Miniature airplane pitch operating method and control mechanism

A control mechanism and aircraft technology, applied in aircraft control, aircraft parts, transportation and packaging, etc., can solve the problems of reduced aerodynamic efficiency, opposite direction of force and torque, stall, etc., and achieve high reliability, easy operation, and simple mechanism Effect

Inactive Publication Date: 2006-01-11
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
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AI Technical Summary

Problems solved by technology

[0005] In order to overcome the problem in the prior art that when the rudder surface is deflected, the airflow separation area on the airfoil will increase, resulting in a decrease in aerodynamic efficiency or even a stall, and the opposite direction of the force and moment generated by the rudder surface. The method of realizing the manipulation of micro-aircraft by position

Method used

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  • Miniature airplane pitch operating method and control mechanism
  • Miniature airplane pitch operating method and control mechanism
  • Miniature airplane pitch operating method and control mechanism

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Embodiment Construction

[0021] This embodiment is a relatively independent miniature aircraft with wings and fuselage. Comprising a wing 4, a fuselage 8, a wing lug 12, a fuselage lug 17, a wing / body connecting rod 13 and a control steering gear 16 formed by connecting the left wing and the right wing.

[0022] The aerodynamic center of the aircraft mainly depends on the wing characteristics, and the position of the center of gravity mainly depends on the fuselage structure and loading. In practice, when factors such as wing, fuselage shape and loading are determined, the positions of aerodynamic center and center of gravity can be determined.

[0023] The wing 4 is positioned above the fuselage 8, and a pair of lugs 12 are mounted on the lower surface of the wing at the junction of the left and right wings. There are shaft holes for connection on the lugs; a pair of lugs 17 are also fixedly installed at the axial position above the fuselage, and the distance between the fuselage lugs 17 along the f...

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Abstract

A method and its control mechanics for manipulating the pitching of the miniature airplane feature that the relative position of the airplane's gravitation center to its pneumatic center on the axis of airplane body and the length of the force arm between pneumatic power and said gravitation center are changed by connecting wing and airplane body to become a parallelogram to generate additional pitching moment for manipulating airplane.

Description

(1) Technical field [0001] The invention relates to a micro-aircraft, and relates to a pitching control method and a control mechanism of the aircraft by moving the front and rear positions of the center of gravity of the micro-aircraft. (2) Background technology [0002] Micro-aircraft is an emerging technical field in recent years, usually defined as: the size of each dimension does not exceed 150mm, and the weight is 10-100g. It has the characteristics of flexible maneuvering, wide range of applications, and strong concealment when performing tasks, so it has high military and civilian application values. [0003] At present, the traditional steering gear / rudder surface system is the most commonly used in the control of micro-aircraft. By controlling the deflection position of the rudder surface, the pitching moment is generated, the effective angle of attack of the wing is changed, and the lift coefficient is changed, thereby controlling the flight state. However, due t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C19/00
Inventor 袁昌盛张炜宋笔锋
Owner NORTHWESTERN POLYTECHNICAL UNIV
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