CN2759940Y

CN2759940Y - Rotor blade and double rotor on the blade

Info

Publication number: CN2759940Y
Application number: CN 03207441
Authority: CN
Inventors: 欧阳厚成
Original assignee: Individual
Current assignee: Individual
Priority date: 2003-08-18
Filing date: 2003-08-18
Publication date: 2006-02-22
Anticipated expiration: 2013-08-18

Abstract

The utility model is adaptable to power aircrafts with fixed wings. The utility model has two kinds of flying performance, which are the fixed-wing aircraft flying performance and the helicopter flying performance. When the utility model is used on a horizontal tail wing, a vertical tail wing can be canceled. In the utility model, an engine is arranged on a fuselage or a fixed wing through a wing tip, the fixed wing is positioned near the fuselage and the wing can rotate around a drive shaft. Double rotary wings which have opposite rotating directions are arranged on the wing, Power passes through the engine and the drive shaft and reaches a conical gear group where the power is changed into torque in the opposite direction. The torque passes through the drive shaft of the rotary wings so as to reach the double rotary wings. Just the rotating wing and the double rotary wings arranged on the wing can complete the control of flying states and the conversion of flying functions. The double rotary wings are used so that the aircraft can use a runway to carry out short distance takeoff. Consequently, the goals of energy consumption reduction, loading capacity increase and cost reduction are reached.

Description

The bispin wing on the rotor blade and the wing

Technical field

The utility model is applicable to the fixed-wing power-driven aircraft.Can make this aerocraft have two kinds of performances of fixed wing aircraft and autogyro.On tailplane, use and then can cancel empennage.

Background technology

Tiltrotor is to have helicopter vertical takeoff and landing, hovering, do not need good flight performances such as airport; It is fast to have the fixed wing aircraft speed of a ship or plane again, and economic performance is both two kinds of power-driven aircrafts that flying method has concurrently well.

Existing tiltrotor is that the rotor engine pack that a cover can rotate between level attitude and upright position respectively is being installed on the wing tip of similar fixed wing aircraft wing.When the rotor engine pack was in vertical position, tiltrotor just was equivalent to side-by-side helicopter, had the premium properties of helicopter.When engine pack was horizontal, tiltrotor just had the premium properties of fixed wing aircraft.

Existing fixed wing power-driven aircraft is to rely on vertical tail to keep the stable of course.Finish and turn to by handling aileron on the vertical tail.

Summary of the invention

The purpose of this utility model provides the bispin wing on a kind of rotor blade and the wing.

Because the driving engine of tiltrotor is to be installed on the wing tip together with rotor, the high velocity air that produces during rotor work produces certain resistance because of the existence of driving engine; And make the design of wing and driving engine and control complicatedly, increased the cost of manufacturing, maintenance.When the rotor engine pack is in vertical position when entering the helicopter flight state, the high speed down gust that rotor work produces is subjected to the obstruction of fixed wing, has formed certain resistance on wing, has reduced the load-carrying ability of aircraft.Because what tiltrotor was used on wing tip is single rotor, for reaching vertical lift, must make the height of the diameter of rotor greater than fuselage, making tiltrotor can not make full use of short takeoff increases load-carrying ability.And formation potential safety hazard.

At above-mentioned deficiency, do following correction: driving engine is placed on fuselage place or the close fixed wing of fuselage by wing tip.Wing can be around the power drive shaft rotation.The opposite bispin wing of hand of rotation (equal diameters of the bispin wing or do not wait) is installed on the wing.The rotor required drive is imported the torque that the conical gear group is transformed to switched in opposite from driving engine through the wing intermediate solid drive shaft, sends to the bispin wing by the rotor transmission shaft.In the cabin,, the bispin wing on the wing and the wing can be rotated to needed position angle from level attitude by handling rotating mechanism (machinery, hydraulic pressure, electronic, pneumatic etc. mode) rotation wing S. A..

Use the bispin wing to compare, reduce the diameter of rotor, make this power-driven aircraft under appropriate condition, can utilize runway to carry out short takeoff, landing, increase load-carrying ability with single rotor.The bispin wing is improved energy utilization rate because hand of rotation is opposite.In lifting process,, can also obtain ground effect lift owing to rotor height overhead is very low down.Because of wing and rotor are to rotate simultaneously, vertical lift, hover and the switching process of level and vertical flight in, it is minimum that the resistance that wing forms reaches.In level and vertical flight switching process, wing can also produce certain lift.And can cancel on original fixed wing as the aileron of controlling flight course.

Engine installation at the fuselage place or near on the fixed wing of fuselage, is compared with tiltrotor, and simplified design and control reduce the cost of making, keeping in repair, and reduce the resistance of flight, improve rate of energy.

The vertical tail that existing fixed wing aerocraft uses produces very big form resistance in flight course.Resistance is bigger in steering procedure.

In that the bispin wing on the rotor blade and the wing is installed on the tailplane of power-driven aircraft,, can finish coursekeeping and the aloft function that turns to that vertical tail rises by control to bispin wing rotating speed.Accomplish to cancel vertical tail, reduce flight resistance, improve energy utilization rate, increase load-carrying ability.By handling rotating mechanism, rotor blade is finished the state of flight control action that tailplane and aileron play.

Description of drawings

Fig. 1: be the structural representation of the bispin wing on the rotor blade and the wing.Among the figure 1, power drive shaft.2, wing S. A..3 wings.4 rotors.5 rotor transmission shafts.6 conical gear groups.

Fig. 2: be four rotor structure scheme drawings on the rotor blade and the wing.Among the figure 1, power drive shaft.2, wing transmission shaft.3, wing.4, rotor.5, rotor transmission shaft.6, conical gear group.7 universal-joints.

Fig. 3: the birds-eye view that the power-driven aircraft of the bispin wing on the rotor blade and the wing all is installed for wing and empennage.Among the figure 1, fuselage.2, driving engine.3, rotating mechanism.4 rotors

Fig. 4: for the front elevation of the power-driven aircraft of the bispin wing on the rotor blade and the wing has been installed on wing and the empennage.Mark is identical with Fig. 3 among the figure

Fig. 5: for the lateral plan of the power-driven aircraft of the bispin wing on the rotor blade and the wing has been installed on wing and the empennage.Mark is identical with figure three among the figure

The specific embodiment

The contrast drawings and Examples are described as follows:

Fig. 1 is the bispin wing on the rotor blade and the wing.End at wing (3) has wing S. A. (2) to be connected with rotating mechanism.Power drive shaft (1) is connected with conical gear group (6) at wing (3) by wing rotation axis hole.The bispin wing (4) is connected with the conical gear group in wing by rotor transmission shaft (5) on the wing.

The torque that driving engine produces among the figure reaches conical gear group (7) through power drive shaft (1).Produce two rightabout torques by the conical gear group and carry out work to two rotors (4) through rotor S. A. (6).The bispin wing can rotate to needed angle position around power drive shaft on the rotor blade and the wing.

Fig. 2 can install four rotors or more rotor for adapting to the needs of large-sized power aerocraft on wing.As shown in the figure.Need consideration that universal-joint (7) is installed because of transmission shaft is long among the figure.

The wing of Fig. 3,4,5 medium power aerocrafts and empennage are installed the bispin wing on the rotor blade and the wing.Right side wing (as shown in Figure 4) is the upright position among the figure.When the right side wing rotated to be level attitude by the upright position, this power-driven aircraft just was equivalent to fixed wing aircraft, can carry out short takeoff, landing and horizontal flight.Has the advantage quick, that economic performance is good.The upper and lower rotation of wing level attitude is finished the state of flight controllable function of aileron on original fixed wing by handling rotating mechanism awing.Control the rotating speed of rotor on the empennage as required and come the direction of stabilized flight and turn to, finish the state of flight controllable function that tailplane and aileron play by handling on the empennage rotating mechanism rotor blade.When handling rotating mechanism the rotor blade on wing and the empennage is all rotated to the upright position, this power-driven aircraft just is equivalent to side-by-side helicopter, has the helicopter lifting, hovers, do not need good airworthiness such as airport.

Claims

1, be applicable to the bispin wing on the rotor blade of power-driven aircraft and the wing, it is characterized in that: the end at wing (3) has wing S. A. (2) to be connected with the aircraft rotating mechanism; Power drive shaft (1) is connected with conical gear group (6) in wing by wing rotation axis hole; The bispin wing (4) on the wing is connected with the conical gear group in wing by rotor transmission shaft (5); In the cabin,, rotate wing S. A. (2) and the bispin wing (4) on the wing (3) and the wing can be rotated to needed position angle by handling rotating mechanism.

2, according to the bispin wing on claim 1, described rotor blade and the wing, it is characterized in that also being: the rotor required drive is to pass through the torque that conical gear group (6) is transformed into switched in opposite from driving engine by wing intermediate solid drive shaft (1), sends to by rotor transmission shaft (5).

3, according to the bispin wing on claim 1, described rotor blade and the wing, it is characterized in that also being: four rotors or more rotors (shown in figure two) can be installed on the wing.