Aircraft trajectory generation and control for minimum fuel and time efficient climb

Abstract

This paper presents a novel approach for generating the best possible climb trajectory that ensures minimum fuel and time efficient climb. The problem is first formulated using standard steady climb equations, which generate a unique combination of flight velocity and flight path angle at each altitude. A possible scenario, such as air density, mass, available power, and required powered variation with altitude, is taken into account when defining the problem. Thereafter, sliding-mode-based trajectory tracking control is formulated with its design procedures, system stability with applied control inputs, finite-time convergence analysis, and complete architecture. A Hansa-3 research aircraft is considered as an example model to demonstrate the work. The findings of generated trajectory are then produced and discussed. In order to follow the design trajectory and achieve the same, the sliding-mode-based control command is supplied. The novelty of the present work lies in proposed strategy of trajectory generation, wherein the aircraft path and velocity are found out to make the fuel and time efficient climb possible. Subsequently, robust control law is developed which shows the applicability of the proposed work on autopilot. The results show that the proposed controller not only controls the aircraft but is also able to follow the design trajectory with minimal errors. To further explore the impact of aircraft mass on climb performance, repeated set simulation is carried out. The outcome is compared with conventional climb, which promises its practical implementation since the proposed solution is simple and compatible to integrate with the existing aircraft autopilot.