aircraft的案例
Aircraft stability and control
（忽略發動機響應動力學的影響)
When you finish all the work above, it will be easy for you to solve the lateral stability and control problem of the example aircraft.
Here we also share a Cessna case, step elevator response at cruise configuration.
Please feel free to leave a comment!
Clarification: The course mentioned at the beginning is none of my business. And the post here is either none of its business. However, they are solving the same problem of aircraft. And its my pleasure to share my knowledge to you.
展開 設計仿真 | Adams Aircraft起落架功能簡述
作為專業的整機與起落架仿真工具，Aircraft可完成新型飛行器完整的、參數化的仿真模型建立工作，方便地定義起落架的布局，輪軸的排列，吸能裝置，以及其他關鍵性能。另外，團隊成員在其工作站上就可以完成一系列的仿真分析，如運動學，靜力學，動力學等，從而確定飛行器的升力，穩定性，載荷情況，乘員舒適性等，并且試驗測量數據可立刻用于分析及對試驗裝置進行快速修改。這其中最關鍵的一環就是所有的一切都可先在計算機上進行，完成起落架性能的提升與優化，并且在進行物理試驗甚至在真實樣機生產之前完成。
圖2：Adams/Aircraft界面
圖3：基于Adam
Aircraft建立的整機模型
02
功能介紹
Adams起落架功能是進行飛機仿真的工程設計環境。
基于子系統的架構將復雜任務分開并提供直觀的用戶界面；
基于模板構建器可以快速高效地完成新設計的模型創建；
基于數據庫確保各總成的標準化并方便數據管理；
基于系統的方法幫助工程師理解各獨立總成和子系統的相關性對飛機行為的影響；
提供了許多專業模塊如有限元，液壓，控制系統及其他學科功能（Adams內部建模實現）；
利用仿真菜單可進行不同類型的仿真，完成飛機模型的虛擬測試；
繪圖環境提供了方便的方式查看結果，對其任何細節進行把握。
展開 Aircraft Rib Intercostal Topology Optimi
Aircraft Rib Intercostal Topology Optimisation
In order to demonstrate the application of GENESIS to aerospace structures, a topology optimisation study was performed to determine the optimum rib layout for a wing rib intercostal.
The objective of the study was to determine the optimum rib layout for a shear panel intercostal configuration to support a flaptrack system.
展開 應用ADAMS／Aircraft建立飛機起落架模型
然后對模型進行 考慮升力的落震試驗分析，仿真試驗結果表明利用ＭＳＣ．ＡＤＡＭＳ軟件可以對起落架 精確建模和仿真分析
應用ADAMS／Aircraft建立飛機起落架模型.pdf
長航時無人機關鍵技術研究進展
Lateral-directional stability of near-space solar-powered aircraft[J]. Chinese Journal of Aerodynamics, 2016, 37(4): 1148. DOI: 10.7527/S1000-6893.2015.0225
[130]HAGHIGHAT S, LIU H T, MARTINS J R A. Model-predictive gust load alleviation controller for a highly flexible aircraft[J]. Journal of Guidance, Control, and Dynamics, 2012, 35(6): 1751. DOI: 10.2514/1.57013
[131]CHANG C S, HODGES D H, PATIL M J. Flight dynamics of highly flexible aircraft[J]. Journal of Aircraft, 2008, 45(2): 538. DOI: 10.2514/1.30890
[132]郭東, 徐敏, 陳士櫓. 彈性飛行器飛行動力學建模研究[J]. 空氣動力學學報, 2013, 31(4): 413
GUO Dong, XU Min, CHEN Shilu. Research on flight dynamic modeling of highly flexible aircrafts[J]. Acta Aerodynamica Sinica, 2013, 31(4): 413
[133]DRELA M.
展開 AMSim論文系列分享(Flight Control) 5
關鍵詞: 結構試驗; 加載作動器; 電液一體化; AMESim 仿真
中圖分類號: TP 271 + ． 4
文獻標識碼: A 文章編號: 1001-5965( 2012) 10-1395-05
Design and efficiency analysis for loading actuator
used in aircraft structure test
Luo Caijin Shang Yaoxing Jiao Zongxia
( Science and Technology on Aircraft Control Laboratory，Beijing University of Aeronautics and Astronautics，Beijing 100191，China)
Abstract: Based on the characteristics of low speed and low system flow in plane structure test especially
in the static loading test，a new type of valve-control electro-hydraulic actuator for aircraft structure loading test
was designed． The system components and working principle was described，and the efficiency of valve-control
system was analyzed．
展開 超長航時太陽能無人機關鍵技術綜述
Energy-optimal path planning for solar-powered aircraft in level flight[C]∥AIAA Guidance, Navigation and Control Conference and Exhibit. Reston, VA: AIAA, 2007: 6655.
[164]KLESH A T, KABAMBA P T. Solar-powered aircraft: Energy-optimal path planning and perpetual endurance[J]. Journal of Guidance Control & Dynamics, 2009, 32(4): 1320-1329.
[165]SPANGELO S C, GILLBERT E, KLESH A, et al. Periodic energy-optimal path planning for solar-powered aircraft[C]∥AIAA Guidance, Navigation, and Control Conference. Reston VA: AIAA, 2009: 6016.
[166]SPANGELO S C, GILLBERT E G. Power optimization of solar-powered aircraft with specified closed ground tracks[J]. Journal of Aircraft, 2013, 50(1): 232-238.
[167]MA D M, SHIAU J K, SU Y J, et al.
展開 CFD專欄丨FlightStream-基于面元法的快速CFD分析工具
Saravanan, B. (2023) Ground Effects on the Aerodynamics of Tailless Aircraft – A Numerical Study.
DiMaggio, G. (2023) Hybrid Wing Body Pitch Control with a Surface-Vorticity Solver.
Soikkeli, J. (2023) Cascaded nonlinear dynamic inversion applied to a fixed-wing distributed electric propulsion aircraft.
Wang, X. (2023) Prediction of Duct Airfoil Aerodynamics using Surface Vorticity.
Simmons, B. (2023) Validation of a Mid-Fidelity Approach for Aircraft Stability and Control Characteristics.
DiMaggio, G. (2023) Solid Rocket Motor Internal Ballistics Using a Vortex Particle Method.
Huynh, D. (2023) Application of a Semi-Empircal Method to Model Subsonic Vortex Lift over Sharp Leading-Edge Delta Wings.
展開 飛機新概念結構設計與工程應用
(in Chinese)
New Concept Structure Design and Engineering Application of Aircraft
Wang Xiangming
Shenyang Aircraft Design ＆ Research Institute
Abstract: Aiming at the defects of overweight and cracking existing in traditional structure and based on the integration of design and manufacturing, this paper puts forward new concept structures such as large-scale integration, gradient compounding, configuration topology, structure function integration, which have significant advantages of high weight reduction, long life, multi-function, low cost, rapid response development, etc.They play an important role in model application,and opens up a new technological for approach aircraft structure innovation.
展開 飛行汽車/eVTOL
<ul><li><span style="color: rgb(51, 51, 51);">Proficiency in design of metallic and composite assemblies</span></li><li>Understanding of aircraft and rotorcraft aerodynamics </li><li>Understanding of aircraft stability and control derivatives </li><li>Basic understanding of Computational Fluid Dynamics (CFD) principles </li></ul><p><br></p><p><br></p>
展開 LMS Virtual.Lab航空聲學解決方案
Acoustic Solutions for Aircraft Noise & Vibration_March2011.part2.rar
Acoustic Solutions for Aircraft Noise & Vibration_March2011.part1.rar
BOEINGmontgomery_AIAA2004_TBL.pdf
BOEINGmontgomery_AIAA2004_TBL.pdf
論文分享 samcef復合材料優化 線性與非線性有限元分析
Through the applications, this paper provides the opportunity to discuss convergence issues and the use of such advanced optimization techniques in the overall aircraft design process.
GenPurpSoft-SMecComp_2010_07_en.pdf
Combustion Research and Flow Technology, Inc.
This formulation also enables aircraft engine manufacturers to reduce emissions and avoid engine flame out conditions, especially for high performance systems.
Software used:
ANSYS Fluent
AMESim仿真技術在飛機液壓系統中的應用
關鍵詞AMESim 仿真建模液壓系統飛機起落架批處理
中圖分類號V233.91; TP391.9 文獻標志碼A
Application of AMESim in aircraft hydraulic
system
GUO Jun, WU Yafeng, CHU Nisheng
(School of Engine & Energy, Northwestern Polytechnical Univ., Xi an Shannxi 710072, China)
Abstract: The features and functions of AMESim developed by Imagine Co. are analyzed,
which is specialized in engineering system modeling, simulation and dynamic
performance analysis for advanced hydraulic/mechanical system. Under the AMESim
environment, a hydraulic simulation of the former-undercarriage of aircraft is
constructed. The simulation model of the component is built by graphical modeling
method. The simulation result is analyzed. And the batch running me- thod by AMESim
is proposed to optimize system parameters.
展開 solidworks公司正式發布solidworks2008 產品
“solidwoks2008的UI因更直觀的感受而顯得完美”，用戶Executive Aircraft Completions的工程師Josh A. Mings說。
"The SolidWorks 2008 UI is very slick with an even more intuitive feel," said beta user Josh A. Mings, interior engineer of Executive Aircraft Completions, Tulsa, Okla.
“你會更加的有效率因為通過菜單你有更多的機會工作在模型的上面、里面以及四周。在文件之間的切換也更迅速，因為你可以在切換之前自動的看到你要切換的文件。”
展開 