Emergency mechanical and communication systems and methods for aircraft

• US 9,440,749 B1
• Filed: 03/03/2016
• Issued: 09/13/2016
• Est. Priority Date: 03/05/2015
• Status: Active Grant

• Current Assignee: Comac America Corporation
• Original Assignee: Comac America Corporation
• Inventors: Ye, Wei, Sun, Jianhong
• Primary Examiner(s): Mawari, Redhwan K
• Application Number:
  US15/060,367
• Publication Number:
  US 20160257421A1
• Time in Patent Office: 194 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. A system for rapid separation of a flight data recorder from an aircraft, the system comprising:

a flight data recorder, said flight data recorder comprising a wireless communication hardware configured to communicate flight information to a remote device;

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, said rapid ejection system comprising a housing for storing the flight data recorder and a pneumatic system configured to eject the flight data recorder out of an opening in the 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;

wherein the soft landing system comprises one or more inflatable airbags configured to be positioned about the flight data recorder when inflated;

wherein the one or more inflatable airbags comprise at least;

a first airbag configured to be annularly shaped when inflated;

a second airbag configured to be annularly shaped when inflated; and

a third airbag configured to be annularly shaped when inflated, the third airbag positioned between the first and second airbags; and

wherein the flight data recorder is configured to be separated from the aircraft and configured to receive and transmit flight information and images of the aircraft to the remote device immediately after the emergency event.

2. The system of claim 1, wherein the rapid ejection system further comprises an extraction parachute coupled to the flight data recorder.

3. The system of claim 2, wherein the extraction parachute is a spring-loaded parachute.

4. The system of claim 1, wherein the soft landing system comprises a descent control parachute coupled to the flight data recorder, the descent control parachute adapted to reduce a descending rate of the flight data recorder.

5. The system of claim 4, further comprising:

a detachment mechanism configured to detach the descent control parachute from the flight data recorder; and

a sensor configured to detect a water landing, to enable the detachment mechanism to cause detachment of the descent control parachute after a water landing.

6. The system of claim 1, wherein determining that the emergency event is occurring comprises determining that data received from each of at least two sensors exceeds a threshold level.

7. The system of claim 1, further comprising:

a tracking system stored within the housing of the rapid ejection system and adapted to be ejected with the flight data recorder out of the opening in the housing, the tracking device comprising at least one camera; and

a towing cable having a first end and a second end, wherein the first end is coupled to the housing or configured to be coupled to the aircraft,

wherein the tracking device is coupled to the second end of the towing cable, and the at least one camera of the tracking device is positioned to enable capturing of one or more images of the aircraft when the tracking device is towed behind the aircraft in flight by the towing cable.

8. The system of claim 1, further comprising the aircraft, wherein the housing of the rapid ejection system is coupled to the aircraft.

9. A system for rapid separation of a flight data recorder from an aircraft, the system comprising:

a housing comprising an internal cavity and an opening;

a flight data recorder positioned within the internal cavity of the housing and configured to be ejectable from the housing through the opening of the housing;

a pressurized gas source comprising a pressurized gas;

an ejector slidably positioned internal to the housing;

a valve configured to selectively fluidly couple the pressurized gas source to the ejector, wherein the valve comprises an open position and a close position, wherein the valve in the close position separates the pressurized gas from the ejector, and wherein the valve in the open position allows the pressurized gas to apply a force on the ejector to rapidly eject the flight data recorder from the housing;

the flight data recorder adapted to cause the valve to move from the close position to the open position when the flight data recorder detects an emergency event;

a landing mechanism coupled to the flight data recorder, the landing mechanism adapted to reduce impact forces during landing of the flight data recorder;

wherein the landing mechanism comprises an airbag system adapted to be inflated and to prevent the flight data recorder from sinking in water or to reduce the impact forces during landing;

wherein the airbag system comprises one or more inflatable airbags, the one or more inflatable airbags comprising at least;

a first annular shaped airbag positioned at a first end of the airbag system;

a second annular shaped airbag positioned at a second end of the airbag system; and

a third annular shaped airbag positioned between the first and second annular shaped airbags; and

a wireless communication system adapted to transmit data from the flight data recorder to at least one of a satellite, a second aircraft, and a base station.

10. The system of claim 9, wherein the landing mechanism comprises a descent control parachute coupled to the flight data recorder, the descent control parachute adapted to reduce a descending rate of the flight data recorder.

11. The system of claim 10, wherein the descent control parachute is a spring-loaded parachute.

12. The system of claim 10, wherein the descent control parachute is also adapted to apply a pulling force to the flight data recorder while the flight data recorder is being ejected from the housing.

13. The system of claim 10, further comprising:

an extraction parachute separate from the descent control parachute, the extraction parachute adapted to apply a pulling force to the flight data recorder while the flight data recorder is being ejected from the housing.

14. The system of claim 10, further comprising:

a detachment mechanism configured to detach the descent control parachute from the flight data recorder; and

a sensor configured to detect a water landing, to enable the detachment mechanism to cause detachment of the descent control parachute after a water landing.

15. The system of claim 9, further comprising the aircraft, wherein the housing is coupled to the aircraft.

16. The system of claim 9, further comprising:

a panel coupled to the housing and configured to at least partially cover the opening of the housing when the panel is in a closed position;

a spring that biases the panel toward an open position; and

a locking mechanism configured to retain the panel in the closed position and selectively release the panel to enable the panel to move toward the open position.