CNC machining and machinery Longitudinal control law design and flight test for a small UAV based on Eigenstructure Assignment

2015 ◽  
pp. 261-266
Keyword(s):  
Flight Test ◽  
Cnc Machining ◽  
Control Law ◽  
Eigenstructure Assignment ◽  
Longitudinal Control ◽  
Small Uav

Design and development of a backstepping controller autopilot for fixed-wing UAVs

2021 ◽  
pp. 1-27
Author(s):  
D. Sartori ◽  
F. Quagliotti ◽  
M.J. Rutherford ◽  
K.P. Valavanis
Keyword(s):  
Real Time ◽  
Control Law ◽  
Parametric Uncertainties ◽  
Hardware In The Loop ◽  
Aircraft Control ◽  
Backstepping Approach ◽  
Small Uav ◽  
Backstepping Controller ◽  
Definition Of ◽  
Performance Results

Abstract Backstepping represents a promising control law for fixed-wing Unmanned Aerial Vehicles (UAVs). Its non-linearity and its adaptation capabilities guarantee adequate control performance over the whole flight envelope, even when the aircraft model is affected by parametric uncertainties. In the literature, several works apply backstepping controllers to various aspects of fixed-wing UAV flight. Unfortunately, many of them have not been implemented in a real-time controller, and only few attempt simultaneous longitudinal and lateral–directional aircraft control. In this paper, an existing backstepping approach able to control longitudinal and lateral–directional motions is adapted for the definition of a control strategy suitable for small UAV autopilots. Rapidly changing inner-loop variables are controlled with non-adaptive backstepping, while slower outer loop navigation variables are Proportional–Integral–Derivative (PID) controlled. The controller is evaluated through numerical simulations for two very diverse fixed-wing aircraft performing complex manoeuvres. The controller behaviour with model parametric uncertainties or in presence of noise is also tested. The performance results of a real-time implementation on a microcontroller are evaluated through hardware-in-the-loop simulation.

Take-off characteristics and longitudinal controllability of FanWing

2016 ◽  
Vol 88 (6) ◽  
pp. 783-790 ◽  
Author(s):  
Lin Meng ◽  
Yongqiang Ye
Keyword(s):  
Deflection Angle ◽  
Rotation Speed ◽  
Cross Flow ◽  
Control Law ◽  
Great Success ◽  
Variable Cross ◽  
Longitudinal Control ◽  
Content Type ◽  
Cross Flow Fan ◽  
Practical Implications

Purpose This paper aims to study the short take-off characteristics and longitudinal controllability of FanWing. As a new structural plane, it has achieved great success at the air shows, but the existing literature is mostly on feasibility and prototype study while little on short take-off performance analysis and controllability. Thus, the paper will do some research on those two aspects. Design/methodology/approach This paper focuses on a certain type of a 3.5 kg FanWing and builds the longitudinal model based on its structure characteristics and operation principle. Its take-off process is simulated and the longitudinal control law is designed. Findings The short take-off performance and the large load characteristic are verified. To attain a better short take-off performance, several factors that influence the take-off distance are researched, and the optimal no-load take-off distance 5 m is obtained when the elevator deflection angle is −30°, the center of gravity is 0.42 m and the cross-flow fan rotation speed is 2500 r/min. The longitudinal controllability is verified through simulation. And without variable cross-flow fan rotation speed control, the longitudinal control of FanWing is the same to that of the conventional aircraft. Practical implications The presented efforts provide markers for designing the fan wing aircraft that would have better performances. And the control of FanWing is similar to that of a conventional airplane. Originality/value It is proved that FanWing can offer a better take-off performance through reasonable configuration. The paper also offers a useful reference on the control of FanWing.

Design and Simulation of Anti-Violent Rocket Engine on Small UAV

2013 ◽  
Vol 562-565 ◽  
pp. 1063-1068
Author(s):  
Xing Yu Liu ◽  
San Xue Guo
Keyword(s):  
Control System ◽  
Rocket Engine ◽  
Flight Test ◽  
Small Uav

Anti-violent rocket on small UAV creatively combines the anti-riot shell with the UAV,utilizing the theory of rocket lanching,realizing that Anti-violent Shell is launched far in the sky.It is significant for CAPF to realize variety of targets battle in the emergency and mission. This paper focuses on sumulation and testing of anti-violent rocket engine on Small UAV,and the flight test-fired experimental of engine is carried on with control system,which demonstrates its feasibility.

Multidisciplinary Control Law Design and Flight Test Demonstration on a Business Jet

2008 ◽  
Author(s):  
Dagfinn Gangsaas ◽  
John Hodgkinson ◽  
Clay Harden ◽  
Nomaan Saeed ◽  
Kaiming Chen
Keyword(s):  
Flight Test ◽  
Control Law ◽  
Business Jet
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