[특허]Projectile guidance with accelerometers and a GPS receiver

Northrop Grumman Corporation

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Projectile guidance with accelerometers and a GPS receiver

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41G-007/00 F42B-015/01
미국특허분류(USC)	244/003.15; 244/003.1; 244/003.19; 342/357.01; 342/357.06; 342/357.08; 701/207; 701/213
출원번호	US-0402644 (2003-03-28)
발명자 / 주소	Ratkovic, Joseph A. Brockstein, Allan J. Buchler, Robert J.
출원인 / 주소	Northrop Grumman Corporation
인용정보	피인용 횟수 : 22 인용 특허 : 13

초록
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A projectile guidance system without gyros in which the projectile has an orthogonal body coordinate system. The projectile has a triax of accelerometers providing x, y and z acceleration data measured along the x, y and z axes respectively. A GPS antenna and receiver means provides onboard GPS position and velocity data in earth referenced navigational coordinates. A computer and program means stores and accesses time indexed GPS position and GPS velocity data and transforms x, y and z axis acceleration data from body to navigation coordinates. The program means is responsive to corresponding time indexed acceleration data and to GPS velocity and position data for calculating and outputting an estimated projectile roll, pitch and yaw angle via optimal smoothing techniques with respect to local level for each time index iteration of present position to a flight control system, which actuates a divert propulsion system for guiding the projectile to a predetermined location.

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1. A projectile guidance system with accelerometers and a GPS receiver comprising:a projectile having a triax of accelerometers mounted in the projectile and providing roll, pitch and azimuth axis acceleration data; a GPS antenna and receiver means mounted in the projectile for providing and updating present position data; a computer and memory mounted in the projectile and executing a guidance program; and divert propulsion means; wherein the guidance program is responsive to the roll, pitch and azimuth axis acceleration data and to the sampled present position data for calculating and outputting time indexed roll, pitch and azimuth angles, time indexed present position and velocity to a flight control system for guiding the projectile to a predetermined target location; and wherein the divert propulsion means are responsive to the guidance program. 2. The projectile guidance system of claim 1 wherein said divert propulsion means comprises one or more control surfaces located exterior to the projectile.3. The projectile guidance system of claim 1 wherein said divert propulsion means is configured to change the attitude of the projectile in response to a command from the guidance program.4. The projectile guidance system of claim 1 wherein said divert propulsion means is configured to change the flight path of the projectile in response to a command from the guidance program.5. The projectile guidance system of claim 1 wherein said divert propulsion means is positioned interior to the projectile.6. The projectile guidance system of claim 5 wherein said divert propulsion means comprises gas metering means.7. The projectile guidance system of claim 6 wherein said divert propulsion means comprises gas directing means.8. The projectile guidance system of claim 7 wherein said gas directing means comprises a filter.9. The projectile guidance system of claim 6 wherein said divert propulsion means comprises a chamber for storing compressed gas and means for supplying compressed gas to said chamber.10. The projectile guidance system of claim 9 wherein said means for supplying compressed gas comprising a supply port positioned to receive high pressure launch gasses during launch of the projectile, said supply port configured to permit entry of launch gasses during launch and to retain said launch gasses after launch.11. The projectile guidance system of claim 10 wherein said gas metering means comprises a filter.12. The projectile guidance system of claim 9 wherein said means for supplying compressed gas comprises a supply port positioned to receive high pressure gasses prior to launch of the projectile, said supply port configured to permit entry of high pressure gasses prior to launch and to retain said high pressure gasses after launch.13. The projectile guidance system of claim 9 wherein said means for supplying compressed gas comprises a combustion apparatus for combusting solid propellant.14. The projectile guidance system of claim 9 wherein said means for supplying compressed gas comprises a combustion apparatus for combusting liquid propellant.15. The projectile guidance system of claim 9 wherein said means for supplying compressed gas comprises a combustion apparatus for combusting a combination of liquid propellant and solid propellant.16. The projectile guidance system of claim 5 wherein said divert propulsion means comprises one or more supply ports located on a leading portion of the projectile.17. The projectile guidance system of claim 5 wherein said divert propulsion means comprises one or more exit ports located on a side of the projectile.18. The projectile guidance system of claim 5 wherein said divert propulsion means comprises one or more exit ports located on a trailing portion of the projectile.19. A projectile guidance system without gyros comprising:the projectile having at least a triax of accelerometers comprising an x accelerometer for providing x-axis acceleration data measured along the x-axis, an accelerometer for providing y-axis acceleration data measured along the y-axis and a z-accelerometer for providing z-axis acceleration data measured along the z-axis, a GPS antenna and receiver means for providing onboard GPS position and GPS velocity data in earth referenced navigational coordinates, a computer and memory and program means for storing and accessing time indexed GPS position and GPS velocity data and for transforming the x, y and z axis acceleration data from body to navigation coordinates, the acceleration data being arrayed and having time indexes common with the GPS position and velocity data; and divert propulsion responsive to the program means; wherein the program means is responsive to correcting time indexed acceleration data and to GPS velosity and position data for calculating and outputting an estimated projectile roll, pitch and yaw angle with respect to local level for each time index iteration of present position, velocity and acceleration data to a flight control system for guiding the projectile to a predetermined target location. 20. A projectile guidance system process for the guidance of a vehicle or projectile without gyros, the vehicle having been launched and having an orthogonal coordinate system with a longitudinal or x-axis for roll measurement, a y-axis for pitch measurement, and a z-axis for yaw measurement, a triax of accelerometers outputting x, y and z axis acceleration, and a GPS antenna and receiver means for providing GPS position and GPS velocity data in earth referenced navigational coordinates, the projectile guidance system process comprising the steps of:receiving, indexing and storing GPS position and velocity data with concurrent x, y and z axis acceleration data with a computer and memory means executing a program to calculate a trajectory for the vehicle as a function of a set of state equations, the program converting the x, y and z axis acceleration data to a local level navigational reference system, the program then solving a set of time indexed state equations to update the system's estimated state, and then computing a time indexed pitch, roll and yaw angle in locally level coordinates, the program then outputting the time indexed pitch, roll yaw angle in locally level coordinates with a corresponding time indexed present position to a flight control system for guiding the projectile to a destination; the flight control system controlling divert propulsion means to guide the vehicle or projectile.

이 특허에 인용된 특허 (13)

이 특허를 인용한 특허 피인용횟수: 22

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Projectile guidance with accelerometers and a GPS receiver

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이 특허를 인용한 특허 피인용횟수: 22

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Projectile guidance with accelerometers and a GPS receiver

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이 특허에 인용된 특허 (13)

이 특허를 인용한 특허 피인용횟수: 22

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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