EMERGENCY MECHANICAL AND COMMUNICATION SYSTEMS AND METHODS FOR AIRCRAFT

• US 20170029128A1
• Filed: 08/02/2016
• Published: 02/02/2017
• Est. Priority Date: 03/05/2015
• Status: Active Grant

• Current Assignee: Comac America Corporation
• Original Assignee: Comac America Corporation
• Inventors: Ye, Wei, Sun, Jianhong
• Granted Patent: US 9,771,160 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 1/14 Absorbing landing shocks
• CPC Class Codes: B64D 17/00 Parachutes non canopied parachutes B64D19/00
• CPC Class Codes: B64D 2045/0065 Black boxes, devices automatically broadcasting distress signals
• CPC Class Codes: B64D 25/20 Releasing of crash position indicators
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 47/08 Arrangements of cameras
• CPC Class Codes: B65H 2701/34 electric cords or electric power cables
• CPC Class Codes: G06F 1/18 Packaging or power distribution
• CPC Class Codes: G07C 5/008 communicating information to a remotely located station transmission systems for measured values G08C
• CPC Class Codes: G07C 5/0858 wherein the data carrier is removable

Abstract

A system for rapid separation of a flight data recorder from an aircraft comprises a flight data recorder; an emergency detection system comprising a plurality of sensors for detecting flight parameters and at least one computer processor for analyzing the flight parameters and determining, based on the analysis, that an emergency event is occurring; a rapid ejection system comprising a pneumatic system configured to eject the flight data recorder out of an opening in a housing and through the skin of the aircraft when the emergency detection system determines that the emergency event is occurring; and a soft landing system, said soft landing system being attached to the flight data recorder and configured to reduce force of impact upon landing and increase buoyancy of the flight data recorder.

Claims

1-20. -20. (canceled)

21. An aircraft flight data recorder ejection and landing system comprising:

a flight data recorder comprising electronic storage for storing therein of at least data representative of a flight state of an aircraft;

an ejection system for rapid ejection of the flight data recorder from the aircraft, the ejection system comprising;

a housing comprising an internal cavity, the flight data recorder being positioned at least partially within the internal cavity;

an ejection system pressurized fluid source;

a fluid path fluidly coupled to the internal cavity of the housing and the ejection system pressurized fluid source; and

a valve operatively coupled to the fluid path to selectively allow pressurized fluid to flow from the ejection system pressurized fluid source to the internal cavity of the housing to cause ejection of the flight data recorder from the housing; and

a landing system for reducing landing impact forces and increasing buoyancy, the landing system coupled to the flight data recorder, the landing system comprising;

one or more landing system pressurized fluid sources;

a plurality of inflatable airbags configured to be disposed at least partially about an exterior surface of the flight data recorder when inflated, each of the plurality of inflatable airbags being selectively fluidly coupled to one or more of the one or more landing system pressurized fluid sources; and

a trigger mechanism configured to trigger one or more landing system valves to cause inflation of the plurality of inflatable airbags by the one or more landing system pressurized fluid sources upon occurrence of a condition,

wherein the condition is based on at least one of the following;

a passage of time since ejection of the flight data recorder from the aircraft, detecting that the flight data recorder has passed below a predetermined altitude, and detecting a loss of communication with the aircraft.

22. The aircraft flight data recorder ejection and landing system of claim 21, wherein the landing system further comprises:

one or more descent control parachutes coupled to the flight data recorder and configured to reduce a descending rate of the flight data recorder after ejection of the flight data recorder from the aircraft.

23. The aircraft flight data recorder ejection and landing system of claim 21, further comprising:

an antenna for wireless transmission of data from the flight data recorder to a remote device, the antenna coupled to the flight data recorder.

24. The aircraft flight data recorder ejection and landing system of claim 23, further comprising:

a ballast weight coupled to the flight data recorder at a first end of the flight data recorder, and

wherein the antenna is coupled to the flight data recorder at a second end of the flight data recorder, the second end being opposite the first end.

25. The aircraft flight data recorder ejection and landing system of claim 21, wherein the ejection system further comprises:

one or more extraction parachutes coupled to the flight data recorder.

26. The aircraft flight data recorder ejection and landing system of claim 22, wherein the one or more descent control parachutes are coupled to the flight data recorder at a first end of the flight data recorder, and wherein the plurality of inflatable airbags comprises at least an airbag positioned at a second end of the flight data recorder, the second end being opposite to the first end.

27. The aircraft flight data recorder ejection and landing system of claim 26, wherein the landing system further comprises:

a water sensor positioned at the second end of the flight data recorder, and

wherein the airbag positioned at the second end of the flight data recorder comprises an inflated shape having an opening through which water can pass to be detected by the water sensor.

28. The aircraft flight data recorder ejection and landing system of claim 27, wherein the airbag positioned at the second end of the flight data recorder comprises an annular shape.

29. The aircraft flight data recorder ejection and landing system of claim 27, wherein the landing system is configured to, responsive to detection of water by the water sensor, disconnect the one or more descent control parachutes from the flight data recorder.

30. A method of ejecting and landing an ejectable flight data recorder, the method comprising:

monitoring a flight condition of an aircraft;

initiating, responsive to detection of an abnormal flight condition, ejection of the flight data recorder from the aircraft, wherein the initiating comprises;

transmitting at least data representative of a flight state of the aircraft to the flight data recorder; and

opening a valve fluidly coupled to an ejection system pressurized fluid source, wherein opening the valve causes fluid from the pressurized fluid source to force the flight data recorder from a housing;

deploying a descent control parachute coupled to the flight data recorder, the descent control parachute configured to reduce a descending rate of the flight data recorder;

triggering, responsive to occurrence of a condition, inflation of a plurality of airbags, wherein the plurality of airbags are configured to be disposed at least partially about an exterior surface of the flight data recorder when inflated;

detecting a water landing of the flight data recorder; and

disconnecting the descent control parachute from the flight data recorder, responsive to detecting the water landing.

31. The method of claim 30, further comprising:

transmitting, wirelessly via an antenna coupled to the flight data recorder, data to a remote device.

32. The method of claim 30, wherein the initiating ejection of the flight data recorder further comprises:

deploying an extraction parachute.

33. The method of claim 30, wherein the condition is based on at least one of the following:

a passage of time since ejection of the flight data recorder from the aircraft, detecting that the flight data recorder has passed below a predetermined altitude, and detecting a loss of communication with the aircraft

34. The method of claim 30, wherein triggering inflation of the plurality of airbags comprises causing at least some of the plurality of airbags to be inflated into an annular shape.

35. An aircraft flight data recorder ejection and landing system comprising:

a flight data recorder comprising electronic storage for storing therein of at least data representative of a flight state of an aircraft;

an ejection system for rapid ejection of the flight data recorder from the aircraft, the ejection system comprising;

an ejection system pressurized fluid source; and

an ejection valve operatively coupled to the ejection system pressurized fluid source to selectively allow pressurized fluid to flow from the ejection system pressurized fluid source to an expandable cavity adjacent the flight data recorder, wherein the expandable cavity is configured such that expansion of the cavity causes the flight data recorder to be ejected from the aircraft; and

a landing system for reducing landing impact forces and increasing buoyancy, the landing system coupled to the flight data recorder, the landing system comprising;

one or more landing system pressurized fluid sources;

a plurality of inflatable airbags configured to be disposed about an exterior surface of the flight data recorder when inflated, each of the plurality of inflatable airbags being selectively fluidly coupled to one or more of the one or more landing system pressurized fluid sources; and

a trigger mechanism configured to trigger one or more airbag valves to cause inflation of the plurality of inflatable airbags by the one or more landing system pressurized fluid sources.

36. The aircraft flight data recorder ejection and landing system of claim 35, wherein the landing system further comprises:

one or more descent control parachutes coupled to the flight data recorder and configured to reduce a descending rate of the flight data recorder after ejection of the flight data recorder from the aircraft.

37. The aircraft flight data recorder ejection and landing system of claim 35, wherein the trigger mechanism is configured to trigger the one or more airbag valves upon occurrence of a condition, wherein the condition is based on at least one of the following:

a passage of time since ejection of the flight data recorder from the aircraft, detecting that the flight data recorder has passed below a predetermined altitude, and detecting a loss of communication with the aircraft.

38. The aircraft flight data recorder ejection and landing system of claim 35, wherein the ejection system further comprises:

one or more extraction parachutes coupled to the flight data recorder.

39. The aircraft flight data recorder ejection and landing system of claim 36, wherein the plurality of inflatable airbags comprises at least:

a first airbag configured to be, when inflated, positioned at an end of the flight data recorder opposite an end of the flight data recorder having the one or more descent control parachutes coupled thereto; and

a second airbag configured to be, when inflated, annularly shaped and positioned about a body of the flight data recorder.