Ejectable flight data recorder unit

Patent metadata

Field	Value
Publication number	US-10796509-B2
Application number	US-201815897929-A
Country	US
Kind code	B2
Filing date	Feb 15, 2018
Priority date	Feb 16, 2017
Publication date	Oct 6, 2020
Grant date	Oct 6, 2020

Abstract

An apparatus for recording aircraft flight data including a primary flight data recorder unit for recording data generated by aircraft systems during operation of an aircraft and a secondary flight data recorder unit in communication with the primary flight data recorder unit. The secondary flight data recorder unit is configured to receive and store data from the primary flight data recorder. The secondary flight data recorder unit is ejectable from the aircraft, and comprises a propulsion system to enable powered flight of the secondary flight data recorder unit.

First claim

The invention claimed is:

1. An apparatus for recording aircraft flight data, the apparatus comprising:
a primary flight data recorder unit configured to record data generated by aircraft systems during operation of an aircraft; and
a secondary flight data recorder unit in communication with the primary flight data recorder and configured to receive and store data from the primary flight data recorder;
wherein the secondary flight data recorder unit is ejectable from the aircraft, and comprises a propulsion system to enable powered flight of the secondary flight data recorder unit;
wherein the secondary flight data recorder unit further comprises a guidance system configured to guide the secondary flight data recorder unit to a selected destination,
wherein the selected destination comprises a land-based location nearest to a last recorded location of the aircraft, and
wherein the land-based location nearest to the last recorded location of the aircraft is determined based on aircraft flight data most recently received, prior to ejection, by the secondary flight data recorder unit from the primary flight data recorder unit.

2. The apparatus according to claim 1 , wherein the guidance system comprises one or more of: a gyroscope and a GPS system.

3. The apparatus according to claim 1 , wherein the secondary flight data recorder unit comprises one or more of:
a power source;
a wireless communications interface for wirelessly receiving data from the primary flight data recorder unit;
a wired communications interface connectable to the primary flight data recorder unit by a data cable;
a locating system to transmit a localization signal for facilitating locating of the secondary flight data recorder unit;
a memory for storing received data; and
a camera for acquiring image and/or video data after ejection of the secondary flight data recorder unit from the aircraft.

4. The apparatus according to claim 1 , wherein the propulsion system comprises an electric motor.

5. The apparatus according to claim 1 , wherein the secondary flight data recorder unit comprises a housing.

6. The apparatus according to claim 1 , wherein the secondary flight data recorder unit comprises an unmanned aerial vehicle (UAV).

7. The apparatus according to claim 1 , wherein the primary flight data recorder unit is configured to continuously transmit current flight data to the secondary flight data recorder unit.

8. The apparatus according to claim 1 , wherein the secondary flight data recorder unit is configured to store flight data relating to a time period ending at the acquisition time of a most recently received flight data, and is configured to update the stored flight data when new flight data is received from the primary flight data recorder unit.

9. An apparatus for recording aircraft flight data, the apparatus comprising:
a primary flight data recorder unit configured to record data generated by aircraft systems during operation of an aircraft; and
a secondary flight data recorder unit in communication with the primary flight data recorder and configured to receive and store data from the primary flight data recorder;
wherein the secondary flight data recorder unit is ejectable from the aircraft, and comprises a propulsion system to enable powered flight of the secondary flight data recorder unit;
wherein a total weight of the secondary flight data recorder unit is less than half of a total weight of the primary flight data recorder unit, and/or a largest dimension of the secondary flight data recorder unit is less than half of a largest dimension of the primary flight data recorder unit.

10. An aircraft comprising:
a primary flight data recorder unit configured to record data generated by aircraft systems during operation of an aircraft;
a secondary flight data recorder unit in communication with the primary flight data recorder and configured to receive and store data from the primary flight data recorder, wherein the secondary flight data recorder unit is ejectable from the aircraft, and the secondary flight data recorder comprises a propulsion system to enable powered flight of the secondary flight data recorder unit;
a conduit connecting a location of the secondary flight data recorder unit to the outside of the aircraft, the conduit configured to enable ejection of the secondary flight data recorder unit from the aircraft; and
an ejection mechanism for ejecting the secondary flight data recorder unit from the aircraft via the conduit, wherein the ejection mechanism is configured to activate in response to a predetermined criterion being met,
wherein the ejection mechanism comprises a compressed air source configured for selectably delivering compressed air into the conduit to create a suction force at the location of the secondary flight data recorder, wherein the compressed air source is configured to deliver compressed air into the conduit in response to a predetermined criterion being met.

11. The aircraft according to claim 10 , wherein the ejection mechanism comprises at least one g-force sensor to measure current g-force on the aircraft, and wherein the predetermined criterion comprises a minimum g-force threshold and is defined such that a current g-force less than the threshold does not meet the predetermined criterion and a current g-force greater than the threshold meets the predetermined criterion.

12. The aircraft according to claim 10 , wherein the secondary flight data recorder unit comprises a rechargeable battery and the aircraft comprises a charging system configured to maintain the rechargeable battery in a substantially fully charged state.

13. An aircraft comprising:
a primary flight data recorder unit configured to record data generated by aircraft systems during operation of an aircraft; and
a secondary flight data recorder unit in communication with the primary flight data recorder and configured to receive and store data from the primary flight data recorder, wherein the secondary flight data recorder unit is ejectable from the aircraft, and comprises a propulsion system to enable powered flight of the secondary flight data recorder unit;
a conduit connecting a location of the secondary flight data recorder unit to outside of the aircraft, wherein the conduit is configured to enable ejection of the secondary flight data recorder unit from the aircraft; and
an ejection mechanism for ejecting the secondary flight data recorder unit from the aircraft via the conduit, wherein the ejection mechanism is configured to activate in response to a predetermined criterion being met,
wherein the conduit comprises a first selectably openable door between an interior of the conduit and the outside of the aircraft, and a second selectably openable door between the location of the secondary flight data recorder unit and the interior of the conduit, wherein each of the first and second selectably openable doors is configured to open in response to the predetermined criterion being met.

14. A method comprising:
positioning an ejectable secondary flight data recorder unit in an aircraft adjacent a conduit in the aircraft and an ejection mechanism, wherein the conduit comprises a first selectably openable door between the an interior of the conduit and outside of the aircraft, and a second selectably openable door between the secondary flight data recorder unit in the aircraft and the interior of the conduit, wherein each of the first and second selectably openable doors are configured to open in response to a predetermined criterion being met, and the ejection mechanism is configured to eject the secondary flight data recorder

Assignees

• Airbus Operations Ltd

Inventors

• Satyanarayana Kartik

Classifications

• B64U80/82

  Airborne vehicles · CPC title

• B64U2101/20

  for use as communications relays, e.g. high-altitude platforms · CPC title

• B64U80/70

  in containers (B64U80/60 takes precedence) · CPC title

• B64U2101/30

  for imaging, photography or videography · CPC title

• B64U70/20

  for releasing or capturing UAVs in flight by another aircraft · CPC title