Optimal design of the aerodynamic parameters for a supersonic two-dimensional guided artillery projectile

An optimization method is introduced to design the aerodynamic parameters of a dual-spin twodimensional guided projectile with the canards for trajectory correction. The nose guidance component contains two pairs of canards which can provide lift and despin with the projectile for stability. The optimal design algorithm is developed to decide the profiles both of the steering and spinning canards,and their deflection angles are also simulated to meet the needs of trajectory correction capabilities.Finally, the aerodynamic efficiency of the specific canards is discussed according to the CFD simulations.Results that obtained here can be further applied to the exterior ballistics design.

A new calibration algorithms of spinning projectile aerodynamic parameters

This paper demonstrates that the application of calibration algorithms of aerodynamic parameters for the trajectory of spinning projectile is successful. First, from the point of view of the trajectory simulation, a general summary of well-known trajectory models is given. A five degrees of freedom (5 DOF) model is developed that can match the projectile motion essentially in the vertex region, and the results obtained by 5 DOF model are in close agreement with those of a more sophisticated 6 DOF model for elevation angles above 45 degrees. Secondly, the calibration algorithms have been developed and are summarized. The methods of calibrating the flight trajectory models are compared, and these methods are shown to be effective in the representative cases. In addition, the method of Mach number calibration (MNC) is presented; some possible areas in MNC for further investigation are indicated together with benefits to be gained. The utilization of MNC schemes not only allow a worthwhile reduction of calibration rounds firing in range and accuracy (R&A) trial and production of firing tables (PFT) test, but also make PFT and fire control data (FCD) more cost effective.

Influences of aerodynamic loads on hunting stability of high-speed railway vehicles and parameter studies

The influences of steady aerodynamic loads on hunting stability of high-speed railway vehicles were investigated in this study.A mechanism is suggested to explain the change of hunting behavior due to actions of aerodynamic loads：the aerodynamic loads can change the position of vehicle system（consequently the contact relations）,the wheel/rail normal contact forces,the gravitational restoring forces/moments and the creep forces/moments.A mathematical model for hunting stability incorporating such influences was developed.A computer program capable of incorporating the effects of aerodynamic loads based on the model was written,and the critical speeds were calculated using this program.The dependences of linear and nonlinear critical speeds on suspension parameters considering aerodynamic loads were analyzed by using the orthogonal test method,the results were also compared with the situations without aerodynamic loads.It is shown that the most dominant factors a ff ecting linear and nonlinear critical speeds are different whether the aerodynamic loads considered or not.The damping of yaw damper is the most dominant influencing factor for linear critical speeds,while the damping of lateral damper is most dominant for nonlinear ones.When the influences of aerodynamic loads are considered,the linear critical speeds decrease with the rise of cross wind velocity,whereas it is not the case for the nonlinear critical speeds.The variation trends of critical speeds with suspension parameters can be significantly changed by aerodynamic loads.Combined actions of aerodynamic loads and suspension parameters also a ff ect the critical speeds.The effects of such joint action are more obvious for nonlinear critical speeds.

The Maximum Likelihood Method of Aerodynamic Parameter Identification

In this paper a method of aerodynamic parameter identification of vehicle, the maximum likelihood method, is introduced. The aerodynamic model of vehicle is identified and the basic equations using maximum likelihood method are established. After that, the simulation data is identified to verify the correctness of the mathematic model and identification method. Last, the practical flight data is identified and analyzed.

Comparison of linear and nonlinear aerodynamic parameter estimation approaches for an unmanned aerial vehicle using unscented Kalman filter

Aerodynamic parameter estimation provides an effective way for aerospace system modeling using measured data from flight tests, especially for the purpose of developing elaborate simulation environments and designing control systems of unmanned aerial vehicle （UAV） with short design cycles and reduced cost. However, parameter identification of airplane dynamics by nonlinear mod- els is complicated because of the noisy and biased sensor measurements. Using linear models for system identification is an alternative way if the fidelity can be guaranteed, as control design procedures are better established in linear systems. This paper considers the application and comparison of linear as well as nonlinear aerodynamic parameter estimation approaches of an UAV using unscented Kalman filter （UKF）. It also highlights the degree of deterioration of the linear model in the UKF identification process. The results show that both the linear and nonlinear methodologies can accurately estimate the control system design. Furthermore, considering loss of accuracy to be negligible, the linear model can be employed for control design of the UAV as presented here.

On extended state Kalman filter-based identification algorithm for aerodynamic parameters

In this paper, the problem of time-varying aerodynamic parameters identification under measurement noises is studied. By analyzing the key aerodynamic parameters that affect the aircraft control system, a system model with extended states for identifying equivalent aerodynamic parameters is established, and error parameters are extended to the system state, avoiding the difficulty caused by the unknown dynamic in the system. Furthermore, an identification algorithm based on extended state Kalman filter is designed, and it is proved that the algorithm has quasi-consistency, thus, the estimation error can be evaluated in real time. Finally, the simulation results under typical flight scenarios show that the designed algorithm can accurately identify aerodynamic parameters, and has desired convergence speed and convergence precision.

Numerical Analysis of Aerodynamic Characteristics of the HALE Diamond Joined-Wing Configuration UAV

The investigation on the aerodynamic characteristics of the high-attitude long-endurance (HALE) Diamond Joined-Wing configuration unmanned aerial vehicle ( UAV) was carried out by the theoretical analysis method and numerical simulation. Research indicates that as the wing of the UAV is composed of the front wing and the after wing, the after wing has the ability to transmit the front wing's boundary layer to the after wing root which can inhibit the front wing's flow separation. Although the front wing was affected by the retardation of the after wing, the aerodynamic performance of the front wing was better than that of alone front wing in most cases. The after wing was also affected by the wake and downwash of the front wing, and its aerodynamic performance was greatly decreased. The characteristic curve of the pitching moment of the UAV had nonlinear characteristics. The flow field structure of the after wing changed by the front wing wake direct sweep and flow separation at the after wing root were the main reasons that non-linear ′rise′phenomenon occurred in two segments ( α = 0° and α = 8° ) of the characteristic curve of pitching moment. Moreover, coupling of the flow separation characteristic of the front wing and the after wing resulted in the pitching moment ′pitchup′ phenomenon. The lateral-directional static stability of the flat layout was weak. The HALE Diamond Joined-Wing configuration UAV ' s aerodynamic performance can be improved and the problems in engineering applications can be effectively alleviated by adjusting the overall layout parameters.

Numerical Study on Aerodynamic Characteristics of Ducted Fan Aircraft

Based on investigations into the flow field of ducted fan aircrafts,structural parameters of duct are quantified.A three-dimensional model is established for numerical simulation,and adaptive Cartesian grid is used to mesh the model in order to improve calculation speed and solution accuracy.Three-dimensional Navier-Stokes equations are brought in to analyze different duct styles.Generalization of simulation results leads to several conclusions in duct aerodynamics to help design ducted fan aircrafts.

Study of the aerostatic and aerodynamic stability of super long-span cable-stayed bridges

With the increase of span length,the bridge tends to be more flexible,and the wind stability becomes an important problem for the design and construction of super long-span cable-stayed bridges. By taking a super long-span cable-stayed bridge with a main span of 1 400 m as example,the aerostatic and aerodynamic stability of the bridge are investigated by three-dimensional nonlinear aerostatic and aerodynamic stability analysis,and the results are compared with those of a suspension bridge with a main span of 1 385 m,and from the aspect of wind stability,the feasibility of using cable-stayed bridge in super long-span bridge with a main span above 1 000 m is discussed. In addition,the influences of design parameters including the depth and width of the girder,the tower structure,the tower height-to-span ratio,the side-to-main span ratio,the auxiliary piers in the side span and the anchorage system of stay cables,etc on the aerostatic and aerodynamic stability of super long-span cable-stayed bridges are investigated numerically;the key design parameters are pointed out,and also their reasonable values are proposed.

Multi-objective aerodynamic optimization design of high-speed maglev train nose

Purpose–The nose length is the key design parameter affecting the aerodynamic performance of high-speed maglev train,and the horizontal profile has a significant impact on the aerodynamic lift of the leading and trailing cars Hence,the study analyzes aerodynamic parameters with multi-objective optimization design.Design/methodology/approach–The nose of normal temperature and normal conduction high-speed maglev train is divided into streamlined part and equipment cabin according to its geometric characteristics.Then the modified vehicle modeling function(VMF)parameterization method and surface discretization method are adopted for the parametric design of the nose.For the 12 key design parameters extracted,combined with computational fluid dynamics(CFD),support vector machine(SVR)model and multi-objective particle swarm optimization(MPSO)algorithm,the multi-objective aerodynamic optimization design of highspeed maglev train nose and the sensitivity analysis of design parameters are carried out with aerodynamic drag coefficient of the whole vehicle and the aerodynamic lift coefficient of the trailing car as the optimization objectives and the aerodynamic lift coefficient of the leading car as the constraint.The engineering improvement and wind tunnel test verification of the optimized shape are done.Findings–Results show that the parametric design method can use less design parameters to describe the nose shape of high-speed maglev train.The prediction accuracy of the SVR model with the reduced amount of calculation and improved optimization efficiency meets the design requirements.Originality/value–Compared with the original shape,the aerodynamic drag coefficient of the whole vehicle is reduced by 19.2%,and the aerodynamic lift coefficients of the leading and trailing cars are reduced by 24.8 and 51.3%,respectively,after adopting the optimized shape modified according to engineering design requirements.

Regularity and sensitivity analysis of main parameters of plate effects on the aerodynamic braking drag of a high-speed train

With increase of train speed,braking plate technology has a good application prospect in the high-speed stage of the train.Based on the 1/8 scaled symmetrical train model composed of two half cars,the Reynolds Av era ge Navier-Stokes(RANS)equations and Shear Stress Transfer(SST)k-ωturbulence model are adopted to simulate the aerodynamic performance of the train with plate.The aer odynamic dra g de pendence of single par ameter of the plate(shape,area,angle,position and n umber)is anal ysed,and identification resear c h of the main aerodynamic parameters of the plate is carried out.The numerical settings used in this paper are verified by wind tunnel test data.Results show that the braking plate with an aspect ratio of one has better performance on aerodynamic drag.The area,opening angle and number of plates are basically positively correlated with the total aerodynamic drag of the target car and plate.Arr anging plates at the downstream of the vehicle is a good method of raising total aerodynamic drag.Within the range of plate parameter design in this paper,by using orthogonal design of experiment and the method of range analysis and analysis of variance,the influence degrees of plate parameters on aer odynamic dra g ar e determined,and the order is n umber,ar ea and opening angle of plate.The research results provide theoretical support for the design and safe operation of high-speed trains with aerodynamic braking plates.

高速S-CO_(2)向心透平几何参数优化及变工况特性分析

透平是热力循环中实现热功转换的核心设备,优化透平几何参数以改善气动性能,是提升系统热效率的关键。该文以面向某船舶主机烟气余热利用的超临界二氧化碳布雷顿循环透平设计参数为基础,给出向心透平主要几何参数,采用耦合CO_(2)真实物性参数的CFX仿真方法,分析几何参数动、静叶包角以及叶轮出口几何角对透平性能的影响规律并进行参数优化,进一步研究非设计工况下的透平运行特性。结果表明:增大静叶包角会使动叶前缘出现扰动涡流并减少余速损失,增大叶轮出口几何角,动叶包角对透平效率的影响规律不变,但效率峰值点会沿动叶包角减小的方向移动;动、静叶包角和叶轮出口几何角分别为49°、21.5°、25°时透平设计点总-静等熵效率高达87.99%,相比优化前,提高0.54个百分点;透平偏离设计点±20%工况下等熵效率大于80%。结果可为超临界二氧化碳高速向心透平设计提供一定参考。

基于飞行实测载荷的副翼操纵导数识别

某型飞机横向操纵时副翼和扰流板会耦合偏转实现飞机的滚转运动,现有气动力参数辨识方法无法单独识别出副翼和扰流板的操纵导数。基于飞机控制律设计逻辑和滚转运动时结构的受载特点,提出一种基于飞行实测载荷的副翼操纵导数识别方法。通过实测机动飞行中机翼各测载剖面的结构载荷并结合剖面外结构质量与加速度分布,提出了机动飞行中机翼气动载荷的测量方法;结合飞机横向操纵瞬时滚转力矩平衡方程和操纵面偏转逻辑,推导了滚转改出时副翼操纵导数识别过程,提出了基于机翼实测载荷的副翼操纵导数识别方法;基于前述方法开展了副翼操纵导数识别,并分析了不同马赫数对副翼操纵导数的影响。研究表明,基于飞行实测载荷能够进行副翼操纵导数识别,而且同一马赫数下副翼操纵导数识别结果集中度较好,随着马赫数的增加,副翼操纵效能将会降低。飞行载荷实测结果可用于气动参数辨识工作中。

参数耦合下风力发电机叶片机械颤振检测研究

受气候、风速等因素影响,会使风力发电机叶片的运行条件发生较大变化,增加了颤振检测的难度。为此,该文提出参数耦合下风力发电机叶片机械颤振检测方法。建立风力发电机叶片结构模型,推导结构动力学方程,并利用优化后的参数耦合算法对其求解,获取非稳态气动载荷,通过动力学模型反馈得到叶片的结构响应和振动情况;构建非稳态气动降阶模型,采用能量法分析叶片的结构响应与气动载荷的时域或频域,计算能量交换角度,确定叶片的颤振程度,实现颤振检测。实验结果表明,该方法气动阻尼系数计算结果准确、检测正确率高、计算时间短。

KJS-400型对旋风机性能分析及改进

为提高KJS-400型对旋风机的除尘效率,通过对旋风机的一、二级叶轮轴向距离、输入压力及不同叶片形式进行单因素实验。为了方便更直观地观察改变不同参数对风机处理风量产生的影响,并获得优化方案并仿真验证,将体积流率作为评价指标。体积流率越大,证明单位时间内风机处理的风量越多。利用ANSYS中的Fluent模块对风机运转方式以及内外流场进行仿真,得到风机内流场的初始流动状态和进风量。再对有影响的参数采用控制变量法进行改进调试,利用单因素实验和正交实验确定KJS-400型对旋风机的最佳设计参数,从而提高对旋风机的除尘效率。

风雨场中汽车乘员舱气动噪声声品质预测模型研究

为研究雨天行驶时汽车的声品质,对风雨场中汽车乘员舱气动噪声信号进行声品质客观参量计算和主观评价,并对二者进行了相关分析。采用基于改进鲸鱼优化算法的反向传播(IWOA-BP)算法,以响度、粗糙度、抖动度、语音清晰度、语言干扰度和声压级6个客观参数为输入,以主观评分作为输出,建立预测模型,并与传统的反向传播(BP)神经网络预测模型和鲸鱼优化算法-反向传播(WOA-BP)预测模型进行了对比。结果表明,BP、WOA-BP、IWOA-BP算法的平均绝对百分比误差分别为28.33%、6.35%和2.82%,证明了基于IWOA-BP算法建立的风雨场中汽车乘员舱气动噪声声品质预测模型精度更高,效果更好。

基于MPL-CS自适应反步法的过失速机动控制

超机动能力仍是未来飞机的重要性能指标,而过失速机动控制的效果将成为决定近距空战胜负的关键。本文提出了一种基于最小参数学习和布谷鸟搜索(MPL-CS)的自适应反步法的过失速机动控制方法,以解决先进布局飞机过失速机动中严重的非线性、耦合性和迟滞性等导致的鲁棒性差和控制精度低等问题。首先,基于一套完整的先进布局飞机缩比模型大振幅振荡风洞试验数据,在给定的建模精度目标下,通过改进极限学习机(ELM)方法,建立了大迎角下先进布局飞行器精确的非定常气动模型。其次,设计了一种基于MPL的自适应反步法,以减少需要优化的参数数量。在不确定性和模型扰动的影响下,结合串接链分配方法完成了分配设计。基于CS方法对MPL下自适应反步控制律的关键参数进行了优化。最后,经典的眼镜蛇机动仿真结果表明,该方法的控制精度高于传统的基于MPL的自适应反步方法,且充分考虑了工程的实际需求,控制精度高、鲁棒性强。该方法为未来先进布局飞机的过失速机动控制提供了理论支撑和技术路径。

A practical filter error method for aerodynamic parameter estimation of aircraft in turbulence

It is common for aircraft to encounter atmospheric turbulence in flight tests.Turbulence is usually modeled as stochastic process noise in the flight dynamics equations.In this paper,parameter estimation of nonlinear dynamic system with both process and measurement noise was studied,and a practical filter error method was proposed.The linearized Kalman filter of first-order approximation was used for state estimation,in which the filter gain,along with the system parameters and the initial states,constituted the parameter vector to be estimated.The unknown parameters and measurement noise covariance were estimated alternately by a relaxation iteration method,and the sensitivities of observations to unknown parameters were calculated by finite difference approximation.Some practical aspects of the method application were discussed.The proposed filter error method was validated by the flight simulation data of a research aircraft.Then,the method was applied to the flight tests of a subscale aircraft,and the aerodynamic stability and control derivatives were estimated.All the estimation results were compared with the results of the output error method to demonstrate the effectiveness of the approach.It is shown that the filter error method is superior to the output error method for flight tests in atmospheric turbulence.

双轴燃气轮机启动过程的动态建模与参数影响分析

为了对高度非线性的双轴燃气轮机启动过程进行模拟,在稳态模型中加入燃机动态方程,研究了燃气轮机启动过程的气动参数变化规律。首先,结合压气机、燃烧室、燃气涡轮、动力涡轮及空气系统等热力学模块,建立了燃气轮机启动过程的稳态工作模型;考虑低转速的部件特性,给出了燃气发生器和动力涡轮的转子动态方程,并利用改进欧拉法进行高效迭代求解,实现燃气轮机从启动到慢车稳定运行的动态仿真模拟。其次,在大气温度288.15K、大气压力101.325kPa的环境条件,以及给定供油规律和启动机功率特性下,分析了燃气发生器转速、动力涡轮转速、排气温度及燃气发生器转子剩余功率等随时间的变化规律。最后,在仿真模型中输入某型双轴燃气轮机的相关数据,开展仿真模型与试验数据的对比分析研究。研究结果表明,仿真结果和试验数据在整体趋势上符合度较好,即该模型具有较高的仿真精度,可以对工程设计、试验起到很好的指导作用。

涵道螺旋桨气动特性的CFD模拟及结构参数影响分析

涵道螺旋桨的气动特性对涵道飞行器的动力性能有直接影响。对影响涵道气动特性的结构参数进行量化,采用单一变量法,对具有不同桨尖间隙、唇口半径、桨盘安装位置、涵道扩散角的涵道模型进行了计算流体力学(CFD)仿真研究,通过对流场结构及升力特性进行对比分析,得到了涵道螺旋桨结构参数对增升特性的影响规律。