CN2112585U

CN2112585U - Helicopter without tail surface

Info

Publication number: CN2112585U
Application number: CN 91202582
Authority: CN
Inventors: 韩明; 刘玉锁
Original assignee: Individual
Current assignee: Individual
Priority date: 1991-02-13
Filing date: 1991-02-13
Publication date: 1992-08-12

Abstract

The utility model relates to a helicopter without tail propellers, which is characterized in that the inner part of a tail beam is provided with a one-gear or a multi-gear constant-speed blast fan driven by a tail drive axle; a spout of the tail beam is provided with a vertical rudder which can swing back and forth; one side face of the vertical rudder is a curved surface, and the other side face of the vertical rudder is a plane. When the blast fan rotates in a high speed, the air current jet out of the spout in a high speed, and the air-meeting air current angle of the curved surface of the rudder is adjusted to control the yawing and the anti-rotary wing torques. Simultaneously, the blast fan provides most forward-flying push force of the helicopter, and the function of the rotary wing is merely utilized to sustain the needed lift force of the horizontal flying the helicopter. The utility model has the advantages of simple structure, light weight and convenient operation.

Description

Helicopter without tail surface

The utility model is a kind of No Tail Rotor helicopter, is specifically related to a kind of helicopter that fan is set in tail boom.

Present helicopter horizontal tail one side all is equipped with tail-rotor, and the end of tail boom links to each other with the front end of crooked tail boom, and the terminal horizontal of crooked tail boom connects horizontal tail, and the transmission shaft of tail-rotor is located in the tail boom, as shown in Figure 1.The effect that tail-rotor is set is to offset the moment of torsion that the lifting airscrew rotation produces, and guarantees the steady of helicopter.Simultaneously, tail-rotor is set also brings unfavorable factor such as safety and speed aspect, easily hit with surface facility extensions such as trees, electric wires as the blade of tail-rotor, the dynamic loading on main shaft and the rotor blade is bigger, influenced the flying speed of helicopter, these all are that the designer is in common knowledge.Thereby design a kind of No Tail Rotor helicopter is that the designer explores always.The engineer of the U.S. steps the afterbody fan helicopter scheme that gram .S. Mang Siji discloses a kind of No Tail Rotor, the afterbody fan is one to be contained in the tail boom end, reinforce shaft drying constant speed ducted fan by main drive, outside air is sucked by inlet channel, gas sprays from the opening of duct side or slit, has played the effect of control driftage and derotation wing moment of torsion.Though this kind helicopter has been cancelled conventional tail-rotor, but the designer thinks that also the weak point of afterbody fan solutions is that the afterbody fan is than conventional tail oar system Heavy Weight, the center of gravity and the quality distribution of pure helicopter have been changed, at present also among further studying.

The purpose of this utility model is to provide a kind of simple in structure, in light weight, easy to operate tail boom fan to add the No Tail Rotor helicopter of vertical direction rudder.

The utility model is achieved in that has cancelled conventional tail-rotor, with the tail boom of helicopter as duct, the constant speed fan that one or more levels is driven by tail transmission shaft is set in its tail boom duct, (end of tail-rotor just) is provided with a vertical tail that can swing at tail boom duct spout place, also can be described as the vertical direction rudder, a side of vertical direction rudder is a curved surface, and the another side is the plane.On the base that the vertical direction rudder can be positioned at tail boom links to each other, can be provided with hydraulic gear in the base, by being located at the control lever in the operator's compartment, the vertical direction rudder can swing back and forth, controls driftage and derotation wing moment of torsion with the angle of adjusting yaw rudder and tail boom duct spout.

Fig. 1 is conventional tail-rotor helicopter structure figure.

Fig. 2, Fig. 3, Fig. 4 are the design's structural representation.

Below in conjunction with accompanying drawing the design is described in detail.

With the tail boom of helicopter as duct, the constant speed fan 3 that one or more levels is driven by tail transmission shaft 2 is set in the front portion of tail boom duct 1, there is admission port 4 in the place ahead of fan 3, at spout 5 places of tail boom duct 1 a vertical direction rudder 6 that can swing back and forth is set, a side of vertical direction rudder is a curved surface, the another side is the plane, and the principle design that produces lift when vertical direction rudder 6 can move ahead according to the fixed wing aircraft wing is made.When the fan high speed revolution, in the tail boom road is contained, produced backward high velocity air and by the spout ejection, this action of high-speed airflow has just produced athwartship moment on the vertical direction rudder, having played the effect of driftage control and anti-rotor wing torque.Because the moment size that the vertical direction rudder is produced when helicopter in hover or high-speed flight is different; so when helicopter in hover or low-speed operations; the air-flow angle of meeting of vertical direction rudder can be transferred to maximum position; the air-flow at spout place is acted on the yaw rudder; so that guarantee the required enough anti-rotor wing torques of body; when helicopter reaches certain speed or high-speed flight; the air-flow angle of meeting of yaw rudder can be turned down to zero; at this moment; the vertical direction rudder flies to produce under the action of high-speed airflow of air-flow and spout before rising the high speed of machine athwartship moment is enough to play the effect of anti-rotor wing torque; air resistance when so just having reduced helicopter flight; simultaneously; before providing major part, tail fine strain of millet ducted fan flies thrust; this moment, the effect of rotor only was to produce to keep the flat required lift that flies; so the dynamic loading that acts on its main shaft and the blade is obviously little than the dynamic loading of the conventional tail-rotor helicopter that flies under this state, so just can reduce oil consumption, improves the flying speed of helicopter.

The base of vertical direction rudder 6 can be equipped with main shaft 7 and sliding bar 8, vertical direction rudder 6 is positioned on the base 9 that links to each other with the terminal bottom of tail boom duct 1 by main shaft 7 and sliding bar 8, corresponding spindle hole 10 and chute 11 are arranged on the base 9, can be provided with hydraulic gear 12 in the base 9, hydraulic pipe 13 enters operating mechanism in the body through tail boom duct 1.Horizontal tail 14 is positioned at the end of tail boom 1.

Behind engine starting, when rotor and tail boom ducted fan reach normal operating speed, the driver's operation aircraft rises to the position of hovering, will the vertical direction rudder be transferred to the maximum air-flow angle of meeting this moment, the filter process that flies state before being changed over to by floating state also only adopts conventional operative technique, when aircraft low speed, chaufeur can suitably be adjusted the vertical direction rudder by operation hydraulic gear or other operating mode, to guarantee enough anti-rotor wing torque effects, make aircraft keep balance and driftage control, when aircraft reaches certain speed, the position of vertical direction rudder can be turned down to zero, at this moment, ducted fan provides the most of thrust that flies before the aircraft, the effect of rotor only is to produce to keep that aircraft is flat to fly required lift, the dynamic loading that acts on its main shaft and the blade is obviously little than the dynamic loading of the conventional tail-rotor helicopter that flies under this state, although flying speed increases, rotor blade still can remain on little pitch state, thereby the moment of torsion that produces on the main transmission part is also very little.

This tail boom ducted fan adds the helicopter of adjustable vertical direction rudder and compares with simple afterbody fan helicopter, has simple in structure, in light weight, easy to operate advantage, can also improve simultaneously the flying speed of helicopter to greatest extent, do not adopt Mechanical ﹠ Electrical Transmission to regulate the vertical direction rudder if do not use hydraulic gear, its weight also can further reduce.

Claims

1, a kind of No Tail Rotor helicopter, comprise body, rotor, tail boom, operating system, driving system etc., it is characterized in that in tail boom, being provided with the constant speed fan that one or more levels is driven by tail transmission shaft, tail boom is as the air-flow duct of fan, at the spout place of tail boom duct a vertical direction rudder that can swing back and forth is set, a side of vertical direction rudder is a curved surface, and the another side is the plane, on the base that the vertical direction rudder can be positioned at tail boom links to each other, there is admission port in the place ahead of fan.

2, No Tail Rotor helicopter as claimed in claim 1 is characterized in that the hydraulic gear of regulating the swing of vertical direction rudder is arranged in the base.