System and method for deploying loads out of an aircraft

Patent metadata

Field	Value
Publication number	US-9718546-B2
Application number	US-201313891290-A
Country	US
Kind code	B2
Filing date	May 10, 2013
Priority date	Nov 10, 2010
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

First claim

What is claimed is:

1. A system for deploying loads out of an aircraft, comprising:
an aerial delivery parachute with an aerial-delivery parachute line;
an activator configured to place the aerial delivery parachute in an enveloping flow past the aircraft;
a receiving device located in a fuselage of the aircraft that is configured to wirelessly receive signals;
a first force measuring device located outside the fuselage of the aircraft during a deployment process that is connected in series to the aerial-delivery parachute line to thereby measure a measured tractive force acting on the aerial-delivery parachute line; and
a first autarkical voltage supply as well as a wireless first transmitting device that is connected to the first autarkical voltage supply and to the first force measuring device so that the first autarkical voltage supply, the wireless first transmitting device and the first force measuring device are all located outside the fuselage of the aircraft,
wherein the first transmitting device is equipped to transmit to the receiving device signals representing the measured tractive force acting on the aerial-delivery parachute line to the receiving device located in the fuselage of the aircraft.

2. The system of claim 1 , further comprising:
a drogue parachute with a drogue parachute line; and
a second force measuring device that is connected in series to the drogue parachute line to thereby acquire second measuring data representing a second measured tractive force acting on the drogue parachute line, and includes a second autarkical voltage supply and a wireless second transmitting device that is connected to the second autarkical voltage supply,
wherein the second transmitting device is designed to transmit to the receiving device signals representing the acquired second measuring data and/or the data representing the acquired second measuring data from the second force measuring device.

3. The system of claim 1 , wherein the receiving device is connected to an electronics unit that is designed to compare the measured tractive force acting on the aerial-delivery parachute line with a maximum value of the tractive force, and to generate a warning signal if the maximum value of the tractive force is exceeded.

4. The system of claim 1 , further comprising a display unit that is designed to be connected to the receiving device and that is designed to display at least one of the measured tractive force and an instance of the measured tractive force exceeding a maximum value.

5. The system of claim 1 , further comprising an acoustic signaling device that is designed to be connected to the receiving device and that is designed to signal any instance of exceeding a maximum value of the tractive force.

6. The system of claim 1 , further comprising at least one mobile electronics device that is designed to display or further process the signals that are received by the receiving device.

7. The system of claim 1 , further comprising an emergency release device through which the aerial-parachute delivery line is feedable, wherein the emergency release device is designed to cut the aerial-parachute delivery line.

8. The system of claim 1 wherein the activator is a tow plate.

9. The system of claim 1 further comprising an electronics unit coupled to receive the signals representing the measured tractive force acting on the aerial-delivery parachute line from the receiving device and to increase a thrust applied to the aircraft when the measured tractive force acting on the aerial-delivery parachute line exceeds a maximum value.

10. The system of claim 1 further comprising an electronics unit coupled to receive the signals representing the measured tractive force acting on the aerial-delivery parachute line from the receiving device and to detach the aerial-delivery parachute when the measured tractive force acting on the aerial-delivery parachute line exceeds a maximum value.

11. The system of claim 1 further comprising a storage unit coupled to receive the signals representing the measured tractive force acting on the aerial-delivery parachute line from the receiving device and to store the measured tractive force acting on the aerial-delivery parachute line for subsequent analysis.

12. The system of claim 11 further comprising a global positioning system (GPS) receiver configured to provide location data that is stored in the storage unit in conjunction with the signals representing the measured tractive force acting on the aerial-delivery parachute line.

13. An aircraft having a fuselage, the aircraft comprising:
a closeable opening; and
a system for deploying loads out of the opening, the system including:
an aerial delivery parachute with an aerial-delivery parachute line;
an activator configured to place the aerial delivery parachute in an enveloping flow past the aircraft;
a receiving device located in the fuselage of the aircraft configured to wirelessly receive signals representing acquired measuring data indicating a measured tractive force acting on the aerial-delivery parachute line;
a first force measuring device that is located outside of the fuselage of the aircraft during a deployment process and that is connected in series to the aerial-delivery parachute line to thereby acquire the measuring data representing the measured tractive force acting on the aerial-delivery parachute line; and
a first autarkical voltage supply as well as a wireless first transmitting device that is connected to the first autarkical voltage supply and to the first force measuring device so that the first autarkical voltage supply, the wireless first transmitting device and the first force measuring device are all located outside the fuselage of the aircraft,
wherein the first transmitting device is equipped to transmit to the receiving device the signals representing the measured tractive force acting on the aerial-delivery parachute line to the receiving device located in the fuselage of the aircraft.

14. The aircraft of claim 13 , further comprising:
a drogue parachute with a drogue parachute line; and
a second force measuring device that is connected in series to the drogue parachute line to thereby acquire second measuring data representing a second tractive force acting on the drogue parachute line, and includes a second autarkical voltage supply and a wireless second transmitting device that is connected to the second autarkical voltage supply,
wherein the second transmitting device is designed to transmit to the receiving device signals representing the acquired second measuring data from the second force measuring device.

15. The aircraft of claim 13 , wherein the receiving device is connected to an electronics unit that is designed to compare the measured tractive force acting on the aerial-delivery parachute line with a maximum value of the tractive force, and to generate a warning signal if the maximum value of the tractive force is exceeded.

16. The aircraft of claim 13 , further comprising a display unit that is designed to be connected to the receiving device and that is designed to display at least one of a determined value of the tractive force and an instance of the tractive force exceeding a maximum value.

17. The aircraft of claim 13 , further comprising an acoustic signaling device that is designed to be connected to the receiving device and that is designed to signal an instance of exceeding a maximum value of the tractive force.

18. The aircraft of claim 13 , further comprising at least one mobile electronics device that

Assignees

• Airbus Operations Gmbh
• Airbus Sas

Inventors

• Bohlen Carsten
• Bohlen Holger

Classifications

• B64D1/10 Primary

  Stowage arrangements for the devices in aircraft · CPC title

• B64D17/62

  Deployment · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64D17/38

  Releasable fastening devices between parachute and load or pack · CPC title

• B64D17/68

  attached to apex of main canopy · CPC title