Radar updated strapdown inertial midcourse guidance performance analysis for missiles

Bose, Sam C.

doi:10.2514/6.1979-1726

Cited by 6 publications

(2 citation statements)

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“…In this way, the linearization of the force equation involves the small-rotation vectors Á and Ã, as well as errors in specific force measured by accelerometers and errors in angular velocity measured by the gyros both in the body frame. A similar expression of the linearized force equations for the AEM has been derived in [5]. Definitions of the aerodynamic coefficients (dimensionless and dimensional derivatives) are the same as in [10] and [12] and are listed in this work.…”

Section: Introductionmentioning

confidence: 99%

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A strapdown inertial navigation system for the flat-Earth model

Lovren

Pieper

1997

IEEE Trans. Aerosp. Electron. Syst.

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The development of a strapdown inertial navigation system (SINS) for aerodynamically controlled vehicles, which are limited to altitudes below 30 km (that is, a small distance compared with the Earth's radius of about 7000 km), or using the so-called flat-Earth model (FEM), is the principal objective of this work. In dealing with the FEM equations, the north, east, down (NED) frame on the surface of the Earth is taken as an inertial reference frame. Although, this frame is both accelerating and rotating, the accelerations associated with the Earth's rotation are negligible compared with the acceleration that can be produced by a maneuvering aircraft. Also, in this model, the gravity is taken as constant. In developing the SINS for the FEM, the aerodynamic force and moment have dominant roles, depending primarily on such variables as the angle of attack and sideslip, their derivatives, components of the angular velocity of the aircraft, and the control inputs. On the other hand, the SINS deals with such variables as the small-angle rotation vectors. Thus, it was necessary to link both set of variables as state variables of the strapdown FEM, as is done in this work. The developed model is relevant for small (less than 20 ± ) angles of attack and sideslip.

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Section: Introductionmentioning

confidence: 99%

“…The developed INS, for example, [2][3][4][5][6][7][8][9][10][11], are related to the so-called around-Earth model (AEM). That is, they have mostly focused on the effect of the Earth's rotation and the variation of the gravitational field.…”

Section: Introductionmentioning

confidence: 99%

A strapdown inertial navigation system for the flat-Earth model

Lovren

Pieper

1997

IEEE Trans. Aerosp. Electron. Syst.

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Attitude correction algorithm using GPS measurements for flight vehicles

Kim

Kwag

Proceedings. The 21st Digital Avionics Systems Conference

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For flight systems with an on-board seeker the attitude error is the major factor to determine the seeker pointing error at the time of object acquisition. To achieve a desired mission it must be minimized. The proposed algorithm corrects the attitude error in the guidance computer during flight by taking its position and velocity measurements fiom GPS or radar. This is possible since navigator's position and velocity states are correlated with attitude state. Computer simulation is shown to prove the proposed algorithm.

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Design of an optimal midcourse guidance law to enhance the probability of target acquistion

Liu

2015

2015 IEEE International Conference on Mechatronics and Automation (ICMA)

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Radar updated strapdown inertial midcourse guidance performance analysis for missiles

Cited by 6 publications

References 0 publications

A strapdown inertial navigation system for the flat-Earth model

A strapdown inertial navigation system for the flat-Earth model

Attitude correction algorithm using GPS measurements for flight vehicles

Design of an optimal midcourse guidance law to enhance the probability of target acquistion

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