Formation Flight Simulation and Flight Test of Multiple Ducted-fan UAV

2019 ◽  
Vol 25 (5) ◽  
pp. 398-406
Author(s):  
Taegyun Kim ◽  
Seungkeun Kim ◽  
Jinyoung Suk
Keyword(s):  
Flight Test ◽  
Flight Simulation ◽  
Formation Flight ◽  
Ducted Fan

Rotorcraft Lateral-Directional Oscillations: The Anatomy of a Nuisance Mode

2021 ◽  
Author(s):  
Dheeraj Agarwal ◽  
Linghai Lu ◽  
Gareth D. Padfield ◽  
Mark D. White ◽  
Neil Cameron
Keyword(s):  
Simulation Model ◽  
Simulation Models ◽  
Flight Test ◽  
Flight Simulation ◽  
Stability And Control ◽  
Systems Research ◽  
Control Derivatives ◽  
Research Aircraft ◽  
Level Of Understanding ◽  
And Control

High-fidelity rotorcraft flight simulation relies on the availability of a quality flight model that further demands a good level of understanding of the complexities arising from aerodynamic couplings and interference effects. One such example is the difficulty in the prediction of the characteristics of the rotorcraft lateral-directional oscillation (LDO) mode in simulation. Achieving an acceptable level of the damping of this mode is a design challenge requiring simulation models with sufficient fidelity that reveal sources of destabilizing effects. This paper is focused on using System Identification to highlight such fidelity issues using Liverpool's FLIGHTLAB Bell 412 simulation model and in-flight LDO measurements from the bare airframe National Research Council's (Canada) Advanced Systems Research Aircraft. The simulation model was renovated to improve the fidelity of the model. The results show a close match between the identified models and flight test for the LDO mode frequency and damping. Comparison of identified stability and control derivatives with those predicted by the simulation model highlight areas of good and poor fidelity.

scholarly journals Design, manufacture and flight test of an Electric Ducted Fan (EDF) powered cruise missile

2018 ◽  
Vol 1130 ◽  
pp. 012030
Author(s):  
G Nugroho ◽  
M A Bramantya ◽  
M A Ghani ◽  
S S Wang ◽  
Y A Kurniawan
Keyword(s):  
Flight Test ◽  
Cruise Missile ◽  
Ducted Fan

Distributed Turbulence Model with Rigorous Spatial Cross-Correlation for Simulation of Helicopter Flight in Atmospheric Turbulence

2019 ◽  
Vol 64 (4) ◽  
pp. 1-13
Author(s):  
Honglei Ji ◽  
Renliang Chen ◽  
Pan Li
Keyword(s):  
Atmospheric Turbulence ◽  
Turbulence Model ◽  
Cross Correlation ◽  
Turbulence Models ◽  
Flight Test ◽  
Longitudinal Direction ◽  
Flight Simulation ◽  
Quality Analysis ◽  
Frequency Range ◽  
Helicopter Flight

This paper presents a distributed turbulence model with rigorous spatial cross-correlation for helicopter flight simulation in atmospheric turbulence and for future handling-quality analysis. First, digital filters with longitudinal correlations of the von Kármán turbulence are developed to generate discrete turbulence velocity components. Meanwhile, transverse turbulence correlations are considered by relating the filters in different positions with mathematically rigorous spatial cross-correlation. Then, the distributions of the related filters on the transverse plane in front of helicopter and their velocity components in the longitudinal direction of airspeed, as well as turbulence models of helicopter aerodynamic surfaces, are established. Finally, a flight dynamics model coupled with the turbulence model is developed and validated against the flight-test data. The proposed model can achieve accurate real-time simulations of helicopter response to atmospheric turbulence in the frequency range of interest of handling qualities. The effect of transverse turbulence correlations on helicopter frequency response is also analyzed. The results show that the simulation model regardless of transverse turbulence correlations would aggravate the "rotor-to-body attenuation" effect of the main rotor and therefore underpredict the helicopter roll, pitch, and heave rate responses to atmospheric turbulence in the frequency range of interest.

Attitude algorithm and initial alignment method for SINS applied in short-range aircraft

2017 ◽  
Vol 31 (19-21) ◽  
pp. 1740081 ◽  
Author(s):  
Rong-Hui Zhang ◽  
Zhao-Cheng He ◽  
Feng You ◽  
Bo Chen
Keyword(s):  
Digital Signal Processor ◽  
Short Range ◽  
Digital Signal ◽  
Flight Test ◽  
Micro Electro Mechanical System ◽  
Flight Simulation ◽  
Engineering Practice ◽  
Alignment Method ◽  
Initial Alignment ◽  
Simulation Test

This paper presents an attitude solution algorithm based on the Micro-Electro-Mechanical System and quaternion method. We completed the numerical calculation and engineering practice by adopting fourth-order Runge–Kutta algorithm in the digital signal processor. The state space mathematical model of initial alignment in static base was established, and the initial alignment method based on Kalman filter was proposed. Based on the hardware in the loop simulation platform, the short-range flight simulation test and the actual flight test were carried out. The results show that the error of pitch, yaw and roll angle is fast convergent, and the fitting rate between flight simulation and flight test is more than 85%.

Helicopter flight simulation trim in the coordinated turn with the hybrid genetic algorithm

2017 ◽  
Vol 233 (3) ◽  
pp. 1159-1168 ◽  
Author(s):  
Wei Wang ◽  
Dongsheng Li ◽  
Chun Liu
Keyword(s):  
Genetic Algorithm ◽  
Hybrid Genetic Algorithm ◽  
Flight Test ◽  
Flight Simulation ◽  
Control Vector ◽  
Experimental Platform ◽  
Helicopter Flight ◽  
Quasi Newton ◽  
General Method ◽  
Good Agreement

Helicopter trim models are multivariate nonlinear equations and it is difficult to determine these initial trim points comparable to flight conditions. To solve this question, a hybrid genetic algorithm is presented in this paper, that combines the quick convergence ability of the quasi-Newton method and the advantages of genetic algorithm, such as global convergence. The trim control vector and the constraint conditions were established in the coordinated-turn based on the helicopter flight dynamic model. The coordinated turn flight of a UH-60 A helicopter was taken as an example to simulate on the experimental platform. Comparisons were made between the trim results and flight test data and there is a good agreement among them, and the efficiency of the algorithm presented is verified. It is a general method that can be applied to trim the helicopter of different flight conditions.

Real-Time Flight Simulation for Multirotor UAV Integrated with the Dynamic Inflow Aerodynamics

2021 ◽  
Author(s):  
SunHoo Park ◽  
JeongUk Yoo ◽  
Sihun Lee ◽  
SangJoon Shin
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Real Time ◽  
Dynamic Characteristics ◽  
Flight Test ◽  
Flight Simulation ◽  
Forward Flight ◽  
Physical Constraints ◽  
Rotor Aerodynamics ◽  
Aerial Vehicles ◽  
Present Simulation

A real-time flight simulation for multirotor unmanned aerial vehicles (UAV) is performed in combination with dynamic inflow aerodynamics. The present combination procedure includes rotor/fuselage aerodynamics and trim analysis. The rotor aerodynamics is based on dynamic inflow aerodynamics, which is appropriate for the analysis of multirotor UAVs. The present simulation uses an appropriate formulation for fuselage aerodynamics. Trim analysis was conducted for climb and forward flight to determine the physical constraints of the UAV. Based on this procedure, a simulation was performed and validated against the flight test. It was found that the accuracy of flight simulation increased if the simulation is performed in combination with dynamic inflow aerodynamics. Using this methodology, the dynamic characteristics that affect the performance of UAVs were investigated.

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