# US 10,371,494 B2 · Automated determination of rocket configuration > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,371,494 B2 - Document ID: US10371494B2 - Status: Granted - Kind: B2 - Application number: 15/357,407 - Filed: 2016-11-21 - Published: 2018-05-24 - Granted: 2019-08-06 - Earliest claimed: 2016-11-21 - Assignees: BAE Systems Information and Electronic Systems Integration Inc. - Applicants: BAE SYSTEMS Information and Electronic Systems Integration Inc. - Inventors: David J. Schorr; Matthew F. Damiano; James H. Steenson, Jr. - Web page: https://patentgrep.com/patent/US10371494B2 ## CPC - F42B 15/01: 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]) - F41G 7/00: Direction control systems for self-propelled missiles (flight control B64C, G05D1/00 {; counter-measures against guided missiles F41H11/02; spin-stabilised missiles F42B10/26}; self-propelled or guided missiles having direction control systems only installed aboard F42B15/01; rocket torpedoes F42B17/00; marine torpedoes or sea-mines having self-propulsion means F42B19/00; locating by use of radio or other waves G01S; computing aspects G06) - F41G 7/001: {Devices or systems for testing or checking} - F42B 15/08: 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} - F42B 35/00: Testing or checking of ammunition {(apparatus for measuring the energy of projectiles G01L5/14)} - G06F 30/17: Mechanical parametric or variational design - B64U 70/20: for releasing or capturing UAVs in flight by another aircraft - G06F 2111/10: Numerical modelling - F42B: EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION (explosive compositions C06B; fuzes F42C; blasting F42D) - F41G: WEAPON SIGHTS; AIMING (optical aspects thereof G02B) - G06F: ELECTRIC DIGITAL DATA PROCESSING (computer systems based on specific computational models G06N) - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 2) The method of claim 2, wherein the minimum of the obtained accelerations occurs within a selected time period after the maximum acceleration. ### Claim 4 (depends on 1) 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. ### Claim 5 (depends on 1) The method of claim 1, wherein the rocket or missile configuration is associated with a class of warhead affixed to the rocket or missile. ### Claim 6 (depends on 1) 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. ### Claim 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. ### Claim 8 (depends on 7) 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. ### Claim 9 (depends on 8) The system of claim 8, wherein the minimum of the measured accelerations occurs within a selected time period after the maximum acceleration. ### Claim 10 (depends on 7) 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. ### Claim 11 (depends on 7) The system of claim 7, wherein the rocket or missile configuration is associated with a class of warhead affixed to the rocket or missile. ### Claim 12 (depends on 7) 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. ### Claim 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. ### Claim 14 (depends on 13) 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. ### Claim 15 (depends on 14) 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. ### Claim 16 (depends on 13) 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. ### Claim 17 (depends on 13) 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.