Guided missile control systems

• US 3,883,091 A
• Filed: 07/30/1956
• Issued: 05/13/1975
• Est. Priority Date: 07/30/1956
• Status: Expired due to Term

• Current Assignee: Jacob W. Schaefer
• Original Assignee: Jacob W. Schaefer
• Inventors: Schaefer, Jacob W.
• Primary Examiner(s): Borchelt, Benjamin A.
• Assistant Examiner(s): Webb, Thomas H.
• Application Number:
  US03/600,858
• Time in Patent Office: 6,861 Days
• Field of Search: 244/14,3.13,3.14
• US Class Current: 244/3.13
• CPC Class Codes: F41G 7/30 Command link guidance systems homing F41G7/2206

Abstract

1. In an antiaircraft system, target tracking means for continuously establishing the position of a target aircraft in space, missile tracking means for similarly establishing the position of a missile, computing means responsive to position information from both said target and missile tracking means to produce control signals for said missile to insure interception of the target thereby and means for substituting the target tracking means for said missile tracking means as a source of missile position information for said computing means during the final phases of an engagement.

Claims

1. In an antiaircraft system, target tracking means for continuously establishing the position of a target aircraft in space, missile tracking means for similarly establishing the position of a missile, computing means responsive to position information from both said target and missile tracking means to produce control signals for said missile to insure interception of the target thereby and means for substituting the target tracking means for said missile tracking means as a source of missile position information for said computing means during the final phases of an engagement.

2. In an antiaircraft system a tracking radar for establishing the position of a target aircraft in space, a second tracking radar for similarly establishing the position of a missile launched against said target aircraft, computing means responsive to position information from both of said radars to produce control signals for said missile to insure interception of the target aircraft thereby, means for detecting the approach of the missile to within a predetermined separation from said target aircraft and means responsive to said detecting means for substituting the target tracking radar for said missile tracking radar as a source of missile position information.

3. In an antiaircraft system target tracking means for continuously establishing the azimuth, elevation and range to a target aircraft, missile tracking means for similarly establishing the position of a missile, computing means responsive to the position information from both target and missile tracking means to control the path of said missile to insure interception of the target thereby and means for substituting the target tracking means for said missile tracking means as the source of missile azimuth and elevation information during the final phases of an engagement.

4. In an antiaircraft system a missile tracking radar opErating at a first frequency, a target tracking radar comprising a transmitter operated at a second frequency and receiving means capable of separate response to echo signals of both said first and second frequencies, computing means normally responsive to target and missile position information derived from said first and second radars respectively to control the path of said missile to insure interception of the target thereby and means operative during the final phase of an engagement to substitute as a source of missile position information for said computer the output of the target tracking receiving means produced in response to echoes of said second frequency in place of the output of the missile tracking radar.

5. In an antiaircraft system a target tracking radar for continuously establishing the position of a target aircraft in space, a missile tracking radar for similarly establishing the position of a missile launched against said target aircraft, computing means responsive to position information from both said target and missile tracking radars to produce control signals for said missile to insure interception of the target aircraft thereby, means for determining the angular separation in both elevation and azimuth of the tracking beams of said radars and means operative when both of said angular separations are reduced below predetermined values for substituting the target tracking radar for said missile tracking radar as a source of missile position information for application to said computing means.

6. Apparatus for controlling a guided missile relative to a target comprising missile tracking radar apparatus, target tracking radar apparatus and computer apparatus connected with said respective missile tracking and target tracking radar apparatus, said target tracking radar apparatus comprising means independently receiving radio signals from said missile and said target for simultaneously supplying said computer apparatus with information signals in accordance with the angular position of said missile and the range and angular position of said target.

7. In an antiaircraft system target tracking means for continuously establishing the position of a target aircraft in space, missile tracking means independent thereof for similarly establishing the position of a missile launched against said target aircraft, a computer, means for applying the output of said target tracking means to said computer, means for applying the output of said missile tracking means to said computer after correction for parallax between said missile and target tracking means, said computer being arranged to produce orders for said missile to insure interception of the target aircraft by said missile and means operative when the target aircraft and missile approach one another to within a predetermined separation for substituting the output of said target tracking means as a source of missile position information in place of the missile tracking means and the means for correcting for parallax as to the information for which such substitution is made.