CN109353495A - It is a kind of can VTOL unmanned autogyro - Google Patents
It is a kind of can VTOL unmanned autogyro Download PDFInfo
- Publication number
- CN109353495A CN109353495A CN201811453657.8A CN201811453657A CN109353495A CN 109353495 A CN109353495 A CN 109353495A CN 201811453657 A CN201811453657 A CN 201811453657A CN 109353495 A CN109353495 A CN 109353495A
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- rotor
- fuselage
- main rotor
- autogyro
- tilting
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- 230000008450 motivation Effects 0.000 claims description 2
- 230000008901 benefit Effects 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000000523 sample Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The invention discloses it is a kind of can VTOL unmanned autogyro, comprising: the propeller is installed on afterbody, and fuselage two sides are provided with wing and are installed on the nacelle of wing outer end；The main rotor system includes being installed on main rotor steerable system, rotor head and the main rotor blades of fuselage roof caudal, and main rotor blades are installed at the top of main rotor steerable system by rotor head；The tilting rotor system includes the tilting rotor steerable system for being installed on nacelle front end, propeller hub and tilting rotor blade, and is provided in nacelle and is respectively used to realize that tilting rotor system is verted the steering engine and motor of adjustment and rotation driving.The advantages of present invention incorporates helicopter and autogyros, have the characteristics that structure is simple, cost is relatively low, easy to operate, it is provided simultaneously with VTOL ability, hedgehopping ability and active manipulation, substantially increases the mobility of autogyro, is conducive to promote the use of.
Description
Technical field
The present invention relates to it is a kind of can VTOL unmanned autogyro, belong to aviation aircraft technical field.
Background technique
In recent years, with the fast development of aeronautical chart, various aircraft emerge one after another.Helicopter is huge because its VTOL
Big advantage holds a high place in aeronautical chart, but helicopter also have the shortcomings that it is obvious: complicated mechanism is heavy, and cost is high
It is high.And as the aircraft more longer than helicopter history, autogyro also has the advantages that huge: structure is simple, cost
Inexpensively.There is not a kind of aircraft for combining helicopter and autogyro advantage also at present, for this phenomenon, the present invention is set
Counted it is a kind of can VTOL unmanned autogyro, the tasks such as can be used for military transportation and go sightseeing.
Summary of the invention
Goal of the invention: in order to overcome the deficiencies in the prior art, the present invention provide it is a kind of can VTOL nobody
Autogyro has the characteristics that structure is simple, cost is relatively low, easy to operate, is provided simultaneously with VTOL ability, extreme low-altitude flies
Row ability and active manipulation greatly improve the mobility of autogyro, are conducive to promote the use of.
Technical solution: to achieve the above object, the technical solution adopted by the present invention are as follows:
It is a kind of can VTOL unmanned autogyro, including fuselage, propeller, main rotor system, tilting rotor system
System；
Wherein, the propeller is installed on afterbody, and the engine with propeller driving is provided in fuselage；It is described
Bikini undercarriage is installed on the downside of fuselage, and fuselage two sides are provided with wing and are installed on the nacelle of wing outer end；The master
Rotor system includes main rotor steerable system, rotor head and the main rotor blades for being installed on fuselage roof caudal, and main rotor paddle
Leaf is installed at the top of main rotor steerable system by rotor head；The tilting rotor system includes being installed on verting for nacelle front end
Rotor control system, propeller hub and tilting rotor blade, and be provided in nacelle and be respectively used to realize that tilting rotor system is verted tune
Whole and rotation driving steering engine and motor.
Further, the fore-body is provided with fuselage hatch door, can outside opened door, convenient for load maintenance.
Further, the steering of the two sides tilting rotor blade is on the contrary, to offset mutual reaction torque.
Further, the paddle disk of the tilting rotor system is in parastate with ground when taking off, and works as main rotor blades
Revolving speed state perpendicular to the ground is adjusted to by steering engine when reaching setting value.It, can be by controlling both sides during flat fly
The rotational speed difference of rotor controls the course of unmanned autogyro to reach, thus the unmanned autogyro do not need rudder and
Tail beam structure has achieved the purpose that reduce longitudinal fuselage size.
The utility model has the advantages that one kind provided by the invention can VTOL unmanned autogyro, compared with the existing technology, tool
It has the advantage that 1, combine helicopter and autogyro advantage, compact-sized simple, cost is relatively low, and it is easy to operate, together
When have VTOL ability, hedgehopping ability and active manipulation；2, putting down can be by controlling both sides rotor during flying
Rotational speed difference to reach the course for controlling unmanned autogyro, do not need rudder and tail beam structure, it is vertical to effectively reduce fuselage
To size, be conducive to Longitudinal static stability.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the embodiment of the present invention；
Fig. 2 is schematic diagram of the embodiment of the present invention in flat winged state；
Fig. 3 is schematic diagram of the embodiment of the present invention in takeoff condition；
It include: 1, main rotor blades in figure, 2, tilting rotor blade, 3, propeller hub, 4, fuselage, 5, undercarriage, 6, nacelle, 7,
Propeller, 8, main rotor steerable system, 9, rotor head, 10, fuselage hatch door, 11, wing, 12, tilting rotor steerable system.
Specific embodiment
The present invention will be further explained with reference to the accompanying drawing.
As shown in Figure 1 for it is a kind of can VTOL unmanned autogyro, including fuselage 4, propeller 7, main rotor system
System, tilting rotor system；
Wherein, the propeller 7 is installed on 4 tail portion of fuselage, and the engine driven with propeller 7 is provided in fuselage 4；
Bikini undercarriage 5 is installed, and 4 two sides of fuselage are provided with wing 11 and are installed on 11 outer end of wing on the downside of the fuselage 4
Nacelle 6；The main rotor system includes the main rotor steerable system 8 for being installed on 4 top caudal of fuselage, rotor head 9 and main rotor
Blade 1, and main rotor blades 1 are installed on 8 top of main rotor steerable system by rotor head 9；The tilting rotor system includes
It is installed on tilting rotor steerable system 12, propeller hub 3 and the tilting rotor blade 2 of 6 front end of nacelle, and is provided with difference in nacelle 6
For realizing tilting rotor system vert adjustment and rotation driving steering engine and motor.
In the present embodiment, 4 front of fuselage is provided with fuselage hatch door 10, can outside opened door, convenient for load maintenance；
The steering of the two sides tilting rotor blade 2 is on the contrary, to offset mutual reaction torque.
A specific embodiment of the invention is as follows:
When on the ground, tilting rotor paddle disk and ground are in parastate (as shown in Figure 3), are controlled by control system short
Motor speed in cabin changes the revolving speed of tilting rotor, and when revolving speed rises to certain value, the lift that tilting rotor generates will
The gravity for balancing autogyro, continues to lift up revolving speed, autogyro, which can be realized, to take off vertically；
After rising to safe altitude, the engine of autogyro fuselage interior, hair are located at by control system starting
Motivation will drive propeller rotation, and the thrust by propeller, autogyro can be realized autogyro at this time
Preceding to fly, the blade of main rotor system is by the rotation due to effect of incoming flow at this time, and autorotation speed will be before with autogyro
Rapidly degree increases and increases, and the lift that rotor generates will also increase with the increase of revolving speed；
When rotor generate lift be equal to autogyro weight (rotor generate lift size have with rotor revolving speed
It closes, for the autogyro, can obtain rotor revolving speed by the reading of rotor speed probe, when the arrival of rotor revolving speed is a certain
When revolving speed, the lift that rotor generates will be equal in weight with autogyro) when, pass through control system and controls rudder in nacelle
Tilting rotor is tilted to paddle disk state perpendicular to the ground (as shown in Figure 2) by machine；At this point, autogyro is in the horizontal direction
On by the thrust by air drag, airscrew thrust and tilting rotor, will be by rotor lift, wing in vertical direction
The effect of additional lift.Because wing can generate additional lift, the rotor of autogyro will be unloaded, with not wing
Autogyro is compared, and the maximum forward flight speed of the unmanned autogyro will increase.Therefore the unmanned autogyro can be because of rotation
Wing unloading and the additional thrust effect of tilting rotor and realize and fly before high speed.
In the sky when flight, lateral feathering and longitudinal feathering can be carried out to rotor by rotor control system,
The pitching and rolling maneuver that autogyro can be realized, the rotor rotational speed difference by controlling tilting rotor can be realized to be rotated certainly
The yaw maneuver of wing machine.When to be landed, tilting rotor is tilted to paddle disk state parallel to the ground, by its revolving speed control
Certain value is made, engine is closed, autogyro will be because the thrust of horizontal direction disappears and quick deceleration, rotor at this time
Leaf revolving speed will be reduced because of the reduction of forward flight speed, and when its revolving speed is down to zero, rotor will not generate lift, and adjustment is verted rotation
The revolving speed of the wing is to certain value, and the lift for generating it is less than the gravity of autogyro, and autogyro can be realized vertical at this time
It lands vertically and falls.
The above is only a preferred embodiment of the present invention, it should be pointed out that: for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (4)
1. one kind can VTOL unmanned autogyro, which is characterized in that including fuselage (4), propeller (7), main rotor
System, tilting rotor system；
Wherein, the propeller (7) is installed on fuselage (4) tail portion, and the hair with propeller (7) driving is provided in fuselage (4)
Motivation；It is equipped with bikini undercarriage (5) on the downside of the fuselage (4), and fuselage (4) two sides are provided with wing (11) and are installed on
The nacelle (6) of wing (11) outer end；The main rotor system includes being installed on the main rotor steerable system of caudal at the top of fuselage (4)
(8), rotor head (9) and main rotor blades (1), and main rotor blades (1) are installed on main rotor steerable system by rotor head (9)
(8) top；The tilting rotor system include be installed on the tilting rotor steerable system (12) of nacelle (6) front end, propeller hub (3) and
Tilting rotor blade (2), and nacelle (6) in be provided be respectively used to realize tilting rotor system vert adjustment and rotation driving
Steering engine and motor.
2. one kind according to claim 1 can VTOL unmanned autogyro, which is characterized in that the fuselage
(4) front is provided with fuselage hatch door (10).
3. one kind according to claim 1 can VTOL unmanned autogyro, which is characterized in that it is described two roll
The steering for rotating wing blade (2) is opposite.
4. one kind according to claim 1 can VTOL unmanned autogyro, which is characterized in that the rotation of verting
The paddle disk of wing system is in parastate with ground when taking off, and passes through rudder when the revolving speed of main rotor blades (1) reaches setting value
Machine is adjusted to state perpendicular to the ground.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811453657.8A CN109353495A (en) | 2018-11-30 | 2018-11-30 | It is a kind of can VTOL unmanned autogyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811453657.8A CN109353495A (en) | 2018-11-30 | 2018-11-30 | It is a kind of can VTOL unmanned autogyro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109353495A true CN109353495A (en) | 2019-02-19 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811453657.8A Pending CN109353495A (en) | 2018-11-30 | 2018-11-30 | It is a kind of can VTOL unmanned autogyro |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110422327A (en) * | 2019-08-26 | 2019-11-08 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tilting rotor wing unmanned aerial vehicle triangle power configuration method and structure |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN110949662A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Novel concept layout airplane with double-wing configuration |
| CN111498104A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111498101A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111762314A (en) * | 2020-07-02 | 2020-10-13 | 洛阳罗德普蓝旋翼机科技有限公司 | Rotor aircraft capable of vertically taking off and landing |
| CN112659830A (en) * | 2020-12-30 | 2021-04-16 | 上海欧少航空科技有限公司 | Self-rotary wing aerocar |
| CN114476043A (en) * | 2021-12-31 | 2022-05-13 | 中国航天空气动力技术研究院 | Electronic distributing type rotor unmanned transport plane |
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| US20070170307A1 (en) * | 2004-03-05 | 2007-07-26 | Industria Helicat Y Alas Giratorias, S.L. | Convertible aircraft operating method |
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| CN209479966U (en) * | 2018-11-30 | 2019-10-11 | 南京航空航天大学 | It is a kind of can VTOL unmanned autogyro |
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- 2018-11-30 CN CN201811453657.8A patent/CN109353495A/en active Pending
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| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110422327A (en) * | 2019-08-26 | 2019-11-08 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tilting rotor wing unmanned aerial vehicle triangle power configuration method and structure |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN110949662A (en) * | 2019-12-06 | 2020-04-03 | 江西洪都航空工业集团有限责任公司 | Novel concept layout airplane with double-wing configuration |
| CN111498104A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111498101A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
| CN111762314A (en) * | 2020-07-02 | 2020-10-13 | 洛阳罗德普蓝旋翼机科技有限公司 | Rotor aircraft capable of vertically taking off and landing |
| CN112659830A (en) * | 2020-12-30 | 2021-04-16 | 上海欧少航空科技有限公司 | Self-rotary wing aerocar |
| WO2022143444A1 (en) * | 2020-12-30 | 2022-07-07 | 吴斌 | Autogyro flying car |
| CN114476043A (en) * | 2021-12-31 | 2022-05-13 | 中国航天空气动力技术研究院 | Electronic distributing type rotor unmanned transport plane |
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