integrated propulsion system 中文意思是什麼
integrated propulsion system
解釋
綜合式推進系統- integrated : adj. 完整的，完全的。 an integrated iron and steel works 鋼鐵聯合企業。 an integrated oil company 大型石油（聯合）公司。
- propulsion : n. 推進（力）。 a propulsion engineer 動力裝置工程師。 jet propulsion 噴氣推進。
- system : n 1 體系，系統；分類法；組織；設備，裝置。2 方式；方法；作業方法。3 制度；主義。4 次序，規律。5 ...
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Distributed real - time simulation system design for integrated flight fire propulsion control system
戰術任務綜合控制系統分散式實時模擬系統設計 -
A integrated flight / propulsion control ( ifpc ) theoretical schema was designed based on this concept and a engineering schema was developed after take consideration of currently engineering condition and the requirements of in - service aircraft upgrade. a auto - flight system was designed which can achieve accurate flight movement control and increase performance of flight task such as ascend, cruise, te
基於該概念設計了飛推綜合原理方案，並在考慮工程實現條件及現役飛機改進、改型要求后建立了工程實現方案，設計了軌跡跟蹤方式的自動飛行系統，解決了軌跡生成、表示、管理、跟蹤等問題，能夠實現運動狀態的精確控制，提高爬升、巡航等任務的性能。 -
As to the modelling of integrated flight / propulsion system, this paper mainly investigated and the modelling methods of flight kinetics and propulsion system thermodynamics, building up the real - time models of body kinetics. then we integrated the component - level thermodynamics model of engine, solved the problem of matching of initial points in the integrated simulation of flight / engine and the interactive parts of flight system and propulsion system
對于綜合飛行/推進系統建模，本文主要研究的是飛行動力學和推進系統熱力學的建模方法，建立了飛機動力學實時模擬模型。並結合前人已建立的發動機部件級熱力學模型，本課題在解決了飛機/發動機綜合模擬中的起始點匹配問題的基礎上，完成飛行系統和推進系統的交互部分，最終建立飛行/發動機綜合實時模擬模型。 -
Both advantages of rocket engine and air - breathing engine are integrated into one kind of propulsion system, called rocket - based - combined - cycle ( rbcc ), which has multiple operating woke modes, including ejecting, subsonic combustion, supersonic combustion and rocket mode, with each mode operating at varying flying stage. rbcc has prominent potential of high efficiency and low cost, and so it is recognized as an advanced propulsion system of future single - stage - to - orbit reusable spacecraft and hipper - sonic missile. it has been broadly investigated in foreign countries and has been progressed into small and full - scale flying stage
火箭基組合動力循環（ rbcc ， rocketbasedcombinedcycle ）將傳統的火箭發動機和吸氣式發動機的優點集中組合到一個具有多種工作模態（包括引射、亞燃、超燃及火箭模態）的發動機里，在不同的飛行階段啟用不同的工作模態，因此具有大幅提高航天推進系統經濟性與高效性的潛在優勢，並可能發展成為下一代單級可重復使用航天器以及高超聲速導彈武器的動力系統。 -
Fourthly, a discussion is devoted to study the integrated flight / propulsion control system
接著，對新一代殲擊機的綜合飛行/推進控制系統進行研究。 -
On the basis of designing robust flight control system of the new generation fighter, this dissertation is devoted to the design of the integrated fire / flight control system and the integrated flight / propulsion control system and the integrated fire / flight / propulsion control system
以研究新一代殲擊機的魯棒飛行控制系統為前提，進一步研究其綜合火力飛行控制系統、綜合飛行推進控制系統以及綜合火力飛行推進控制系統的魯棒控制問題。 -
The flight control and propulsion system will become a single smart aircraft movement control system which incorporate all kind of control capability of aircraft and was highly integrated with comm and, control, sensor, navigation and attacking system
飛控、推進等系統也將演進成為一種一體化的、智能的、綜合了各種飛機控制能力並與指揮、控制、傳感、導航、攻擊等系統高度綜合的飛機運動控制系統。 -
With respect to the issue of integrated flight / propulsion control system design, adopting the decentralized solutions of system integration, this article studied the key technologies in this integrated control system, based on which a real - time integrated closed - loop model of plane / engine was built and a study of variable structure control of integrated flight / pro - pulsion control system was conducted. through a great many simulations, the feasibility of the solution was verified and a simulating platform of integrated flight / propulsion control system was designed and developed by utilizing directx multi - media development libraries
本文針對飛行/推進綜合控制系統設計問題，採用分散的系統綜合方案，研究了飛行/推進綜合控制中的關鍵技術，在此基礎上建立了飛機/發動機綜合閉環實時模型，進行了發動機的變結構控制研究，通過大量的模擬，驗證了控制方案的可行性，並基於directx多媒體開發庫設計完成飛/推綜合控制系統模擬平臺界面的開發。 -
Study on an integrated fire flight propulsion control system and its digital simulation design platform
推綜合控制系統及其模擬平臺研究 -
This paper first takes an overview of the performance seeking control ( psc ) system of nasa, usa. focused on the disadvantages of this original system, this paper studied the two most critical parts of the psc system : engine deterioration parameter ( edp ) estimation algorithm and integrated propulsion system optimization algorithm
針對美國性能尋優控制存在的不足，本文從非線性方法的角度研究了性能尋優控制中的兩個最重要的部分：發動機部件性能變化參數估計部分和推進系統性能優化部分。 -
The research work as the exploratory study, which has been done provides a base for the next study of integrated propulsion system control
本文對進氣道進行的建模研究作為一種探索性研究為進一步開展推進系統一體化控制的研究奠定了基礎。 -
This paper presents a theoretical analysis of the above two problems from a totally new perspective. also, some theoretical solutions are presented to the detail problems. it can be a new way to the integrated propulsion system performance seeking control design
本文從全新的角度對以上兩個問題進行了理論上的分析，對其中存在的一些細節問題也給出了一些解決方案，在理論上對推進系統綜合性能尋優控制給出了新的方法。 -
In order to meet these requirements, the aeronautical propulsion system has to provide more powerful and sustainable force. this also poses new requirements for propulsion control system. as a result, integrated propulsion system performance seeking control is introduced
要達到這一目標，航空推進系統必須能夠提供更強大更持久的動力，這也對推進系統的控制提出了新的更高的要求，為此需要對推進系統進行最優控制規律研究。 -
To accomplish the complicated missions safely and effectively, it must have an advanced integrated fire / flight / propulsion system for the new generation fighter. synchronously, the integrated fire / flight / propulsion system is a complicated, uncertain and multi - variable nonlinear large - scale system. so its control problem is an active subject in the modern control area
而新一代殲擊機的綜合火力飛行推進系統是其能夠安全、有效地完成復雜戰術戰略使命的基本前提，同時新一代殲擊機的綜合火力飛行推進系統是一個復雜的、具有不確定性的、多變量非線性大系統，因此它的設計與控制問題是現代控制領域所面臨的一大挑戰。 -
Integral rocket - ramjet is a propulsion system with great potential. using missile - engine integrated design method to realize the conceptual design of integral rocket - ramjet missile is of great significance to improve quality and efficiency of missile design
整體式火箭沖壓發動機是一種很有前途的動力裝置，採用導彈和發動機一體化設計方法進行整體沖壓式導彈的總體設計，對于提高導彈的設計質量和設計效率具有重要的意義。
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