Flight system drop point error correction method based on dimensionless form

Abstract

The invention relates to a flight system drop point error correction method based on a dimensionless form. Brand new design thought is adopted, the method aims at the whole process that a projectile body device flies from a static state to a landing state, the control variables acting on the projectile body device randomly select two target control quantities, function derivation between target control quantity non-dimensionalization and actual drop point polar coordinates is applied to obtain an iterative relational expression, by utilizing a comparison result of the distance between the actual landing point and the target landing point compared to the preset accuracy interval of the landing point, iterative optimization is carried out on the control variable, the actual drop point position of the projectile body device is continuously corrected, the accuracy of the projectile body device relative target landing point is improved, the whole design method is faster in convergence speedand higher in convergence precision, the actual drop point error can be rapidly corrected to meet the requirement of engineering precision under the condition of a small number of iterations, the iterative relation is simple, programming is easy, calculation consumption is low, and real-time optimization of the drop point error of the projectile body device can be achieved.

Description

technical field [0001] The invention relates to a method for correcting landing point errors of a flight system based on a dimensionless form, and belongs to the technical field of trajectory optimization control. Background technique [0002] In order to ensure the stability of the projectile in the air and reduce the landing speed of the projectile, a parachute is generally added to the tail of the projectile to form a parachute flight system, and the parachute is separated from the projectile after landing. Because the external environment (for example: the movement of the launcher, the change of the meteorological wind field, etc.) has a great influence on the trajectory of the parachute flight system, the landing point of the projectile will deviate. Therefore, it is necessary to adjust the control variables in real time to ensure that the parachute flight system has sufficient landing point accuracy under different external environmental interference conditions. [00...

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Problems solved by technology

Existing trajectory optimization methods mainly include indirect method and direct method. Among them, the indirect method uses the extremum principle to convert the trajectory optimization problem into a two-point boundary value problem, and then solves it by numerical method, but it has a certain influence on the initial value of the variable. Higher requirements, narrow application range; the direct method is to parameterize the landing point state and control quantity through a certain strategy, transform the trajectory optimization problem into a limited dimensional parameter optimization problem with constraints, and then use the nonlinear programming algorithm To solve, the global optimization algorithm is mainly used, such as genetic algorithm, ant colony algorithm, particle swarm optimization algorithm, etc., but due to the external environment interference, real-time changes will occur, and the global optimization algorithm consumes a lot of calculation and takes a long time, so it is difficult to realize the parachute Real-time landing point optimization of flight system under external environment interference

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