Predictive guidance flight
| DWPI Title: Interceptor for providing predictive guidance during interception of a target, comprises a motor, which generates thrust for the interceptor and potential trajectories are computed at future point in time based on position of interceptor |
| Abstract: The various technologies presented herein relate to utilizing predictive guidance during one or more phases of a trajectory flown by an interceptor during interception with a target. The trajectory of the interceptor comprises an initial phase, a predictive phase, and a final phase. The initial phase includes the launching of the interceptor and can be unguided. The predictive phase directs the interceptor towards the target, wherein the predictive phase utilizes predictive guidance to control the trajectory of the interceptor based upon a predicted location of the target relative to the current locations of the target and the interceptor. During the predictive phase, a motor(s) can be cycled on and off, causing a period(s) where the interceptor is being propelled by the ignited motor, and a period(s) where the interceptor is propelled by its own momentum after cessation of power from the motor, e.g., unpowered flight. |
| Use: Interceptor for providing predictive guidance during interception of a target, such as a meteor, flying object and missile. |
| Advantage: Interceptor can be guided towards the target with higher degree of accuracy. Interceptor uses less fuel and less expensive hardware configurations. |
| Novelty: The interceptor (100) comprises a motor, which generates thrust for the interceptor. A processor with a memory includes instructions. Multiple potential trajectories (200) of the interceptor are computed at a future point in time based on a position (220) of the interceptor and the computed trajectory of the target (210). A zero effort miss value is determined for each of the trajectories. A first control signal is computed for a desired trajectory of the interceptor based upon the zero effort miss values. The first control signal is transmitted to the motor. The first control signal causes the motor to deliver thrust responsive to receipt of the first control signal. The first control signal is configured to cause the interceptor to have the desired trajectory at the future point in time. |
| Filed: 10/29/2015 |
| Application Number: US14927118A |
| Tech ID: SD 13498.0 |
| This invention was made with Government support under Contract No. DE-NA0003525 awarded by the United States Department of Energy/National Nuclear Security Administration. The Government has certain rights in the invention. |
| Data from Derwent World Patents Index, provided by Clarivate All rights reserved. Republication or redistribution of Clarivate content, including by framing or similar means, is prohibited without the prior written consent of Clarivate. Clarivate and its logo, as well as all other trademarks used herein are trademarks of their respective owners and used under license. |