| US 7,566,026 B2 | ||
| Onboard guidance method for ballistic missiles | ||
| Frank C. Lam, Tucson, Ariz. (US); and Gerald C. Chiang, Suhuarita, Ariz. (US) | ||
| Assigned to Raytheon Company, Waltham, Mass. (US) | ||
| Filed on Mar. 29, 2006, as Appl. No. 11/392,131. | ||
| Prior Publication US 2009/0127377 A1, May 21, 2009 | ||
| Int. Cl. F42B 15/01 (2006.01); F42B 15/10 (2006.01); G06F 19/00 (2006.01); F42B 15/00 (2006.01) | ||
| U.S. Cl. 244—3.15 [244/3.1; 244/3.16; 244/3.19] | 19 Claims |
| 17. A ballistic missile comprising:
an inertial measurement unit that determines position and velocity of the missile in real time; and
an onboard computer operatively coupled to the inertial measurement unit, wherein the onboard computer includes:
means for numerically simulating in real time a flight path of the missile using a model with at least three degrees of freedom;
and
means for updating in real time a predicted intercept point of the missile and an aim point of the missile.
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