A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted
A guidance method for a powered ballistic missile involves using an onboard computer to numerically simulate the flight path of the missile in real time, using a model with at least 3 degrees of freedom. The results of this simulation are used to update in real time an aim point and/or a predicted intercept point. An iterative process may be used in adjusting the aim point and/or the predicted intercept point. The process may be carried out until a specified number of steps have been completed, and/or until a specified heading error threshold of the aim point and a specified time of flight threshold have been achieved. The use of real time updating of an aim point of the missile advantageously takes into account variations in missile velocity and position due to individual variations in the rocket motor of the missile.
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What is claimed is: 1. A method of onboard guidance of a powered ballistic missile, the method comprising: in real time, during flight of the missile, and using an onboard computer on the missile, numerically simulating a flight path of the missile using a model with at least three degrees of freed
What is claimed is: 1. A method of onboard guidance of a powered ballistic missile, the method comprising: in real time, during flight of the missile, and using an onboard computer on the missile, numerically simulating a flight path of the missile using a model with at least three degrees of freedom; updating one or both of a predicted intercept point of the missile and an aim point of the missile, in real time and using the onboard computer, using results of the numerical simulation; providing guidance information from the onboard computer, based on the numerically simulating and the updating, to a guidance system of the missile; and controlling a course of the missile using the guidance system. 2. The method of claim 1, wherein the updating includes updating both the predicted intercept point and the aim point. 3. The method of claim 2, wherein the updating includes updating the aim point such that a heading error between a trajectory of the missile and the predicted intercept point, is below a predetermined heading error threshold. 4. The method of claim 3, wherein the updating includes updating the predicted intercept point if a calculated predicted time of flight exceeds an initial predicted time of flight by a predetermined time of flight threshold. 5. The method of claim 1, wherein the numerically simulating includes numerically simulating substantially all of the remainder of the flight path, including both a powered phase of flight and a ballistic phase of flight. 6. The method of claim 1, further comprising determining current missile position and current missile velocity from sensors on the missile; wherein the numerically simulating includes using the current missile position and the current missile velocity as inputs. 7. The method of claim 1, further comprising iteratively numerically simulating the flight path and updating one or more of the predicted intercept point of the missile and the aim point of the missile. 8. The method of claim 7, wherein the iteratively numerically simulating and the updating until 1) both a heading error threshold is met and a time of flight threshold is met, or 2) a predetermined number of iterations have been performed without the heading error threshold being met. 9. The method of claim 8, wherein, if the heading error threshold is met and the predicted time of flight threshold is met, the providing information includes sending an updated aim point to the guidance system of the missile. 10. The method of claim 9, further comprising, if the heading error threshold is met and the predicted time of flight threshold is not met, updating the predicted intercept point. 11. The method of claim 8, wherein, if the predetermined number of iterations have been performed without the heading error threshold being met, the providing information includes sending a previous aim point to the guidance system. 12. A method of onboard guidance of a powered ballistic missile, the method comprising: iteratively in real time during flight of the missile, in an onboard computer on board the missile: numerically simulating a flight path of the missile, using a model with at least three degrees of freedom, using current missile position and current missile velocity as inputs, and using an aim point as an input; if a heading error threshold is met and a time of flight threshold is met, forwarding an updated aim point to a guidance system of the missile; and if the heading error is greater than the heading error threshold, and if a predetermined number of iterations have not been performed, selecting a new aim point and performing a new iteration; and controlling a course of the missile using the guidance system; wherein the guidance system uses a received aim point received from the onboard computer in the controlling the course of the missile; and wherein if the heading error threshold is met and the time of flight threshold is met, the received aim point is the undated aim point. 13. The method of claim 12, further comprising, if the heading error threshold is met and the predicted time of flight threshold is not met, updating the predicted intercept point. 14. The method of claim 12, further comprising, if the predetermined number of iterations has been performed, sending a previous aim point to the guidance system of the missile. 15. The method of claim 12, further comprising determining the current missile position and the current missile velocity from sensors on the missile. 16. The method of claim 12, wherein the numerically simulating includes simulating both a powered phase of flight and a ballistic phase of flight. 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. 18. The missile of claim 17, further comprising a guidance system that selectively alters course of the missile; wherein the onboard computer is operatively coupled to the guidance system. 19. The missile of claim 17, wherein the means for numerically simulating includes means for simulating both a powered phase of flight and a ballistic phase of flight.
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