Automated determination of rocket configuration

Patent metadata

Field	Value
Publication number	US-10371494-B2
Application number	US-201615357407-A
Country	US
Kind code	B2
Filing date	Nov 21, 2016
Priority date	Nov 21, 2016
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

Techniques are provided for automated determination of a rocket configuration based on acceleration during rocket motor burn-out and temperature. The rocket configuration is associated with a class of warhead affixed to the rocket. A methodology implementing the techniques according to an embodiment includes measuring the acceleration of the rocket over a period of time associated with the flight of the rocket. The method also includes calculating an acceleration difference between the measured acceleration associated with the start of rocket motor burn-out and the measured acceleration associated with the end of rocket motor burn-out. The method further includes measuring an internal temperature of the rocket and selecting a delta acceleration threshold based on the measured temperature. The method further includes comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket configuration. The estimated rocket configuration is used by guidance and control circuitry to select autopilot parameters.

First claim

What is claimed is:

1. A processor-implemented method for determination of a rocket or missile configuration, the method comprising:
obtaining, by a processor, acceleration of a rocket or missile over a period of time during flight of the rocket or missile;
calculating, by the processor during the flight, an acceleration difference between the obtained acceleration associated with a start of motor burn-out and the obtained acceleration associated with an end of motor burn-out;
measuring, by the processor during the flight, an internal temperature of the rocket or missile;
selecting, by the processor during the flight, a delta acceleration threshold based on the measured internal temperature;
comparing, by the processor during the flight, the calculated acceleration difference to the selected delta acceleration threshold to estimate the rocket or missile configuration; and
providing the estimated rocket or missile configuration to guidance and control circuitry of the rocket or missile to enable selection of autopilot parameters.

2. The method of claim 1 , wherein the calculation of acceleration difference comprises:
determining a maximum of the obtained accelerations;
determining a minimum of the obtained accelerations; and
calculating the acceleration difference between the maximum acceleration and the minimum acceleration.

3. The method of claim 2 , wherein the minimum of the obtained accelerations occurs within a selected time period after the maximum acceleration.

4. The method of claim 1 , wherein the calculation of acceleration difference comprises:
calculating a first derivative of the obtained acceleration to generate a jerk signal;
determining a first time associated with the start of motor burn-out based on the jerk signal decreasing below a selected jerk threshold;
determining a second time associated with the end of motor burn-out based on the jerk signal increasing above the selected jerk threshold; and
integrating the jerk signal between the first time and the second time to estimate the acceleration difference.

5. The method of claim 1 , wherein the rocket or missile configuration is associated with a class of warhead affixed to the rocket or missile.

6. The method of claim 1 , wherein the temperature measurement is associated with an internal temperature of a guidance and control circuit module of the rocket or missile.

7. A system for determination of a rocket or missile configuration, the system comprising:
an accelerometer to measure acceleration of a rocket or missile over a period of time during flight of the rocket or missile;
a delta calculation circuit to calculate an acceleration difference between the measured acceleration associated with a start of motor burn-out and the measured acceleration associated with an end of motor burn-out;
a temperature sensor to measure an internal temperature of the rocket or missile;
a threshold selection circuit to select a delta acceleration threshold based on the measured internal temperature;
a comparator circuit to compare the calculated acceleration difference to the selected delta acceleration threshold to estimate the rocket or missile configuration; and
a guidance and control circuit configured to receive the estimated rocket or missile configuration to enable selection of autopilot parameters.

8. The system of claim 7 , further comprising a latching circuit configured to determine a maximum of the measured accelerations and a minimum of the measured accelerations, wherein the delta calculation circuit is further to calculate the acceleration difference between the maximum acceleration and the minimum acceleration.

9. The system of claim 8 , wherein the minimum of the measured accelerations occurs within a selected time period after the maximum acceleration.

10. The system of claim 7 , further comprising:
a differentiator circuit configured to calculate a first derivative of the measured acceleration to generate a jerk signal;
a trigger circuit configured to determine a first time associated with the start of motor burn-out based on the jerk signal decreasing below a selected jerk threshold;
the trigger circuit further configured to determine a second time associated with the end of motor burn-out based on the jerk signal increasing above the selected jerk threshold; and
an integration circuit configured to integrate the jerk signal between the first time and the second time to estimate the acceleration difference.

11. The system of claim 7 , wherein the rocket or missile configuration is associated with a class of warhead affixed to the rocket or missile.

12. The system of claim 7 , wherein the temperature sensor is configured to obtain the internal temperature measurement of a guidance and control circuit module of the rocket or missile.

13. At least one non-transitory computer readable storage medium having instructions encoded thereon that, when executed by one or more processors, result in the following operations for determination of a rocket or missile configuration, the operations comprising:
measuring acceleration of a rocket or missile over a period of time during flight of the rocket or missile;
calculating an acceleration difference between the measured acceleration associated with a start of motor burn-out and the measured acceleration associated with an end of motor burn-out;
measuring an internal temperature of the rocket or missile;
selecting a delta acceleration threshold based on the measured internal temperature;
comparing the calculated acceleration difference to the selected delta acceleration threshold, to estimate the rocket or missile configuration; and
providing the estimated rocket or missile configuration to guidance and control circuitry of the rocket or missile to enable selection of autopilot parameters.

14. The computer readable storage medium of claim 13 , wherein the calculation of acceleration difference further comprises the operations of:
determining a maximum of the measured accelerations;
determining a minimum of the measured accelerations; and
calculating the acceleration difference between the maximum acceleration and the minimum acceleration.

15. The computer readable storage medium of claim 14 , wherein the minimum of the measured accelerations occurs within a selected time period after the maximum acceleration.

16. The computer readable storage medium of claim 13 , wherein the calculation of acceleration difference further comprises the operations of:
calculating a first derivative of the measured acceleration to generate a jerk signal;
determining a first time associated with the start of motor burn-out based on the jerk signal decreasing below a selected jerk threshold;
determining a second time associated with the end of motor burn-out based on the jerk signal increasing above the selected jerk threshold; and
integrating the jerk signal between the first time and the second time to estimate the acceleration difference.

17. The computer readable storage medium of claim 13 , wherein the rocket or missile configuration is associated with a class of warhead affixed to the rocket or missile.

Assignees

• Bae Sys Inf & Elect Sys Integ

Inventors

• Schorr David J
• Damiano Matthew F
• Steenson Jr James H

Classifications

• B64U70/20

  for releasing or capturing UAVs in flight by another aircraft · CPC title

• G06F30/17

  Mechanical parametric or variational design · CPC title

• G06F2111/10

  Numerical modelling · CPC title

• F42B15/08

  for carrying measuring instruments; {Arrangements for mounting sensitive cargo within a projectile}(adaptations for meteorology G01W1/08); {Arrangements for acoustic sensitive cargo within a projectile} · CPC title

• F42B35/00 Primary

  Testing or checking of ammunition {(apparatus for measuring the energy of projectiles G01L5/14)} · CPC title