Naïve concepts of aerodynamic lift – data lessons from different (learning) cultures

First a new autopilot design model is presented for the interceptor missile with the blended aerodynamic lift and reaction jet. The reaction jet can improve the response speed, but the structure of control system becomes more complex. Therefore how to design control strategy properly is an urgent problem. Second, considering the discrete property of the lateral pulse jet thrusters and the continuous property of the aerodynamic fins, a kind of ADRC (active disturbance rejection control) autopilot system was designed for the aerodynamic lift/reaction jet missile. Finally, through a testing in the simulation of MATLAB, it is shown that, due to the sufficient utilization of the reaction jet, there is a significant improvement in the fast response and robust performance of the proposed controller. It is applicable to design the autopilot of aerodynamic lift and reaction jet blended missile.

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AERODYNAMIC LIFT FORCES ON MULTIHULLED MARINE VEHICLES

The International Journal of Maritime Engineering ◽

10.5750/ijme.v152ia2.825 ◽

2021 ◽

Vol 152 (A2) ◽

Author(s):

A G W Williams ◽

M Collu ◽

M H Patel

Keyword(s):

High Speed ◽

Vehicle Stability ◽

Aerodynamic Design ◽

Forward Motion ◽

Marine Vehicles ◽

Marine Transport ◽

Stability Model ◽

Lift Forces ◽

High Payload ◽

Aerodynamic Lift

The need for high-speed high-payload craft has led to considerable efforts within the marine transport industry towards a vehicle capable of bridging the gap between conventional ships and aircraft. One such concept uses the forward motion of the craft to create aerodynamic lift forces on a wing-like superstructure and hence, reduce the displacement and skin friction. This paper addresses the specific aerodynamic design of multihull for optimal lift production and shows that significant efficiency can be achieved through careful shaping of a ducted hull, with lift-to-drag ratios of nearly 50 for a complete aerodynamic hull configuration. Further analysis is carried out using a hybrid vehicle stability model to determine the effect of such aerodynamic alleviation on a theoretical planing hull. It is found that the resistance can be halved for a fifty metre, three hundred tonne vehicle with aerodynamic alleviation travelling at 70 knots. Results are presented for a candidate vessel.

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The Spatial Approach: Aerodynamic Lift

How High the Sky? ◽

10.1163/9789004366022_008 ◽

2018 ◽

pp. 113-119

Keyword(s):

Spatial Approach ◽

Aerodynamic Lift

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Exploring research on high-speed vehicle attitude control with plasma virtual flap manipulation

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018804089 ◽

2018 ◽

Vol 233 (10) ◽

pp. 3627-3634

Author(s):

Wang Xin ◽

Yan Jie ◽

Zhang Yerong

Keyword(s):

Attitude Control ◽

High Speed ◽

Long Duration ◽

Aerodynamic Control ◽

Control Authority ◽

Attitude Controller ◽

Lift And Drag ◽

Cruise Flight ◽

Aerodynamic Lift ◽

High Speed Vehicle

This work provides an attitude solution for a high-speed vehicle using plasma aerodynamic control called “plasma virtual flap” manipulation. This paper describes the concept of using plasma active control as plasma virtual flap for off-design attitude manipulation problem. Design of an attitude controller considering plasma aerodynamic effects for the high-speed vehicle is presented. The aerodynamic lift and drag force features in the high speed, long duration cruise flight with plasma actuator effect are introduced, where the estimated models and attitude controller are established. This paper documents the development and capabilities of plasma virtual flap attitude control authority. Simulation results are presented to exhibit the effectiveness of the proposed method.

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The effect of aerodynamic lift on satellite orbits

Vacuum ◽

10.1016/0042-207x(65)91648-9 ◽

1965 ◽

Vol 15 (3) ◽

pp. 157

Keyword(s):

Satellite Orbits ◽

Aerodynamic Lift

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Corrigendum to Experimental and analytical analysis of aerodynamic lift of an ornithopter at low and high angles of attack

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410020916068 ◽

2020 ◽

Vol 234 (7) ◽

pp. NP1-NP1

Keyword(s):

Analytical Analysis ◽

High Angles Of Attack ◽

Aerodynamic Lift

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Aerodynamic Lift, Part 1: The Science

The Physics Teacher ◽

10.1119/1.5064558 ◽

2018 ◽

Vol 56 (8) ◽

pp. 516-520 ◽

Cited By ~ 1

Author(s):

Doug McLean

Keyword(s):

Aerodynamic Lift

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Aeroelastic Tailoring of Helicopter Blades

Volume 7A: 9th International Conference on Multibody Systems, Nonlinear Dynamics, and Control ◽

10.1115/detc2013-12848 ◽

2013 ◽

Author(s):

Donatien Cornette ◽

Benjamin Kerdreux ◽

Yves Gourinat ◽

Guilhem Michon

Keyword(s):

Dynamic Behaviour ◽

Vertical Shear ◽

Dynamic Loads ◽

Modal Approach ◽

Aeroelastic Tailoring ◽

Helicopter Blades ◽

Shear Modification ◽

Elastic Couplings ◽

The Impact ◽

Aerodynamic Lift

The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress of components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization is done thanks to couplings between the flapwise-bending motion and the torsion motion. The impact of elastic couplings (composite anisotropy) on the blade dynamic behaviour and on dynamic loads are evaluated in this paper. Firstly, analytical results, based on a purely linear modal approach, are given to understand the influence of those couplings in terms of frequency placement, aerodynamic lift load and vertical shear modification. Then, those elastic couplings are introduced on a simplified but representative blade (homogeneous beam with constant chord) and results are presented.

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