Results 1 to 10 of about 16,873 (217)
Non-Linear Dynamic Inversion Control Design for Rotorcraft
Aerospace, 2019 Flight control design for rotorcraft is challenging due to high-order dynamics, cross-coupling effects, and inherent instability of the flight dynamics.
Joseph Horn
exaly +3 more sources
HeliCAT-DARTS: A High Fidelity, Closed-Loop Rotorcraft Simulator for Planetary Exploration
AerospaceHeliCAT-DARTS is a high-fidelity rotorcraft dynamics simulator developed for the design and development of rotorcraft for planetary exploration. While initially developed for the life cycle use of the Ingenuity Mars Helicopter mission, the simulator now ...
Abhinandan Jain +2 more
exaly +3 more sources
Distributed pod wing modeling and aeroelastic analysis
Xibei Gongye Daxue Xuebao, 2022 基于准线性化隐式建模方法, 建立适用于大展弦比机翼的动力学模型, 研究分布式吊舱机翼的气动弹性特点。其中结构模型采用中等变形梁模型, 气动模型采用准定常理论, 利用小扰动和有限差分法, 建立求解机翼气弹稳定性的方法。在验证结构和气动模型准确性基础上, 研究吊舱的个数、质量、展向站位、弦向/法向偏置等参数对分布式吊舱机翼气动特性的影响。分析结果发现: 吊舱越靠近机翼中部、弦向和法向偏置越大机翼稳定性越高, 但质量分布不均时反而会降低稳定性; 机翼经历了振动收敛、单频简谐振动和倍频简谐振动 ...
CHENG Yi +3 more
doaj +1 more source
Development of a multipurpose test rig - TAILTEST [PDF]
MATEC Web of Conferences, 2021 The paper discusses an innovative multipurpose test rig designed with the aim of full-scale rotorcraft fin verification. The developed test rig includes a load application mechanism able to distribute loads representative for rotorcraft tail structure ...
Oberthor Martin +2 more
doaj +1 more source
Vibration loads analysis of coaxial rigid rotor in rotor interaction
Xibei Gongye Daxue Xuebao, 2021 A vibration load computing method for a coaxial rigid rotor was developed and applied to analyzing its vibration load in rotor interference. The structural dynamics model based on the medium-size deformation beam theory and the double-rotor aerodynamics ...
Yu Zhihao +3 more
doaj +1 more source
Shock and Vibration, 2021 Current control laws for active control of helicopter structural vibration are designed for steady-state flight conditions, while the vibration response of maneuvering flight has not been taken into consideration yet.
Yifan Qin +3 more
doaj +1 more source
Shock and Vibration, 2022 The gear meshing noise generated by the helicopter main reducer is one of the important sources of noise in the helicopter cabin. By improving the isolation performance of the struts supporting reducer to the gear meshing vibration, the purpose of ...
Yue Hui-yu +5 more
doaj +1 more source
Aeroelastic stability analysis of rotor blade with complex three-dimensional design
Xibei Gongye Daxue Xuebao, 2023 A rotor dynamic analysis method for the complex three-dimensional design blade was developed and applied to analyzing its aeroelastic stability. Based on the medium-size deformation beam theory and Hamilton principle, the joint transfer matrix was used ...
DENG Jinghui +3 more
doaj +1 more source
International Journal of Aerospace Engineering, 2022 This paper presents a numerical investigation of unsteady surface blowing using periodic variations of jet velocity with azimuthal angle to reduce helicopter rotor blade-vortex interaction (BVI) noise.
Yan Sun, Guohua Xu, Yongjie Shi
doaj +1 more source
An Improved Feedforward-Robust Algorithm for Active Vibration Control of Helicopter Maneuver Flight
International Journal of Aerospace Engineering, 2023 To solve the problem of secondary path mutation and external disturbance abrupt changes during helicopter maneuver flight, the previous research proposed a hybrid active vibration control law.
Yifan Qin, Yang Lu, Huiyu Yue
doaj +1 more source