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On the predicted errors of atmospheric guidance laws

Jalali Naini, S. H ; Sharif University of Technology | 2008

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  1. Type of Document: Article
  2. DOI: 10.1108/00022660810873692
  3. Publisher: 2008
  4. Abstract:
  5. Purpose - The purpose of this paper is to develop a novel solution for the predicted error and introduces a systematic method to develop optimal and explicit guidance strategies for different missions. Design/methodology/approach - The predicted error is derived from its basic definition through analytic]al dynamics. The relations are developed for two classes of systems. First, for systems in which the acceleration commands are truncated at a specified time. Second, for systems in which the corrective maneuvers are cut off at a specified time. The predicted error differential equation is obtained in a way that allows for derivation of several optimal and explicit guidance schemes. Findings - The effect of tangential acceleration in conjunction with autopilot dynamics can be realized in guidance gain and the predicted error. The differential equation of velocity-to-be-gained is obtained assuming the gravitational acceleration to be given as a vectorial function of time. The relations for different velocity profiles are obtained and discussed including the effective navigation ratio. Research limitations/implications - The guidance/control system is modeled as a linear time-varying dynamic and of arbitrary-order. The gravitational acceleration is assumed as a given vectorial function of time. Practical implications - The presented schemes are applicable to both midcourse and terminal guidance laws with/without velocity constraints. Originality/value - Providing a new analytical solution of predicted errors with final position and velocity constraints and their differential equations considering the thrust/drag acceleration and autopilot dynamics in the presence of gravity
  6. Keywords:
  7. Acceleration ; Automation ; Differential equations ; Error analysis ; Error correction ; Flight control systems ; Flight dynamics ; Autopilot dynamics ; Gravitational acceleration ; Predictor-corrector methods ; Aerodynamics
  8. Source: Aircraft Engineering and Aerospace Technology ; Volume 80, Issue 3 , 2008 , Pages 262-273 ; 00022667 (ISSN)
  9. URL: https://www.emerald.com/insight/content/doi/10.1108/00022660810873692/full/html