraft to the aircraft when the first flight state determination module determines to be YES.
  • the invention provides a first flight state detecting module 10, a first flight state determining module 11 and a first catapult module 12 on the aircraft.
  • the first flight detection module disposed on the aircraft monitors its flight condition in real time, and when the first flight state detection module 10 acquires the current flight data, it is electrically connected to the first flight state detection module 10.
  • the first flight state determination module 11 determines, based on the flight data, whether the aircraft is in a dangerous state at the current time.
  • the first ejection module 12 ejects the first black box set on the aircraft.
  • the risk of flying risk is various, may impact, or may be due to loss of control or stall, which eventually leads to the crash of the aircraft. Therefore, the above flight data includes impact signals, runaway signals and stall signals, but not limited to impact signals, runaway signals and stall signals. .
  • a preferred embodiment of the black box control system provided by the embodiment of the present invention further includes a second flight state detecting module, a second flight state determining module, and a second catapult module:
  • a second flight state detecting module configured to acquire a current altitude signal of the aircraft
  • a second flight state determining module configured to determine, according to the altitude signal, whether the aircraft is in a state of impending groundfall at the current time
  • a second ejection module configured to eject the second black box set on the aircraft to the aircraft when the second flight state determination module determines to be YES.
  • the second flight state detecting module on the aircraft acquires the current altitude signal of the aircraft, and the second flight state determining module determines whether the current time is in a state of impending groundfall according to the altitude signal, when the second flight state determining module determines The result is YES, the second ejection module will be placed in the second black box on the aircraft to eject the aircraft.
  • the altitude signal is the altitude of the aircraft at that moment.
  • the second flight state detecting module, the second flight state determining module and the second catapult module are only a preferred embodiment of the present invention, and the second black box that is ejected has the same function as the first black box, and after the plane crashes, the phase Looking for a black box, looking for two black boxes increases the efficiency of search and rescue personnel. In the same way, setting a number of black boxes on the plane and popping up in sequence during the crash of the aircraft also increases the efficiency of the search and rescue personnel. It is also within the scope of the present invention to provide a plurality of black boxes.
  • a preferred embodiment of the black box control system provided by the embodiment of the present invention further includes a black box signal transceiver device, and the black box signal transceiver device is disposed in the first black box or the second black box, and includes:
  • the black box signal receiving module 20 is configured to acquire a crash signal
  • a black box signal storage module 21 configured to store the crash signal into a local memory
  • the black box signal sending module 22 is configured to send the crash signal to the rescue center system.
  • Figure 5 is a diagram showing the black box signal transceiver.
  • the black box signal receiving module 20 inside the black box can acquire the crash signal, that is, can continuously record the position of the plane crash and the flight condition (including flight speed, direction, altitude, aircraft condition, etc.).
  • the black box signal storage module 21 inside the black box can store the crash signal described above into the local memory.
  • the signal transmitting module inside the black box can send the crash signal to the rescue center system in real time, and the rescuer can remotely obtain the information stored in the black box.
  • the process of a plane crash does not require a lot of time to search for the black box to get the information stored in it. Rescuers can quickly determine the location of the crash based on the information received in real time, and arrive at the crash site and rescue operations in the first place, saving valuable search and rescue time.
  • a preferred embodiment of the black box control system provided by the embodiment of the present invention further includes a pop-up structure used by the black box on the aircraft, and the pop-up structure used by the black box is used to eject the first black box or the second black box, including the aircraft.
  • the upper body 30 is electrically connected to the push-out portion of the aircraft ejecting trigger circuit, and the push-out portion includes a push rod 31;
  • the cabin 30 is a hollow cavity having an opening at one end;
  • the push rod 31 is located inside the cabin 30 and is used for ejecting motion in the direction of the opening of the cabin after receiving the trigger signal of the aircraft pop-up trigger circuit to eject the first black box or the second black box into the aircraft.
  • the specific structure of the pop-up structure is shown in Figure 6.
  • the pop-up structure used by the black box on the plane will pop up the black box.
  • the ejection movement of the pop-up structure is made by the push rod 31 disposed inside the cabin 30, after receiving the aircraft. Execute after the trigger signal of the trigger circuit is popped up.
  • the above-mentioned cabin 30 is preferably a hollow cylindrical cavity, but is not limited to a hollow cylindrical cavity, but may be other forms of hollow cylindrical cavity.
  • the pusher 31 is a rod-shaped pusher 31, but is not limited to the rod-shaped pusher 31, and may be in the form of a push-out portion in which one end is connected to the plate-shaped sealing plate 32.
  • the seal plate 32 at the end of the push rod 31 is integrated with the push rod 31. forming.
  • the sealing plate 32 at the end of the push rod 31 is sealingly connected to the inner wall of the cabin 30, and a gasket-like reinforced airtight member may be added at the position of the sealing connection. After the pusher 31 ends the ejection movement, the sealing plate 32 can fill the opening of the cabin 30 to ensure the airtightness of the interior of the cabin 30.
  • the pushing portion further includes a fixed lock and a motor for driving the fixed lock.
  • the push rod 31 is provided with a card slot, and the fixed lock extends into the card slot to limit Position pusher 31;
  • the motor is electrically connected to the trigger circuit for driving the fixed lock to extend the card slot after receiving the trigger signal of the aircraft pop-up trigger circuit, so that the push rod 31 is ejected toward the opening of the cabin 30, and then the first Black box or second black box pops up the plane.
  • the black box control method and system provided by the embodiments of the present invention can also manually eject black boxes.
  • the motor for driving the fixed lock is electrically connected with a switch button, and the switch button is set in the flying cab. When the captain judges that the aircraft is about to crash, the button can be manually pressed to eject the black box.
  • the black box control method and system provided by the embodiment of the invention further includes a safety device for preventing the black box control system from being misjudged.
  • the motor is a driving source for driving the fixed lock to open and close. Since the motor and the trigger circuit are electrically connected, after receiving the trigger signal of the aircraft pop-up trigger circuit, the motor drives the fixed lock to open, that is, the fixed lock extends out of the card slot. .
  • the fixed lock is preferably annular, but is not limited to an annular shape, but may be other shapes.
  • the motor can drive the fixed lock to lock the push rod 31.
  • the pushing portion further includes a first ejector for permanently generating thrust.
  • the push rod 31 in the ejection structure is always under the force state, and the push rod 31 is fixed by the fixed lock.
  • the motor After receiving the trigger signal of the aircraft pop-up trigger circuit, the motor will drive the fixed lock. Open, that is, the fixed lock extends out of the card slot.
  • the pusher 31 which was always under the force state, performs the ejection motion.
  • the first ejector is preferably a resettable spring structure.
  • the first ejector is preferably a resettable spring structure or a motor drive structure.
  • the pushing portion further includes a second ejector for generating a thrust after receiving the trigger signal.
  • the second ejector is different from the first ejector.
  • the push rod 31 in the ejection structure is not always in a stressed state, but receives a trigger signal of the aircraft pop-up trigger circuit. Thereafter, the second ejector generates a thrust on the push rod 31.
  • the second ejector can be a lock spring with a lock. When the push rod 31 is not under the force state, the return spring is in a compressed state under the restriction of the lock. After receiving the trigger signal of the aircraft pop-up trigger circuit, the lock is opened, and the spring is opened. Reset, push the push rod to do the ejection movement.
  • the second ejector can also be a motor drive structure.
  • the motor When the pop-up signal is not received, the motor is in a closed state. Upon receiving the pop-up signal, the motor drives the push rod 31 to perform a pop-up motion, and the sealing plate 32 reaches the hatch 30 position. When the gap of the hatch 30 is filled, the motor stops applying force to the push rod 31, or the motor stops operating.
  • a preferred embodiment of the pop-up structure of the black box control system provided by the embodiment of the present invention further includes a housing 04 and a card lock carrying the black box;
  • the latch is used to provide a clamping force to the outer casing 04 of the black box so that the outer casing 04 is fixed on the cabin 30 under the clamping force;
  • the thrust is greater than the clamping force.
  • the outer casing 04 which is clamped to the cabin 30 by the clamping force can eject the cabin 30 under the action of the thrust of the push rod 31.
  • the latch may be an annular telescopic claw mounted on the end of the push rod 31 (on the sealing plate 32 when the end of the push rod 31 is provided with the sealing plate 32) or on the inner wall of the cabin 30. .
  • the claws When the push rod 31 is not subjected to the ejection movement, the claws will protrude into the outer casing 04 to fix the outer casing 04; when the push rod 31 is used for the ejection movement, the annular claws will be disposed along the inner end of the push rod 31 or the inner wall of the cabin 30. The curved passage is retracted to achieve the function of releasing the outer casing 04.
  • the structure of the above latch is only a preferred embodiment of the embodiment, and may be other forms of latching structure.
  • a preferred embodiment of the pop-up structure of the black box control system provided by the embodiment of the present invention further includes a baffle 33 disposed at the opening of the cabin 30;
  • One end of the baffle 33 is rotatably connected to the edge of the push-out end;
  • the other end of the baffle 33 extends toward the center of the opening.
  • the state before the pusher 31 is subjected to the ejection movement is as shown in Fig. 7.
  • the outer casing 04 is fixed to the end of the push rod 31 by the latch, and the shutter 33 is closed.
  • the thrust on the push rod 31 is transmitted to the outer casing 04 fixed to the end of the push rod 31, so that the outer casing 04 generates a thrust against the baffle 33, and the baffle 33 is blocked by the thrust.
  • the end of the plate 33 extending toward the center of the opening moves toward the outside of the aircraft, and the opening gradually increases.
  • the clamping force disappears and the outer casing 04 makes a parabolic motion.
  • the cabin 30 is a hollow hollow body with an inner wall, and the outer surface of the outer casing 04 is in contact with the inner wall of the cabin 30.
  • the above-mentioned latch is the rough inner wall of the cabin 30, and the clamping force is the outer casing 04. The frictional force received, and the frictional force is smaller than the thrust of the push rod 31 when the ejection motion is performed.
  • the push rod 31 preferably has a structure with a sealing plate 32 at one end, similar to a piston rod.
  • the sealing plate 32 stays at the opening of the cabin 30 to ensure the cabin 30. Airtight, the baffle 33 returns to its original state, as shown in FIG.
  • the number of the baffles 33 may be one or more. When the number of the baffles 33 is set to one, as shown in FIG. 16, if the external fluid and the baffle 33 are relatively moved from left to right, the switching mode fluid can help the baffle 33 to close. When the contents in the cabin 30 are ejected, since the discharge member ejects the shutter 33, the closing action of the fluid on the shutter 33 cannot be achieved.
  • the number of the baffles 33 is set to be plural, the opening of the cabin 30 is viewed upward from below the cabin 30, as shown in FIG. 17, the structure 1 is the case of the two baffles 33 of the cylindrical pod 30; the structure 2 is the cylinder compartment The case of the body 30 is four baffles 33; the structure 3 is the case of the two baffles 33 of the square columnar body 30.
  • a preferred embodiment of the pop-up structure of the black box control system provided by the embodiment of the present invention further includes a lower plate and a moving plate 34 disposed at the opening of the cabin 30;
  • a through hole is formed in the center of the lower plate to form an opening of the cabin 30;
  • the lower plate is annular, and the inner wall is provided with a telescopic groove
  • the moving plate 34 is slidably coupled to the telescopic groove and is reciprocable along the telescopic groove to close or open the opening of the cabin 30.
  • the structure of the moving plate 34 is viewed from below the cabin 30 as shown in FIG. It should be emphasized that the manner in which the moving plate 34 moves toward the telescopic slot is only one possible way of moving, and the moving plate 34 can also pass through the motor. Drive to complete the movement of the moving plate 34 into the telescopic slot.
  • the cabin 30 is a hollow hollow body with an inner wall, and the outer surface of the outer casing 04 is in contact with the inner wall of the cabin 30.
  • the above-mentioned latch is the rough inner wall of the cabin 30, and the clamping force is the outer casing 04. The frictional force received, and the frictional force is smaller than the thrust of the push rod 31 when the ejection motion is performed.
  • the push rod 31 preferably has a structure with a sealing plate 32 at one end, similar to a piston rod.
  • the sealing plate 32 stays at the opening of the cabin 30 to ensure the cabin 30. Airtight, the moving plate 34 is moved to the initial position. As shown in Figure 11.
  • an inner wall of the cabin is further provided with an opening for installing black box or other garnish from the inside.
  • the tank is closed by a door panel with pressure sensing elements.
  • the door panel is closed to avoid sudden sudden changes in the internal pressure of the cabin and affect safety.
  • the closing and opening forms of the door panel may be in the form of opening and closing of the aforementioned baffle, or may be in the form of opening and closing after the sliding connection of the lower plate and the moving plate.
  • the above-mentioned opening as a black box or other placing object is further provided with a closing door panel, and the closing and opening forms of the closing door panel may be in the form of opening and closing of the foregoing baffle plate, or may be a sliding connection between the lower plate and the moving plate. After opening and closing forms.
  • a moving roller is further disposed at the open end, and when the black box or other objects to be placed in the cabin is too heavy, the black box or the product to be installed into the cabin can be sent into the cabin by moving the roller. .
  • a preferred embodiment of an ejection device provided by an embodiment of the present invention further includes a supercharger for balancing the air pressure inside and outside the cabin.
  • the pressure of the cabin will change.
  • opening the opening provided in the inner wall of the cabin presents a safety problem.
  • the pressure inside the cabin can be constantly balanced to maintain a small pressure difference with the outside world to ensure the safety when opening the inner wall of the cabin.
  • the above-mentioned supercharger can be replaced with a decompressor. After the submarine or submersible is placed, the liquid can enter the interior of the cabin. Before opening the opening inside the cabin, the decompressor can withdraw the liquid from the cabin.
  • the shell structure used in the black box of the black box control system provided by the embodiment of the present invention is used to carry the first black box or the second black box, including the shell 40 carrying the black box, the floater 41 and the slow speed. 42
  • the retarder 42 is disposed at an upper portion of the housing 40;
  • the floater 41 is disposed on the outer wall of the housing 40.
  • the floater 41 is annular, including a plurality of floating air cushions 411 and a plurality of connecting members 412;
  • the plurality of floating air cushions 411 are arranged in a ring shape, and the adjacent two floating air cushions 411 are connected by a connecting member 412, and the floater 41 surrounds the outer surface of the casing 40 and is detachably connected to the outer surface of the casing 40;
  • the retarder 42 is used to reduce the impact force received after landing.
  • the retarder 42 disposed on the outer casing 04 operates, and the retarder 42 is used to slowly lower the outer casing 04 to prevent the outer casing 04 from landing (or floating). And the surface of the water was damaged by severe impact. After the outer casing 04 is ejected from the cabin 30, it may fall on the ground or may fall on the sea surface. In order to prevent the outer casing 04 from sinking into the seabed with the black box, it is difficult to salvage, and the outer casing 04 is also provided with a floater 41. When the outer casing 04 comes into contact with water or is stably landed, the retarder 42 stops working and the floater 41 starts to work as shown in FIG.
  • the housing 40 of the carrier material is preferably a cylindrical hollow cavity, but is not limited to the structure of the cylindrical hollow cavity.
  • one end of the hollow cavity is provided with a retarder 42 mounting area for mounting the retarder 42.
  • the mounting area of the retarder 42 may specifically be a recess that is recessed toward the interior of the hollow cavity, and a mounting hole is provided in the recess, and the retarder 42 is screwed to the groove through the mounting hole. It should be noted here that the above-mentioned retarder 42 mounting area is only a preferred embodiment of the embodiment, and the retarder 42 mounting area may also be designed in other structural forms to realize the connection of the retarder 42 to the housing 40.
  • the floater 41 includes a floating air cushion 411 and a connecting member 412, and the specific structure is as shown in Figs. 19 and 20, respectively.
  • the floating air cushion 411 shown in Fig. 19 is provided with a screw hole at a position in fixed contact with the casing 40, and is connected to the casing 40 by screws. It should be noted here that the connection manner of the floating air cushion 411 and the housing 40 is not limited to the screw connection, but can also be a snap connection or the like.
  • the number of floating air cushions 411 is plural, and can also be one.
  • Figure 20 shows the connector 412. Both ends of the connector 412 are provided with flanges, and the adjacent two floating air cushions 411 are screwed through the mounting holes in the flange.
  • the floater 41 point and the connecting member 412 shown in FIG. 19 and FIG. 20 are only a preferred embodiment of the embodiment, and the specific structure thereof can be based on the shape and size of the article carried by the carrier or the shape of the casing 40.
  • the size is correspondingly designed to achieve the connection of the floater 41 to the housing 40.
  • a plurality of floating air cushions 411 are uniformly wrapped around the outer surface of the housing 40 as shown in FIG.
  • a preferred embodiment of the housing structure used for the black box in the black box control system provided by the embodiment of the present invention further includes a first water detecting element, a telescopic device 43 disposed at the bottom of the housing 40, and a telescopic trigger circuit;
  • the first water detecting element, the telescopic trigger circuit and the telescopic device 43 are electrically connected in sequence;
  • the telescopic trigger circuit is configured to trigger the operation of the telescopic device 43 when the first water detecting component acquires the first water signal.
  • the first water detecting element disposed in the outer casing 04 collects the first water signal and triggers the telescopic trigger circuit.
  • the telescopic device 43 electrically connected to the telescopic trigger circuit 43 start working.
  • the telescopic device 43 is used to enhance the stability of the entire outer casing 04 so as to prevent the outer casing 04 from being tilted by the action of the wind when it encounters a strong wind at sea, or even turning over, thereby affecting the normal operation of the devices inside the outer casing 04.
  • the telescoping device 43 disposed on the outer casing 04 can provide a restoring force to the outer casing 04, making the outer casing 04 resemble a tumbler, reducing the possibility of the outer casing 04 flipping.
  • the telescopic device 43 includes a plurality of expansion joints that are sleeved with each other;
  • the telescoping energy dissipation extends away from the housing 40.
  • each of the expansion joints is a hollow columnar body, and the expansion joints of the sleeves have different inner diameters and outer diameters, and two expansion joints that are sleeved with each other, wherein one outer diameter of the expansion joint is equal to the other expansion joint Inner diameter.
  • the expansion joint having the largest outer diameter projects in a direction away from the casing 40.
  • the expansion joint having the smallest outer diameter is connected to the outer casing 04.
  • a preferred embodiment of the housing structure used in the black box control system of the black box control system provided by the embodiment of the present invention further includes a second water detecting element 45 and a floater trigger circuit 44;
  • the second water detecting element 45, the floater trigger circuit 44 and the floater 41 are sequentially electrically connected;
  • the floater trigger circuit 44 is configured to trigger the floater 41 to operate when the second water detecting element 45 collects the second water signal.
  • the second water detecting element 45 is configured to collect the second water signal, and the floater 41 is triggered to operate by the floater trigger circuit 44 when the second water detecting element 45 collects the second water signal.
  • the second water detecting element 45 may be an independent detecting element different from the first water detecting element, or may be a first water detecting element.
  • the first water detecting element and the buoyant trigger circuit 44 are electrically charged. The connection, when the first water detecting element detects the first water signal, triggers the buoyant 41 to operate while triggering the operation of the telescopic device 43.
  • Figure 15 is a schematic diagram of the floating module working module.
  • a preferred embodiment of the housing structure used by the black box in the black box control system provided by the embodiment of the present invention further includes a height detecting component and a first slow trigger circuit;
  • the height detecting component, the first slow trigger circuit and the retarder 42 are electrically connected in sequence;
  • the first slow trigger circuit is configured to trigger the retarder 42 to work when the altitude detecting component collects the altitude signal.
  • the retarder 42 can start working immediately, or can be started at a certain altitude and altitude.
  • the height detecting element is used to collect the altitude signal, and after the altitude signal is acquired, the retarder 42 is triggered to operate by the first slow trigger circuit.
  • the height detecting component may be a GPS positioning component that detects the current first altitude signal through the GPS positioning component.
  • the height detecting element can also be a radio height detecting element. The height of the ground or water surface is obtained by the radio height detecting component, and the retarder is activated at the specified height.
  • the retarder 42 is any one of a parachute or a propeller.
  • a preferred embodiment of the outer casing structure used for the black box on the aircraft provided by the embodiment of the present invention further includes a third water detecting component, a disengagement buckle and a disengagement trigger circuit;
  • the third water detecting component, the disengagement buckle and the disengagement trigger circuit are sequentially electrically connected;
  • the disengagement trigger circuit is configured to trigger the disengagement release disengagement retarder 42 when the third water detecting component collects the third water signal.
  • the retarder 42 stops working and the floater 41 starts to work.
  • the retarder 42 is stopped in the form of a retarder 42 that is disengaged from the outer casing 04 by a disengagement.
  • the third water detecting element is configured to collect the third water signal, and triggers the disengagement release disengagement 42 when the third water detecting element acquires the third water signal.
  • the third water detecting element may be an independent detecting element different from the first water detecting element and the second water detecting element 45, or may be the first water detecting element or the second water detecting element 45.
  • the third water detecting element is the first water detecting element
  • the first water detecting element is electrically connected to the disengagement trigger circuit, and when the first water detecting element detects the first water signal, the triggering expansion device 43 operates and the floater At the same time as the work of 41, the disengagement buckle is disengaged from the retarder 42.
  • the third water detecting element is the second water detecting element 45
  • the second water detecting element 45 is electrically connected to the disengagement trigger circuit, and when the second water detecting element 45 detects the second water signal, the trigger floats. While the device 41 is operating, the disengagement buckle is disengaged from the retarder 42.
  • a preferred embodiment of the housing structure used in the black box in the black box control system provided by the embodiment of the present invention further includes a timing element and a second slow trigger circuit;
  • the timing element, the second slow trigger circuit and the retarder 42 are electrically connected in sequence;
  • the second slow trigger circuit is configured to trigger the retarder 42 to work when the timing component reaches the preset time.
  • the retarder 42 can start working immediately, or can be started at a preset time.
  • the retarder 42 is started at a certain time, when the timing component reaches the preset time, the retarder 42 is triggered to operate by the second slow trigger circuit.
  • a preferred embodiment of the outer casing structure used in the black box in the black box control system provided by the embodiment of the present invention further includes a first rechargeable battery, a solar device, a fourth water detecting element, and a solar trigger circuit;
  • the fourth water detecting element, the solar trigger circuit and the solar device are sequentially electrically connected;
  • a solar trigger circuit for triggering operation of the solar device when the fourth water detecting component collects the fourth water signal
  • a solar device for supplying power to the first rechargeable battery after operation.
  • the solar device is capable of powering the first rechargeable battery, and the first rechargeable battery is capable of powering all of the electrical components inside the casing 04 to enhance the endurance of the casing 04.
  • the fourth water detecting element is configured to collect the fourth water signal, and triggers the solar device to operate when the fourth water detecting element collects the fourth water signal.
  • the fourth water detecting element may be an independent detecting element different from the first water detecting element, the second water detecting element 45 and the third water detecting element, or may be the first water detecting element or the second water.
  • the detecting element 45 or the third water detecting element may be the first water detecting element or the second water.
  • the fourth water detecting element is the first water detecting element
  • the first water detecting element is electrically connected to the solar trigger circuit, and when the first water detecting element detects the first water signal, the expansion device 43 is triggered to operate and the floater 41 operates. At the same time as the disengagement buckle is disengaged, the solar device is triggered by the solar trigger circuit.
  • the fourth water detecting element is the second water detecting element 45
  • the second water detecting element 45 is electrically connected to the solar trigger circuit, and when the second water detecting element 45 detects the second water signal, the floating device is triggered.
  • the 41 work and disengagement buckles disengage the retarder 42 while triggering the solar device operation through the solar trigger circuit. The same is true when the fourth water detecting element is the third water detecting element.
  • a preferred embodiment of the outer casing structure used in the black box in the black box control system provided by the embodiment of the present invention further includes a second rechargeable battery, a wind energy device, a fifth water detecting element and a wind energy trigger circuit;
  • the fifth water detecting element, the wind energy triggering circuit and the wind energy device are sequentially electrically connected;
  • the wind energy triggering circuit is configured to trigger the wind energy device to work when the fifth water detecting component collects the fifth water signal.
  • the wind energy device can power the second rechargeable battery, and the second rechargeable battery can also supply all of the electrical components inside the casing 04, thereby enhancing the endurance of the casing 04.
  • the fifth water detecting element is used to collect the fifth water signal, and triggers the wind energy device to work when the fifth water detecting element collects the fifth water signal.
  • the fifth water detecting element may be an independent detecting element different from the first water detecting element, the second water detecting element 45, the third water detecting element and the fourth water detecting element, or may be the first water.
  • the fifth water detecting element is the first water detecting element
  • the first water detecting element is electrically connected to the wind energy triggering circuit, and when the first water detecting element detects the first water signal, triggering the expansion device 43 to work and the floating device 41 to work.
  • the wind energy trigger circuit is triggered to trigger the operation of the wind energy device.
  • the fifth water detecting element is the second water detecting element 45
  • the second water detecting element 45 is electrically connected to the wind energy triggering circuit, and when the second water detecting element 45 detects the second water signal, the floating device is triggered.
  • the wind energy trigger circuit triggers the wind energy device to work.
  • the above-described fifth water detecting element is the same as the third water detecting element or the fourth water detecting element.
  • the first water detecting element, the second water detecting element, the third water detecting element, the fourth water detecting element, and the fifth water detecting element may each be a water level detecting element made of a separate PCB board used in the water tower, and the first water The detecting element, the second water detecting element, the third water detecting element, the fourth water detecting element, and the fifth water detecting element may each be replaced with a height detecting module.
  • the height detection module can be a GPS positioning unit or a radio height detection module.
  • the altitude detection module includes a GPS positioning unit, a radio altimeter for detecting the current flying altitude, and a near-ground warning GPWS for issuing a warning when the flying height is detected to be too low.
  • a preferred embodiment of a carrier for an airdrop item provided by an embodiment of the present invention further includes a navigator, a navigation trigger circuit, and a first GPS locator;
  • the navigator, the navigation trigger circuit and the first GPS locator are sequentially electrically connected;
  • the navigation trigger circuit is configured to trigger the navigator to work when the first GPS locator acquires the position signal.
  • the navigator may be a propeller disposed outside the casing 40.
  • the first GPS positioner collects the current position signal and triggers the propeller work, and the propeller provides the vehicle with the power to move on the water surface, which is determined according to the current position signal.
  • the direction of movement of the carrier so that the carrier carries the item to the shore or to the area covered by the signal.
  • a preferred embodiment of a carrier for an airborne article provided by an embodiment of the present invention further includes an unmanned aerial vehicle, an aircraft trigger circuit, and a second GPS locator;
  • the UAV, the aircraft trigger circuit and the second GPS locator are sequentially electrically connected;
  • the aircraft trigger circuit is configured to trigger the navigator to work when the second GPS positioner acquires the second position signal.
  • the second GPS locator collects the current second position signal, and determines the target delivery position of the item according to the current second position signal, so as to accurately transport the material to the target area.
  • the carrier of the airdrop item provided by the embodiment is mainly used for carrying the airdrop item, and the airdrop item is not limited to the disaster relief material described in the embodiment, and can also be used for carrying the black box in the aircraft.
  • the captain can manually or automatically eject the vehicle carrying the black box, and the aircraft carrying the black box falls into the water.
  • the carrier of the airdrop item provided by the utility model can effectively prevent the black box from sinking into the water bottom. It is difficult to salvage, and it is convenient for search and rescue personnel to find black boxes, saving search and rescue time.
  • a preferred embodiment of the housing structure used by the black box in the black box control system provided by the embodiment of the present invention further includes a signal transceiving gain device;
  • Signal transceiving gain device for enhancing the crash signal received and sent by the black box.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Emergency Alarm Devices (AREA)

Abstract

La présente invention concerne un procédé de commande de boîte noire qui consiste : à acquérir des données de vol actuelles d'un aéronef, les données de vol comprenant un signal de collision, un signal de perte de contrôle et un signal de décrochage ; à déterminer, en fonction des données de vol, si l'aéronef est actuellement dans un état dangereux ; lorsqu'un premier module de détermination d'état de vol détermine que l'aéronef est actuellement dans l'état dangereux, à éjecter, hors de l'aéronef, une première boîte noire disposée au niveau de l'aéronef. La présente invention porte également sur un système de commande de boîte noire. Lorsqu'un accident d'aéronef se produit, la boîte noire interne est éjectée pour atterrir ou flotter au niveau d'une zone proche de la collision de l'aéronef. La boîte noire reçoit des informations de collision de l'aéronef et transmet en temps réel, à un système de centre de sauvetage, les informations de collision. Par conséquent, le système de centre de sauvetage peut déterminer rapidement, en fonction des informations de collision, un emplacement de collision d'aéronef, ce qui permet de trouver rapidement la boîte noire de l'aéronef accidenté.
PCT/CN2017/100287 2016-09-01 2017-09-01 Procédé et système de commande de boîte noire WO2018041253A1 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
CN201610805098.7 2016-09-01
CN201610805054.4A CN106477045B (zh) 2016-09-01 2016-09-01 一种空投物品的载具
CN201610805054.4 2016-09-01
CN201610805107.2 2016-09-01
CN201610805107.2A CN106347690B (zh) 2016-09-01 2016-09-01 一种黑匣子控制方法及系统
CN201610805098.7A CN106314796A (zh) 2016-09-01 2016-09-01 一种弹射装置

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CN111907707A (zh) * 2020-06-15 2020-11-10 哈尔滨工业大学 一种电磁驱动的黑匣子抛放机构
CN111907706A (zh) * 2020-06-15 2020-11-10 哈尔滨工业大学 一种电磁驱动的黑匣子抛放分离机构
CN114926919A (zh) * 2022-05-06 2022-08-19 中国民用航空飞行学院 一种具有防静电结构的航空数据记录设备

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Publication number Priority date Publication date Assignee Title
CN111907707A (zh) * 2020-06-15 2020-11-10 哈尔滨工业大学 一种电磁驱动的黑匣子抛放机构
CN111907706A (zh) * 2020-06-15 2020-11-10 哈尔滨工业大学 一种电磁驱动的黑匣子抛放分离机构
CN111907707B (zh) * 2020-06-15 2021-09-07 哈尔滨工业大学 一种电磁驱动的黑匣子抛放机构
CN114926919A (zh) * 2022-05-06 2022-08-19 中国民用航空飞行学院 一种具有防静电结构的航空数据记录设备

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