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Noise-Induced Miss Distance Analysis of First-Order Explicit Guidance Law

Document Type : Original Article

Authors

Tarbiat Modares University

Abstract

This study presents the miss distance analysis of the first-order explicit guidance law due to seeker noise using the adjoint method. For this purpose, linearized equations are utillized and the adjoint model is developed. Then the first-order equations are obtained and converted into nondimensional ones. The analysis is carried out for different values of the power of the alpha function, defined as the time decrease rate of the zero-effort miss distance to unit control input. The unity power gives the first-order optimal guidance strategy, minimizing the integral of the square of the commanded acceleration during the total flight time.The seeker and control system is assumed as a fifth-order binomial transfer function. Due to computational error and stability consideration, the effective navigation ratio is kept constant for very small time-to-go until intercept, which its effect on the miss distance is also investigated. Finally, approximate formulas are obtained using curve fitting method for rms miss distance due to seeker noise.

Keywords

Main Subjects

Article Title [Persian]

Noise-Induced Miss Distance Analysis of First-Order Explicit Guidance Law

Authors [Persian]

  • Ali Arabian Arani
  • S.H. Jalali Naini
  • mohammad hossein Hamidi nejad

Tarbiat Modares University

Abstract [Persian]

This study presents the miss distance analysis of the first-order explicit guidance law due to seeker noise using the adjoint method. For this purpose, linearized equations are utillized and the adjoint model is developed. Then the first-order equations are obtained and converted into nondimensional ones. The analysis is carried out for different values of the power of the alpha function, defined as the time decrease rate of the zero-effort miss distance to unit control input. The unity power gives the first-order optimal guidance strategy, minimizing the integral of the square of the commanded acceleration during the total flight time.The seeker and control system is assumed as a fifth-order binomial transfer function. Due to computational error and stability consideration, the effective navigation ratio is kept constant for very small time-to-go until intercept, which its effect on the miss distance is also investigated. Finally, approximate formulas are obtained using curve fitting method for rms miss distance due to seeker noise.

Keywords [Persian]

  • Explicit Guidance
  • Optimal Guidance
  • Miss Distance Analysis
  • Seeker Noise
References
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[18] Jalali-Naini, S. H., "Noise-Induced Miss Distance Formulas of First-Order Control System Under Proportional Navigation for Arbitrary Navigation Ratios," presented at the 15th International Conference of Iranian Aerospace Society, Civil Aviation Technology College, Tehran, Iran, 2016.
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[23] Jalali-Naini, S. H. and Arabian Arani, A., "Explicit Guidance Law with Variable Navigation Coefficient," Presented at the 29th Annual International Conference of the Iranian Association of Mechanical Engineers, Tehran, Iran, 2021 (in Persian).
Journal of Aerospace Science and Technology
Volume 15, Issue 1
June 2022
Pages 129-138
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