尽管目前只有IXV一个飞行器计划，当IXV从海洋中打捞并分析，会带来其他的试验飞行器的项目。
Although only one flight of the IXV is currently planned, its recovery from the ocean would allow further experimental flights to be conducted.
欧洲再入大气层试验飞行器是简单的不载人座舱式飞行器。它将随“阿里安5”火箭的第二次鉴定飞行发射升空。
The second qualification flight of Ariane - 5(V502) will carry an atmospheric Reentry Demonstrator(ARD) which is a simple unmanned capsule - type vehicle.
并且高超音速飞机目前只演示过由其他飞行器携带小型无人机至高速，而且其他计划中的试验飞行器同样太小不能坐人。
Plus, hypersonic flight has so far only been demonstrated for small unpiloted craft carried to high speed by other vehicles - and other planned experimental craft are too small to carry a pilot.
这个计划将负责进行一些诸如飞行器自动会合和外层空间对接，以及轨道内加油和充气式居留舱等新技术的试验。
The program would be responsible for flight tests of new technologies such as autonomous rendezvous and docking, in-orbit refueling, and inflatable habitat modules.
二是目标飞行器按后续空间实验室的要求设计，可在完成交会对接任务的同时，验证部分关键技术；三是还可同时开展科学实验和技术试验。
Another one is that the target flight module designed as required for follow-on space LABS can test and verify the key skill while completing the task of rendezvous and docking.
航天试验离心机人和动物在其里面并旋转以模仿宇宙飞行器的加速作用的一种仪器。
An apparatus in which human beings or animals are enclosed and which is revolved to simulatethe effects of acceleration in a spacecraft.
高超声速飞行器的设计工具，即地面试验、计算和飞行试验，在模拟高超声速飞行方面都有其局限性。
The developing tools for hypersonic vehicle, i. e. ground test, computation and flight lest all have limitations for simulating hypersonic flight.
相变热图试验技术是通过在飞行器表面喷涂具有一定相变温度的相变涂料来进行大面积热测绘的一项风洞试验技术。
The phase change thermography technique is a wind tunnel test technique to spray some phase change paint on the aircraft surface for measuring heat distribution in a large area.
阐述了在进行高超声速飞行器外形设计中，应用试验设计方法的必要性。
The essential of using experimental design method to configuration design of hypersonic aircraft are expounded.
利用典型状态的风洞试验结果对十字布局与叉字布局再入机动飞行器的气动特性进行了分析与比较。
In this paper aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results.
本文采用飞行器六自由度运动方程组，建立了飞行试验数据相容性检验的数学模型。
In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft.
载人飞船返回舱的烧蚀热防护技术研究和试验表明，碳化烧蚀材料是再入飞行器最有效的热防护层。
Investigations and experiments indicate that charring ablators provide the most efficient thermal protection shield for the re-entry vehicles.
航空地面试验设备必须得到更新以适应未来飞行器尺寸增大、性能提高的要求。
Aeronautical ground facilities must be upgraded to match the increased size and performance of future aircraft.
启动空间飞行器在轨服务与维护系统建设，利用多种资源，开展新原理、新技术、新产品在轨试验验证。
It plans to build in-orbit servicing and maintenance systems for spacecraft and make in-orbit experiments on new theories, technologies and products by tapping various resources.
本文对飞行器天线罩的雨蚀问题、试验测试方法及其防护措施的研究现状进行了综述。
This paper reviews the rain erosion problem on the surface of the radomes, as well as the rain erosion testing methods and the protection methods.
通过建立扇翼飞行器的二维数学模型进行模拟分析、设计试验模型并进行了相关实验比较分析，证明垂直升降的可行性。
According to comparative analysis between the 2d mathematical model simulation and the of test model design of fan wing aircraft, the feasibility of VTOL is proven.
试验结果表明该系统具有较高的可靠性，可用于指示需要进行姿态控制的各类飞行器的姿态。
The results of tests indicate that the system has higher reliability and this method can be used to determine the attitude of aircraft which needs to be controlled.
迎角风洞试验技术是先进高机动飞行器研制必需的关键技术。
High Angle of attack wind tunnel test techniques is necessary for development of high-maneuverability flight vehicles.
研究了具有验前信息下的飞行器落点精度的鉴定问题，适用于只作一次现场飞行试验的情况。
This paper discusses the detecting problem of the fall point of vehicle with Prior information. This proposed method may used under the circumstance of only one flight lest.
这些模式和故障诊断树都是为快速查找飞行器故障服务的，可以有效地提高飞行器试验的成功率。
These patterns and failure diagnostic tree both have served a search Vehicle failure quickly, could made a success of Vehicle experiment on it effectively in practical.
该装置已成功应用于某飞行器综合匹配试验，其性能和指标均优于应用要求。
This device has been successfully applied to a vehicle matching test, its performance is better than application requirements.
试验结果表明，本文提出的控制算法能够保证阵风干扰情况下小型无人飞行器的航迹控制精度，同时具有良好的动态响应。
Tests confirm that the proposed method can improve the path following performance and dynamic response for the small unmanned aerial vehicle under wind disturbance.
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.
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.
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