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Test system and control method for full state blowing experiment of tilting rotor

A technology for a tiltrotor and a test system, which is applied in the field of unmanned aerial vehicle model blowing experiment control system, can solve the problem of less full-state tiltrotor, etc., and achieve the effect of reducing risks.

Inactive Publication Date: 2018-01-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] At this stage, some scholars in China have carried out experimental research on the tilt rotor aircraft model or structural components such as the nacelle system, but there are few reports on the blowing experiments on the tilt rotor aircraft with power and full state. It is of great scientific significance to carry out the power and full-state blowing experiment of the rotorcraft

Method used

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  • Test system and control method for full state blowing experiment of tilting rotor
  • Test system and control method for full state blowing experiment of tilting rotor
  • Test system and control method for full state blowing experiment of tilting rotor

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Embodiment Construction

[0040] In order to make the technical problems solved by the present invention clearer and the technical solutions more specific and feasible, the present invention will be further described below in conjunction with the accompanying drawings and the specific implementation process. Wherein the experimental platform adopts a small unmanned tiltrotor full-scale model machine, it should be understood that the embodiments described here are only used to illustrate the present invention and are not intended to limit the present invention.

[0041] Such as Figure 1 to Figure 7Shown, the present invention is a kind of test system that is used for the full-state blowing experiment of tilt rotor aircraft, and this system comprises ground measurement and control system, full-scale tilt rotor aircraft platform, connecting support, balance, platform support column, wind tunnel and data acquisition equipment, of which:

[0042] A connecting bracket is installed on the center of gravity ...

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Abstract

The invention discloses a test system and control method for a full state blowing experiment of a tilting rotor, and the test system and the control method comprise an unmanned tilting rotor platform,a power system, a transmission system, a data calibration system, a data link system, a ground test and control system, a control system and a control method. The test system and control method for the full state blowing experiment of the tilting rotorhave the ability to calibrate, test and control the integrated blowing experiment of the tilting rotor blowing model. The ground test and control system communicates commands with an on-board control system through a wireless data link to complete the full state blowing experiment under the matching of different blowing speeds and nacelle angles, which is particularly suitable for studying the interference relation between the tail flow and the wing / fuselage in the dynamic state of the rotor and to provide a reliable parameter basis for analyzing the aerodynamic interference mechanism of the tilting rotor and optimizing the nonlinear flight dynamics modeling of the tilting rotor. The integrated control system has the advantages of simplewiring, high experimental efficiency and perfect test state, and effectively improves the efficiency of the full state blowing experiment of the tilting rotor.

Description

technical field [0001] The invention relates to a model blowing experiment control system for an unmanned aerial vehicle, especially for the development of a full-state and powered blowing experiment system for an unmanned aerial vehicle with a complex configuration such as a tilt rotor, and belongs to the technical field of ground testing of control systems. Background technique [0002] Tilting rotorcraft is an aircraft that combines the flight advantages of helicopters and fixed-wing propeller aircraft. The pull vector of the rotor system is converted between vertical and horizontal directions through the tilting of the nacelle, thereby completing the flight mode of the helicopter and the fixed-wing propeller aircraft. switch. Its unique aerodynamic layout can reasonably solve the flight characteristics of UAVs such as vertical take-off and landing, high-speed cruise, etc., increase the flight time and range of UAVs, and expand the flight envelope of conventional configur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/60
Inventor 郭剑东宋彦国高艳辉仲倩李志宇
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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