V—22型侧旋翼机

1982年第5期《航空知识》上有一篇《直升机和“直升飞机”》。此文反对把直升飞机一词代替直升机。如把这两个名词等同起来,就把什么是飞机也弄胡涂了。但是直升飞机还是一个有用的名词。它代表既是飞机又是直升机的一种航空器。 1994年第7期《航空知识》上有一篇《飞机、直升机、直升飞机》。此文说明了这三个名词的区别,并说明了直升飞机可以分为多少种类。     

乌兰乌德Mi-171直升机与中国的救援服务

发生在四川的地震再次证明了直升飞机是执行营救生命、运输物资等救援任务最有效的方式。由于基础设施遭受严重破坏,因此其它运输方式无     

NOVEL RADAR SIGNAL SORTING METHOD BASED ON GEOMETRIC COVERING

With the increase of complexity of electromagnetic environment and continuous appearance of advanced system radars, signals received by radar reconnaissance receivers become even more intensive and complex. There- fore, traditional radar sorting methods based on neural network algorithms and support vector machine （SVM） cannot process them effectively. Aiming at solving this problem, a novel radar signal sorting method based on the cloud model theory and the geometric covering algorithm is proposed. By applying the geometric covering algo- rithm to divide input signals into different covering domains based on their distribution characteristics, the method can overcome a typical problem that it is easy for traditional sorting algorithms to fall into the local extrema due to the use of complex nonlinear equation to describe input signals. The method uses the cloud model to describe the membership degree between signals to be sorted and their covering domains, thus it avoids the disadvantage that traditional sorting methods based on hard clustering cannot deinterleave the signal samples with overlapped param- eters. Experimental results show that the presented method can effectively sort advanced system radar signals with overlapped parameters in complex electromagnetic environment.     

DYNAMIC RESPONSE ANALYSIS OF CARRIER-BASED AIRCRAFT DURING LANDING

In view of the complexity of landing on the deck of aircraft carrier, a systematic model, composed of six- degree-of-freedom mathematic model of carrier-based aircraft, four-degree-of-freedom model of landing gears and six-degree-of-freedom mathematic model of carrier, is established in the Matlab-Simulink environment, with damping function of landing gears and dynamic characteristics of tires being considered. The model, where the car- rier movement is introduced, is applicable for any abnormal landing condition. Moreover, the equations of motion and relevant parameter are also derived. The dynamic response of aircraft is calculated via the variable step-size Runge-Kuta algorithm. The effect of attitude angles of aircraft and carrier movement during the process of landing is illustrated in details. The analytical results can provide some reference for carrier-based aircraft design and main- tenance.     

直升机旋翼空气动力学的发展

本文分两大部分，即旋翼理论分析的发展（认识旋翼）及旋翼浆叶外形的发展（改造旋翼）。在第一部分中，阐述了旋翼滑流理论、叶素理论、涡流理论（其中又包括固定尾迹的经典涡流理论、预定尾迹的半经验涡流理论、自由尾迹的现代涡流理论）和旋翼CDD方法。在第二部分中，讨论了旋翼桨叶的翼型、浆尖形状、扭转角分布等的变化历程。最后，作为总结，提出了旋翼理论分析和浆叶气动外形的四代发展阶段的划分。     

OPTIMIZED STRAPDOWN CONING CORRECTION ALGORITHM

Traditional coning algorithms are based on the first-order coning correction reference model. Usually they reduce the algorithm error of coning axis （z） by increasing the sample numbers in one iteration interval. But the increase of sample numbers requires the faster output rates of sensors. Therefore, the algorithms are often lim- ited in practical use. Moreover, the noncommutivity error of rotation usually exists on all three axes and the in- crease of sample numbers has little positive effect on reducing the algorithm errors of orthogonal axes （x, y）. Considering the errors of orthogonal axes cannot be neglected in the high-precision applications, a coning algorithm with an additional second-order coning correction term is developed to further improve the performance of coning algorithm. Compared with the traditional algorithms, the new second-order coning algorithm can effectively reduce the algorithm error without increasing the sample numbers. Theoretical analyses validate that in a coning environ- ment with low frequency, the new algorithm has the better performance than the traditional time-series and fre- quency-series coning algorithms, while in a maneuver environment the new algorithm has the same order accuracy as the traditional time-series and frequency-series algorithms. Finally, the practical feasibility of the new coning al- gorithm is demonstrated by digital simulations and practical turntable tests     

GAS PATH ELECTROSTATIC SENSOR MONITORING AND COMPARISON EXPERIMENT ON TURBOJET ENGINE

A monitoring and comparison experiment with two types of sensors on a turbojet engine is carried out. Compared with a probe-typed sensor, which is designed successfully before, signals are collected to verify the va- lidity and better feasibility of the circular sensor. According to the signals monitored over 131 h, the typical signals of 125--129 phases are analyzed. The results show that the unusual exhaust particles are carbon depositions from fuel spray nozzle. Therefore, with the electrostatic sensor, early warning can be provided for initial fault condition, as well as real-time reference for the condition-based maintenance.     

OLEOPHOBIC AND HYDROPHOBIC FEATURE EXPERIMENTS OF FLUORINATED HIGH DENSITY POLYETHYLENE

The surface performances of directly fluorinated high density polyethylene （HDPE） are studied with Fourier transform infrared （FT-IR） spectra, scanning electron microscopy （SEM） and contact angle （CA） system. The SEM images show that there is a three-layer structure called the reaction, virgin and boundary layer structure. The depth of fluorinated layer is 5.75 ~m with 1 h fluorination time and 7.86 b~m with 2 h. The depths are 5.46 /~m and 5.07 /~m when fluorine density is 2G and 1~/0, respectively. CA indicates that the HDPE surface property becomes more hydrophobic with the increasing water contact angle from 78.5~ to 104.5~. Oleophobic and hydrophobic features of HDPE are identified by comparison of mass change experiments. It is shown that the in- crement rate of fluorinated HDPE is much lower than that of un-fluorinated HDPE filled in neither distilled water nor jet fuel.     

V-BLAST BASED LDPC-CODED RELAY COOPERATION

An efficient LDPC-coded multi-relay cooperation architecture is proposed based on virtual vertical Bell Labs layered space-time （V-BLAST） processing for uplink communication, where minimum-mean-square-error （MMSE） and BP-based joint iterative decoding based on the introduced muhi-layer Tanner graph are effectively de- signed to detect and decode the corrupted received sequence at the destination. By introducing V-BLAST transmis- sion to the coded multi-relay cooperation, relays send their streams of symbols simultaneously, which increases the data rate and significantly reduces the transmission delay. The theoretical analysis and numerical results show that the new LDPC coded cooperation scheme outperforms the coded non-cooperation under the same code rate, and it also achieves a good trade-off among the performance, signal delay, and the encoding complexity associated with the number of relays. The performance gain can be credited to the proposed V-BLAST processing architecture and BP-based joint iterative decoding by the introduced multi-layer Tanner graph at a receiver-side.     

直升机飞行品质评估数学模型研究

针对飞行品质评估需要，结合建模工作中的经验，讨论了模型复杂度和真实度之间的关系，分析了不同阶次的入流模型和非定常气动模型对结果的影响，考虑了旋翼尾迹对机身的气动干扰作用，并对涡轮轴发动机和飞行控制系统模型在飞行力学模型中的重要作用做了阐述。还地逆仿真方法在飞行品质研究中的应用提出了一些见解。