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 Title: |
US6244536:
Air to air homing missile guidance
[ Derwent Title ]
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| Country: |
US United States of America
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| Inventor: |
Cloutier, James R.; Niceville, FL
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| Assignee: |
The United States of America as represented by the Secretary of the Air Force, Washington, DC
other patents from UNITED STATES OF AMERICA, AIR FORCE (597180) (approx. 4,754)
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| Published / Filed: |
2001-06-12
/ 1998-11-23
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| Application Number: |
US1998000197927
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| IPC Code: |
Advanced:
F41G 7/22;
G05D 1/12;
Core:
F41G 7/20;
more...
IPC-7:
F41G 7/36;
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| ECLA Code: |
F41G7/22H; G05D1/12;
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| U.S. Class: |
Current:
244/003.19;
244/003.14;
244/003.15;
342/062;
701/001;
701/004;
Original:
244/003.19;
342/062;
244/003.14;
244/003.15;
701/001;
701/004;
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| Field of Search: |
244/3.1,3.15,3.16-3.22,3.14
342/062
701/001-6,11
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| Government Interest: |
RIGHTS OF THE GOVERNMENT
The invention described herein may be manufactured and used by or for the Government of the United States for all governmental purposes without the payment of any royalty.
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| Priority Number: |
| 1998-11-23 |
US1998000197927 |
| 1997-11-26 |
US1997000066661P |
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| Abstract: |
An air to air homing missile guidance algorithm based on a state-dependent Riccati equation solution of a spherical-based nonlinear intercept representation of the intercept kinematics problem. The achieved algorithm also provides characteristics asymptotically stabilizing the intercept kinematics achieved with the classic proportional navigation or PRONAV intercept algorithm but provides reduced hunting instability and other fuel-consuming and time consuming missile maneuvers. The disclosed algorithm is in the form of four state equations, two equations for an angular acceleration embodiment and two for a linear acceleration embodiment. Each such embodiment includes seven state variables each having a gain coefficient of complex fraction form; each embodiment is additionally refined for differing cross-channel couplings. Each algorithm avoids need to estimate the time-to-go parameter and achieves indirect rather than faulted direct minimization of missile miss distance when provided with accurate target and missile acceleration data.
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| Attorney, Agent or Firm: |
Hollins, Gerald B. ;
Kundert, Thomas L. ;
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| Primary / Asst. Examiners: |
Gregory, Bernarr E.;
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| INPADOC Legal Status: |
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| Parent Case: |
CROSS REFERENCE TO RELATED PATENT DOCUMENTS
This application claims the benefit of Provisional Application 60/066,661, filed Nov. 26, 1997. The application is somewhat related to the previously filed and commonly assigned patent applications "Proportional Guidance (PROGUIDE) and Augmented Proportional Guidance (Augmented Proguide)", AF 21054, Ser. No. 08/233,588, filed Apr. 26, 1994, now U.S. Pat. No. 6,064,332, and "Adaptive Matched Augmented Proportional Navigation", AF 21474, Ser. No. 08/753,754, filed Nov. 29, 1996, an S.I.R. Application.
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| Family: |
None
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First Claim:
Show all 24 claims |
What is claimed is:
1. Missile and target acceleration tolerant, azimuth channel and elevation cross-channel coupling-inclusive air to air homing missile guidance apparatus comprising the combination of:
- an autopilot apparatus operably connected with flight control fin surfaces of said missile;
- sensor elements generating electrical output signals representative of trajectory changes accomplished by said target and said missile;
- missile guidance algorithm apparatus located intermediate said sensor elements and said autopilot apparatus and generating elevation channel and azimuth channel missile command signals, signals responsive to trajectory changes of said missile and said target;
- said missile guidance algorithm apparatus incorporating an embodied mathematical relationship including:
- an azimuth channel line-of-sight rate first azimuth input parameter multiplied by a first azimuth gain determination coefficient;
- an azimuth channel target acceleration second azimuth input parameter multiplied by a second azimuth gain determination coefficient;
- an azimuth channel target elevation acceleration cross-channel third azimuth input parameter multiplied by a third azimuth gain determination coefficient;
- an azimuth channel missile azimuth velocity cross-channel fourth azimuth input parameter multiplied by a fourth azimuth gain determination coefficient;
- an azimuth channel missile elevation velocity fifth azimuth input parameter multiplied by a fifth azimuth gain determination coefficient;
- an azimuth channel missile azimuth acceleration sixth azimuth input parameter multiplied by a sixth azimuth gain determination coefficient;
- an azimuth channel missile elevation acceleration cross-channel seventh azimuth input parameter multiplied by a seventh azimuth gain determination coefficient;
- an elevation channel line-of-sight rate first elevation input parameter multiplied by a first elevation gain determination coefficient;
- an elevation channel target acceleration rate cross-channel second elevation input parameter multiplied by a second elevation gain determination coefficient;
- an elevation channel target elevation acceleration third elevation input parameter multiplied by a third elevation gain determination coefficient;
- an elevation channel missile azimuth velocity cross-channel fourth elevation input parameter multiplied by a fourth elevation gain determination coefficient;
- an elevation channel missile elevation velocity fifth elevation input parameter multiplied by a fifth elevation gain determination coefficient;
- an elevation channel missile elevation velocity change sixth elevation input parameter multiplied by a sixth elevation gain determination coefficient; and
- an elevation channel missile azimuth velocity change seventh cross-channel elevation input parameter multiplied by a seventh elevation gain determination coefficient.
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| Background / Summary: |
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| Drawing Descriptions: |
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| Description: |
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| Forward References: |
Show 12 U.S. patent(s) that reference this one
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