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Ducted coaxial helicopter control mechanism

A coaxial helicopter and control mechanism technology, applied in the direction of rotorcraft, motor vehicles, aircraft parts, etc., can solve the problems of unsatisfactory effect, complicated helicopter flight principle, and high difficulty, so as to reduce aerodynamic interference, reduce the distance between upper and lower rotors, Wide range of effects

Inactive Publication Date: 2014-02-05
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

Due to the complex flight principle of helicopters and the varied flight environments, this method of decoupling the control system is very difficult and the effect is not ideal

Method used

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  • Ducted coaxial helicopter control mechanism
  • Ducted coaxial helicopter control mechanism
  • Ducted coaxial helicopter control mechanism

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Embodiment approach

[0029] Such as Figure 1 to Figure 3 As shown, a control mechanism of a ducted coaxial helicopter includes an upper rotor system, a lower rotor system, a connecting block 14 and a strut 15, wherein the upper rotor system includes a hub 1, a blade 2, a first connecting Rod 3, rocker arm assembly 4, automatic tilter 5, second connecting rod 6, upper support seat 7, steering gear base 8, steering gear 9, slideway 10, motor 11, large toothed disc 12, pinion gear 13, rotor Shaft 16, the pinion 13 is connected with the motor 11, the large toothed disc 12 is meshed with the pinion 13, one end of the rotor shaft 16 is connected with the large toothed disc 12, and the other end is connected with the connected to the hub 1, the steering gear 9 is fixed below the hub 1 through the steering gear base 8, the upper support base 7 is set above the steering gear base 8, and the slideway 10 is set on the On the above-mentioned support seat 7, there are a moving ring and a fixed ring on the au...

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Abstract

The invention relates to a ducted coaxial helicopter control mechanism, which aims at solving the flight coupling problem of ducted coaxial helicopters, and realizes the control effect of obtaining single output by single input. According to the control mechanism, an upper and a lower rotor systems are distributed at the middle part of a helicopter body; the upper and the lower rotors are provided with three control channels respectively, that is, two more channels are provided than a common ducted coaxial helicopter; the six control channels are respectively collective pitch synchronous control, collective pitch differential control, vertical periodic variable pitch synchronous control, vertical periodic variable pitch differential control, horizontal periodic variable pitch synchronous control, horizontal periodic variable pitch differential control; the forward speed, lateral speed, vertical speed, pitch angle, roll angle, and course angle of an aircraft can be controlled individually. The control mechanism offsets coupling caused by control through symmetry, realizes decoupling control; an aircraft with the decoupling control system solves the control coupling problem of few input and excessive output by a control mode of six freedom degrees, and the control of the aircraft becomes simpler. The control mechanism has wide application prospects in military and civil fields.

Description

Technical field [0001] The design of the present invention relates to the control mechanism of rotorcraft such as ducted aircraft and coaxial helicopters, in particular to the control mechanism of ducted coaxial helicopters. Background technique [0002] In recent years, UAVs have developed rapidly, especially coaxial unmanned helicopters with axisymmetric layout. Since the coaxial dual-rotor helicopter has no tail rotor, the coupling of motion and power is small, and the flight control system is easy to implement. At the same time, it has high hovering efficiency and compact structure. Therefore, many unmanned helicopters adopt a coaxial layout. Among the coaxial unmanned helicopters that have appeared recently, the ducted coaxial unmanned helicopter with axisymmetric shape has also been greatly developed. The characteristic of the ducted layout is that the rotor is enclosed in the duct, which can protect the rotor very well, and the duct can provide additional lift and im...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/10B64C9/00
Inventor 林志昆郭剑东胡庆王兴龙刘龑
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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