Micromechanical inertial guidance navigation and control systems in gun launched projectiles

Sitomer, James; Kourepenis, A.; Connelly, J.

doi:10.2514/6.1999-4074

Cited by 6 publications

(7 citation statements)

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“…The multiphase optimal control problem (denoted by P) corresponding to the multiphase trajectory optimization problem of a gun-launched glide guided projectile will now be stated formally. Using the trajectory phase division given in the previous subsection, the control variables (t), (t) and parameters (t 0 ), t i , t c , and t g that minimize the objective function of equation (10), and satisfy the dynamic constraint of equation 1, boundary constraints of equations (3) and (4), path constraints of equations (5) to (8), and interior point constraints of equation 9need to be determined.…”

Section: Optimal Control Problemmentioning

confidence: 99%

“…The groundbreaking work of adding movable canards to extend the range of the projectile was conducted by Costello, 1,2 which showed that the range of a fin stabilized projectile can be significantly increased using canards to generate additional vertical force on the projectile. Sitomer et al 3 described the application of micromechanical inertial instruments to Navy and Army gun-launched guided projectiles. Regarding range extension, many articles have proposed moveable canards to extend the range of indirect fire munitions using both the projectile body and canard lift introduced by Costello.…”

Section: Introductionmentioning

confidence: 99%

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Multiphase trajectory optimization for gun-launched glide guided projectiles

Chen

Wang²,

Chang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, an approach that considered both the continuous and discrete variables using the Gauss pseudospectral method is presented for multiphase trajectory optimization of gun-launched glide guided projectiles. The entire projectile trajectory is divided into four flight phases that connect to each other sequentially to ensure continuity. Continuous variables are utilized to describe the projectile's state and control. Meanwhile, discrete variables are proposed to express the initial flight path angle and switching times between different flight phases. The trajectory optimization problem is posed as a constrained multiphase nonlinear optimal control problem, which is then transcribed into a nonlinear programming problem using the Gauss pseudospectral method and is finally solved using the interior point algorithm. Simulation results demonstrate the feasibility and effectiveness of this approach, as well as a detailed analysis of the key features of the trajectory parameters.

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Section: Optimal Control Problemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multiphase trajectory optimization for gun-launched glide guided projectiles

Chen

Wang²,

Chang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…To meet this requirement, existing gun-lunched artillery projectile should possess high precise guidance and navigation abilities, which mean better performance of inertial navigation kit is needed. Known to all, satellite positioning and angular rate gyro are widely used in navigation field to measure attitude of guided projectile, thus gyro's own precision has immensely influence on guided weapon [1].…”

Section: Introductionmentioning

confidence: 99%

MEMS Gyro Random Error On-line Modeling Based on Recursive Least-Squares Method of System Identification

Wang¹,

Keyu²,

Shi³

et al. 2016

Proceedings of the 2016 2nd Workshop on Advanced Research and Technology in Industry Applications

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To develop the guided projectile with higher hit precision, promotes gyro's performance has immensely affection on trajectory measurement. According to the difficulty in method of MEMS angular rate gyro random error on-line modeling, this paper proposes a new algorithm of recursive least-squares method that used in the system identification processing. With this recursive least-squares method, a few known gyro output data are used to roughly estimate system parameters, then newly obtained data are added to the measurement formula using the recursive algorithm in order to make estimated parameters approach to its truth-value. This study indicates that the residual error between outputs of gyro random error model and outputs of real gyro highly approximates white noise, which means the error model accurately describes statistical features of gyro random error and the recursive algorithm realizes on-line modeling.

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“…[1][2][3][4] Integrating six different degree of freedom inertial sensors usually including the x-axis, y-axis, z-axis accelerometer and gyroscope on the carrier to form one inertial measurement unit (IMU), could provide the kinetic information of the moving carrier for the further attitude measurement. [5][6][7][8][9] Thus the inertial measurement unit could find many applications in the fields of automotive, robotics and consumer electronics.…”

Section: Introductionmentioning

confidence: 99%

“…The present commercial products usually take this way to realize the integration. [5,6] However, the mechanical assembling could limit the batch fabrication of the integrated sensor. Moreover, it's very difficult to reach the exact mutual orthogonality between every two sensors' input axes.…”

Section: Introductionmentioning

confidence: 99%

One Bulk Micromachined Single-Chip Inertial Measurement Unit

Chang

Yuan

Cui

et al. 2006

2006 5th IEEE Conference on Sensors

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This paper presented one single chip micro inertial measurement unit based on ordinary bulk micromachining process. The sample chip integrated six inertial sensors, i.e. the x-axis, y-axis and z-axis accelerometers and gyroscopes, on one area which was smaller than nine square millimeters on the silicon wafer. The test results showed that the bias stability of these gyroscopes was at least better than 3753 degree per hour and the sensitivity was bigger than 2.7 millivolt per deg/sec. And the minimal mechanical sensitivity of the accelerometers was about 19.1 millivolt per gravity acceleration. The experiments prove the feasibility of the simple integration method, which could greatly reduce the size of inertial measurement unit.I.

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Micromechanical inertial guidance navigation and control systems in gun launched projectiles

Cited by 6 publications

References 0 publications

Multiphase trajectory optimization for gun-launched glide guided projectiles

Multiphase trajectory optimization for gun-launched glide guided projectiles

MEMS Gyro Random Error On-line Modeling Based on Recursive Least-Squares Method of System Identification

One Bulk Micromachined Single-Chip Inertial Measurement Unit

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