Abstract
There is an optimal cruise point with the lowest fuel consumption when a hypersonic vehicle performs steady-state cruise. The optimal cruise point is composed of the optimal cruise altitude and the optimal cruise Mach number, and its position is closely related to the aircraft parameters. This article aims to explore the relationship between the optimal cruise point and relevant aircraft parameters and establish a model to describe it, then an aircraft parameter optimization method of adjusting the optimal cruise point to the target position is explored with validation by numerical simulation. Firstly, a parameterized model of a hypersonic vehicle is obtained as a basis, then the optimal cruise point is obtained by the optimization method, and the influence of a single aircraft parameter on the optimal point is investigated. In order to model the relationship between the aircraft parameters and the optimal cruise point, a neural network is employed. Finally, the model is used to optimize the aircraft parameters under multiple constraints. The results show that, after aircraft parameters optimization, the optimal cruise point is located at the predetermined position and the fuel consumption is lower, which provides a new perspective for the design of aircraft.
Highlights
Step 3: calculate the fuel consumption averaged by range at the altitude and Mach number represented by a particle as the fitness function value; represented by a particle as the fitness function value; Step 4: update the velocity and position of particles according to the fitness function value
The lift coefficient needs to increase by 5%, while the drag coefficient will increase by 2.5% as a result; the inlet area should increase by 25.93%, while the mass will increase by 8.64%, and the reference area will increase by 12.91%; the specific impulse needs to increase by 10%
To clarify the influence of the aircraft parameters on the optimal cruise point, the optimal cruise point under a basic parametric aircraft model was firstly solved by an optimization algorithm, and the influence of different parameters was investigated with modeling by a neural network
Summary
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. In order to describe the influence of aircraft parameters on the cruise point, a sensitivity analysis and surrogate model technology with the optim method is employed. Based on a parametric hypersonic vehicle model, the an optimization problem with high dimensions, the PSO algorithm is demonstrated to be of the and optimal is quickly by the has PSO algorithm On this basi suitable is alsocruise easy to point program, so a greatsolved deal of research adopted it [30,31]. The aircraft parameters are o of the optimal cruise point is quickly solved by the PSO algorithm On this basis, the under various constraints adjust the optimal pointisto the given influence law of a single aircraftto parameter on the optimalcruise cruise point explored, and position. Models should be adjusted, which is able to provide guidance in the design of a hypersonic vehicle
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