姿態基準 的英文怎麼說
中文拼音 [zītàijīzhǔn]
姿態基準
英文
att attitude reference-
Attitude detemination and control system of a satellite contains two parts, one is the attitude detemination system and the other is the attitude control system. detemination of attitude is the search about attitude arientation on a benchmark. control of attitude is the access of direction on the predefine way. this paper only refer the system of attitude control for lace of space. if there is no special explain, the control system refered in this paper does ’ t contain attitude detemination system
衛星的姿態控制系統包括姿態的確定和姿態的控制兩部分，姿態的確定是研究衛星相對于某個基準的姿態定位，而姿態控制是指衛星在某個規定或預先確定的方向上定向的過程。本文限於篇幅，僅對姿態的控制部分進行了分析，如果沒有特殊說明，文中所說的姿態控制系統均不包括姿態的確定部分。Abstract : solid propellant rocket motors are preferred for most ballistic missiles because they need simple maintenance and can be launched quickly. but the conventional thrust termination devices limit the depletion of every stage ' s grain and increase some extra - weight. an improved method for designing a multi - stage solid rocket based depleted shutdown was provided. in order to solve the problem of lack of thrust termination devices, a device to adjust the burnout angle will match the final burnout velocity and satisfy the desired range. the method can also limit the detection from anti - ballistic missile system
文摘:由於維護簡單和發射快速，彈道導彈多用固體火箭發動機，但繁雜的推力終止裝置使各級裝藥不能耗盡並讓結構增重.提出了一種對基於耗盡關機多級固體火箭概念設計的改進方法，此方法滿足導彈系統主要的戰技要求.為解決無推力終止裝置的末速不準問題，可在末級發動機採用姿態調整裝置，對射角進行調整，配合末速以滿足射程要求.本方法還可抑制敵方反導探測The balance change under the influence of gravity might cause a spurious torque resulting in drift of the gyro attitude reference.
在重力的影響下平衡的改變會形成不必要力矩，結果使陀螺姿態基準產生漂移。To solve the problems caused by the varieties of the missile dynamics with the difference of flight height, velocity and attitude angle in modeling the missile, in this thesis, the theory of variable structure model reference adaptive control is used to design a pitch channel autopilot based on a longitudinal missile model, the status equation using the measurable parameters of load and angular rate is established, and the methodology to choosing the reference model is discussed also, and the performance of the controller is analyzed by means of simulation
為了解決攔截彈氣動參數隨飛行高度、速度、姿態的不同，變化范圍大，控制系統難以準確建模的困難，基於縱向平面攔截彈模型，採用模型參考變結構控制理論設計了俯仰通道姿控復合控制系統，以可測量變量過載和角速度作為狀態量建立了系統的狀態方程，討論了參考模型的選擇方法，並對系統的性能作了模擬分析。Design of data acquisition syste
分散式捷聯姿態基準中數據採集系統的設計4. conclude and verify detailedly attitude algorithm and conical scan control algorithm in process of initial alignment. on the base of static initial alignment technology, reach the dynamic initial alignment technology used on moving carrier
四、對在初始對準中採用的姿態解算和圓錐掃描控制演算法進行了詳細的理論推導和模擬驗證，然後在靜態初始對準的基礎上，引出了用於載體移動過程中的動態初始對準。Study on strapdown inertial navigation system ( sins ) the concept, process and the already done work of initial alignment of sins arc introduced briefly. for selecting coordinate and deriving the error model, presenting some kinds of coordinate in the inertial navigation system ( ins ) ; the initial alignment of sins theory is introduced in detail ; the linear error model of moving base initial alignment of sins is derived, including analysis in characteristic and influence of system error of inertial apparatus.
捷聯慣導系統的研究：首先概要介紹了慣導系統的相關知識，闡述了捷聯慣導系統的優點；分析了初始對準姿態確定的幾種坐標系，為建模定義了坐標系選擇和姿態矩陣；詳細研究了捷聯慣導系統的初始對準原理，推導並給出了捷聯慣導系統動基座初始對準的誤差方程，並分析了誤差特性以及慣性儀表誤差對系統誤差的影響；分享友人