CN100398398C

CN100398398C - Rotary wing helicopter

Info

Publication number: CN100398398C
Application number: CNB2006100605847A
Authority: CN
Inventors: 刘昌喆
Original assignee: Individual
Current assignee: Individual
Priority date: 2006-04-29
Filing date: 2006-04-29
Publication date: 2008-07-02
Anticipated expiration: 2026-04-29
Also published as: CN1847090A; WO2007124624A1

Abstract

The present invention relates to a helicopter with umbrella-surface rotary-wing traces. At least one connecting member is connected between the external end of a rotary wing and a propeller hub, wherein both ends of the connecting member are respectively hinged with the external end of the rotary wing and the lower end of the propeller hub. When the present invention works, the rotary wing, the connecting member and the propeller hub rotate together. A control ring is arranged below the propeller hub, and an auxiliary connecting member is connected between the external end of the rotary wing and the control ring. The rotary trace surface of a wingtip of the present invention is approximate to 'rigidity', so the safety, the reliability, and the loading capacity of the external end of the rotary wing are enhanced. The rotary wing forms an umbrella-shaped rotary trace surface during flight, so that air stream pressing toward the lower part of the rotary wing can be gathered, and the lifting efficiency of the rotary wing can be increased. Therefore, the present invention can save energy and enhance effective load. The torque load of structures of a rotary wing, a propeller hub and a connecting member on the normal plane is uniformly resolved to tension without the concentration of stress. Therefore, the design and the structure of the present invention can be compact. The auxiliary connecting member of the present invention is used for adjusting the lifting angle of the rotary wing for controlling a heading direction of flight. The tension is directly exerted on the external end of the rotary wing, which can avoid the lag of torsional vibration and operational reaction.

Description

The helicopter of umbrella cover rotor track

[technical field]

The present invention relates to a kind of heligyro, relate in particular to a kind of helicopter of umbrella cover rotor track.

[background technology]

At present, the rotor of helicopter all is the beam type structure, and for obtaining enough lift, its span all designs quite longly.Moment loading condiction harsh on normal plane makes rotary-wing root section, flapping hinge and rotation propeller hub all must design solid thick and heavyly, so that reduced capacity weight and increased manufacturing cost.

During present helicopter flight, the lift effect upwarps beam type structure rotor, its rotational trajectory is umbrella shape face or the conical suface that opening makes progress, the air-flow post that rotor is depressed is outwards dispersed, reduce the upper and lower difference of pressure of aerofoil, thereby make the efficient that produces lift lower, very most of power of waste driving engine.The direction control mechanism of existing helicopter acts on the root of rotor the inner, and the position of aerodynamic force effect the strongest (the most effective) is the outer end of rotor, the drawback that this just brings easy generation torsional oscillation and operant response to lag behind.The lift angle of tip station and the wing root of tradition rotor change asynchronous be easy to generate also under special flying condition that the gas bullet causes tremble or the paddling track plane " wafts partially ", the airplane crash record that existing so far many examples are correlated with.

[summary of the invention]

Technical matters to be solved by this invention is to provide a kind of helicopter of umbrella cover rotor track, and its safety is higher, and the lift efficient of its rotor is higher, can effectively save the energy, increases capacity weight.

The further technical matters to be solved of the present invention is to provide a kind of helicopter that can effectively avoid the umbrella cover rotor track of rotor generation torsional oscillation and operant response hysteresis.

For solving the problems of the technologies described above, the technical solution adopted in the present invention is: the helicopter that a kind of umbrella cover rotor track is provided, it has rotor and propeller hub, the root of described rotor is articulated in the upper end of propeller hub, between the outer end of rotor and propeller hub, be connected with at least one attaching parts, the two ends of described attaching parts are articulated in the outer end of rotor and the lower end of propeller hub respectively, during work, rotor and attaching parts rotate with propeller hub, and described attaching parts keeps the wing tip of rotor to be lower than other positions of rotor all the time.

More specifically, described attaching parts can be side tension cords or pull bar.

More specifically, also be provided with a control loop in described propeller hub below, between the outer end of rotor and control loop, be connected with a secondary attaching parts, the outer end that the two ends of described secondary attaching parts are articulated in rotor respectively is near wing tip trailing edge place and control loop, and itself and the hinged place of rotor and the hinged place of described attaching parts and rotor have certain distance on chordwise.

More specifically, described secondary attaching parts can be side tension cords or pull bar.

More specifically, described control loop is the translation control loop, and itself and propeller hub rotate synchronously, can revolve translation on the vertical surface again simultaneously.

More specifically, the outer end chord length of described rotor is greater than inner chord length.

Compared with prior art, the present invention has following beneficial effect: because the wing tip of rotor of the present invention is along going up by relative fixed at " normal plane " under aerofoil pulling force, centnifugal force and the effect of attaching parts pulling force three-dimensional, the circle of its wing tip rotational trajectory face approximate " rigidity ", thereby increased safe reliability, also increased the load-bearing capacity of rotor outer end.The linear velocity of rotor outer end is higher relatively, and the lift when being the rotor rotation is partly maximum.Since at the pulling force of attaching parts, propeller hub along under the entad pulling force and the effect of aerofoil lift of rotor, the rotor tip is lower than other positions of rotor all the time, rotor at uniform lift and down by gravity (component) effect transmitted at rotor two ends, centre portion arches up, at this moment rotational trajectory is just as the crown of Western-style umbrella.During flight, " Western-style umbrella " crown shape rotational trajectory face that forms draws the air-flow of pressing to the rotor below in, increases the upper and lower faces difference of pressure of rotor, improve the lift efficient of rotor, this can significantly reduce waste, the energy savings of idle work and alleviate the weight of driving engine and increase capacity weight.The moment load that is configured on the normal plane of rotor, propeller hub and attaching parts is decomposed into tension force equably, does not have stress concentration, can design light and handy structure, reduces weight, increases capacity weight.In addition, when control loop biasing, off-axis center, wing tip trailing edge by secondary attaching parts pulling of the present invention, make rotor twist its outer section lift angle in half cycle and increase, and lift angle reduces in other half cycle, thereby make rotor at lift and attaching parts pulling force rebalancing, lift angle is done opposite degree change in cooresponding two half cycles, secondary attaching parts is used to adjust the rotor lift angle, and its pulling force directly acts on the outer end of rotor, can not produce torsional oscillation and operant response hysteresis phenomenon.And the outer end chord length that makes rotor just makes the outer end rotor widen greater than inner chord length, and design can increase active area like this, thereby increases lift, and the design that this external load increases still can't realize in existing helicopter design.

[description of drawings]

The present invention is described in further detail below in conjunction with the drawings and specific embodiments:

Fig. 1 is the structural representation of a preferred embodiment of the present invention.

Fig. 2 is the elevational schematic view of Fig. 1 middle part subassembly.

[specific embodiment]

See also Fig. 1 and Fig. 2, it is a preferred embodiment of the present invention, the helicopter of umbrella cover rotor track of the present invention has rotor 2 and rotation propeller hub 1, the root of rotor 2 is articulated in the upper end of propeller hub 1, be connected with at least one attaching parts 4 between the outer end of rotor 2 and propeller hub 1, described attaching parts 4 can be side tension cords or connecting rod, and its two ends are articulated in the outer end of rotor 2 and the lower end of propeller hub 1 respectively, during work, rotor 2 and attaching parts 4 are with propeller hub 1 rotation.

Also be provided with a control loop 6 in the below of above-mentioned propeller hub 1, described control loop 6 is the translation control loop, itself and propeller hub 1 rotate synchronously, simultaneously translation on the vertical surface can revolved again, thereby make rotor 2 control the course in the locational lift difference of each covering of the fan of full circle week, wherein, the sense of motion of control loop 6 please refer to the direction of arrow among Fig. 2.Between the outer end of rotor 2 and control loop 6, be connected with a secondary attaching parts 5, be used to adjust the lift angle of rotor 2.Described secondary attaching parts 5 can be side tension cords or pull bar equally, its two ends are articulated in the outer end of rotor 2 respectively near on wing tip trailing edge place and the control loop 6, and the hinged place 3 ' of the hinged place 3 of itself and rotor 2 and described attaching parts 4 and rotor 2 has certain distance on chordwise.The effect of secondary attaching parts 5 of the present invention is identical with the effect of the lift angle pull bar of pure helicopter, and it utilizes the same principle of drag-line control sail, and under the combined action of centnifugal force, the lift angle of control rotor 2 is handled flight course.Secondary attaching parts 5 of the present invention is with the difference of the lift angle pull bar of pure helicopter, the pulling force of secondary attaching parts 5 of the present invention directly acts on the outer end of rotor 2, control loop 6 biasings, during the off-axis center, the wing tip trailing edge of secondary attaching parts 5 pullings, its outer section of rotor 2 distortions lift angle in half cycle is increased, and lift angle reduces in other half cycle, thereby make rotor 2 at lift and attaching parts 4 pulling force rebalancings, lift angle is done opposite degree change in cooresponding two half cycles, secondary attaching parts 5 is used to adjust rotor 2 lift angles, its pulling force directly acts on the outer end of rotor 2, thereby can not produce torsional oscillation and operant response hysteresis phenomenon.

The helicopter of umbrella cover rotor track of the present invention since at the pulling force of attaching parts 4, propeller hub 1 along under the entad pulling force and the effect of aerofoil lift of rotor 2, rotor 2 tips are lower than rotor 2 other positions all the time, rotor 2 is uniform lift and transmitting under gravity (component) effect by rotor 2 two ends, the centre portion arch, at this moment rotational trajectory is just as the crown of Western-style umbrella.During flight, " Western-style umbrella " crown shape rotational trajectory face that forms, the air-flow of pressing to rotor 2 belows is drawn in, increase the upper and lower faces difference of pressure of rotor 2, thereby improve the lift efficient of rotor 2, this can significantly reduce waste, the energy savings of idle work and alleviate the weight of driving engine and increase capacity weight.

Because lift of the present invention can not concentrate on rotor 2 roots, rotor 2 outer ends can be by the part lift of making a concerted effort to bear of stretching force and centnifugal force, propeller hub 1 can design lightly relatively, the outer end chord length of rotor 2 can design than inner bigger, being about to the rotor outer end widens, design can increase active area like this, thereby increases lift, and the design that this external load increases still can't realize in existing helicopter design.It is asymmetric that aerofoil section can be designed to string, and this wing wing with common dopey is identical, has higher 1ift-drag ratio, therefore can further improve lift efficient.

Claims

1. the helicopter of a umbrella cover rotor track, have rotor (2) and propeller hub (1), the root of described rotor (2) is articulated in the upper end of propeller hub (1), between the outer end of described rotor (2) and propeller hub (1), be connected with at least one attaching parts (4), the two ends of described attaching parts (4) are articulated in the outer end of rotor (2) and the lower end of propeller hub (1) respectively, during work, described rotor (2) and attaching parts (4) are with propeller hub (1) rotation, and it is characterized in that: described attaching parts (4) keeps the wing tip of described rotor (2) to be lower than other positions of rotor (2) all the time.

2. the helicopter of umbrella cover rotor track as claimed in claim 1 is characterized in that: described attaching parts (4) is a side tension cords.

3. the helicopter of umbrella cover rotor track as claimed in claim 1 is characterized in that: described attaching parts (4) is a pull bar.

4. as the helicopter of any described umbrella cover rotor track in the claim 1 to 3, it is characterized in that: also be provided with a control loop (6) in described propeller hub (1) below, between the outer end of rotor (2) and control loop (6), be connected with a secondary attaching parts (5), the two ends of described secondary attaching parts (5) are articulated in the outer end of rotor (2) respectively near on wing tip trailing edge place and the control loop (6), and the hinged place of the hinged place of itself and rotor (2) and described attaching parts (4) and rotor (2) has certain distance on chordwise.

5. the helicopter of umbrella cover rotor track as claimed in claim 4 is characterized in that: described secondary attaching parts (5) is a side tension cords.

6. the helicopter of umbrella cover rotor track as claimed in claim 4 is characterized in that: described secondary attaching parts (5) is a pull bar.

7. the helicopter of umbrella cover rotor track as claimed in claim 4 is characterized in that: described control loop (6) is the translation control loop, and the rotation synchronously of itself and propeller hub (1) can revolved translation on the vertical surface again simultaneously.

8. the helicopter of umbrella cover rotor track as claimed in claim 1 is characterized in that: the outer end chord length of described rotor (2) is greater than inner chord length.