Investigation of the handling qualities of fighter aircraft with relaxed static stability at high angles of attack using a holistic simulation approach

1998 ◽  
Author(s):  
L.D. Evangelou
Keyword(s):  
Static Stability ◽  
Simulation Approach ◽  
Fighter Aircraft ◽  
Handling Qualities ◽  
High Angles Of Attack

Trimmed deep stall on the F-16 Fighting Falcon

2001 ◽  
Vol 105 (1054) ◽  
pp. 679-683 ◽  
Author(s):  
L. D. Evangelou ◽  
A. W. Self ◽  
J. E. Allen ◽  
S. Lo
Keyword(s):  
High Performance ◽  
Reliable Method ◽  
Control Problems ◽  
Fighter Aircraft ◽  
Handling Qualities ◽  
Handling Characteristics ◽  
Combat Effectiveness ◽  
Flight Envelope ◽  
High Angles Of Attack

Abstract High performance fighter aircraft have problems with handling qualities, at high angles of incidence. Pilots are limiting combat effectiveness by cautiously avoiding hazardous regions of the flight envelope. This paper presents and extends existing work on the F-16 aircraft's handling characteristics during the deep stall condition. Inflight experience shows that there are two types of control problems when flying at high angles-of-attack, the ‘pitch departures’ and the ‘deep stall trim’. This paper investigates the critical deep stall condition, assesses the effectiveness of the proposed method of recovery and suggests an augmented and reliable method of returning to normal flight.

On Nonlinear Dynamics and Flight Control at High Angles of Attack With Uncertain Aerodynamics

2016 ◽  
Author(s):  
Mateus de Freitas Virgílio Pereira ◽  
Igor Afonso Acampora Prado ◽  
Davi Ferreira de Castro ◽  
José Manoel Balthazar ◽  
Roberto Gil Annes da Silva ◽  
...  
Keyword(s):  
Flight Control ◽  
Parametric Uncertainty ◽  
Linear Feedback ◽  
Fighter Aircraft ◽  
Generalized Polynomial ◽  
Hamilton Jacobi Bellman Equation ◽  
Optimal Linear ◽  
Hamilton Jacobi Bellman ◽  
High Angles Of Attack ◽  
Lyapunov Sense

In this paper we consider the flight dynamics of fighter aircraft at high angles of attack with uncertain aerodynamic coefficients. Stochastic parametric uncertainty is dealt with by employing spectral decomposition of the random variables by means of the generalized polynomial chaos expansion. We propose an optimal linear feedback strategy for the automatic pilot system to recover the aircraft from stall and provide acceptable dynamic response. Optimality of the proposed control law is proved by solving the Hamilton-Jacobi-Bellman equation and asymptotically stability of the controlled nonlinear aircraft model is guaranteed in the Lyapunov sense. Numerical results are verified with Monte-Carlo simulations.

scholarly journals Conceptual Design, Flying, and Handling Qualities Assessment of a Blended Wing Body (BWB) Aircraft by Using an Engineering Flight Simulator

Aerospace ◽  
2020 ◽  
Vol 7 (5) ◽  
pp. 51 ◽  
Author(s):  
Clayton Humphreys-Jennings ◽  
Ilias Lappas ◽  
Dragos Mihai Sovar
Keyword(s):  
Static Stability ◽  
Flight Simulator ◽  
Handling Qualities ◽  
Stability And Control ◽  
Flying Qualities ◽  
Blended Wing Body ◽  
And Control ◽  
Drag Ratio ◽  
Lift To Drag Ratio ◽  
Mission Profile

The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3000 nautical miles, carrying 200 passengers. The BWB design was flight tested at an engineering flight simulator to first determine its static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the mean aerodynamic chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; while meeting all the requirements of the dynamic modes.

Nonlinear dynamics and linear control applied to an fighter aircraft in longitudinal flight at high angles of attack

2018 ◽  
Author(s):  
Guilherme Pacheco dos Santos ◽  
Angelo Marcelo Tusset ◽  
Frederic Conrad Janzen ◽  
Rodrigo Tumolin Rocha ◽  
Airton Nabarrete ◽  
...  
Keyword(s):  
Nonlinear Dynamics ◽  
Linear Control ◽  
Fighter Aircraft ◽  
High Angles Of Attack
Sign in / Sign up

Export Citation Format

Share Document