Predictive guidance flight

Patent metadata

Field	Value
Publication number	US-10317852-B1
Application number	US-201514927118-A
Country	US
Kind code	B1
Filing date	Oct 29, 2015
Priority date	Oct 29, 2015
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

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.

First claim

What is claimed is:

1. An interceptor comprising:
a motor, wherein the motor generates thrust for the interceptor;
a processor; and
memory that comprises instructions that, when executed by the processor, cause the processor to perform acts comprising:
computing a trajectory of a target at a future point in time;
computing a plurality of potential trajectories of the interceptor at a future point in time based on a position of the interceptor and the computed trajectory of the target;
determining a zero effort miss value for each of the trajectories in the plurality of trajectories;
computing a first control signal for a desired trajectory of the interceptor based upon the zero effort miss values; and
transmitting the first control signal to the motor, wherein the first control signal causes the motor to deliver thrust responsive to receipt of the first control signal, the first control signal configured to cause the interceptor to have the desired trajectory at the future point in time.

2. The interceptor of claim 1 , wherein the desired trajectory is one of the plurality of trajectories, the acts further comprising:
comparing the respective zero effort miss values for the trajectories in the plurality of trajectories;
determining, based upon the zero effort miss value comparisons, the desired trajectory has a lowest zero effort miss value; and
selecting the desired trajectory for computation of the first control signal.

3. The interceptor of claim 1 , wherein the desired trajectory is a zero effort miss trajectory.

4. The interceptor of claim 3 , wherein the desired trajectory is computed during a predictive phase portion of a trajectory being traversed by the interceptor, wherein the predictive phase is subsequent to an initial phase of the traversed trajectory and is prior to a final phase of the traversed trajectory.

5. The interceptor of claim 4 , the acts further comprising:
terminating control of the interceptor with the first control signal at a transition from the predictive phase to the final phase.

6. The interceptor of claim 5 , the acts further comprising:
generating a second control signal to control flight of the interceptor during the final phase; and
transmitting the second control signal to the motor, wherein the second control signal causes the motor to deliver thrust responsive to receipt of the second control signal, the second control signal configured to cause the interceptor to intercept the target.

7. The interceptor of claim 6 , wherein the motor comprises at least a first stage motor and a second stage motor, wherein the first control signal is transmitted to the first stage motor and the second control signal is transmitted to the second stage motor.

8. The interceptor of claim 4 , wherein a portion of the desired trajectory includes a portion of unpowered flight.

9. The interceptor of claim 4 , wherein the acts further comprising:
determining a distance between the interceptor and the target;
comparing the distance with an operational range of a sensor located on the interceptor; and
determining, based upon comparison of the determined distance and the operational range of the sensor, that the distance between the interceptor and the target has a magnitude enabling the predictive phase to end and the final phase to be initiated, wherein during the final phase, guidance of the interceptor to the target is based upon a signal generated by the sensor, wherein the sensor signal is a direction to the target.

10. The interceptor of claim 4 , wherein during the predictive phase the processor is operating with a first sample rate and during the final phase the processor is operating with a second sample rate, wherein the first sample rate is slower than the second sample rate.

11. The interceptor of claim 9 , wherein the first sample rate is about 1 Hertz and the second sample rate is about 100-200 Hertz.

12. The interceptor of claim 1 , the acts further comprising receiving a navigation signal from a remotely located radar system, wherein the navigation signal includes at least one of a current position of the target or a current position of the interceptor.

13. A method comprising:
computing a trajectory of a target at a future point in time, wherein the target is to be intercepted by an interceptor;
computing a plurality of potential trajectories of the interceptor at a future point in time based on a position of the interceptor and the computed trajectory of the target;
determining a zero effort miss value for each of the trajectories in the plurality of trajectories;
computing a first control signal for a desired trajectory of the interceptor based upon the zero effort miss values; and
transmitting the first control signal to a motor, wherein the first control signal causes the motor to deliver thrust to the interceptor responsive to receipt of the first control signal, the first control signal configured to cause the interceptor to have the desired trajectory at the future point in time.

14. The method of claim 13 , wherein the desired trajectory is one of the plurality of trajectories, the method further comprising:
comparing the respective zero effort miss values for the trajectories in the plurality of trajectories;
determining, based upon the zero effort miss value comparisons, the desired trajectory has the lowest zero effort miss value; and
selecting the desired trajectory for computation of the first control signal.

15. The method of claim 13 , wherein the desired trajectory is a zero effort miss trajectory.

16. The method of claim 15 , wherein the desired trajectory is computed during a predictive phase portion of a trajectory being traversed by the interceptor, wherein the predictive phase is subsequent to an initial phase of the traversed trajectory and is prior to a final phase of the traversed trajectory.

17. The method of claim 16 , further comprising:
determining a distance between the interceptor and the target;
comparing the distance with an operational range of a sensor located on the interceptor;
determining, based upon comparison of the determined distance and the operational range of the sensor, that the distance between the interceptor and the target has a magnitude enabling the predictive phase to end and the final phase to be initiated;
generating a second control signal, the second control signal generated in response to determining the final phase is to be initiated, the second control signal is generated based upon a direction to the target provided by the sensor; and
transmitting the second control signal to the motor, wherein the second control signal causes the motor to deliver thrust responsive to receipt of the second control signal, the second control signal configured to cause the interceptor to intercept the target.

18. The method of claim 16 , wherein during the predictive phase a processor is operating with a first sample rate to compute the desired trajectory of the interceptor, and during the final phase the processor is operating with a second sample rate, wherein the first sample rate is slower than the second sample rate.

19. The method of claim 18 , wherein the first sample rate is about 1 Hertz and the second sample rate is about 100-200 Hertz.

Assignees

• Nat Tech & Eng Solutions Sandia Llc

Inventors

• Spooner Jeffrey T

Classifications

• G05B13/026 Primary

  using a predictor · CPC title

• F42B15/01 Primary

  Arrangements thereon for guidance or control ({steering arrangements F42B10/60}; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]) · CPC title

• F42B15/10

  Missiles having a trajectory only in the air · CPC title