共查询到20条相似文献,搜索用时 15 毫秒
1.
The statement and a technique for solving a problem of parametric synthesis and rational choice of structural parameters for a stationary multichannel flow-type aerometric receiver using the results of the experiment being planned are clarified. The scheme of a design model and a receiver structure that provide an increase in noise immunity and extension of working velocities in the helicopter air data system are described. 相似文献
2.
The structural and functional scheme of helicopter air data system based on a stationary combined aerometric receiver using
the aerometric field information of the main rotor vortex column is considered. According to the algorithms of information
signal formation, the requirements to metrological characteristics of primary information sensors for the measurement channel
system are substantiated. 相似文献
3.
N. N. Makarov A. A. Porunov V. V. Soldatkin V. M. Soldatkin 《Russian Aeronautics (Iz VUZ)》2008,51(2):188-197
In this paper, a problem of measuring the altitude-speed helicopter performance in the range of low and near-zero flight velocities is considered. The structural functional scheme of the omnidirectional helicopter air data system based on the stationary aerometric multichannel transducer (AMT) as well as the jet-convective measuring channels is shown and algorithms for the formation of the system output signals are presented. In order to extend the lower bound of operating speeds, it is proposed that the omnidirectional system be integrated with the aeromechanical measuring computer system that realizes the VIMI method with Luenberger’s observer. Also given is the algorithm support and the accuracy of the integrated system operation is estimated. 相似文献
4.
A functional diagram of the air data system and a structural scheme of the air data sensor are described. The special features of generating and processing the air data of aerometric and ion-tagging measurement channels at parking, takeoff and landing modes of the helicopter operation are examined. 相似文献
5.
Features of constructing and information processing algorithms for the system of air signals of an aircraft with the stationary non-protrusive flow receiver, built on the basis of ion-beacon sensor of aerodynamic angle and true airspeed, are disclosed. 相似文献
6.
E. O. Ariskin A. V. Nikitin V. V. Soldatkin V. M. Soldatkin 《Russian Aeronautics (Iz VUZ)》2015,58(4):454-460
The problem and features of measuring the speed and the direction angle of the wind vector relative to the longitudinal helicopter axis during parking, starting and takeoff-landing modes by onboard means are considered. The construction principles, information processing algorithms and advantages of onboard system for measuring the wind vector parameters based on ion-beacon and aerometric measuring channels, are disclosed. 相似文献
7.
高位垂直进气转静系旋转盘腔流场的实验 总被引:3,自引:1,他引:3
利用粒子图像测速技术(简称PIV)对高位垂直进气的转静系旋转盘腔流场进行了实验研究.该盘腔由一个旋转盘、一个静止盘及静止的外围盘罩组成.实验结果表明:PIV粒子成像技术可以应用于旋转盘腔结构的流场测试, 在本实验的工况范围内, 大部分区域的流动已为湍流, 两盘间的流动结构明显具有Batch-elor流型的特点, 转盘和静盘两个表面附近形成各自独立的边界层, 两边界层之间有一个旋转核心, 核心区内旋流系数β比大间隙封闭系统湍流流动时旋流系数的值0.43要小.流量系数和旋转雷诺数的变化对旋流系数β的影响较小, 但转静间隙的变化对β的影响较为显著. 相似文献
8.
A methodology of creating a loading imitation model of a single-rotor helicopter with artificial neural network algorithms is considered. Stages of creation, the structure, and an algorithm of searching for an optimal neural networks configuration of loading imitation model are presented. 相似文献
9.
V. V. Soldatkin 《Russian Aeronautics (Iz VUZ)》2009,52(4):455-462
The principles of construction and algorithms for processing informative signals of the aerometric system for measuring low
helicopter airspeeds are considered; a stationary spherical pitot tube was used to record the angular position and parameters
of the resultant incoming airflow from the main rotor vortex column. The aerodynamic and kinematic distortions introduced
by an induced vortex column flow and helicopter rotation are taken into account. 相似文献
10.
11.
E. S. Efremova 《Russian Aeronautics (Iz VUZ)》2016,59(2):243-248
This paper considers the purpose, principles of construction, algorithms of generating output signals and the functional diagram of a simulator of aircraft air signals that is built based on the vortex sensor of aerodynamic angle and true airspeed. 相似文献
12.
In this paper, a problem of ensuring the helicopter flight safety in off-optimum situations is considered. We describe the most typical critical regimes and flight limitations imposed on the helicopter motion parameters. Also presented are some dependences that determine the operating regime limits with respect to the basic flight parameters of the critical flight regimes warning system. 相似文献
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14.
V. V. Soldatkin 《Russian Aeronautics (Iz VUZ)》2008,51(3):305-313
The special features of construction, a model and the results of simulating an aeromechanical system for calculation of true helicopter airspeed vector components are considered; the system is based on the solution of equations for an “immobile” helicopter with the use of the Luenberger observer. It is proposed that the aeromechanical system be integrated with the system for measuring low helicopter airspeed on the basis of a stationary multichannel aerometric transducer. 相似文献
15.
V. M. Soldatkin A. A. Arkhipov V. A. Olaev A. A. Uglov 《Russian Aeronautics (Iz VUZ)》2012,55(2):184-191
We consider the function, the problems being solved and the construction principles for a starting system of warning the critical regimes for a single-rotor helicopter at parking, taxiing and maneuvering on the ground, takeoff and landing as well as at descending and hovering regimes. The structural-functional scheme and the algorithms of system channel warning are presented. 相似文献
16.
We consider the peculiarities of constructing and the algorithms of primary information processing for a starting system of measuring the value and direction of the wind velocity vector during parking, in moving and maneuvering on the ground surface. Also the components of the true airspeed vector at the takeoff/landing and hovering regimes are considered. 相似文献
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18.
用多重网格方法计算旋翼跨声速无粘流场 总被引:3,自引:2,他引:3
发展了一种加快悬停旋翼无粘流场计算收敛速度的多重网格方法。由于悬停旋翼流场中存在不可压区域,同时旋翼尾涡系统的发展需要较长的时间,使得旋翼流场的收敛速度远低于固定翼流场,因此研究旋翼流场的多重网格算法具有重要意义。空间离散格式采用了中心有限体积方法,时间推进应用了五步龙格-库塔法。采用3层网格的V循环,对一跨声速悬停旋翼无粘流场进行了数值计算。计算结果表明:尽管多重网格方法对旋翼流场的加速收敛作用不如对固定翼流场的加速收敛效果,但是多重网格方法仍然可以显著地加快旋翼流场收敛。 相似文献
19.