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A general method for closed-loop inverse simulation of helicopter maneuver flight 被引量:3
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作者 Wei WU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2017年第6期1799-1808,共10页
Maneuverability is a key factor to determine whether a helicopter could finish certain flight missions successfully or not. Inverse simulation is commonly used to calculate the pilot controls of a helicopter to comple... Maneuverability is a key factor to determine whether a helicopter could finish certain flight missions successfully or not. Inverse simulation is commonly used to calculate the pilot controls of a helicopter to complete a certain kind of maneuver flight and to assess its maneuverability.A general method for inverse simulation of maneuver flight for helicopters with the flight control system online is developed in this paper. A general mathematical describing function is established to provide mathematical descriptions of different kinds of maneuvers. A comprehensive control solver based on the optimal linear quadratic regulator theory is developed to calculate the pilot controls of different maneuvers. The coupling problem between pilot controls and flight control system outputs is well solved by taking the flight control system model into the control solver. Inverse simulation of three different kinds of maneuvers with different agility requirements defined in the ADS-33 E-PRF is implemented based on the developed method for a UH-60 helicopter. The results show that the method developed in this paper can solve the closed-loop inverse simulation problem of helicopter maneuver flight with high reliability as well as efficiency. 展开更多
关键词 CLOSED-LOOP Flying quality Helicopters Inverse simulation maneuver flight
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Analysis of Maneuvering Flight of an Insect 被引量:1
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作者 SunadaS. WangH. +1 位作者 ZengLijiang KawachiK. 《Journal of Bionic Engineering》 SCIE EI CSCD 2004年第2期88-101,共14页
Wing motion of a dragonfly in the maneuvering flight, which was measured by Wang et al. [1]was investigated. Equations of motion for a maneuvering flight of an insect were derived. These equations were applied for an... Wing motion of a dragonfly in the maneuvering flight, which was measured by Wang et al. [1]was investigated. Equations of motion for a maneuvering flight of an insect were derived. These equations were applied for analyzing the maneuvering flight. Inertial forces and moments acting on a body and wings were estimated by using these equations and the measured motions of the body and the wings. The results indicated the following characteristics of this flight: (1)The phase difference in flapping motion between the two fore wings and two hind wings, and the phase difference between the flapping motion and the feathering motion of the four wings are equal to those in a steady forward flight with the maximum efficiency. (2)The camber change and the feathering motion were mainly controlled by muscles at the wing bases. 展开更多
关键词 insect flight maneuvering flight equations of motion
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Numerical Study on Aerodynamic Performance of CK Drone Aircraft Air Inlet in Maneuvering Flight
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作者 CAO Guangzhou LI Bo +1 位作者 LIANG Shibo TAN Hongming 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2020年第5期739-749,共11页
In view of the engineering background that CK drone aircraft needs modification and upgrading to improve its maneuvering performance,numerical research and analysis of air inlet aerodynamic performance are carried out... In view of the engineering background that CK drone aircraft needs modification and upgrading to improve its maneuvering performance,numerical research and analysis of air inlet aerodynamic performance are carried out.Firstly,based on the introduction of the theoretical knowledge involved in aircraft maneuvering flight,parameters such as aircraft attitude and engine mass flow etc.required for the aerodynamic performance calculation of CK drone aircraft air inlet are determined.By analyzing the test data of WP6 engine inlet distortion simulation board,the typical indexes are extracted as the basis for evaluating the air inlet performance of CK drone aircraft.Then,the aerodynamic characteristics of the inlet of CK drone aircraft under different maneuvering conditions are numerically studied,and the total pressure recovery coefficient and pressure distortion index of the outlet section are obtained.Several conclusions and suggestions are formed after the study.When CK drone aircraft flies at positive angle of attack,the inlet has good aerodynamic characteristics,which can meet the requirements of engine intake during high maneuverable flight.In the flight of negative angle of attack,the total pressure loss and pressure distortion at the outlet section of air inlet increase sharply,which cannot guarantee the stable working of the engine.On the premise that the aircraft attitude is satisfied,CK drone aircraft can use three engine thrust states of"Rated","Modified rated"and"Maximum"for high maneuverable flight. 展开更多
关键词 CK drone aircraft high maneuvering flight suspended nacelle inlet total pressure recovery coefficient pressure distortion index
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多源性能约束的无人机可靠动态航路规划算法 被引量:1
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作者 孙淑光 朱晓文 《中国惯性技术学报》 EI CSCD 北大核心 2024年第2期187-195,共9页
为提高无人机动态航路规划的安全性,提出一种基于机载导航系统实际导航性能和无人机机动性能的多源性能约束的改进A^(*)航路规划算法。分析了无人机航路规划系统架构及约束条件,构建了融合无人机最大允许转弯角、导航系统位置不确定度... 为提高无人机动态航路规划的安全性,提出一种基于机载导航系统实际导航性能和无人机机动性能的多源性能约束的改进A^(*)航路规划算法。分析了无人机航路规划系统架构及约束条件,构建了融合无人机最大允许转弯角、导航系统位置不确定度和最短路径的加权启发函数,实现无人机动态航路规划的多约束适应性,最后进行了仿真分析验证。仿真结果表明:在相同的运行环境下,基于性能约束的改进A^(*)算法所规划航路的安全裕度比传统A^(*)算法提高1.8倍,角度变化百分比降低为传统算法的42.4%,航路规划用时缩短28%,所规划航路的安全裕度和无人机机动性能符合度都得到有效改善。 展开更多
关键词 无人机航路规划 位置不确定度 机动性能 航路安全性 航路可行性 改进A^(*)算法
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吸气式高超声速机动飞行样式及其关键技术分析
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作者 段鹏飞 高书亮 +1 位作者 王恩亮 王瀚 《航空兵器》 CSCD 北大核心 2024年第2期99-105,共7页
机动飞行性能是确保吸气式高超声速飞行器实现多种应用的关键能力之一,本文重点对吸气式高超声速飞行器机动能力特点进行研究。首先分析了国外吸气式高超声速飞行器的发展趋势,就其典型机动能力水平和机动样式进行了初步分析,以美国当... 机动飞行性能是确保吸气式高超声速飞行器实现多种应用的关键能力之一,本文重点对吸气式高超声速飞行器机动能力特点进行研究。首先分析了国外吸气式高超声速飞行器的发展趋势,就其典型机动能力水平和机动样式进行了初步分析,以美国当前典型高超声速导弹项目为例,梳理了吸气式高超声速飞行器的典型机动应用样式。在此基础上,从总体设计、气动外形、飞发一体、制导控制、多场耦合等方面,梳理分析了确保和提升吸气式高超声速飞行器机动能力的关键支撑性技术。 展开更多
关键词 高超声速飞行器 吸气式 机动能力 气动外形 飞发一体 制导控制 多场耦合
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ADAPTIVE FLIGHT CONTROL SYSTEM OF ARMED HELICOPTER USING WAVELET NEURAL NETWORK METHOD 被引量:1
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作者 ZHURong-gang JIANGChangsheng FENGBin 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI 2004年第2期157-162,共6页
A discussion is devoted to the design of an adaptive flight control system of the armed helicopter using wavelet neural network method. Firstly, the control loop of the attitude angle is designed with a dynamic invers... A discussion is devoted to the design of an adaptive flight control system of the armed helicopter using wavelet neural network method. Firstly, the control loop of the attitude angle is designed with a dynamic inversion scheme in a quick loop and a slow loop. respectively. Then, in order to compensate the error caused by dynamic inversion, the adaptive flight control system of the armed helicopter using wavelet neural network method is put forward, so the BP wavelet neural network and the Lyapunov stable wavelet neural network are used to design the helicopter flight control system. Finally, the typical maneuver flight is simulated to demonstrate its validity and effectiveness. Result proves that the wavelet neural network has an engineering practical value and the effect of WNN is good. 展开更多
关键词 adaptive control helicopter flight control system dynamic inversion wavelet neural network maneuver flight
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Transient state analysis of a rub-impact rotor system during maneuvering flight
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作者 Jun WANG Yunfei LIU +2 位作者 Zhaoye QIN Liang MA Fulei CHU 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2024年第7期236-251,共16页
Maneuvering flight substantially affects the dynamic behavior of rotors;particularly,such flight may cause rubbing between a rotor and stator,which is one of the most serious damages in aircraft engines.In this paper,... Maneuvering flight substantially affects the dynamic behavior of rotors;particularly,such flight may cause rubbing between a rotor and stator,which is one of the most serious damages in aircraft engines.In this paper,a nonlinear dynamic model for describing the dynamic characteristics of a rub-impact rotor system during maneuvering flight is established based on the Lagrange equations.Subsequently,numerical simulations employing the Newmark method are performed,delving into the detailed discussion of the influence of parameters such as rotational speed and maneuvering flight on the transient and steady-state responses of the rotor system.The effect mechanism of maneuver load and its coupling with rub impact is revealed.The results show that the impact response induced by maneuvering flight is more obvious in the subcritical state than in the supercritical state.The additional stiffness and damping are also induced;in particular,the additional damping has a coupling effect.Moreover,the rub impact imposes an additional constraint on the rotor system,thereby weakening the influence of the maneuver load and becoming the major factor that determines the dynamic behavior of the rotor system at high speeds. 展开更多
关键词 maneuvering flight Rub impact Rotor system Dynamic response Impact response
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Unsteady aerodynamics modeling for flight dynamics application 被引量:13
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作者 Qing Wang Kai-Feng He. +3 位作者 Wei-Qi Qian Tian-Jiao Zhang Yan-Qing Cheng Kai-Yuan Wu 《Acta Mechanica Sinica》 SCIE EI CAS CSCD 2012年第1期14-23,共10页
In view of engineering application, it is practicable to decompose the aerodynamics into three components: the static aerodynamics, the aerodynamic increment due to steady rotations, and the aerodynamic increment due... In view of engineering application, it is practicable to decompose the aerodynamics into three components: the static aerodynamics, the aerodynamic increment due to steady rotations, and the aerodynamic increment due to unsteady separated and vortical flow. The first and the second components can be presented in conventional forms, while the third is described using a one-order differential equation and a radial-basis-function (RBF) network. For an aircraft configuration, the mathematical models of 6- component aerodynamic coefficients are set up from the wind tunnel test data of pitch, yaw, roll, and coupled yawroll large-amplitude oscillations. The flight dynamics of an aircraft is studied by the bifurcation analysis technique in the case of quasi-steady aerodynamics and unsteady aerodynam- ics, respectively. The results show that: (1) unsteady aerodynamics has no effect upon the existence of trim points, but affects their stability; (2) unsteady aerodynamics has great effects upon the existence, stability, and amplitudes of periodic solutions; and (3) unsteady aerodynamics changes the stable regions of trim points obviously. Furthermore, the dynamic responses of the aircraft to elevator deflections are inspected. It is shown that the unsteady aerodynamics is beneficial to dynamic stability for the present aircraft. Finally, the effects of unsteady aerodynamics on the post-stall maneuverability 展开更多
关键词 Unsteady aerodynamics High angle of attack Mathematical model flight dynamics - Bifurcation analysis Post-stall maneuver
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Study on Intelligent Control and 3D Real-time Distributed Animation Simulation for Super-maneuver Attack of the New Generation Fighter 被引量:8
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作者 黎明 姜长生 +1 位作者 叶文青 张立 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2001年第4期235-244,共10页
The super-maneuver flight performance has a very high tactical value, and the development of this tactical value has great significance. A discussion is devoted to the study of intelligent control methods and technolo... The super-maneuver flight performance has a very high tactical value, and the development of this tactical value has great significance. A discussion is devoted to the study of intelligent control methods and technologies of real-time distributed 3-dimensional animation simulation for the super-maneuverable attack of new generational fighter in this paper. A flight control system of super-maneuver is reconstructed by adopting three layers BP neural networks of number 3, and the fire/flight coupler is designed by introducing a fuzzy control rule whose universe of discourse and gain are regulated adaptively on the line. Furthermore, a new method of real-time distributed 3-dimensional animation simulation is put forward, and a real-time distributed 3-dimensional animation simulation tool platform is constructed in this paper. The simulation result is lifelike, perceivable directly and useful. 展开更多
关键词 ANIMATION Computer simulation flight dynamics Fuzzy control Intelligent control maneuverABILITY Neural networks
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SA METHOD FOR PREDICTING THE PERFORMANCE OF DASH STOP MANEUVER OF HELICOPTER
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作者 Chen Renliang Department of Aircraft Engineering, NUAA29 Yudao Street, Nanjing 210016, P. R. China Yao Wei (Nanjing Newspaper Office, Nanjing 210016, P. R. China) 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI 1996年第1期35-41,共7页
The Dash Stop flight at the extreme condition is the primary interest of this study. This paper describes some research on the flight characteristics of helicopter in Dash Stop. A set of equations which govern the Das... The Dash Stop flight at the extreme condition is the primary interest of this study. This paper describes some research on the flight characteristics of helicopter in Dash Stop. A set of equations which govern the Dash Stop is developed. A method which determines the acceleration and deceleration is proposed. Formulas are then developed which relate the aircraft angular rates and attitudes to flight speed, angle of attack and acceleration or deceleration. Finally the DOLPHIN helicopter is taken as an example to calculate its acceleration/deceleration capability, pilot control and aircraft attitudes in space. It is found that the results are reasonable. 展开更多
关键词 HELICOPTER motion equation maneuvering flight flight performance calculation method
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飞机超机动状态动力学特征及对控制系统的挑战 被引量:17
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作者 朱纪洪 张尚敏 +2 位作者 周池军 王向阳 刘凯 《控制理论与应用》 EI CAS CSCD 北大核心 2014年第12期1650-1662,共13页
超机动能力作为第四代战斗机的重要标志性特征,在近距空战中具有极其重要的作用.针对非线性非定常气动效应、强耦合和操纵器异构冗余等超机动状态飞机的基本动力学特征,分析了其非线性气动力/力矩、非定常迟滞效应、参数快时变、惯性耦... 超机动能力作为第四代战斗机的重要标志性特征,在近距空战中具有极其重要的作用.针对非线性非定常气动效应、强耦合和操纵器异构冗余等超机动状态飞机的基本动力学特征,分析了其非线性气动力/力矩、非定常迟滞效应、参数快时变、惯性耦合和推力矢量等因素给控制系统带来的挑战,总结了超机动飞机的非线性非定常气动力建模、飞行控制和控制分配的研究现状,给出了一种基于非线性补偿和气动力模型数据库的鲁棒解耦控制策略,为超机动飞行控制方法的工程应用提供了参考. 展开更多
关键词 超机动 动力学 解耦控制 飞行控制
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飞翼无人机机动飞行航迹优化和自生成方法 被引量:3
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作者 李继广 陈欣 +2 位作者 李亚娟 王鑫 张榕 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2018年第4期536-547,共12页
虚拟机动指令是飞翼无人机机动飞行的基础,是制导回路和控制回路必要的输入。为了生成合理虚拟机动指令,提出了优化基本航路—建立机动数据库—战场信息匹配输出的机动飞行航路生成方法。由于复杂的机动动作可由基本机动动作组合而成,... 虚拟机动指令是飞翼无人机机动飞行的基础,是制导回路和控制回路必要的输入。为了生成合理虚拟机动指令,提出了优化基本航路—建立机动数据库—战场信息匹配输出的机动飞行航路生成方法。由于复杂的机动动作可由基本机动动作组合而成,本文以飞翼无人机基本机动飞行动作为优化研究对象,提出了以飞翼无人机控制量变化率为优化参数、航迹片段建立约束条件的无人机机动航路优化方法。其中,机动飞行控制量变化率体现了无人机控制能力的限制;航迹片段约束体现了航迹准确和操作柔和的要求,并对无人机的筋斗、滚桶、盘旋机动进行了优化计算,介绍了机动数据库建立的方法。最后,以机动目标跟踪和有人机追击为设定进行了仿真,结果显示所提方法有效。 展开更多
关键词 飞翼无人机机动飞行 航迹优化 机动数据库
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基于ATR动力的飞行器性能分析 被引量:2
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作者 李平 柳长安 +1 位作者 何国强 南向谊 《弹箭与制导学报》 CSCD 北大核心 2011年第6期173-175,共3页
空气涡轮冲压发动机(ATR)是一种具有大空域、宽速域特点的新型吸气式组合动力。为了分析这种动力的应用特点,文中首先进行了ATR发动机和某型涡扇发动机性能的对比,然后按相同飞行器平台进行了加速和爬升等基本飞行性能的分析,获得了切... 空气涡轮冲压发动机(ATR)是一种具有大空域、宽速域特点的新型吸气式组合动力。为了分析这种动力的应用特点,文中首先进行了ATR发动机和某型涡扇发动机性能的对比,然后按相同飞行器平台进行了加速和爬升等基本飞行性能的分析,获得了切向过载和经济爬升性等指标的比较结果。结果表明ATR动力可以提升飞行器机动性,扩展飞行包线。 展开更多
关键词 ATR发动机 涡扇发动机 机动性 飞行包线
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直升机机动飞行新分析方法 被引量:4
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作者 吴伟 陈仁良 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2010年第6期680-686,共7页
提出了一种研究直升机机动飞行新的分析方法。不同于以往研究直升机机动飞行的逆解方法,该方法用若干导航参数来描述机动科目,简化了机动科目的数学描述,通过综合运用导航、控制和直升机飞行动力学方法来确定完成飞行品质规范规定的直... 提出了一种研究直升机机动飞行新的分析方法。不同于以往研究直升机机动飞行的逆解方法,该方法用若干导航参数来描述机动科目,简化了机动科目的数学描述,通过综合运用导航、控制和直升机飞行动力学方法来确定完成飞行品质规范规定的直升机机动飞行科目所需的操纵量,提高了研究机动飞行的分析计算效率。以UH 60直升机为例,分别针对ADS-33E-PRF所规定的障碍滑雪机动科目和向心回转机动科目,得到完成机动科目所需的操纵,结果合理。 展开更多
关键词 直升机 机动性 飞行品质 规范
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细长体简谐振动绕流的数值模拟 被引量:1
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作者 李锋 周伟江 +1 位作者 王强 汪翼云 《空气动力学学报》 CSCD 北大核心 1997年第1期114-120,共7页
用数值模拟方法研究了椭圆锥细长体简谐振动(模拟飞行器的曲线机动飞行)非定常过程的流场特性。数值模拟的出发方程是可压缩流的全N-S方程,计算格式为TVD格式。数值模拟中,研究了细长体简谐振动绕流的非定常流场特性、不同振动缩... 用数值模拟方法研究了椭圆锥细长体简谐振动(模拟飞行器的曲线机动飞行)非定常过程的流场特性。数值模拟的出发方程是可压缩流的全N-S方程,计算格式为TVD格式。数值模拟中,研究了细长体简谐振动绕流的非定常流场特性、不同振动缩减频率和压缩性效应的影响,揭示了非定常流场的特性和流动机理。 展开更多
关键词 非定常流 数值模拟 机动飞行 飞行力学
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飞机大攻角空间机动气动力建模研究 被引量:17
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作者 汪清 何开锋 +1 位作者 钱炜祺 毛仲君 《航空学报》 EI CAS CSCD 北大核心 2004年第5期447-450,共4页
准确的气动力模型是大攻角机动仿真与控制等飞行动力学问题研究的基础。针对纵向运动建立的非线性非定常气动力微分方程模型扩展应用于一般空间运动形式,在分析大攻角非定常流动机理和试验数据的基础上,发展了一种多自由度非线性非定常... 准确的气动力模型是大攻角机动仿真与控制等飞行动力学问题研究的基础。针对纵向运动建立的非线性非定常气动力微分方程模型扩展应用于一般空间运动形式,在分析大攻角非定常流动机理和试验数据的基础上,发展了一种多自由度非线性非定常气动力数学模型,并探讨了模型辨识和参数估计问题。用全机构形的大攻角动态风洞试验数据对模型进行的验证表明所发展的气动力模型能够描述大攻角气动力主要的非线性和非定常特性。 展开更多
关键词 空气动力学 气动建模 微分方程模型 大攻角 模型辨识 参数估计
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低动压着舰状态下飞机的操纵特性研究 被引量:30
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作者 王新华 杨一栋 朱华 《飞行力学》 CSCD 北大核心 2007年第4期29-32,36,共5页
低动压着舰状态下飞机的操纵特性下降,导致轨迹角不能跟踪姿态角的变化,从而对着舰安全造成严重影响。首先通过剖析历史上已有的观点,提出研究低动压状态飞机轨迹角响应问题时应全面考虑速度稳定性、轨迹稳定性和机动性。其次对两种动... 低动压着舰状态下飞机的操纵特性下降,导致轨迹角不能跟踪姿态角的变化,从而对着舰安全造成严重影响。首先通过剖析历史上已有的观点,提出研究低动压状态飞机轨迹角响应问题时应全面考虑速度稳定性、轨迹稳定性和机动性。其次对两种动力补偿系统进行了分析,其中速度恒定动力补偿实际上对应速度稳定性和轨迹稳定性,而迎角恒定动力补偿兼具速度稳定性、轨迹稳定性和机动性增强。最后的仿真证实,考虑速度稳定性、轨迹稳定性和机动性的迎角恒定动力补偿是全面的、可行的。 展开更多
关键词 低动压 速度稳定性 轨迹稳定性 机动性 动力补偿
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导弹抗激光毁伤分析 被引量:3
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作者 周旭宜 王清海 《航空兵器》 2011年第4期18-20,34,共4页
高能激光武器的日趋成熟对导弹的生存能力提出了严峻的挑战,发展导弹的抗激光毁伤技术十分必要。本文分析了高能激光对导弹的光学、热学、力学和等离子体等多种毁伤效应,以及导弹可能采取的隐形化、机动飞行、弹体旋转、采用新材料等措... 高能激光武器的日趋成熟对导弹的生存能力提出了严峻的挑战,发展导弹的抗激光毁伤技术十分必要。本文分析了高能激光对导弹的光学、热学、力学和等离子体等多种毁伤效应,以及导弹可能采取的隐形化、机动飞行、弹体旋转、采用新材料等措施。分析表明,这些措施可以有效提高导弹抗激光毁伤能力。 展开更多
关键词 高能激光武器 激光毁伤 热烧蚀 机动飞行 导弹旋转
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超机动飞机非线性建模仿真与操纵特性分析 被引量:5
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作者 谢蓉 王新民 李俨 《计算机仿真》 CSCD 北大核心 2010年第8期18-21,32,共5页
研究建立较为准确的超机动飞机非线性模型,对新型战斗机的研发具有重要意义。在分析超机动飞机非线性特性的基础上,建立了带推力矢量的超机动飞机非线性动态模型,着重分析了气动力、气动力矩以及发动机的建模过程。为改善系统的动态特性... 研究建立较为准确的超机动飞机非线性模型,对新型战斗机的研发具有重要意义。在分析超机动飞机非线性特性的基础上,建立了带推力矢量的超机动飞机非线性动态模型,着重分析了气动力、气动力矩以及发动机的建模过程。为改善系统的动态特性,采用动态逆结合PID的方法设计了超机动飞机在大迎角机动下的控制律,并进行了"眼睛蛇"机动仿真。根据"眼镜蛇"机动的仿真结果,分析了超机动飞机在大迎角飞行时操纵特性,证明了所建立模型的合理性与有效性。 展开更多
关键词 飞行控制 超机动 非线性建模 动态逆 操纵特性
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水平风洞模型自由飞试验技术研究现状及展望 被引量:15
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作者 孙海生 岑飞 +1 位作者 聂博文 刘志涛 《实验流体力学》 EI CAS CSCD 北大核心 2011年第4期103-108,共6页
介绍国外水平风洞模型自由飞试验技术研究现状,阐述水平风洞模型自由飞试验平台的组成、作用与意义,重点展望该试验技术的应用前景。对试验平台中动力相似模型设计加工技术、动力模拟技术、舵机运动控制技术、模型姿态实时精确测量技术... 介绍国外水平风洞模型自由飞试验技术研究现状,阐述水平风洞模型自由飞试验平台的组成、作用与意义,重点展望该试验技术的应用前景。对试验平台中动力相似模型设计加工技术、动力模拟技术、舵机运动控制技术、模型姿态实时精确测量技术、飞行控制系统设计与集成技术等关键技术问题进行分析,对发展该试验技术具有指导作用。完善水平风洞模型自由飞试验技术,把传统风洞试验拓展到流动-飞行-控制一体化试验,有利于全面研究和充分挖掘飞行器的气动性能与控制性能,对新一代飞机器的发展、新概念新技术的工程应用将起到重要的推动作用。 展开更多
关键词 自由飞 风洞试验 飞行控制 系统辨识 过失速机动
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