CN102020016A - Helicopter without rotor - Google Patents
Helicopter without rotor Download PDFInfo
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- CN102020016A CN102020016A CN2009102509551A CN200910250955A CN102020016A CN 102020016 A CN102020016 A CN 102020016A CN 2009102509551 A CN2009102509551 A CN 2009102509551A CN 200910250955 A CN200910250955 A CN 200910250955A CN 102020016 A CN102020016 A CN 102020016A
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- rudder
- primary structure
- structure member
- rotating shaft
- engine installation
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Abstract
A helicopter without rotors is composed of three parts: a power plant, an aircraft fuselage, and an operation control mechanism. The core of the three parts is the power plant, which comprises rotating blades, a rotating shaft, a stressed member, a rudder shaft, a rudder, a power plant bearing, a stressed member bearing, a power machine, and a rudder. The lift force of the vertical motion and the driving force of the horizontal motion are generated by the stressed member as a result of the centrifugal action generated by the air rotation caused by the rotating blades. The helicopter without rotors provided by the present invention has neither the long wings of common airliners nor the rotors of common helicopters; the helicopter without rotors has the advantages of simple structure, small volume, high operability, and good stealth effect.
Description
Technical field
The present invention relates to a kind of autogyro, especially a kind of centrifugal effect of the blade drive air high speed rotating of rotation that relies on produces the lift upwards and a kind of no rotor autogyro of horizontal motion power.
Background technology
At present, the aircraft in the world mainly contains two kinds, a kind of is the path of leaning on the alteration of form air flows of wing, make the wing upper and lower surface produce difference of pressure and obtain lift, the present passenger plane and the lift of most of fighter plane all are based on this mode and obtain, and its advantage is that lift is big, shortcoming is that aircraft must have certain kinematic velocity could produce enough lift, can not aloft hover, wing is oversize, makes overall aircraft seem huge; Another kind of aircraft is a helicopter, and helicopter mainly is made up of body (containing rotor and tail-rotor), power, transmission three big systems and airborne flight equipment etc.Rotor is generally driven by the machine driven system of being made up of transmission shaft and retarder etc. by turboaxle motor or piston engine, also can be driven by the antagonistic force of the jet generation of blade tip.Practical application at present be the single-rotor helicopter and the twin-rotor helicopter of mechanically driver type, wherein maximum with single-rotor helicopter quantity again.The outstanding feature of helicopter is to do low latitude, low speed and the maneuvering flight of heading unmodified, particularly can be in small size place vertical takeoff and landing.Because these characteristics make it have wide purposes and development prospect.Be widely used in attacking over the ground aspect military, machine fall land, weapon transports, logistics support, rescue of battlefield, reconnaissance patrol, commander's control, signal communication, antisubmarine clearance, electronic countermeasure etc.Aspect civilian, be applied to short-distance transport, medical aid, disaster relief lifesaving, emergency resuce, hanging device, geoexploration, protect a forest fire extinguishing, aerophotography etc.Personnel between offshore field and base and goods and materials transportation are importances of coml.The present relative aircraft of helicopter vibrates and noise level is higher, the Maintenance and Repair work capacity is big, use cost is higher, and speed is lower, and voyage is shorter.
Summary of the invention
Existing autogyro complex structure, volume are big in order to overcome, the Maintenance and Repair work capacity is big, use cost is higher, the shortcoming of complicated operation, the invention provides a kind of no rotor of brand new, the autogyro of No Tail Rotor, mainly form by fuselage, engine installation, control setup three parts, its compact conformation, simple, volume less (no rotor takes up room), the Maintenance and Repair work capacity is little, simple to operate, use cost is lower.
The technical solution adopted for the present invention to solve the technical problems is:
Key component of the present invention is an engine installation, the rotating blade that employing has horizontal shaft (rotor of helicopter is a vertical axis) drives the air high speed rotating, the high speed rotating air centrifugal effect under, the power that produces lift upwards and all around move, this engine installation and fuselage combination, add that the fuselage technology of existing maturation and control technology just become a kind of brand new and do not have the wing autogyro, no rotor autogyro of the present invention, the long wing that had not both had skycoach, the rotor that does not also have pure helicopter, compact conformation, volume is little, simple in structure, simple to operate, stealth effect is good.
Description of drawings
The invention will be further described below in conjunction with drawings and Examples.
Fig. 1 is power set rotating vane schematic diagram of the present invention.
1. rotating vanes among the figure, 2. rotating shaft, 3. primary structure member, 4. air molecule, the 5. axis of rudder, 6. rudder, 7. angle A.
In Fig. 1, rotating vane 1 is connected with rotating shaft 2, rotating shaft 2 and horizontal direction almost parallel, when rotating shaft 2 is rotated, 1 rotation of driven rotary blade, near the rotating vane 1 large quantity of air molecule 4 is and then rotation also, the air molecule high speed rotating need to obtain centripetal force, this power is born by primary structure member 3, primary structure member 3 provides centripetal force, itself has just obtained rightabout reaction force, and the direction of this power roughly makes progress, and primary structure member 3 usefulness bearings are connected in the rotating shaft 2, can do the deflection of certain angle, there is an angle A 7 in it with horizontal direction on one side, and angle A7 is under the control of controlling organization, and its angular dimension can change, angle A7 varies in size, vertical stress component and the horizontal component of the power that primary structure member 3 is subjected to are in different size, by regulating angle A7 angle, can obtain simultaneously lift upwards and the power that advances forward or backward; Rudder 6 is positioned at the lower right, outer of blade 1, under the effect of operating mechanism, rudder 6 can be done around the axis of rudder 5 rotation of certain angle, in order to change the direction of air, simultaneously itself be subjected to a reaction force, this power can change the direction of actuating unit, when actuating unit is used for helicopter, also just can change the direction of motion of helicopter, reach the purpose of turning.
Fig. 2 is an engine installation principle of work scheme drawing of the present invention.
1. rotating blades among the figure, 2. rotating shaft, 3. primary structure member, 8. engine installation bearing, 9. primary structure member bearing, 10. engine.
In Fig. 2, engine 10 drives rotating shaft 2 and rotating blade 1 rotation, engine installation bearing 8 inner rings and rotating shaft 2 closely cooperate, and the outer ring is fixed on the airframe, and primary structure member bearing 9 inner rings and rotating shaft 2 closely cooperate, outer ring and primary structure member 3 leak-tight joints, make rotating shaft 2 rotation and primary structure member 3 does not rotate, but can be by hand, electronic, hydraulic efficiency gear regulates the inclination angle, to change the normal component and the horizontal component of power, normal component is as lift, and horizontal component is as the power of advancing.
Fig. 3 is one embodiment of the present invention scheme drawing.
1. rotating blades among the figure, 2. rotating shaft, 3. primary structure member, the 5. axis of rudder, 6. yaw rudder, 8. engine installation bearing, 9. primary structure member bearing, 10. engine, 11. airframes, 12. alighting gears, 13. air intakes, 14. air discharge ports.
In Fig. 3, engine installation is by rotating blade 1, rotating shaft 2, primary structure member 3, the axis of rudder 5, yaw rudder 6, engine installation bearing 8, primary structure member bearing 9, engine 10 is formed, when engine 10 rotations, rotating shaft 2 driven rotary blades 1 rotate, and near the air the blade 1 also rotates, when the air velocity of rotating is very high, primary structure member is produced huge pressure, and air enters continuously from air intake 13 simultaneously, discharges at a high speed from air discharge port 14; Can change the force direction that is subjected to of primary structure member by the angle of operation primary structure member 3, just change horizontal component and normal component, cooresponding effect is exactly that aircraft rises, descends, advances, retreats, and by the deflection angle of direction of operating rudder 6, just can change the working direction of autogyro.Airframe 11 can be made a lot of shapes, is preferably made UFO-likely, reaches good stealth effect easily, when alighting gear 12 is used for aircraft and is parked on the ground to the support of aircraft.
The specific embodiment
In the embodiments of figure 3, we are that the present invention is further described for example to implement a no heligyro:
Airframe: because the present invention does not have wing, there is not rotor yet, No Tail Rotor, shape need to airframe 11 does not have conventional airplane or autogyro so strict, just random, so present embodiment is selected a flying disk type fuselage, realize a no heligyro, material can be selected generally to make the alloy material that aircraft uses and make, must consider inside and outside difference of pressure, require strength of material height, light, not perishable etc., use existing airframe manufacturing technology generally can reach requirement.
Engine installation: engine installation is installed on waist, engine 10 is selected spark ignition engine, be fixed on the fuselage, the rotating speed of spark ignition engine is lower, can consider change speed gear box, engine installation bearing 8 is selected high-speed bearing, must consider the voltage endurance capability of bearing, because the total weight of aircraft and lift are all born by bearing; Engine installation bearing 8 inner rings and rotating shaft 2 are combined closely, the outer ring is fixed on the fuselage, rotating blade 1 needs with the high light material manufacture of intensity, with pressure and the centnifugal force that bears high-speed operation, primary structure member bearing 9 inner rings and rotating shaft 2 are combined closely, the outer ring is connected with primary structure member 3, because primary structure member 3 will bear the total weight of aircraft, so it is firmly necessary with being connected of primary structure member bearing 9, yaw rudder 6 is enclosed within the yaw rudder rotating shaft 5, and yaw rudder is positioned at position on the lower side, rear portion, when air is got rid of downwards backward through air discharge port 14, it is parallel to get rid of direction as yaw rudder 6 and air, the yaw rudder stress balance does not produce turning efficiency, when direction of operating rudder 6 and air exhaustion direction have certain angle, yaw rudder 6 is stressed, promotes aircraft and turns to.
The operation control mechanism: the present invention is owing to no wing, rotor, tail-rotor, so operate simple relatively, the operation control mechanism divides two parts (not drawing among the figure): 1, the operation of the power of lift and forward-reverse, this can realize by the rotating speed of hydraulic pressure or electric power operation engine and the angle of primary structure member 3,2, the operation of yaw rudder, can realize with the angle of hydraulic pressure or electric power operation yaw rudder 6, because hydraulic operation and electric power operation closely generally use in present generation aircraft, technology is very ripe, just introduces no longer in detail here.
Claims (3)
1. a no heligyro is characterized in that: be made up of engine installation, airframe, operation control mechanism three parts.Wherein most crucial part is an engine installation, is to rely on the blade of rotation to drive that air rotates the centrifugal effect that produces and the power that obtains lift and horizontal motion.
2. a kind of no heligyro as claimed in claim 1, it is characterized in that: engine installation is made up of rotating blade, rotating shaft, primary structure member, the axis of rudder, yaw rudder, engine installation bearing, primary structure member bearing, engine, engine installation bearing inner ring and rotating shaft flush fit, the outer ring is fixed on the airframe, primary structure member bearing inner ring and rotating shaft flush fit, outer ring and primary structure member leak-tight joint, make the rotating shaft rotation and primary structure member does not rotate, can be by hand, electronic, hydraulic efficiency gear regulates its inclination angle, to change the normal component and the horizontal component of power; Yaw rudder is positioned at the outer of blade, and yaw rudder can be done the rotation of certain angle around the axis of rudder, in order to change the direction of air, reaches the purpose of turning.
3. a kind of no heligyro as claimed in claim 2, it is characterized in that: rotating shaft is an approximate horizontal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102509551A CN102020016A (en) | 2009-12-21 | 2009-12-21 | Helicopter without rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009102509551A CN102020016A (en) | 2009-12-21 | 2009-12-21 | Helicopter without rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102020016A true CN102020016A (en) | 2011-04-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009102509551A Pending CN102020016A (en) | 2009-12-21 | 2009-12-21 | Helicopter without rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102020016A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985555A (en) * | 2017-11-13 | 2018-05-04 | 上海顺砾智能科技有限公司 | One kind is without the mute unmanned plane of wing formula |
-
2009
- 2009-12-21 CN CN2009102509551A patent/CN102020016A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985555A (en) * | 2017-11-13 | 2018-05-04 | 上海顺砾智能科技有限公司 | One kind is without the mute unmanned plane of wing formula |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20110420 |