RETRACTABLE STABILIZER FINS AND DRAG BRAKES FOR MISSILES

• US 3,643,599 A
• Filed: 07/22/1968
• Issued: 02/22/1972
• Est. Priority Date: 07/22/1968
• Status: Expired due to Term

• Current Assignee: Henry O. Hubich
• Original Assignee: Henry O. Hubich
• Inventors: Hubich, Henry O.
• Primary Examiner(s): Engle, Samuel W.
• Application Number:
  US04/746,583
• Time in Patent Office: 1,310 Days
• Field of Search: 244/3.27,3.28,17.13,17.17,138,138.1 102/4,34.1
• US Class Current: 102/388
• CPC Class Codes: F42B 10/14 using fins spread or deployed after launch, e.g. after leaving the barrel

Abstract

Retractable stabilizing fins and drag brake apparatus having coactive connection between the stabilizing fins and drag brakes. The stabilizing fins when deployed to a position perpendicular to the missile axis present an edge to air stream. The drag brakes when deployed to a position perpendicular to the missile axis produce aerodynamic drag as well as rotate the stabilizing fins to a position to produce aerodynamic drag.

Claims

1. Stabilizing and drag apparatus for a missile comprising:

a plurality of drag brakes, each drag brake being pivotally mounted on the tail section of the missile for rotation from a first position to a second position about an axis perpendicular to the missile axis and approximately tangent to the surface thereof;

each of sad drag brakes having a first position essentially alongside a longitudinal surface portion of the missile;

a second position essentially radially outward from the tail section of the missile for producing aerodynamic drag; and

a stabilizer fin pivotally mounted on each drag brake for rotation about an axis perpendicular to the axis of rotation of said drag brake.

2. The apparatus of claim 1 further comprising:

drag brake release means for releasably securing said drag brakes in said first position alongside the longitudinal axis of the missile.

3. The apparatus of claim 2 further comprising stabilizer fin release means for releasably securing said stabilizer fins along and overlying said drag brakes.

4. The apparatus of claim 3 further comprising a spring biasing said drag fins outwardly from the body of said missile when in the first position.

5. The apparatus of claim 4 further comprising a spring attached between said stabilizer fin and drag brake biasing said stabilizer fin into a position perpendicular to the missile body.