Abstract
Icing has now become an important factor endangering flight safety. This paper takes the icing data of the NACA 23012 airfoil as an example, establishes an icing influence model for real-time simulation based on icing time and aircraft angle of attack, and analyzes the influence of different icing geometry on aircraft characteristics. The two-dimensional interpolation method is used to improve the model of the aircraft’s stall area, which is mainly divided into the correction of the lift-drag coefficient linear area and the stall area and the correction of the aircraft stability derivative and the control derivative. The aerodynamic equation of the airplane after icing is established, and the modal analysis of the airplane under different icing conditions is completed through the linearization of the flight equation. The closed-loop simulation system of the altitude holding mode and roll attitude holding mode is used to calculate and analyze the flight quality changes of the aircraft after the wing surface is frozen. The analysis results show that, under icing conditions, in the range of small angles of attack, icing has no obvious influence on the aircraft mode. As the degree of icing increases, the throttle skewness and the negative deflection angle of the airplane’s level flight requirements continue to increase. The case of icing flight in altitude hold and roll hold modes shows that flying in the autopilot mode under severe icing conditions is very dangerous and is prone to cause the aircraft to stall.
Highlights
In terms of flight test, the aerodynamic data of the aircraft after icing are identified mainly through the aircraft icing test flight data
Since it is currently impossible to eliminate the hazards of icing to flight safety, there is an urgent need for safety protection under icing conditions
In order to fully understand the effect of icing on the lift-drag characteristics and stability characteristics of aircraft flight, a real-time simulation icing influence model is established in this paper based on NACA 23012 airfoil icing data
Summary
2.1. e Influence of Airfoil Icing on Aircraft Aerodynamics and Model Establishment. 2.1.1. e Influence of Airfoil Icing on Lift-Drag Characteristics. e selected wing of the aircraft is a trapezoidal wing with a large aspect ratio, and the aerodynamic layout is that the airfoil with a larger lift coefficient is arranged at the wing tip. e airfoil with a smaller lift coefficient is arranged at the wing root to ensure that the separation of aircraft airflow gradually spreads from the wing root to the wing tip. E aircraft’s lift, drag, and pitching moment coefficients can be corrected by NASA data, and the icing effect mainly depends on the icing time and the aircraft’s angle of attack.
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