METHOD OF DIRECTING A CLOSE ATTACK MISSILE TO A TARGET
Assignee
Filed
Apr 24, 1974
Granted
Jul 23, 1985
Location
NY US
Abstract
A method of directing a close attack missile launched from a high speed aircraft flying at low altitude with precision accuracy to a target. The method includes three phases: an initial control phase after launching to stabilize and control the missile until the resultant velocity is near zero; a transition pointing phase to automatically reorient the missile after its resultant velocity approaches near zero so that its velocity vector is pointing directly at the target; and a terminal homing phase for automatically guiding the reoriented missile to the target.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 3, 1982
Rescinded
Jan 18, 1985
Duration
2 years, 10 months
Inventor
- 1HERBERT G. DENACI
Record Details
- Patent number
- US 4530270
- Application
- 05463776
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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