Ejection seat parachute deployment systems and methods

Patent metadata

Field	Value
Publication number	US-11834185-B2
Application number	US-202217665368-A
Country	US
Kind code	B2
Filing date	Feb 4, 2022
Priority date	Feb 4, 2022
Publication date	Dec 5, 2023
Grant date	Dec 5, 2023

Abstract

An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: receiving, via the processor, an ejection command for ejecting an ejection seat from an aircraft; determining, via the processor, an aircraft or ejection seat altitude and an aircraft or ejection seat speed; and commanding, via the processor, a simultaneous or staged deployment of a drogue parachute and a main parachute upon or just prior to separation of the ejection seat from the aircraft, the simultaneous or staged deployment being described herein.

First claim

What is claimed is:

1. An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising:
receiving, via the processor, an ejection command for ejecting an ejection seat from an aircraft;
determining, via the processor, an aircraft altitude or ejection altitude and an aircraft speed or an ejection seat speed;
commanding, via the processor, a simultaneous deployment of a drogue parachute and a main parachute upon separation of the ejection seat from the aircraft, the simultaneous deployment being between 0 and 150 milliseconds from one another; and
commanding, via the processor, separation of the drogue parachute after a time threshold measured from the simultaneous deployment, wherein the time threshold is between 100 milliseconds and 400 milliseconds.

2. The article of manufacture of claim 1 , wherein the operations further comprise determining the aircraft altitude and the aircraft speed are within a predetermined zone.

3. The article of manufacture of claim 2 , wherein the predetermined zone comprises an aircraft speed range between 25 knots and 300 knots and an aircraft altitude range between 0 feet (0 meters) and 20,000 feet (6,096 meters).

4. The article of manufacture of claim 3 , wherein a first threshold speed to be considered within the predetermined zone decreases or stays a same speed as the aircraft altitude or the ejection altitude increases.

5. The article of manufacture of claim 1 , wherein the simultaneous deployment is between 0 milliseconds and 100 milliseconds.

6. The article of manufacture of claim 1 , wherein the operations further comprise deploying the drogue parachute prior to deploying the main parachute.

7. The article of manufacture of claim 1 , wherein the operations further comprise determining, via the processor, the ejection seat has separated from the aircraft prior to the simultaneous deployment.

8. An ejection seat, comprising:
a seat back;
a drogue parachute stowed in or on the seat back;
a main parachute stowed in or on the seat back;
a processor; and
a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by the processor, cause the processor to perform operations comprising:
determining, via the processor, whether an aircraft is within a predetermined zone, the predetermined zone including a speed range and an altitude range,
commanding, via the processor, simultaneous deployment of the drogue parachute and the main parachute from the seat back upon separation of the ejection seat from the aircraft in response to determining the aircraft is within the predetermined zone, the simultaneous deployment being between 0 and 150 milliseconds from one anothe r ; and
commanding, via the processor, separation of the drogue parachute after a time threshold measured from the simultaneous deployment, wherein the time threshold is between 100 milliseconds and 400 milliseconds.

9. The ejection seat of claim 8 , wherein the operations further comprise:
receiving, via the processor, sensor data from at least two sensors; and
determining, via the processor, an aircraft speed or ejection seat speed and an altitude of the aircraft or the ejection seat based on the sensor data.

10. The ejection seat of claim 8 , wherein the operations further comprise determining whether an aircraft speed or an ejection seat speed and an altitude of the aircraft or the ejection seat are within the predetermined zone prior to ejection of the ejection seat.

11. An aircraft comprising:
an ejection seat, including:
a first sensor;
a second sensor; and
a drogue parachute stowed in or on the ejection seat;
a main parachute stowed in or on the ejection seat;
a processor in electronic communication with the first sensor and the second sensor;
a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by the processor, cause the processor to perform operations comprising:
determining, via the processor and based on sensor data received from the first sensor and the second sensor, whether the aircraft or the ejection seat is within a predetermined zone, the predetermined zone including a speed range and an altitude range,
commanding, via the processor, simultaneous deployment of the drogue parachute and the main parachute from the ejection seat upon separation of the ejection seat from the aircraft in response to determining the aircraft or the ejection seat is within the predetermined zone, the simultaneous deployment being between 0 and 150 milliseconds from one another; and
commanding, via the processor, deployment of only the main parachute in response to determining the aircraft is in a second zone having a speed less than a speed threshold of the speed range and an altitude less than a maximum altitude of the altitude range.

12. The aircraft of claim 11 , wherein the operations further comprise commanding, via the processor, separation of the drogue parachute after a time threshold measured from the simultaneous deployment.

13. The aircraft of claim 11 , wherein the operations further comprise releasing the drogue parachute first, severing the drogue parachute, and releasing the main parachute just prior or just after severing the drogue parachute in response to determining the aircraft is in a third zone.

14. The aircraft of claim 11 , wherein the first sensor is a static pressure sensor and the second sensor is a dynamic pressure sensor.

15. The aircraft of claim 14 , wherein the operations further comprise:
determining, via the processor, an equivalent airspeed of the aircraft or the ejection seat based on a delta between a first pressure data received from the dynamic pressure sensor and the static pressure sensor;
determining, via the processor, the altitude of the aircraft based on a second pressure data received from the static pressure sensor; and
determining, via the processor, whether the aircraft is in the predetermined zone based on the altitude and the speed of the aircraft.

16. An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising:
receiving, via the processor, an ejection command for ejecting an ejection seat from an aircraft;
determining, via the processor, an aircraft altitude or ejection altitude and an aircraft speed or ejection seat speed;
determining the aircraft altitude and the aircraft speed are within a predetermined zone, wherein the predetermined zone comprises an aircraft speed range between 25 knots and 300 knots and an aircraft altitude range between 0 feet (0 meters) and 20,000 feet (6,096 meters), and wherein a first threshold speed to be considered within the predetermined zone decreases or stays a same speed as the aircraft altitude or the ejection altitude increases; and
commanding, via the processor, a simultaneous deployment of a drogue parachute and a main parachute upon separation of the ejection seat from the aircraft, the simultaneous deployment being between 0 and 150 milliseconds from one another.

17. An aircraft comprising:
an ejection seat, including:
a first sensor including a static pressure sensor;
a second sensor including a dynamic pressure sensor; and
a drogue parachute stowed in or on the ejection seat;
a main par

Assignees

• Rockwell Collins Inc

Inventors

• Carson Kassidy L
• Hampton John

Classifications

• B64D17/56 Primary

  responsive to barometric pressure · CPC title

• B64D25/10 Primary

  Ejector seats · CPC title

• B64D17/62 Primary

  Deployment · CPC title