Automatic fin deployment mechanism

• US 4,884,766 A
• Filed: 05/25/1988
• Issued: 12/05/1989
• Est. Priority Date: 05/25/1988
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Steinmetz, Harold F., Wisdom, Gerald H.
• Primary Examiner(s): Kyle, Deborah L.
• Assistant Examiner(s): Carone, Michael J.
• Application Number:
  US07/198,279
• Time in Patent Office: 559 Days
• Field of Search: 244/3.27, 244/3.28, 244/3.29, 244/3.3, 244/49
• US Class Current: 244/3.27
• CPC Class Codes: F42B 10/20 deployed by combustion gas pressure, or by pneumatic or hydraulic forces

Abstract

The invention comprises a fin fold mechanism for extending a moveable fin from an air flight vehicle wherein the fin deployment mechanism is fixably housed within the vehicle. A pyrotechnic gas generation actuation means is positioned within the fin extension mechanism in order to actuate a drive mechanism comprising a drive piston that pivots the fin into its extended position. Clutch means is connected to the piston for transferring movement from the piston to the moveable fin. A retraction mechanism is also provided for disconnecting the clutch means from the fin after the fin is fully extended; this allows controlled axial rotation of the fin.

Claims

1. A fin fold mechanism for extending a moveable fin from an air flight vehicle housing comprising:

a mechanism housing fixidly positioned within said air flight vehicle;

an actuation means positioned within said mechanism housing;

a drive means connected for actuation to said actuation means and also positioned within said mechanism housing;

clutch means connected to said drive means for transferring rotary movement from said drive means to the moveable fin; and

a retraction mechanism for disconnecting said clutch means from the fin after the moveable fin is fully extended.

2. The fin fold mechanism of claim 1 wherein the actuation means comprises a pyrotechnic gas generator.

3. The fin fold mechanism of claim 2 further comprising a first locking means for locking the moveable fin in a stored position;

and

a second locking means for locking the moveable fin in an extended position.

4. The fin fold mechanism of claim 3 wherein said gas generator is interconnected with said first locking means so that gas from said gas generator releases said first locking means when said gas generator is activated.

5. The fin fold mechanism of claim 3 wherein said second locking means is spring loaded to lock said moveable fin in an upright position while still allowing controlled fin rotation.

6. The fin fold mechanism of claim 1 wherein said drive means further comprises a piston, with internal and external splines, seated within said mechanism housing, said piston engaging said actuation means and said clutch means in order to deliver force from said actuation means to said clutch means.

7. The fin fold mechanism of claim 6 wherein a torque shaft is interposed between said piston and said clutch means.

8. The fin fold mechanism of claim 7 wherein said outer piston splines interlock with spiral inner grooves in said mechanism housing and said inner piston splines interlock with straight grooves on said torque shaft in order to cause rotation said torque shaft and said clutch which results in the extension of said fin.

9. The fin fold mechanism of claim 7 further comprising damping means for braking piston motion in order to prevent damage to said fin during its extension.

10. The fin fold mechansim of claim 7 wherein said retraction mechanism is actuated by full rotation of said piston.

11. A fin fold mechanism for extending a moveable fin from

a flight vehicle housing comprising:

a first locking means for locking the moveable fin in a stored position;

actuation means for activating the fin fold mechanism and releasing said first locking means;

a second locking means for locking the moveable fin in an extended position;

retraction means for disengaging said fin fold mechanism from said moveable fin in order to permit axial rotation of said fin.

12. The fin fold mechanism of claim 11 wherein the fin fold mechanism is positioned within the flight vehicle housing.

13. The fin fold mechanism of claim 11 wherein the actuation means comprises a pyrotechnic gas generator.

14. The fin fold mechanism of claim 13 wherein said gas generator is interconnected with said first locking means so that gas from said gas generator acts to release said first locking means when said gas generator is activated.

15. The fin fold mechanism of claim 11 wherein said second locking means is spring loaded to operate when said fin reaches its fully extended position.

16. The fin fold mechanism of claim 11 wherein said fin fold mechanism further comprises a piston with internal and external splines seated within a housing, said piston engaging said actuation means and said clutch means in order to deliver force from said actuation means to said clutch means.

17. The fin fold mechanism of claim 16 wherein a torque shaft is interposed between said piston and said clutch means.

18. The fin fold mechanism of claim 17 wherein said outer piston splines interlock with spiral inner grooves in said housing and said inner piston splines interlock with straight grooves on said torque shaft so that said piston rotates as it is driven forward by said actuation means which results in rotational movement of said torque shaft and said clutch that is transferred to said fin in order to extend said fin.

19. The fin fold mechanism of claim 16 further comprising damping means for braking piston motion in order to prevent damage to said fin during its extension.

20. The fin fold mechanism of claim 16 further comprising retraction means for disconnecting said clutch from said fin after said fin has been extended.