Research on Improving Directional Stability for Airborne Laser Designator

The major purpose of this paper is to reduce the laser directional deviation of laser designator on a moving platform.A new method of inhibiting the laser beam positional error caused by platform movement and vibration is proposed.In this method,quadrant detector(QD)and fast steering mirror are combined to measure the angle between laser designator axis and the line-of-sight of the target,then a control signal composed with the angle errors is generated to aim the axis of the laser designator at the target steadily.This is a real time processing method and it is suitable for airborne laser-guided weapons with second-class guiding time.

EFFECT OF SKIN FRICTION ON THE DIRECTIONAL STABILITY OF DRIVEN PILES DURING DRIVING

In this paper, the driving forces at a pile top are considered as a periodic load during driving and the Mathieu equation is derived. From the stability charts of this equation, we can obtain the critical length of the pile, and the effect of skin friction upon the critical length is discussed.

NASCS FOR THE ABSOLUTE STABILITY OF LURE DIRECT CONTROL SYSTEMS

In this paper, we transform n-th order Lure direct control systems into nonlinear systems with separating variables, and induce a concept for absolute stability of part arguments. The necessary and sufficient conditions (NASC) for the absolute stability of Lure direct control systems are given and some sufficient conditions are obtained

THE CRITERIONS FOR ABSOLUTE STABILITY OF DIRECT CONTROL SYSTEMS OF LURIE TYPE

In this paper, we give necessary and sufficient conditions for absolute stability of several classes of direct control systems, and discuss the absolute stability of the first canonical form of control system. The corresponding results in references [3,5,6] and [7] are improved.

Enhance the Performance of Directional Feature-based Palmprint Recognition by Directional Response Stability Measurement

Palmprint recognition is an emerging biometrics technology that has attracted increasing attention in recent years. Many palmprint recognition methods have been proposed, including traditional methods and deep learning-based methods. Among the traditional methods, the methods based on directional features are mainstream because they have high recognition rates and are robust to illumination changes and small noises. However, to date, in these methods, the stability of the palmprint directional response has not been deeply studied. In this paper, we analyse the problem of directional response instability in palmprint recognition methods based on directional feature. We then propose a novel palmprint directional response stability measurement (DRSM) to judge the stability of the directional feature of each pixel. After filtering the palmprint image with the filter bank, we design DRSM according to the relationship between the maximum response value and other response values for each pixel. Using DRSM, we can judge those pixels with unstable directional response and use a specially designed encoding mode related to a specific method. We insert the DRSM mechanism into seven classical methods based on directional feature, and conduct many experiments on six public palmprint databases. The experimental results show that the DRSM mechanism can effectively improve the performance of these methods. In the field of palmprint recognition, this work is the first in-depth study on the stability of the palmprint directional response, so this paper has strong reference value for research on palmprint recognition methods based on directional features.

Parameter effects on high-speed UAV ground directional stability using bifurcation analysis

A loss of ground directional stability can trigger a high-speed Unmanned Aerial Vehicle(UAV)to veer off the runway.In order to investigate the combined effects of the key structural and operational parameters on the UAV ground directional stability from a global perspective,a fully parameterized mathematical high-speed UAV ground nonlinear dynamic model is developed considering several nonlinear factors.The bifurcation analysis procedure of a UAV ground steering system is introduced,following which the simulation efficiency is greatly improved comparing with the time-domain simulation method.Then the numerical continuation method is employed to investigate the influence of the nose wheel steering angle and the global stability region is obtained.The bifurcation parameter plane is divided into several parts with different stability properties by the saddle nodes and the Hopf bifurcation points.We find that the UAV motion states will never cross the bifurcation curve in the nonlinear system.Also,the dual-parameter bifurcation analyses are presented to give a complete description of the possible steering performance.It is also found that BT bifurcation appears when the UAV initial rectilinear velocity and the tire frictional coefficient vary.In addition,results indicate that the influence of tire frictional coefficient has an opposite trend to the influence of initial rectilinear velocity.Overall,using bifurcation analysis method to identify the parameter regions of a UAV nonlinear ground dynamic system helps to improve the development efficiency and quality during UAV designing phase.

An experimental investigation on static directiona stability

A generic aircraft usually loses its static directional stability at moderate angle of attack(typically 20–30°). In this research, wind tunnel studies were performed using an aircraft model with moderate swept wing and a conventional vertical tail. The purpose of this study was to investigate flow mechanisms responsible for static directional stability. Measurements of force, surface pressure and spatial flow field were carried out for angles of attack from 0° to 46° and sideslip angles from-8° to 8°. Results of the wind tunnel experiments show that the vertical tail is the main contributor to static directional stability, while the fuselage is the main contributor to static directional instability of the model. In the sideslip attitude for moderate angles of attack, the fuselage vortex and the wing vortex merged together and changed asymmetrically as angle of attack increased on the windward side and leeward side of the vertical tail. The separated asymmetrical vortex flow around the vertical tail is the main reason for reduction in the static directional stability. Compared with the wing vortices, the fuselage vortices are more concentrated and closer to the vertical tail, so the yawing moment of vertical tail is more unstable than that when the wings are absent. On the other hand,the attached asymmetrical flow over the fuselage in sideslip leads to the static directional instability of the fuselage being exacerbated. It is mainly due to the predominant model contour blockage effect on the windward side flow over the model in sideslip, which is strongly affected by angle of attack.

LAGRANGE'S THEOREM FOR A CLASS OF NONHOLONOMICSYSTEMS AND ITS APPLICATION

The stability problem for the manifold of equilibrium positions of a class of nonholonomic systems is studied is studied in this paper .Based on Liapunov's direct method and the definition of stability , Lagrange's theorem of holonomic systems is extended to a class of nonholonomic conservative systems and dissipative systems ,and a new expression is made to the relation between asymptotic stability for the manifold of equilibrium positions of this class of nonholonomic systems and dissipative forces .Twoexamples are finally given to illustrate the application of the theorems .

Stability of a tumblehome hull under the dead ship condition

Some methods for direct stability assessment under the dead ship condition were currently developed by the international maritime organization （IMO） under the Second Generation Intact Stability Criteria. Model tests and simulations are carried out to validate the numerical methods used in assessing the stability under the dead ship condition. This is done in three stages. Firstly, the uncoupled roll mathematical model （1 DOF） is adopted to calculate the roll motion based on the irregular beam waves and the steady wind. Secondly, a drift free experiment is conducted to measure the roll motion under irregular beam waves with zero speed, and then two restrained experiments with counter weights and four springs are performed under the same condition. Finally, the effects of the drift and sway motions on stability under the dead ship condition are then verified by experimental results, and the results of the numerical methods are compared to the results of the model experiments. It is concluded that more accurate numerical methods could be developed for assessing the direct stability under the dead ship condition.