旋翼不穩定性 的英文怎麼說
中文拼音 [xuányìbùwěndìngxìng]
旋翼不穩定性
英文
main rotor instability- 旋 : 旋Ⅰ動詞1 (旋轉) whirl 2 (用車床切削或用刀子轉著圈地削) turn sth on a lathe; lathe; pare Ⅱ名詞...
- 翼 : Ⅰ名詞1 (翅膀) the wing of a bird 2 (像翅膀的東西) the wing of an aeroplane etc : 鼻翼 wing of...
- 不 : 名詞[書面語] (剁物所用的木墩) a block of wood
- 穩 : 形容詞1 (穩定; 穩當) steady; stable; firm 2 (穩重) steady; staid; sedate 3 (穩妥) sure; rel...
- 定 : Ⅰ形容詞1 (平靜; 穩定) calm; stable 2 (已經確定的; 不改變的) fixed; settled; established Ⅱ動詞...
- 性 : Ⅰ名詞1 (性格) nature; character; disposition 2 (性能; 性質) property; quality 3 (性別) sex ...
- 旋翼 : helicopter rotor
- 穩定性 : antiwhip
- 穩定 : 1 (使穩定) stabilize; steady 2 (穩固安定) stable; steady 3 (物質的性能不易改變的作用) stabi...
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To study the influence of this damper configuration to aeromechanical stability, some work has been done in this thesis. first, dynamic equation of the rotor - hub system was modeled with the generalized hamilton principle, which can be used to analyze the stability problem in different conditions like on - ground, hovering and flight. when fastening the fuselage, the model can also be used to analyze the stability problem of isolated rotor system
為了研究這種新型布置減擺器對直升機穩定性的影響,本文所作研究工作如下:首先,本文利用廣義的hamilton原理建立了適用於不同狀態(地面、懸停和前飛)的旋翼/機體耦合系統的動力學模型,該模型中將機體固定可以用來分析孤立旋翼的穩定性問題。During the procedure, the airspeed continues accelerating ( or decreasing ) and the aircraft configuration is rapidly changing. the aerodynamic interactions are complex and lead to dynamic instabilities. the shift between helicopter and airplane flight modes necessitates a change in control strategy
過渡模式下,飛機速度不斷增加(或減小) ,氣動布局不斷改變,飛機動力穩定性差且氣動干擾嚴重,直升機控制和固定翼控制切換,因此過渡模式動力學特性和控制系統研究是整個傾轉旋翼飛機研製的主要難點。An analytical model is developed for the dynamic stability analysis of helicopter rotor / fuselage coupled systems with general connections or inter - blade connections for the nonlinear elastomeric lag dampers
摘要建立了粘彈減擺器不同連接形式時的旋翼機體耦合動穩定性分析模型。To improve the stability, one common method is to install dampers at the roots of blades. however, commonly used dampers can hardly meet different demands when helicopter working in different conditions
為提高旋翼/機體耦合動穩定性,一般採用在槳葉根部安裝減擺器的方法,但目前常用的減擺器很難滿足直升機不同工作狀態下對擺振器阻尼的不同需求。Therefore, in this thesis, the magneto - rheological damper ( mrfd ) was studied which is of simple structure, high reliability and self adaption
為此,本文研究了結構簡單、可靠性高並具有自適應能力的磁流變減擺器(阻尼器) ,用於控制直升機旋翼/機體耦合動不穩定性運動。分享友人