The unsteady flow as thrust vectoring nozzle deflecting dynamically is investigated . the method of calculating the unsteady flow in the nozzle is given and the flow of the nozzle in the maximum power setting and maximum a / b power setting of the engine is calculated 研究了矢量喷管动态偏转过程中气流的非定常流动和矢量喷管非定常流动计算方法，计算了矢量喷管在发动机某中间状态和加力状态下的非定常流场。
More than 200 different condition 3d viscosity steady flow fields in the thrust vectoring nozzle at different nozzle pressure ratio and different nozzle area ratio and different geometric defected angle is calculated by the program developed . and the related performance parameters are acquired by numerical simulation 利用该程序计算了某矢量喷管在不同的压比、面积比和几何偏转角下的200多种三维有粘流场，获得了矢量喷管的性能数据。
Thrust vectoring is the key technique for the modem fighter with agility and post - stall maneuver ability and good flight quality . and now it is the necessary technique for the fourth generation fighter and hot technique for the performance improvement for the third generation fighter 推力矢量技术是现代战机具有敏捷性、过失速机动能力、良好的飞行品质的关键技术，其已成为第四代战斗机的必备技术和第三代战斗机改型的热门技术，得到了越来越多的重视。
And establishing the model of the thrust vectoring nozzle is the base for researching thrust vectoring technique and engine performance with vectoring nozzle , especially the integration of flight and propulsion system control ( ifpsc ) . so thrust vector modeling is very important and meaningful 矢量喷管是实现推力矢量的关键部件，建立其数学模型是推力矢量技术尤其是开展带矢量喷管的发动机研究以及飞推一体化综合控制研究的基础，具有十分重要的意义。
The common map is scanned into grid map , and then vectored in mapinfo . after vectoring , vector data are matched and the spatial coordinate data of resident points , water system and other data are gained . the coordinate of reference points in the freeway are gathered by gps , then after data processing , coordinate transition , data inputting , it turn into the freeway graph , which composes the freeway electronic map with the materials subsidiary to the freeway 将普通纸质地图经过扫描生成栅格地图，然后在mapinfo环境下进行矢量化生成矢量化地图，经过矢量化数据配准，确定居民点、水系等物系的空间坐标数据；利用gps采集的高速公路控制点坐标，经过数据处理、坐标转换、录入，最后生成高速公路图层，和上述高速公路附属物共同构成了完整的高速公路电子地图。
Concentrating on the technology of raster to vector conversion , the paper begins with an analysis of the process of raster to vector conversion , followed by the analysis , comparison , and realization of the algorithms in all stages of raster to vector conversion , including scanning , image binarizing , noise - reducing , separation of text from graphics , line vectoring , arc vectoring , as well as an improvement of several algorithms 本文对光栅图形矢量化技术进行了探讨，首先分析了光栅图形矢量化的过程，然后分别对工程图纸的扫描输入、二值化、噪声消除、图文分离、直线矢量化、圆矢量化等各个阶段的算法进行了分析、比较和实现，并对部分算法进行了改进。
The mechanism of two possible ways of thrust vectoring control : force and moment control are analyzed . the effects of thrust vectoring on aircraft supersonic performance , take - off and landing performance , low speed and high angle of attack performance are studied . the air combat effectiveness of thrust vectoring control and post - stall maneuvers are also analyzed 5 、分析了推力矢量的两种应用方式：力控制和力矩控制的机理，研究了推力矢量对飞机超音速性能、起降性能、低速大迎角性能的影响，讨论了推力矢量与过失速机动对空战效能的影响。
The calculating results of steady flow and unsteady flow in the nozzle are compared . and it proves that both the results of the steady flow and the results of the unsteady . flow are uniform basically . this is very valuable because it is convenient to study the flow in the vectoring nozzle by steady hypothesis or steady test 分析比较了定常流动计算结果和非定常流动计算结果，得出了定常流动计算结果和非定常计算结果的基本一致性，从而为工程通过定常计算或试验来研究矢量喷管以及建立其数学模型提供了依据。
Cfd is also used to get the data of performance parameters of the nozzle at different nozzle pressure ratio , different nozzle area ratio and different geometric defected angle . the theory of function approximation is used to establish the transient model of thrust vectoring with the data calculated 本文通过cfd计算获得矢量喷管的性能参数，如流量系数、推力系数以及有效推力矢量角等与矢量喷管压比、面积比以及几何偏转角之间的关系数据，并利用函数逼近理论建立了矢量喷管的动态数学模型。
3 . the aerodynamic characteristics and mechanism of flight dynamics under the condition of post - stall maneuvers are discussed , and then the inputs of adaptive fuzzy system are determined . using the control law and nonlinear motion equations built above , some typical post - stall maneuvers are simulated and the effects of thrust vectoring on post - stall maneuver are analyzed 3 、讨论了过失速机动条件下的空气动力特性和飞行力学机理，在此基础上对自适应模糊逻辑系统的输入进行了分析，确定了自适应模糊逻辑系统的输入。
