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Calculation method for tilting corridor of tilting quadrotor aircraft with constant speed and periodic variable pitch

A tilting quadrotor, cyclic pitch change technology, applied in computing, computer-aided design, instruments, etc., to achieve the effect of small body waste resistance, safe tilting, and maximum body waste resistance

Active Publication Date: 2021-06-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to provide a calculation method for the tilting corridor of a tilting quadrotor aircraft with a fixed speed band and a periodical variable pitch, so as to overcome the inability to use a suitable method in the prior art to calculate the QTR tilting corridor

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  • Calculation method for tilting corridor of tilting quadrotor aircraft with constant speed and periodic variable pitch
  • Calculation method for tilting corridor of tilting quadrotor aircraft with constant speed and periodic variable pitch
  • Calculation method for tilting corridor of tilting quadrotor aircraft with constant speed and periodic variable pitch

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Embodiment Construction

[0083] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with examples and accompanying drawings, and the contents mentioned in the implementation modes are not intended to limit the present invention.

[0084] refer to figure 1 As shown, a method for calculating the tilting corridor of a tilting quadrotor aircraft with a fixed speed and a periodic variable pitch of the present invention includes the following steps:

[0085] 1) Establish the flight mechanics model of each component of the aircraft, transform all forces and moments into the body shaft system, and establish a six-degree-of-freedom balance equation;

[0086] 2) Select the tilting control mode: constant speed with period variable pitch control;

[0087] 3) Solve the upper and lower boundaries of the pitch angle with the wing lift characteristic as the limiting factor; optimize the trim solution to obtain the control amount a...

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Abstract

The invention discloses a method for calculating the tilting corridor of a tilting quadrotor aircraft with a fixed speed and periodical variable pitch, comprising the following steps: establishing a flight mechanics model of each part of the aircraft, and converting all forces and moments to the body axis system , establish the six-degree-of-freedom balance equation; determine the tilt control mode; take the wing lift characteristics as the limiting factor, solve the upper and lower boundaries of the pitch angle; optimize the trim solution to obtain the control amount and attitude angle under different state conditions; find the corresponding wing lift The characteristic-limited minimum speed boundary and the wing lift characteristic-limited high-speed boundary; by solving the required power at different state points, the available power-limited high-speed boundary is obtained. The present invention is based on a flight mechanics model, considers parameters in various aspects of aircraft design, and reflects the specific attributes of each feasible flight point. The invention is also applicable to the calculation of the tilting corridor of the tilting quadrotor aircraft under different control modes.

Description

technical field [0001] The invention discloses a calculation method for a tilting corridor of a tilting quadrotor aircraft (hereinafter referred to as QTR) controlled at a constant speed with period variable pitch, and belongs to the technical field of flight mechanics and control of tilting rotor aircraft. Background technique [0002] Since Bell Helicopter Company of the United States proposed the concept of QTR at the beginning of this century, QTR is still in the exploration stage at home and abroad. configured as figure 1 As shown, the aircraft has two front and rear wings, and a tiltable rotor nacelle is installed at the two ends of the wing. [0003] QTR takes off and lands vertically in helicopter mode, flies at high speed in fixed-wing aircraft mode, and can enter tilt transition mode by tilting the nacelle. Therefore, QTR has the advantages of helicopter mode vertical take-off and landing, fixed-point hovering and aircraft mode long-distance transportation, high-...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/00B64F5/00G05D1/08
CPCB64F5/00G06F30/15G06F30/20
Inventor 潘浙平陈仁良
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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