The paper presents a qualitatively new approach to terminal guidance at the final trajectory section for the surface-to-surface class aerial vehicles. The proposed structure of the adaptive control system for an aerial vehicle is based on the multi-step terminal guidance algorithm. Adaptive corrections to the control coefficients were calculated using the developed method for identifying the wind disturbances based on the machine learning models. The work describes technique to form an intelligent algorithm for identifying intensity and direction of the wind load acting on the aerial vehicle in flight. Options of the machine learning models used in the guidance system intelligent block were investigated; their operation results are presented; and the comparative analysis has been carried out. The adaptive guidance system operation procedure is demonstrated on a typical model of the aerial vehicle flying in the atmosphere and targeting a fixed object. Numerical simulation results are presented, and possibility of using such an algorithm and implementing the described system are demonstrated.
Creation of aircraft control systems that provide high quality guidance is an urgent task associated with increasing efficiency of the modern missile systems. Classical autonomous guidance systems without integration with any other external correction systems are making it impossible to ensure high-precision target engagement. An approach based on the use of adaptive guidance system is proposed. Besides, an approach to synthesis and analysis of the self-tuning aircraft control system that implements terminal homing is illustrated. A technique for forming the control system structure is presented ensuring the control quality constant level in all operating modes due to self-tuning of the constituent elements variable coefficients. Structural schemes and control equations were determined to correct the aircraft flight. Implementation of the developed technique on board the aircraft is proposed determining relationship between the aircraft control system parameters and the apparent acceleration. Adaptive system operation is demonstrated on a typical model of the aircraft flying in the atmosphere with guidance at the stationary target. Results of numerical simulation are presented, and high efficiency of the developed technique is revealed
The ever-increasing requirements for aircraft control systems lead to their more complex structure and, consequently, synthesis. Thus, there is a need to develop and improve control algorithms that can meet these requirements. To develop control systems for high-precision aircraft, it is important to analyze how adaptive control systems are used. The paper examines the aircraft control system with one-parametric adaptation homing in the final section of the trajectory. The analysis of the test trajectory of the aircraft movement allowed us to establish the criteria for selecting the adaptation parameter. We comparatively analyzed the parameters, found a method to estimate their efficiency, and demonstrated the operation procedure of the adaptive system on a typical model of an aircraft moving in the atmosphere when homing in on a fixed target. The study gives the results of numerical simulation and shows the high efficiency of the method developed.
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