Ejectable flight data recorder systems, methods, and devices
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-045/00
B64D-025/08
출원번호
US-0581709
(2017-04-28)
등록번호
US-9745071
(2017-08-29)
발명자
/ 주소
Wang, Mingwei
Ye, Wei
출원인 / 주소
COMAC AMERICA CORPORATION
대리인 / 주소
Knobbe Materns Olson & Bear LLP
인용정보
피인용 횟수 :
1인용 특허 :
15
초록▼
An ejectable flight data recorder for robust retention of flight data and aiding in locating an aircraft after an emergency situation comprises: a buoyant housing comprising an internal cavity, a door for access to at least a portion of the internal cavity, and an aerodynamic outer shape having a lo
An ejectable flight data recorder for robust retention of flight data and aiding in locating an aircraft after an emergency situation comprises: a buoyant housing comprising an internal cavity, a door for access to at least a portion of the internal cavity, and an aerodynamic outer shape having a longitudinal axis; an energy-dissipating nose cone for reducing an impact load on the housing when the flight data recorder impacts a water surface; a nonvolatile memory configured to store flight data; a position sensor for detecting a geographic position of the flight data recorder; a radio transmitter; an antenna electrically coupled to the radio transmitter; a sustainable power system; and a hydrophone for acoustically tracking a sinking trajectory of the aircraft in a body of water.
대표청구항▼
1. A system for ejecting a flight data recorder from an aircraft in an emergency situation, the system comprising: a flight data recorder disposed within a launching tube, the flight data recorder configured to be ejectable from the launching tube, the flight data recorder comprising a nonvolatile m
1. A system for ejecting a flight data recorder from an aircraft in an emergency situation, the system comprising: a flight data recorder disposed within a launching tube, the flight data recorder configured to be ejectable from the launching tube, the flight data recorder comprising a nonvolatile memory for storing flight data;an ejection system comprising a stored energy source configured to cause rapid ejection of the flight data recorder from the launching tube when the ejection system is triggered; andan emergency detection system comprising: an aircraft data bus interface configured to receive aircraft data bus information comprising at least position data, altitude data, vertical speed data, and airspeed data;a sensor interface configured to receive sensor data generated by a plurality of sensors, the plurality of sensors comprising at least a plurality of collision sensors;an arming controller for automatically arming and disarming the ejection system based at least in part on one or more of the position data, the altitude data, the vertical speed data, or the airspeed data,wherein the arming controller is configured to dynamically disarm the ejection system within a first threshold distance from a first geographic location, and the arming controller is configured to dynamically disarm the ejection system within a second threshold distance from a second geographic location, the second threshold distance being different than the first threshold distance; andan ejection controller for automatically triggering the ejection system responsive to detection of one or more of a plurality of ejection conditions, the plurality of ejection conditions comprising ejection conditions grouped into at least two levels of authority,wherein the ejection controller is configured to, responsive to detection of an ejection condition having a lower level of authority, trigger the ejection system only if the ejection system is armed, andwherein the ejection controller is configured to, responsive to detection of an ejection condition having a higher level of authority, trigger the ejection system regardless of a current arming state of the ejection system. 2. The system of claim 1, wherein the arming controller is further configured to dynamically arm the ejection system below a lower threshold altitude. 3. The system of claim 1, wherein at least one of the plurality of ejection conditions comprises an anticipated collision within a threshold period of time, and wherein the ejection controller is configured to calculate an anticipated time to collision based on at least the altitude data and the vertical speed data. 4. The system of claim 3, wherein the threshold period of time is 0.5 seconds. 5. The system of claim 1, wherein at least one of the plurality of ejection conditions comprises an explosion or a fire. 6. The system of claim 5, wherein the ejection controller is configured to determine that the explosion has occurred by detecting both of the following: a loss in main bus power and a shock load above a threshold value. 7. The system of claim 5, wherein the ejection controller is configured to determine that the fire has occurred by detecting both of following: a loss in main bus power and passage of a threshold amount of time without a return of the main bus power. 8. The system of claim 1, wherein the ejection system further comprises a relief valve operatively positioned between the stored energy source and the flight data recorder to enable selective redirection of energy released from the stored energy source away from the flight data recorder, wherein the arming controller is configured to automatically cause opening of the relief valve when the aircraft is on the ground, to avoid launching of the flight data recorder even if energy is released from the stored energy source, andwherein the arming controller is configured to automatically cause closing of the relief valve when the aircraft is airborne. 9. The system of claim 1, wherein the launching tube is positioned adjacent a fuselage of the aircraft, to enable the flight data recorder to be launched through a hole in the fuselage of the aircraft. 10. The system of claim 9, wherein the launching tube is positioned such that the flight data recorder is configured to be launched from an area positioned between vertical and horizontal fins of the aircraft. 11. A system for ejecting an ejectable flight data recorder from an aircraft in an emergency situation, the system comprising: an ejectable flight data recorder disposed within a launching tube, the ejectable flight data recorder configured to be ejectable from the launching tube, the ejectable flight data recorder comprising a nonvolatile memory;an ejection system comprising a stored energy source configured to cause rapid ejection of the flight data recorder from the launching tube by rapidly pressurizing the launching tube when the ejection system is triggered; anda control system comprising: one or more computer processors configured to receive flight data as stored in a conventional flight data recorder and cockpit voice data as stored in a conventional cockpit voice recorder, and to transmit the flight data and cockpit voice data to the ejectable flight data recorder for storage in the nonvolatile memory of the ejectable flight data recorder;an arming controller for automatically arming and disarming the ejection system based at least in part on data received from an aircraft data bus comprising one or more of position data, altitude data, vertical speed data, or airspeed data; andan ejection controller for automatically triggering the ejection system responsive to detection of one or more of a plurality of ejection conditions,wherein the ejection controller is configured to detect the plurality of ejection conditions by analyzing one or more of the data received from the aircraft data bus and data received from one or more collision sensors. 12. The system of claim 11, wherein the control system further comprises a battery for powering the control system if a loss of main bus power occurs. 13. The system of claim 12, wherein the control system is configured to automatically disable itself when the aircraft is on the ground to prevent discharging of the battery when the aircraft is on the ground. 14. The system of claim 11, wherein the arming controller is configured to dynamically disarm the ejection system when the aircraft is currently in at least one of the following two situations: (1) the aircraft is within a first threshold distance from a first geographic location, or (2) the aircraft is above a lower threshold altitude and below an upper threshold altitude. 15. The system of claim 14, wherein the first geographic location comprises one or more of a populated area, a coastline, or an airport. 16. The system of claim 14, wherein the lower threshold altitude is 6,000 feet, and the upper threshold altitude is a service ceiling of the aircraft. 17. The system of claim 11, wherein the arming controller is configured to dynamically disarm the ejection system when the aircraft is within a first threshold distance from a first geographic location, and the arming controller is configured to dynamically disarm the ejection system when the aircraft is within a second threshold distance from a second geographic location, the second threshold distance being shorter than the first threshold distance. 18. The system of claim 17, wherein the first geographic location comprises a populated area, the second geographic location comprises a coastline, and the arming controller is configured to disregard the first threshold distance when the position data indicates that the aircraft is positioned over a body of water. 19. The system of claim 11, wherein the arming controller is configured to dynamically disarm the ejection system within different threshold distances from at least two of a plurality of geographic locations. 20. The system of claim 11, wherein the stored energy source comprises at least one of a propellant, a pressurized gas, or a combination of both to cause the rapid pressurizing the launching tube when the ejection system is triggered.
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