Semi-active laser seeker gyroscope

• US 4,246,801 A
• Filed: 02/01/1979
• Issued: 01/27/1981
• Est. Priority Date: 02/01/1979
• Status: Expired due to Term

• Current Assignee: United States Of America As Represented By The Secretary Of The Army (Government of the United States of America)
• Original Assignee: The United States Of America As Represented By The Secretary Of The Army
• Inventors: Rodgers, Aubrey, Robertson, William G.
• Primary Examiner(s): Bonck, Rodney H.
• Application Number:
  US06/008,464
• Time in Patent Office: 726 Days
• Field of Search: 74/5 R, 74/5.6 A, 74/5.5, 74/5.1, 74/5.12, 74/5.14, 74/5.7, 308/DIG. 1, 244/3.16
• US Class Current: 74/5.7
• CPC Class Codes: F41G 7/2213 maintaining the axis of an orientable seeking head pointed at the target, e.g. target seeking gyro
• CPC Class Codes: F41G 7/226 Semi-active homing systems, i.e. comprising a receiver and involving auxiliary illuminating means, e.g. using auxiliary guiding missiles
• CPC Class Codes: F41G 7/2293 using electromagnetic waves other than radio waves
• CPC Class Codes: G01C 19/20 in fluid
• CPC Class Codes: G01C 19/26 Caging, i.e. immobilising moving parts, e.g. for transport
• CPC Class Codes: Y10T 74/12 Gyroscopes
• CPC Class Codes: Y10T 74/1257 Damping
• CPC Class Codes: Y10T 74/1282 with rotor drive

Abstract

A gyro in which an elastomeric material is used as a spherical bearing suce in an air bearing type gyro to sustain 12,500 g set back acceleration level during gun launch and have the capability of surviving the launch phase in a non-functioning mode and then being operative in post-launch lower-g environments as a stabilized/torquing seeker capable of tracking laser illuminated moving target so as to enable the gyro to be used for guided projectile systems.

Claims

1. In a gyro adapted to withstand a high-g launching environment, the improvement comprising:

a gyro stator having spherical bearing surface means, a gyro rotor rotatably mounted relative to said stator by spherical bearing surface means, one of said spherical bearing surface means being metal and the other being a resilient material bonded to support material, said resilient material having a hardness ratio of about 0.49 to about 0.5 Poisson and a thickness of about 15 to about 30 thousandth'"'"'s of an inch to provide a thickness sufficient to withstand high-g launching environment of about 12,500 g load, and means in said stator for supplying fluid to said spherical bearing surface means to provide an air bearing space therebetween.

2. In a gyro as set forth in claim 1, wherein said resilient material is ethylene-propylene terpolymer.

3. In a gyro as set forth in claim 2, wherein said air bearing space is a gap of about 500 micro-inches to about 1000 micro-inches.

4. In a gyro as set forth in claim 3, wherein bucket means are provided on said rotor and means for injecting fluid onto said buckets are provided for rotating said rotor up to an operating speed.

5. In a gyro as set forth in claim 1, wherein said resilient means is mounted on said rotor and said resilient means has a thickness of about 15 thousandth'"'"'s of an inch.

6. In a gyro as set forth in claim 5, wherein said resilient material is ethylene-propylene terpolymer with a Poisson ratio of about 0.49.

7. In a gyro as set forth in claim 6, wherein said air bearing space is a gap of about 750 micro-inches.