# US 9,040,886 B1 · Adaptive aerodynamic control system for projectile maneuvering

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- Number: US 9,040,886 B1
- Document ID: US9040886B1
- Status: Granted
- Kind: B1
- Application number: 13/889,483
- Filed: 2013-05-08
- Granted: 2015-05-26
- Earliest claimed: 2013-05-08
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Bradley M. Hopping; Craig R. DeMeester
- Web page: https://patentgrep.com/patent/US9040886B1

## CPC

- F42B 10/18: using a longitudinally slidable support member
- F42B 10/12: using fins longitudinally-slidable with respect to the projectile or missile
- F42B 10/64: of fins
- F42B: EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION (explosive compositions C06B; fuzes F42C; blasting F42D)

## Abstract

A projectile control system includes a plurality of fins, a drive mechanism coupled to each of the plurality of fins to enable the plurality of fins to be independently retracted or deployed, and a control mechanism in communication with the drive mechanisms to independently control the deployment or retraction of the plurality of fins. A projectile having the projectile control system and a method of operating a projectile are also described herein.

## Claims

### Claim 1

A projectile control system comprising:
a substructure;
a plurality of fins;
a drive mechanism coupled to each of the plurality of fins to enable the plurality of fins to be independently retracted or deployed, wherein the drive mechanism includes a motor coupled to the substructure, a drive shaft coupled to the motor, and a yoke coupled between a fin of the plurality of fins and the drive shaft, wherein the yoke comprises a first pair of guide slots and the fin comprises a first pair of guide pins configured to be inserted into the first pair of slots, the first pair of slots configured to enable the fin to move radially inward and outward from the drive shaft; and
a control mechanism in communication with the drive mechanisms to independently control the deployment or retraction of the plurality of fins.

### Claim 2 (depends on 1)

The projectile control system of claim 1, wherein the drive mechanism is configured to incrementally deploy or retract the plurality of fins.

### Claim 3 (depends on 1)

The projectile control system of claim 1, wherein the drive mechanism is configured to incrementally deploy or retract the plurality of fins along a predetermined angle.

### Claim 4 (depends on 1)

The projectile control system of claim 1, wherein the drive mechanism is configured to incrementally deploy or retract the plurality of fins along a predetermined angle that is approximately perpendicular to a maximum aero load on the fins.

### Claim 5 (depends on 1)

The projectile control system of claim 1, further comprising a second pair of guide slots and a third pair of guide slots, at least one of the plurality of fins including a second pair of guide pins configured to translate within the second pair of guide slots and a third pair of guide pins configured to translate within the third pair of guide slots.

### Claim 6 (depends on 5)

The projectile control system of claim 5, wherein the second and third pairs of guide slots are disposed at a predetermined angle that is approximately perpendicular to a maximum aero load on the fins.

### Claim 7

A projectile comprising:
a fuselage; and
a projectile control system coupled to the fuselage, the projectile control system including:
a substructure;
a plurality of fins;
a drive mechanism coupled to each of the plurality of fins to enable the plurality of fins to be independently retracted or deployed, the drive mechanism including a motor coupled to the substructure, a drive shaft coupled to the motor, and a yoke coupled between a fin in the plurality of fins and the drive shaft, wherein the yoke comprises a first pair of guide slots and the fin comprises a first pair of guide pins configured to be inserted into the first pair of slots, the first pair of slots configured to enable the fin to move radially inward and outward from the drive shaft; and
a control mechanism in communication with the drive mechanisms to independently control the deployment or retraction of the plurality of fins.

### Claim 8 (depends on 7)

The projectile of claim 7, wherein the drive mechanism is configured to incrementally deploy or retract the plurality of fins along a predetermined angle.

### Claim 9 (depends on 7)

The projectile of claim 7, wherein the drive mechanism is configured to incrementally deploy or retract the plurality of fins along a predetermined angle that is approximately perpendicular to a maximum aero load on the fins.

### Claim 10 (depends on 7)

The projectile of claim 7, wherein the drive shaft is operable in a first direction to deploy the fin and operable in a second opposite direction to retract the fin.

### Claim 11 (depends on 7)

The projectile of claim 7, wherein the projectile control system further comprises a second pair of guide slots and a third pair of guide slots, the fin including a second pair of guide pins configured to translate within the second pair of guide slots and a third pair of guide pins configured to translate within the third pair of guide slots.

### Claim 12 (depends on 11)

The projectile of claim 11, wherein the first and second pairs of guide slots are disposed at a predetermined angle that is approximately perpendicular to a maximum aero load on the fins.