Aerodynamic Lift, Part 1: The Science

2018 ◽  
Vol 56 (8) ◽  
pp. 516-520 ◽  
Author(s):  
Doug McLean
Keyword(s):  
Aerodynamic Lift

Design of Missile Autopilot with Aerodynamic Lift and Reaction Jets Based on Auto Disturbance Rejection Controller

2012 ◽  
Vol 472-475 ◽  
pp. 1036-1039
Author(s):  
Chong Yang ◽  
Ke Zhang ◽  
Mei Bai Lu
Keyword(s):  
Disturbance Rejection ◽  
Response Speed ◽  
Fast Response ◽  
Urgent Problem ◽  
Robust Performance ◽  
Active Disturbance Rejection ◽  
Disturbance Rejection Control ◽  
Lateral Pulse Jet ◽  
Aerodynamic Lift ◽  
Pulse Jet

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.

AERODYNAMIC LIFT FORCES ON MULTIHULLED MARINE VEHICLES

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.

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

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.

Aeroelastic Tailoring of Helicopter Blades

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.

scholarly journals Research on the Aerodynamic Lift of Vehicle Windshield Wiper

2016 ◽  
Vol 9 (7) ◽  
pp. 2133-2140 ◽  
Author(s):  
Gu Zhengqi ◽  
Chen Zhen ◽  
Tan Peng ◽  
◽  
◽  
...  
Keyword(s):  
Windshield Wiper ◽  
Aerodynamic Lift

scholarly journals The mathematical theory of the motion of rotated and unrotated rockets

1949 ◽  
Vol 241 (837) ◽  
pp. 457-585 ◽  
Keyword(s):  
Numerical Computation ◽  
Mathematical Theory ◽  
Equations Of Motion ◽  
Aerodynamic Forces ◽  
Stable Motion ◽  
General Terms ◽  
Set Up ◽  
Aerodynamic Lift

An account is given of the mathematical theory of the motion of a rocket in flight. The aerodynamic forces and couples, and those due to the action of the burning gases, are investigated as fully as possible, and the equations of motion are set up in their most general form. The effects of a variety of disturbing factors, such as wind and asymmetries of design and functioning, are considered. Solutions of the equations, most of which are suitable for numerical computation, are given under various assumptions regarding the form of the axial spin, the aerodynamic lift moment, the acceleration, etc. A thorough investigation of the conditions necessary for stable motion is carried out. The paper concludes with a summary in which the main features of rocket motion, as revealed by the theory, are discussed in general terms

Optimal wing hinge position for fast ascent in a model fly

2018 ◽  
Vol 849 ◽  
pp. 498-509
Author(s):  
R. M. Noest ◽  
Z. Jane Wang
Keyword(s):  
Stability Analysis ◽  
Body Length ◽  
Weak Dependence ◽  
The Body ◽  
Simplified Model ◽  
Centre Of Mass ◽  
Flight Stability ◽  
Hinge Position ◽  
Stroke Amplitude ◽  
Aerodynamic Lift

It was thought that the wing hinge position can be tuned to stabilize an uncontrolled fly. However here, our Floquet stability analysis shows that the hinge position has a weak dependence on the flight stability. As long as the hinge position is within the fly’s body length, both hovering and ascending flight are unstable. Instead, there is an optimal hinge position, $h^{\ast }$, at which the ascending speed is maximized. $h^{\ast }$ is approximately half way between the centre of mass and the top of the body. We show that the optimal $h^{\ast }$ is associated with the anti-resonance of the body–wing coupling, and is independent of the stroke amplitude. At $h^{\ast }$, the torque due to wing inertia nearly cancels the torque due to aerodynamic lift, minimizing the body oscillation thus maximizing the upward force. Our analysis using a simplified model of two coupled masses further predicts, $h^{\ast }=(m_{t}/2m_{w})(g/\unicode[STIX]{x1D714}^{2})$. These results suggest that the ascending speed, in addition to energetics and stability, is a trait that insects are likely to optimize.

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