随着时间的推移，羽毛变得越来越大，扑翼飞行逐渐发展，鸟类最终完全可以在空中飞行。
As feathers became larger over time, flapping flight evolved and birds finally became fully air-borne.
所以，在扑翼飞行器设计时采用折叠运动是有利的。
Therefore it is very important to consider adopting a wing flexure in flapping wing design.
本文研究为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
The result of wind tunnel test provides guideline in aircraft design of flapping-wing MAV.
研究结果可为带翼刀机翼在扑翼飞行器上的应用提供技术支持。
Results of wind tunnel test provide technology support for application of wing with wing-blade in flapping-wing micro air vehicle.
随着微扑翼飞行器研究的不断深入，对其控制问题研究已引起了人们的重视。
As micro flapping flight is investigated further, its control is paid more attention to.
根据昆虫扑翼飞行节律运动的原理，设计一个压电驱动的两自由度扑翼机构。
A 2-DOF piezo-actuated flapping mechanism was designed according to the theory of flapping-wing flying rhythmic movement of insects.
重点研究了动物扑翼飞行机理，为研制仿生扑翼飞行机器人设计提供了理论依据。
The flapping-wing flight mechanism of animal is investigated in particular, and the results provide a theory foundation for developing BFAR.
根据昆虫扑翼飞行的原理，设计了一种基于昆虫胸腔式结构的静电驱动微扑翼机构。
This paper studied a micro flapping mechanism that was based upon insect thorax and actuated by electrostatic force according to the flapping flying theory of insects.
仿真结果验证了此操控机制可以较好地解决仅一对翼的仿昆扑翼飞行器飞行动力问题。
This dissertation proposes a flapping control mechanism to solve the flight power problems in hovering flight control of the insect-like flapping micro aerial vehicles(IFMAVs).
展向环量的存在是扑翼飞行的特点，在扑翼飞行的仿生研究中必须注意对展向环量的分析。
The existence of spanwise circulation is a characteristic of flapping wi ngs. In biomechanics study of flapping wings, it is key to analysis of spanwise circulation.
研制象昆虫这样能够扑翼飞行的微型飞行器成为目前昆虫运动仿生研究中的一个热门课题。
It is important to study the biomechanics of an insect to improve the specification of Micro Air Vehicles (MAV).
当航速为零时，则是通过鳍在水平位置附近的上下振动来产生升力，与鸟类和昆虫的扑翼飞行相似。
When the speed of AUV is zero or low speed, lift is produced by the vibration of fin stabilizer at the horizontal position, which is similar to the flapping wing flight of insects and birds.
本文对微型扑翼飞行器尾翼的特性、对稳定性和操纵性的影响以及尾翼的设计理论与方法进行了研究。
Therefore, the characteristics, the influence on the stability and control, as well as the design theories of the FMAV empennage are studied here.
从2008年3月开始的第二阶段，该公司将利用6个月时间和63.6万美元对这种3英寸扑翼飞行器系统进行论证。
Phase II, which started in March, is a six-month, ＄636,000 program to demonstrate a rudimentary, 3-inch flapping-wing air vehicle system.
建立由欧拉角所确定的扑翼飞行器的载荷计算方法和步骤，揭示出扑翼飞行器通过扑翼运动同时产生升力、推力的机理。
The evaluation methods and step of the loading for the FMAV are set up so that these Euler angles can be specified to provide wing motions that generate the lift and propulsion for the vehicle.
在对鸟类的飞行参数进行统计分析的基础之上，拟合出扑翼飞行的仿生学公式，并据此进行了微扑翼飞行器的仿生学初步设计。
Based on statistics and analysis of flying parameters of birds, the biomimetic formulas are brought forth and original FMAV design is carried out.
仿生学和空气动力学研究均表明，对于特征尺寸相当于鸟类或者昆虫的微型飞行器来说，扑翼飞行器要优于固定翼和旋翼飞行器。
Research on bionics and aerodynamics indicates that flapping mode is better than rotorcraft and fixed-wing mode when they are about the size of small birds.
起初给扑翼机接上一个直流电源之后，他们发现这个装置的有效载荷为1.5g，这大概可以勉强提起飞行所需的电池。
Having initially connected the ornithopter using a DC power source, they realized that the device could lift 1.5 grams of payload, which was roughly the mass of the batteries required for flight.
对鸟和昆虫的飞行机理进行了有价值的探讨，并对扑翼式微型飞行器机体动力学和机翼空气动力学进行了详细的分析。
The flight mechanism of birds and big insects was probed valuably, and airframe dynamics and airfoil aerodynamics of Flapping Wing Micro Aerial Vehicle (FWMAV) were researched.
当扑翼在小迎角飞行时，机翼带翼刀可以有效地改善扑翼的气动特性。
When flapping-wing flight at small attack Angle, wing had wing-blade improve effectively aerodynamic characteristic of flapping-wing.
通过将试验数据与经验公式计算的结果进行比较，得到了升力与扑翼参数的关系，为进一步设计扑翼式微型飞行器提供了依据。
Instantaneous aerodynamic forces are calculated under a set of kinematic parameters. The study can be used as a preparation for the design of micro air robot with flapping wings.
启合式扑翼发明属航空飞行器空气动力学领域。可解决旋转翼和固定翼航空飞行器的正交方向阻力超升力增加的问题。
The present invention relates to flyer and aerodynamics and can solve the problem that the resistance in orthogonal direction increases faster than lift in rotary wing and fixed wing flyer.
启合式扑翼发明属航空飞行器空气动力学领域。可解决旋转翼和固定翼航空飞行器的正交方向阻力超升力增加的问题。
The present invention relates to flyer and aerodynamics and can solve the problem that the resistance in orthogonal direction increases faster than lift in rotary wing and fixed wing flyer.
应用推荐