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Dynamic temperature prediction of electronic equipment under high altitude long endurance conditions 总被引:1,自引:1,他引:0
Unmanned Aerial Vehicle (UAV) is developing towards the direction of High Altitude Long Endurance (HALE). This will have an important influence on the stability of its airborne electronic equipment using passive thermal management. In this paper, a multi-node transient thermal model for airborne electronic equipment is set up based on the thermal network method to predict their dynamic temperature responses under high altitude and long flight time conditions. Some relevant factors are considered into this temperature prediction model including flight environment, radiation, convection, heat conduction, etc. An experimental chamber simulating a high altitude flight environment was set up to survey the dynamic thermal responses of airborne electronic equipment in a UAV. According to the experimental measurement results, the multi-node transient thermal model is verified without consideration of the effects of flight speed. Then, a modified way about outside flight speed is added into the model to improve the temperature prediction performance. Finally, the corresponding simulation code is developed based on the proposed model. It can realize the dynamic temperature prediction of airborne electronic equipment under HALE conditions. 相似文献
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Based on the acoustic mapping, a prediction model for the ground noise radiated from an in-flight helicopter is established. For the enhancement of calculation efficiency, a high-efficiency second-level acoustic radiation model capable of taking the influence of atmosphere absorption on noise into account is first developed by the combination of the point-source idea and the rotor noise radiation characteristics. The comparison between the present model and the direct computation method of noise is done and the high efficiency of the model is validated. Rotor free-wake analysis method and Ffowcs Williams-Hawkings (FW-H) equation are applied to the aerodynamics and noise prediction in the present model. Secondly, a database of noise spheres with the characteristic parameters of advance ratio and tip-path-plane angle is established by the helicopter trim model together with a parametric modeling approach. Furthermore, based on acoustic mapping, a method of rapid simulation for the ground noise radiated from an in-flight helicopter is developed. The noise footprint for AH-1 rotor is then calculated and the influence of some parameters including advance ratio and flight path angle on ground noise is deeply analyzed using the developed model. The results suggest that with the increase of advance ratio and flight path angle, the peak noise levels on the ground first increase and then decrease, in the meantime, the maximum Sound Exposure Level (SEL) noise on the ground shifts toward the advancing side of rotor. Besides, through the analysis of the effects of longitudinal forces on miss-distance and rotor Blade-Vortex Interaction (BVI) noise in descent flight, some meaningful results for reducing the BVI noise on the ground are obtained. 相似文献
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基于光伏组件产生功率模型,研究了太阳能飞机中飞行速度、高度、时间及区域等状态参数影响组件性能的规律。以单晶硅组件及Xihe太阳能飞机为研究对象,当飞机飞行速度增加时,组件产生的功率随之增加但趋于饱和。原因在于速度的增加能有效降低组件的表面温度,但提升是有限的。飞机所需的功率随飞行速度呈现指数增加,且组件产生的功率与飞机所需的功率有能量平衡点。组件产生的功率随飞行高度的增加而增加,但有饱和的趋势。原因在于,当飞行高度上升,大气温度随之下降,组件表面温度下降;同时海拔越高,大气密度和大气通透率越大,太阳辐射增加,从而组件产生的功率增加了;饱和的原因在于组件本身性能的限制。一天之中,组件产生的功率基本以太阳时12点为中心左右近似对称,中午最强;一年中组件性能在夏季最强,冬季最弱。原因在于组件性能主要由所受太阳辐射决定。随着纬度的增加,组件产生的功率减小。原因在于,纬度越高,太阳高度角越小,组件所能接受到的太阳辐射也就越小;纬度越低,组件总产生功率越高且平稳。纬度低的地区更适合太阳能飞机的飞行。该文为太阳能飞机的能量分配、长时间驻空提供一定的帮助。 相似文献
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There appears to be concern among some people about the possible effects of cosmic radiation on everyday life. The amount
of cosmic radiation that reaches the Earth and its environment is a function of solar cycle, altitude and latitude. The possible
effect of naturally occurring cosmic radiation on airplane crews and space flight personal is a subject of current study.
This paper discusses the variables controlling the cosmic ray flux in the atmosphere and describes models and software that
have been developed that provide quantitative information about the cosmic radiation exposure at flight altitudes. The discussion
is extended to include the cosmic radiation exposure to manned spacecraft.
This revised version was published online in August 2006 with corrections to the Cover Date. 相似文献
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《中国航空学报》2016,(5):1367-1377
A systemic and validated model was developed to predict ultraviolet spectra features from the shock layer of near-space hypersonic vehicles in the ‘‘solar blind" band region. Computational procedures were performed with 7-species thermal non-equilibrium fluid mechanics, finite rate chemistry, and radiation calculations. The thermal non-equilibrium flow field was calculated with a two-temperature model by the finite volume technique and verified against the bow-shock ultra-violet(BSUV) flight experiments. The absorption coefficient of the mixture gases was evaluated with a line-by-line method and validated through laboratory shock tube measurements. Using the line of sight(LOS) method, radiation was calculated from three BSUV flights at altitudes of 38,53.5 and 71 km. The investigation focused on the level and structure of ultraviolet spectra radiated from a NO band system in wavelengths of 200–400 nm. Results predicted by the current model show qualitative spatial agreement with the measured data. At a velocity of 3.5 km/s(about Mach11), the peak absolute intensity at an altitude of 38 km is two orders of magnitude higher than that at 53.5 km. Under the same flight conditions, the spectra structures have quite a similar distribution at different viewing angles. The present computational model performs well in the prediction of the ultraviolet spectra emitted from the shock layer and will contribute to the investigation and analysis of radiative features of hypersonic vehicles in near space. 相似文献
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As one of the promising configurations of the next generation of commercial aircraft,research on departure characteristics of the Blended-Wing-Body(BWB) is of great signification to safe flight limits. A three-degree-of-freedom(3-DOF) virtual flight test in a wind tunnel has been implemented for a candidate configuration to predict the departure characteristics. The support mechanism, the test model and the control law of the virtual flight test are introduced. In order to show the relationship ... 相似文献
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基于飞行仿真平台的相关坐标变换模型 总被引:2,自引:2,他引:0
李莹 《沈阳航空工业学院学报》2008,25(4)
飞行力学中相关的飞行器运动方程都是在地面坐标系中建立的,地面坐标系的前提假设"平面大地"与地球表面具有曲率不符,经纬度能真实反映飞行器的飞行情况,但不能直接运用于飞行器运动方程.针对以上情况,提出了能够运用于地面坐标与经纬度相互转换的模型.在飞行仿真平台上,由飞行器运动方程建立相关的飞行机动动作模型,再由提出的坐标变换模型将运动方程中的相关参数转换为经纬度.实验结果表明,坐标变换模型是合理的,具有实用性,能运用于相关的飞行仿真平台中. 相似文献
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针对红外系统实时跟踪捕获高速飞行弹箭目标的关键问题,提出了一种用于求解其全弹道动态红外辐射(IR)特性的方法.以典型155mm口径无控弹箭为研究对象,基于Simulink建立了模块化的6自由度(DOF)刚体弹道仿真模型,数值计算并分析了弹道诸元的变化规律.应用热网络法建立了弹体表面耦合换热动态热辐射场的物理模型,推导了弹箭高速旋转飞行的气动加热计算模型,并利用蒙特卡洛(M-C)法考虑了环境热辐射的影响.运用Runge-Kutta法耦合求解节点热平衡方程组,得到了动态气动表面传热系数、温度场以及红外辐射场的分布规律,对比分析了目标在整个飞行过程、不同部位、不同波段内的红外辐射特征.结果表明:目标发射后,其表面温度迅速升高,越靠近弹头部,温度升高速率越快,峰值温度越高;在飞行前20s内,其红外辐射特征明显;随着飞行速度衰减,热量散失较快,辐射强度较弱,且主要集中于8~14μm波段. 相似文献
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共轴刚性旋翼直升机上下旋翼间距小,旋翼间气动干扰较为复杂,影响飞行动力学特性。针对这一问题,利用涡环单元动态尾迹方法构建了共轴旋翼气动力模型,通过与风洞试验结果比对说明该模型能够准确地计算存在气动干扰时共轴旋翼的气动力特性。以该共轴旋翼气动力模型为基础,建立了共轴刚性旋翼直升机飞行动力学模型,并以XH-59A直升机为研究对象,计算了前进比为0~0.4时的配平特性。通过与飞行试验数据的比对发现:该飞行动力学模型与飞行试验结果比对良好;且模型计算速度较快。通过对配平结果以及旋翼尾迹运动的分析发现:共轴刚性旋翼直升机旋翼间气动干扰会增加悬停和低速前飞时的配平总距和总距差动;低速前飞时的纵向周期变距负梯度现象是由于旋翼间气动干扰与刚性旋翼挥舞运动特性叠加而造成的。 相似文献
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系统地建立了含湍流的三维低空风切变模型,并综合分析了其对直升机飞行安全的威胁。建立了微下击暴流风场及大气湍流场组合的风切变模型,在不增加计算量的前提下,选取特征点发展直升机飞行动力学模型,有效捕捉了风切变的切变特性,提高了在风场中的动态响应计算精度。模型配备姿态保持功能的控制增稳系统已符合一般直升机的飞行状态,并改善机体响应。根据风速分布的特点,选取不同飞行速度、不同风场位置进行飞行仿真,定性地对比分析状态量变化与风场对应关系,并且以垂向通道为例,从动力学角度分析验证了响应的理论计算表达式。结果表明:湍流主要导致高频姿态角响应,风切变对飞行状态量变化占主导作用,且垂向风是引起威胁的主要因素,据此提出危险风场规避建议。 相似文献
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结冰条件下人-机-环系统的飞行风险概率 总被引:1,自引:0,他引:1
以结冰条件下的飞行风险量化概率为研究对象,基于蒙特卡罗飞行仿真实验对结冰条件下人-机-环系统的耦合特性进行了分析,并获取了飞行参数极值样本。构建了飞行风险发生的判定条件;对飞行参数极值样本进行了统计特性分析,验证了其厚尾分布特征。一维分布类型辨识结果表明广义极值分布对相对速度和迎角极值的描述精度最高。为描述二维变量对相关性的各自影响程度,提出了一种新的双参数变权重Copula模型;辨识结果表明该Copula模型能以较高的精度通过假设检验。相关性分析的结果表明相对速度和迎角同时出现极大值和极小值的概率较大。基于二维极值样本的Copula分布模型求出了不同结冰程度下的飞行风险概率值,探讨了飞行风险的非线性增长趋势。 相似文献
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针对某型无人直升机无铰式旋翼技术验证和飞行试验需求,建立了能够用于实时仿真的非线性飞行动力学模型,并基于经典PID控制算法完成了飞行控制律设计。为验证理论模型准确性和控制参数合理性,相继开展了盘旋飞行和大速度飞行的半物理仿真和飞行试验,并基于飞行试验控制效果评估完成了部分控制参数的优化设计。数据分析表明:半物理仿真和飞行试验的时域响应和配平特性均吻合较好,验证了非线性飞行动力学模型的准确性;飞行试验中无人直升机姿态和速度响应均能够较好地跟踪其设定值,所设计的飞行控制参数能够满足某型无人直升机稳态飞行控制要求。 相似文献
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根据笔者30余年来飞行试验研究的实践,从实际飞行的角度简要综述了影响飞行安全的大迎角过失速机动、超低空重载空投、飞行器突发故障和无人机控制方法研究。描述了操纵稳定性飞行试验获取飞机模型的手段和通常飞行控制器设计对模型的近似,给出了8个飞行鲁棒控制的研究问题;对超低空重载空投控制方法进行了描述,并给出了飞行器出现故障时突变模型和容错控制方法;同时,描述了测量对飞行控制特别是对保障无人机飞行安全的重要性,指出了飞行控制方法研究存在的部分问题,并建议有关高校研究单位从稳定性很好的四旋翼转向固定翼或单旋翼战术无人机等高层次研究。 相似文献