The software is made up for ship rolling gesture control and random sea wave simulation. The simulation and calculation of fix angle-ratio main/flap fin stabilizer joint control system and variational angle-ratio main/flap fin stabilizer joint control system validate that the latter has better control result and saves a lot of energy.
建立船舶横摇姿态控制和随机海浪数字仿真软件平台，对定转角比襟翼减摇鳍控制系统和变转角比襟翼减摇鳍控制系统分别进行了仿真和能量核算，验证了变转角比襟翼减摇鳍控制系统相对定转角比襟翼减摇鳍控制系统和传统单体鳍控制系统不仅有好的控制效果，而且可以节省大量的能量。
A rotor structure for a rotating wing aircraft having substantially rigid rotor head means and rotor blades or wing means arranged in at least one pair, comprising blade angle bearing means (10, 12, 14, 16) for each rotor blade means, tension bar means (6, 8) operatively interconnecting the rotor blade means of a pair which blade means are arranged diametrically opposite each other, said tension bar means having a high bending resistance, whereby transmission of bending moments from the rotor blades to the rotor head means is substantially prevented, each of said blade angle bearing means comprising a structure angularly movable in the wing flap direction and in the wing lead-lag direction, at least one of said blade angle bearing means of a pair comprising means permitting an axial motion of the respective tension bar means supported in said blade angle bearing means, and wherein said blade angle bearing means (10, 12, 14, 16) operatively support said tension bar means (6, 8) on said rotor head means (4) for pitch angle rotation of said tension bar means relative to said rotor head means (4), said rotor structure further comprising means (24) securing said rotor blade means (18) to said tension bar means (6, 8) in a manner rigid against rotation of the blade means about the longitudinal blade axis whereby the securing means prevent flapping, drag and lagging movements of the tension bar means, said tension bar means being constructed as torsion bars which are elastic relative to torsion about said longitudinal blade axis.
1转子结构为旋转翼飞机，有大幅刚性转子头部的手段和转子叶片或机翼的手段安排中至少有一对，组成的叶片角度轴承手段（ 10 ，12 ，14 ，16 ）为每个转子叶片的手段，拉杆手段（ 6，8 ）手术互连转子叶片的手段，其中一对刀片的手段都是安排截然相反的对方说，拉杆手段，有一个高弯曲阻力，即传输弯矩从转子叶片向转子头的意思是，大幅防患于未然，每个叶片角度说，轴承的手段组成的一个结构angularly动产在机翼上皮瓣的方向和在机翼导致滞后的方向，至少有一个叶片角度说，轴承是指一对组成的手段，允许轴向的议案，分别紧张酒吧手段，支持在叶片角度说，轴承的手段，其中，叶片角度说，轴承的手段（ 10 ，12 ，14 ，16 ）手术的支持表示拉杆的手段（ 6 ，8 ）就表示，转子头部的手段（ 4 ）为俯仰角轮换说拉杆手段相对说，转子头部的手段（ 4 ）表示，转子结构进一步组成的手段，（ 24 ）说，确保转子叶片的手段（ 18 ）表示，拉杆手段（ 6 ，8 ）在一个僵化的方式对旋转的叶片即是说，约纵向叶片轴，即确保手段防止扑，拖曳和落后变动的紧张局势，酒吧的手段，说拉杆手段，正在建造的，作为扭杆这是弹性相对扭转约说，纵向叶片轴。
Two normal operation, require the greatest possible flap valve opening angle, and can be stabilized at fully open position.
正常运行时，要求阀瓣有尽可能大的开启角，并能稳定在全开位置。
Zhengzhou Joysun Abrasives Co., Ltd. is a professional manufacturer of high quality of abrasive flap disc, fiber disc, Flap Wheel, PSA, Velcro sanding disc, abrasive sanding belts in China. With the full automatic flap disc machines and the manufacturing, converting lines made in Germany and Italy, we has continuously provided our customers with the creative solutions to the angle grinders, portable sanders and DIY application of metal finishing industry.
W2D74 我公司是制造各种高档涂附磨具的专业厂家，拥有从德国引进的全自动弹性磨盘、纤维磨片高速加工机床和从意大利引进的全套砂带转换加工生产线，采用德国著名厂商提供的原辅材料，大量生产加工锆刚玉、棕刚玉、陶瓷刚玉及碳化硅系列的角向磨光机专用高速弹性磨盘、钢纸纤维磨片、轴式页轮、卡盘页轮、气动抛磨机专用自粘及植绒磨片、手提砂光机专用砂带。
When tapping on the Bellow Seal Globe Valve, Angle, DIN pipes when the pipe thread to determine the size and length, to avoid pipe filled with the valve seat and valve flap.
当对管道进行攻丝时，要测定管道螺纹的尺寸和长度，避免将管道塞满阀座和阀瓣。
When tapping on the Bellow Seal Globe Valve, Angle, DINpipes when the pipe thread to determine the size and length, to aoid pipe filled with the valve seat and valve flap.
当对管道进行攻丝时，要测定管道螺纹的尺寸和长度，避免将管道塞满阀座和阀瓣。
At last, it is the first time that the new method of optimal angle-ratio main/flap fin stabilizer joint control system, at the same time, the relevant drive control method and change strategy of angle-ratio are proceeded.
最后，首次提出了可以实时变化转角比的襟翼减摇鳍控制系统方案，并提出了相应的传动控制方式和转角比变化策略。
3We can also get these conclusion, the effect to improving experimental results is more distinct for the more parts airfoil mode by contrasting the experimental results of the single airfoil mode and the more parts airfoil mode; The effect to improving experimental results is more distinct when the angle of flap is bigger. By this study, we confirm the method of blowing control of wind tunnel side wall layer, especially when the airfoil experiment is to get the bigger lift coefficient. 4 Using the eyeable technique of affixing thread on airfoil mode, we can confirm the separation of the upper surface of airfoil mode can be delayed observably. 5 By comparing the data of this experiment with the correct data, we confirm the blowing system is necessary to the airfoil experiment. 6 By comparing the data of this experiment with the data of WUS wing tunnel, we confirm the blowing system is effective to the airfoil experiment.
以上结论说明风洞侧壁附面层吹除控制对翼型试验是有效的，特别对带襟翼的高升力翼型试验效果是显著的。4通过丝线显示技术，验证了风洞侧壁附面层吹除控制可以有效延缓翼型试验中翼型表面的分离，提高了分离迎角，改善了试验结果。5把试验结果与修正结果进行对比，进一步验证了侧壁附面层吹除技术在翼型实验中的必要性。6通过与WUS风洞试验结果的比较进一步验证NF-3风洞采用的侧壁附面层吹除技术对改善翼型实验中侧壁附面层的干扰的有效性。
The experiment has been done in the NF-3 wind tunnel NWPU(North West Polytechnical University), The main investigation include the flowing content 1 The design and choice of the blowing control system of wind tunnel side wall layer; 2 The experiment method of the blowing control of wind tunnel side wall layer; 3 The measure of pressure distribution of airfoil model and calculating the coefficient of lift、drug、pitching moment、ratio of lift and drug and so on, using the changing of flap angle and the slot wide of main airfoil and flap、the changing of angle of atttack、Reynelds number. Analyze the ameliorative effect of the blowing control method in the different Reynelds number、angle of attack、angle of flap, for particular, the big angle of attack; 4 Searching for the control rule of single airfoil mode and the more parts airfoil mode by using this study and the studying of single airfoil mode previously.
实验在西北工业大学NF—3低速风洞二元试验段中进行，研究内容包括：1风洞侧壁附面层吹除控制系统的设计和选择。2风洞侧壁附面层吹除控制的实验方法。3通过调整襟翼的偏度及缝隙，选择GAW-1两段翼型的不同状态，改变翼型的迎角和控制系统的吹除量，测量翼型展向和弦向的压力分布，计算升力、阻力、俯仰力矩特性和升阻比特性等的变化，分析该方法对多段翼型在不同雷诺数、不同迎角，尤其是大迎角时气体分离的改善程度。4结合NF—3风洞实验室之前对GAW-1单段翼型实验侧壁附面层吹除控制研究的试验结果，寻找吹除法对单段翼型和多段翼型实验中风洞侧壁附面层的控制规律。5用丝线法对翼型绕流进行观察。6通过实验结果与修正结果进行对比，进一步探讨侧壁附面层吹除技术对翼型实验的改善效果。
Clinical observation of an improved suture method of scleral flap in trabeculectomy of acute angle-closure glaucoma
改良巩膜瓣可拆除缝线法在急性闭角型青光眼小梁切除术中的应用
Postoperative follow up for 6 months to 3 years showed that the physiological angle of cervico mandibular angle was recovered and the appearance of flap was satisfactory without swelling and contracture.
其余11例皮瓣完全成活。随访6个月～3年，所有患者颈部活动明显改善，颌颈角生理角度恢复，皮瓣色泽正常，外观不臃肿，未见继发挛缩。
Methods Traditional methods of direct suture were changed and new angle of lips was made by triangle rotation flap.
方法：改变两种传统方法直接缝合口角的方式，而以三角形返折瓣形成新口角；
It features an almost straight main plane (2), and the main flap (1) and upper flap (3) both have a far lower angle of incidence than seen at most tracks.
此款前翼有着几乎完全平直的主平面（2），主翼片（1）和上层翼片（3）。后两者都是在大多数赛道上不常见的小角度（极低下压力）翼片。
The content of simulate including in flotation pool or without grating angle, whether the flap angle, different depth ratio of flotation effect analysis.
主要是对气浮池中有无格板及其角度、有无挡水板及其角度、不同长深比下对气浮效果的影响进行了分析。
Objective To evaluate the clinical efficacy of the scleral flap removable suture in angle-closure glaucoma.
目的评价闭角型青光眼小梁切除术中应用巩膜瓣可拆除缝合技术的临床疗效。
Result: 36 cases of retroauricular groove flap through this surgery were survived, and reconstituted auricles had obvious skull-auricles angle, the symmetry of reconstituted auricles were improved.
结果：36例耳后沟皮瓣均成活，再造耳有明显的颅耳角度，增强了与健耳的对称性。
The control system simulations in different sea conditions and encounter angles are carried out. The curves and statistic values of yawing angle, rudder angle and flap-rudder angle are given.
对多种海情、不同遭遇角下的航行过程进行仿真，给出航向角、舵角的曲线以及统计值。
The simulation showed that the controller was effective. Compared with routine streamlined rudder and angle_ratio being fixed proportion main/flap rudders manners, the strategy proposed in the paper can hold nearly the same heading precision and decrease the consumption of control energy prominently.
仿真表明，控制器具有良好的效果，与常规流线型舵和转角比为比例关系的主舵/襟翼舵相比，同样航向精度下此种控制策略摆舵消耗能量显著降低。
For fluidic throat skewing, smaller flap injector angles would result in larger vector angle without thrust loss;
对于喉道倾斜矢量控制方案，在扩张片上以与主流成某一角度的方向注入气流产生的矢量角最大且没有带来较大的推力损失；
The apex flap deployment had a promising effect on the lift after stalling angle, but it had little effect on the drag.
在失速迎角后，尖顶襟翼对升力系数的提高有明显的效果，而对阻力系数的影响不大；