Calculation method of tilt corridor of tilt four-rotor aircraft with periodic variable pitch at constant rotational speed

A technology of tilting quadrotors and periodic pitch change, which is applied in computing, instruments, aircraft parts, etc.

Active Publication Date: 2018-12-18
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 of tilt corridor of tilt four-rotor aircraft with periodic variable pitch at constant rotational speed
  • Calculation method of tilt corridor of tilt four-rotor aircraft with periodic variable pitch at constant rotational speed
  • Calculation method of tilt corridor of tilt four-rotor aircraft with periodic variable pitch at constant rotational speed

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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 calculation method of a tilt corridor of a tilt four-rotor aircraft with periodic variable pitch at constant rotational speed, which comprises the following steps: establishing flight mechanics models of various parts of the aircraft, converting all forces and moments into a body shaft system, and establishing a six-degree-of-freedom balance equation; determining the tiltcontrol mode; solving the upper and lower boundaries of the pitch angle by taking the lift characteristics of the wing as the limiting factor; obtaining the control variables and attitude angles under different state conditions by optimal trimming; finding the corresponding wing lift characteristic limit minimum speed boundary and wing lift characteristic limit high speed boundary; obtaining theavailable power limiting high-speed boundary by solving the required power at different state points. The invention is based on a flight mechanics model, takes into account the parameters of each aspect of the aircraft design, and reflects the specific attributes of each feasible flight point. The invention is also applicable to the tilt corridor calculation of tilt four-rotor 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 Applications(China)
IPC IPC(8): B64F5/00G06F17/50
CPCB64F5/00G06F30/15G06F30/20
Inventor 潘浙平陈仁良
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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