Pneumatic positioning system

Patent metadata

Field	Value
Publication number	US-9586676-B2
Application number	US-201414242817-A
Country	US
Kind code	B2
Filing date	Apr 1, 2014
Priority date	Apr 1, 2014
Publication date	Mar 7, 2017
Grant date	Mar 7, 2017

Abstract

Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.

First claim

What is claimed is:

1. A pneumatic shaft positioning system comprising:
a first pressure chamber;
a translating shaft protruding through the first pressure chamber;
a pressurized gas source coupled to the first pressure chamber;
a first valve controlling flow of gas from the pressurized gas source into the first pressure chamber; and
a first piston protruding into the first pressure chamber and slidably coupled to the first pressure chamber,
wherein the first piston comprises a first shaft,
wherein a longitudinal axis of the first shaft is parallel and non-collinear to a longitudinal axis of the translating shaft and
wherein the first shaft of the first piston forces the translating shaft into a predetermined position when the gas from the pressurized gas source fills the first pressure chamber.

2. The pneumatic shaft positioning system of claim 1 , further comprising a second pressure chamber and a second piston,
wherein the second pressure chamber is connected to the pressurized gas source,
wherein the first valve controls flow of the gas from the pressurized gas source into the second pressure chamber, and
wherein the second piston protrudes into the second pressure chamber and is slidably coupled to the second pressure chamber, and
wherein a second shaft of the second piston forces the translating shat into the predetermined position when the gas from the pressurized gas source fills the second pressure chamber.

3. The pneumatic shaft positioning system of claim 2 ,
wherein the first shaft of the first piston forces the translating shaft into the predetermined position in a first direction,
wherein the second shaft of the second piston forces the translating shaft into the predetermined position in a second direction, and
wherein the first direction is opposite to the second direction.

4. The pneumatic shaft positioning system of claim 3 , wherein the first shaft of the first piston and the second shaft of the second piston contact the translating shaft when the translating shaft is in the predetermined position.

5. The pneumatic shaft positioning system of claim 4 , further comprising a first stopper and a second stopper,
wherein the first stopper engages with the first piston when the translating shaft is in the predetermined position, and
wherein the second stopper engages with the second piston when the translating shaft is in the predetermined position.

6. The pneumatic shaft positioning system of claim 2 , wherein the first pressure chamber and the second pressure chamber are separated by a second valve preventing flow of the gas from the first pressure chamber to the second pressure chamber, and wherein the first pressure chamber comprises a release valve configured to reduce a pressure in the first pressure chamber relative to the second pressure chamber.

7. The pneumatic shaft positioning system of claim 1 , wherein the first valve receives a signal from a flight control computer and controls the flow of the gas from the pressurized gas source into the first pressure chamber based on the signal.

8. The pneumatic shaft positioning system of claim 1 , wherein the first valve comprises a pyrotechnic burst disc.

9. The pneumatic shaft positioning system of claim 1 , further comprising an interlocking mechanism configured to engage the first piston when the translating shaft is in the predetermined position.

10. An apparatus comprising:
a flight control computer system;
a translating shaft having a longitudinal axis;
an actuator for driving the translating shaft along the longitudinal axis,
wherein the actuator is communicatively coupled to the flight control computer; and

a pneumatic shaft positioning system comprising a pressure chamber, a pressurized gas source connected to the pressure chamber, a valve controlling flow of gas from the pressurized gas source into the pressure chamber, and a piston protruding into the pressure chamber and slidably coupled to the pressure chamber,
wherein the valve is communicatively coupled to the flight control computer system,
wherein the piston comprises a piston shaft,
wherein a longitudinal axis of the piston shaft is parallel and non-collinear to a longitudinal axis of the translating shaft, and
wherein the piston shaft forces the translating shaft into a predetermined position when the gas from the pressurized gas source fills the pressure chamber.

11. The apparatus of claim 10 , wherein the piston slides substantially parallel to the longitudinal axis of the translating shaft.

12. The apparatus of claim 10 , wherein the flight control computer system receives a failure signal from the actuator when the actuator fails and sends an activation signal to the valve of the pneumatic shaft positioning system.

13. The apparatus of claim 10 , wherein the actuator disengages from the translating shaft when the actuator fails.

14. The apparatus of claim 10 , wherein the actuator is an electro-mechanical actuator.

15. A method comprising:
operating a pneumatic shaft positioning system comprising a pressure chamber, a pressurized gas source connected to the pressure chamber, a valve controlling flow of gas from the pressurized gas source into the pressure chamber, and a piston protruding into the pressure chamber and slidably coupled to the pressure chamber;
activating the valve,
wherein the activated valve allows the flow of gas from the pressurized gas source into the pressure chamber thereby pressurizing the pressure chamber and forcing a piston shaft of the piston out of the pressure chamber;

contacting a translating shaft with the piston shaft
wherein a longitudinal axis of the piston shaft is parallel and non-collinear to a longitudinal axis of the translating shaft: and

while contacting the translating shaft with the piston shaft, extending the piston shaft out of the pressure chamber thereby moving the translating shaft to a predetermined position.

16. The method of claim 15 , further comprising receiving an activation signal at the valve, wherein the valve is activated in response to receiving the activation signal.

17. The method of claim 15 , further comprising disengaging the translating shaft from an actuator prior to moving the translating shaft into the predetermined position.

18. The method of claim 15 , further comprising locking the piston when the translating shaft is in the predetermined position, wherein locking the piston prevents the piston from moving slidably relative to the pressure chamber.

19. The method of claim 15 , further comprising releasing the gas from the pressure chamber thereby allowing the translating shaft to move into a new position.

Assignees

• Boeing Co

Inventors

• Coffman Jeffrey C
• Blanding David E

Classifications

• F15B2211/21

  Systems with pressure sources other than pumps, e.g. with a pyrotechnical charge · CPC title

• F15B15/149

  Fluid interconnections, e.g. fluid connectors, passages · CPC title

• F15B2211/8757

  using redundant components or assemblies · CPC title

• F15B15/19

  Pyrotechnical actuators · CPC title

• B64C13/48

  characterised by the fluid being gaseous · CPC title