A flight experimental platform for synchrophasing control based on a small propeller UAV

Cao, Yun Fei; Huang, Xianghua; Sheng, Long; Wang, Zhipeng

doi:10.1007/s11431-018-9329-0

Cited by 9 publications

(4 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Although numerous autonomous UAV platforms have been designed, new concepts of autonomous fixed wings UAVs [2] and helicopter [3] platforms are still being proposed. The research of rotary-wing UAV platforms is even more abundant, as different hardware designs are required for newly appearing applications.…”

Section: A Contributions Beyond State-of-the-artmentioning

confidence: 99%

MRS Modular UAV Hardware Platforms for Supporting Research in Real-World Outdoor and Indoor Environments

Hert,

Baca,

Petracek

et al. 2023

Preprint

View full text Add to dashboard Cite

Section: A Contributions Beyond State-of-the-artmentioning

confidence: 99%

MRS Modular UAV Hardware Platforms for Supporting Research in Real-World Outdoor and Indoor Environments

Hert,

Baca,

Petracek

et al. 2023

Preprint

View full text Add to dashboard Cite

“…From Equation (21), it can be seen that GRM contains the information of time, rotation speed and direction of the rotation axis. The rotation speed equals to 0 when the rotation element keeps still, and then…”

Section: Dynamic Calculation Formulas With Generalized Rotation Matri...mentioning

confidence: 99%

“…As for the rotor system with multiple rotors rotating at the same rotation speed, each of the rotors can be regarded as an individual sound source, and the noise can be modified by only adjusting the initial angles of the rotors. Moreover, the shapes of the blades are not changed, and the noise cancellation can be realized without changing the of dynamic characteristics [16][17][18][19][20][21][22][23][24]. Guan et al have carried out a noise attenuation experiment with a quadrotor using the phase synchronization method [25].…”

Section: Introductionmentioning

confidence: 99%

A Dynamic RCS and Noise Prediction and Reduction Method of Coaxial Tilt-Rotor Aircraft Based on Phase Modulation

Wang

Huang

et al. 2022

Sensors

View full text Add to dashboard Cite

For tilt-rotor aircraft with coaxial rotors (coaxial rotor aircraft), reduction of radar cross section as well as acoustic noise can be essential for stealth design, and the rotation of the coaxial rotors can have an influence on noise and dynamic radar cross section (RCS) characteristics. In this paper, an approach to the prediction of both the sound pressure level (SPL) of noise and the dynamic RCS of coaxial-tilt aircraft is carried out, based on the theories of the FW-H equation, the physics optics method (PO) and the physical theory of diffraction (PTD) method. In order to deal with the rotating parts (mainly including coaxial rotors), a generated rotation matrix (GRM) is raised, aiming at giving a universal formula for the time-domain grid coordinate transformation of all kinds of rotation parts with arbitrary rotation centers and rotation axis directions. Moreover, a compass-scissors model (CSM) reflecting the phase characteristics of coaxial rotors is established, and a method of noise reduction and RCS reduction based on the phase modulation method is put forward in this paper. The simulation results show that with proper CSM parameter combinations, the reduction of noise SPL can reach approximately 3~15 dB and the reduction of dynamic RCS can reach 1.6 dBsm at most. The dynamic RCS and noise prediction and reduction method can be meaningful for the radar-acoustic stealth design of coaxial tilt-rotor aircrafts.

show abstract

“…A variety of micro turbojet engines have been developed. Rig tests of conventional aeroengine can only be carried out in a few research institutes, while the rig test of micro-engines can be carried out in the laboratory, with a low risk and cost; therefore, micro-engine rig tests can be used for verifying advanced control theory of aeroengines [5][6][7]. Advanced turboprop engines have two independent controlled variables, fuel flow, and propeller pitch angle, which makes it possible to keep the propeller rotating stably at variable speeds.…”

Section: Introductionmentioning

confidence: 99%

Research on Modeling of a Micro Variable-Pitch Turboprop Engine Based on Rig Test Data

2020

Self Cite

View full text Add to dashboard Cite

Exact component characteristics are required for establishing an accurate component level aeroengine model. When component characteristics is lacking, the dynamic coefficient method based on test data, is suitable for establishing a single-input and single-output aeroengine model. When it is applied to build multiple-input, multiple-output aeroengine models, some parameters are assumed to be unchanged, which causes large error. An improved modeling method based on rig data is proposed to establish a double-input, double-output model for a micro variable-pitch turboprop engine. The input variables are fuel flow and pitch angle, and the output variables are rotational speeds of the core engine and the propeller. First, in order to gather modeling data, a test bench is designed and rig tests are carried out. Then, two conclusions are obtained by analyzing the rig data, based on which, the power turbine output is taken as the function of the core speed and the propeller speed. The established model has the property that the input variables can vary arbitrarily within the defined domain, without any restriction to the output variables. Simulation results showed that the model has a high dynamic and steady-state accuracy. The maximum error was less than 8%. The real-time performance was greatly improved, compared to the component level model. regulating mechanism is designed and a micro turboprop engine test platform is built.The mathematical model of the aeroengine plays an important role in the design and verification of the aeroengine control system, which can effectively reduce the development time, risk, and cost [8,9]. Micro gas turbine engines are widely used as low-cost solutions, therefore, fewer sensors are usually available than in standard gas turbines [8]. An accurate model can offer reference signals to the control system of micro engines. The modern aeroengine control systems adopt model-based ones, to fully utilize their performance. Modern aeroengine control methods such as performance seeking control, life extending control, and fault-tolerant control require an on-board engine model to track unmeasured parameters [10,11]. Aeroengine modeling methods can be divided into three categories-analytical methods based on operating principles (white box method), system identification methods based on test data (black box method), and gray box methods, which consider synthetic test data and operating principles.A component level model is built based on analytical methods, by using component characteristics and engine operating principles. It is the most common aeroengine modeling method. Fitzgerald et al. from Georgia Tech Institute built a component level model, based on the component characteristics of SPT5 [12,13]. The component characteristics are obtained via rig tests carried out in their own test platform. The model obtained by the analytical method has a high precision and can simulate both steady-state and dynamic engine outputs in the full envelope. However, this method requires accurate component ch...

show abstract

A flight experimental platform for synchrophasing control based on a small propeller UAV

Cited by 9 publications

References 6 publications

MRS Modular UAV Hardware Platforms for Supporting Research in Real-World Outdoor and Indoor Environments

MRS Modular UAV Hardware Platforms for Supporting Research in Real-World Outdoor and Indoor Environments

A Dynamic RCS and Noise Prediction and Reduction Method of Coaxial Tilt-Rotor Aircraft Based on Phase Modulation

Research on Modeling of a Micro Variable-Pitch Turboprop Engine Based on Rig Test Data

Contact Info

Product

Resources

About