CN102267564A - Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer - Google Patents
Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer Download PDFInfo
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- CN102267564A CN102267564A CN2011101229550A CN201110122955A CN102267564A CN 102267564 A CN102267564 A CN 102267564A CN 2011101229550 A CN2011101229550 A CN 2011101229550A CN 201110122955 A CN201110122955 A CN 201110122955A CN 102267564 A CN102267564 A CN 102267564A
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Abstract
The invention provides a tiltable main power system adopted for a microminiature short-distance/vertically taking off and landing flyer. The tiltable main power system is characterized in that: the tiltable main power system comprises a fuselage (6), aerofoils (71,72), empennages (8,9), a screw propeller (2) and a power system (1), wherein the power system can independently be tilted and is provided for driving the screw propeller (2) to realize the vertically/short-distance taking off and landing property.
Description
Technical field
The present invention relates to a kind of power system scheme that is applicable to the active force of verting that microminiature short distance/vertically taking off and landing flyer adopts
Background technology
With regard to present circumstances, test, trial stage that short distance/vertically taking off and landing flyer also is in research and explores.Consider the convenient of control and transmission, most the type aircraft have all adopted electronic scheme---and as propulsion source, still, cause the capacity weight of Electric aircraft little with electrical motor owing to the technical limitation of storage battery self, little during voyage weak point/boat, be difficult to be put to practical application.
Summary of the invention
The present invention is based on the applied research of microminiature short distance/vertically taking off and landing flyer, in conjunction with engineering background, has taken all factors into consideration the power requirement of such aircraft, and control requires and actual operating needs.The present invention is in conjunction with the moving short distance of oil/vertically taking off and landing flyer project, being fit to adopt piston engine or Micro Turbine Jet Engine is propulsion source, by appropriate design driving system and coaxial anti-oar system, guaranteed the power requirement of microminiature short distance/vertically taking off and landing flyer under different flight state, and actv. has increased voyage (during boat) and capacity weight, for practical engineering application has been created condition.Independently power system modular design simultaneously, making has field of application more widely by this scheme power category aircraft that can compatible well microminiature verts.
According to an aspect of the present invention, provide a kind of verted main power system of microminiature short distance/vertically taking off and landing flyer, it is characterized in that comprising: fuselage, wing, empennage, screw propeller, the power system that is used to drive screw propeller that can independently vert, thus realize its vertical/short take-off and landing (STOL) performance.
Description of drawings
Fig. 1 has shown the example of the main power system of verting according to an embodiment of the invention.
Fig. 2 has shown the coaxial anti-oar scheme that adopts according to one embodiment of present invention.
Fig. 3 is used to illustrate the principle of the coaxial anti-oar system that adopts according to one embodiment of present invention.
Fig. 4 has illustrated to show the structure of coaxial anti-oar system according to an embodiment of the invention.
Fig. 5 has shown the scheme of installation of coaxial anti-oar system according to one embodiment of present invention.
Fig. 6 has shown main power system integral structure according to an embodiment of the invention.
Fig. 7 has shown the inclining rotary mechanism scheme drawing of main power system according to an embodiment of the invention.
The specific embodiment
This class unmanned plane of short distance/vertically taking off and landing flyer according to the difference of power form, is divided into thrust orientation formula and thrust deflexion formula two classes.For thrust deflexion formula aircraft, the power system of can verting is the design-calculated key issue.But the present invention is by to the version of tilting type power system, and the appropriate design of the drive path and the steering unit that verts realizes the high-efficiency reliable power system of can verting.
The concrete technical scheme of implementing of the present invention below is described, according to an embodiment of the inventionly vert main power system as shown in Figure 1, the aircraft that adopts this main power system of can verting is except having identical wing (comprising port wing (71) and starboard wing (72)) with conventional airplane, fuselage (6), vertical tail (8), outside tailplane (9) and the alighting gear (comprising nose-gear (50) and main landing gear (51)), also has the power system that independently to vert, with case study on implementation aircraft power device---the takeoff output of piston engine (43) is passed to rotor group (2) by driving system (1).By the direction and the size of thrust of control rotor, thereby realize its vertical/short take-off and landing (STOL) performance.Wherein, for self the anti-torsional moment that guarantees aircraft is issued in a basic balance at the state that does not have the course tail-rotor, adopt coaxial anti-oar scheme, that is: screw propeller (2) comprises rotor (100) and (200) that two secondary character are identical, rotor (100) and (200) are around same rotating shaft (10) contrarotation, make its rotating speed unanimity in design, to reach the inner self-balancing moment of torsion of power system.Adopt the bispin wing simultaneously, thereby improved rotor efficient, reduced the diameter of rotor (100,200) effectively, reduce rotor inertia, help rotor (100, the 200) start of verting, owing to reduced rotor diameter, improve gyroplane rotate speed simultaneously, improved the speed of aircraft horizontal flight.Its general effect figure as shown in Figure 2
In order to realize coaxial oppositely directed function, simultaneously in order to take into account engineering practicability, adopted a cover side steering (change gear case) according to one embodiment of present invention, its principle schematic and structural representation are respectively shown in Fig. 3 and 4.Wherein, adopt conical gear (21) with active force from hand of rotation (horizontal direction) deviation of input shaft (20) to vertical direction, equidirectional with the realization of rotor S. A..Utilize an active conical gear (21) to drive driven gear (25) and (27) that are in these driving tooth both sides simultaneously simultaneously, according to the gear meshing principle, the hand of rotation of conical gear (25) and (27) is opposite.With this to the same axle mounting of gear, and be connected with (26) with axle (24) respectively, rotor (100)/(200) are connected mutually by propeller hub (27)/(28) and concentric shafts (24)/(26), have realized that promptly rotor (100) and rotor (200) around same contrarotation, form coaxial anti-oar system.
In design process, engineering is used in order to gear to actual circumstances more, consider the feasibility of this scheme and economical, in mechanism, introduce free conical gear (23), make the stressed of conical gear (25) and (27) be tending towards symmetrical, make loading transfer comparatively steady, reduced system vibration, improve structural life-time.For economic aim four conical gears (21) in the scheme, (23), (25), (27) profile are designed to same size in addition, have only its mounting hole site that difference is arranged, simplified technology like this, reduced manufacturing cost.
The installation aspect adopts intergral type fitting seat.As shown in Figure 5, the break-in system is installed in the capable mount pad of frame (29), become independent structures, power is passed to the input shaft (20) of input end successively by first synchronous belt (37), second synchronous belt (38) and the 3rd synchronous belt (39), and mount pad is fixed in carbon plate assembly (31).
2) driving system design.
The main power system integral structure as shown in Figure 6.Present microminiature is vertical/the short take-off and landing (STOL) aircraft, mostly attaching engine rotation in carrying out the process that power verts, driving engine verts with rotor system, makes the load of verting strengthen, the manipulation consumed power is big, the complexity of the system design of verting that increases in the time of waste power.So, to take all factors into consideration for structure and transmission two aspects, driving engine in the scheme (43) is designed to fixed form and installs, and by a cover transport sector power is delivered to main rotor.Contrast several type of drive commonly used by analysis, comprehensive practicality and economy are selected synchronous strap drive mode for use, utilize 3 groups of synchronous belts (37,38,39), with the transmission of power of driving engine (43) to change gear case (29).Make for convenience, assemble, as independent modular design, adopt carbon fiber framework (31) main power system as the load parts.When improving its strength and stiffness, structural weight has also obtained reasonable control like this.After main power system assembling finished, more whole main power system and fuselage (6) are linked and packed.
3) the vert design of steering unit
The power steering formula is vertical/and one of the gordian technique of short take-off and landing (STOL) aircraft is the design of inclining rotary mechanism, take all factors into consideration braking and reliability, the transmission precision of leading screw, and can utilize the character of its self-locking to realize verting power system at the lock function of different angles, so chosen the lead screw transmission mode.As shown in Figure 7, utilize steering wheel (41) to drive leading screw (40) rotation according to one embodiment of present invention, leading screw (40) rotating band shakes arm (42) and moves around tiliting axis (49), and rocking arm (42) is fixed on carbon plate assembly (31), then realized utilizing of the motion of verting of steering wheel (41) control rotor group, satisfied the power demand under the different flight state around tiliting axis (49).
Beneficial effect
Advantage of the present invention comprises:
1) succinct coaxial anti-paddle structure form has guaranteed the power system high efficient and reliable.Short distance/the vertically taking off and landing flyer of single rotor-hub configuration along with its rotor diameter of increase of maximum take-off weight also strengthens a lot, brings inconvenience, and simultaneously, for balance self moment of torsion, single rotor-hub configuration form often must adopt tail-rotor, and waste of power is bigger.And the distributing power arrangement is overlapped the reliability that inclining rotary mechanism has reduced system more, adopts coaxial anti-oar scheme can take into account both advantages preferably.Scheme is by the coaxial reverse system of appropriate design, and is simple for structure reliable.
2) the active force rotor that independently verts.With respect to great majority vertical/operating pattern that short take-off and landing (STOL) checking aircraft all adopts rotor to vert with propulsion source (driving engine), this scheme energy consumption is low, the reliability height.
3) power system standalone module design helps making I﹠ M.
Example: the proof machine design of microminiature short distance/vertically taking off and landing flyer
Unmanned plane has the not available characteristics of many manned aircrafts, is subject to people's attention day by day.But the higher site requirements that takes off/land of conventional unmanned plane has limited its field of application.Vertically taking off and landing flyer has application promise in clinical practice because its outstanding vertical takeoff and landing ability with higher flying speed and bigger voyage, has certain superiority and advance, is important directions of contemporary aircraft design-calculated.
In the example of an indefiniteness of the present invention, microminiature is vertical/and short take-off and landing (STOL) Flight Vehicle Design index is the 30Kg maximum take-off weight, and capacity weight is not less than 5Kg.Proof machine adopts the main power system layout, utilize the attitude control system that it is carried out the control of lift mode, have good can be handling and stable, pass through the appropriate design of main power system simultaneously, actv. has reduced aircaft configuration weight, when effectively band carries, when certain boat is arranged/the voyage assurance.
Claims (5)
1. the verted main power system of microminiature short distance/vertically taking off and landing flyer is characterized in that comprising:
Fuselage (6),
Wing (71,72),
Empennage (8,9),
Screw propeller (2),
The power system that is used to drive screw propeller (2) (1) that can independently vert, thus realize its vertical/short take-off and landing (STOL) performance.
2. according to the verted main power system of claim 1, it is characterized in that:
Screw propeller (2) comprises the rotor (100,200) that two secondary character are identical, and two secondary rotors (100,200) are around same rotating shaft (10) contrarotation.
3. according to the verted main power system of claim 2, it is characterized in that power system (1) comprising:
Conical gear (21), be used for active force from the hand of rotation deviation of an input shaft (20) to the perpendicular direction of this input shaft;
Be in first driven gear (25) and second driven gear (27) of this conical gear (21) both sides,
The rotation direction of the rotation direction of described first driven gear (25) and second driven gear (27) and conical gear (21) is perpendicular,
Described first driven gear (25) and the same axle mounting of second driven gear (27), and be connected with second (26) with primary shaft (24) respectively,
Described screw propeller (2) comprises first rotor (100) and second rotor (200),
First rotor (100) and second rotor (200) are connected with primary shaft (24) and second (26) mutually by first propeller hub (27) and second propeller hub (28) respectively, thereby realized that first rotor (100) and second rotor (200) around the contrarotation of same axle, form coaxial anti-oar system.
4. according to the verted main power system of claim 2, it is characterized in that further comprising:
The driving engine (43) that fixed form is installed;
Framework (31), described conical gear (21) is rotatably mounted on the framework (31).
5. according to the verted main power system of claim 2, it is characterized in that further comprising:
Leading screw (40);
Support frame (45), described leading screw (40) one ends are articulated in support frame (45), and the other end is connected with the rocking arm that verts (42),
The described rocking arm that verts (42) is connected with the power system (1) of can verting, and power system (1) can be rotated around tiliting axis (49),
Leading screw (40) rotates and drives rocking arm (42) motion of verting, and realizes the vert action of power system (1) around tiliting axis (49) then.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011101229550A CN102267564A (en) | 2011-05-12 | 2011-05-12 | Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011101229550A CN102267564A (en) | 2011-05-12 | 2011-05-12 | Tiltable main power system adopted for microminiature short-distance/vertically taking off and landing flyer |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103552686A (en) * | 2013-10-21 | 2014-02-05 | 北京航空航天大学 | Combined type ducted aerial reconnaissance robot |
| CN107117288A (en) * | 2017-05-18 | 2017-09-01 | 郝思阳 | A kind of twin shaft rotatable mechaninism based on driving cog ring structure |
| CN107311094A (en) * | 2017-06-21 | 2017-11-03 | 常州沃米尔智能机械设备有限公司 | PET bottle automatic filling line air conveyance devices with sliver adjusting means |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
| CN108313284A (en) * | 2018-03-14 | 2018-07-24 | 长沙市云智航科技有限公司 | Rotor for the vehicle that carries people to fly |
| CN109130743A (en) * | 2018-07-03 | 2019-01-04 | 北京海空行科技有限公司 | A kind of rotor inclining rotary mechanism of close coupled type hovercar |
| CN111522356A (en) * | 2020-03-27 | 2020-08-11 | 北京航空航天大学 | Strong-robustness full-envelope integrated control method for tilt rotor unmanned aerial vehicle |
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| CN1857965A (en) * | 2006-05-18 | 2006-11-08 | 胡俊峰 | Rotor shaft controllable tilting coaxial rotor wing helicopter |
| CN101274665A (en) * | 2007-03-30 | 2008-10-01 | 李荣德 | Double rotor and propeller coaxial helicopter |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
| 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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| CN1857965A (en) * | 2006-05-18 | 2006-11-08 | 胡俊峰 | Rotor shaft controllable tilting coaxial rotor wing helicopter |
| CN101274665A (en) * | 2007-03-30 | 2008-10-01 | 李荣德 | Double rotor and propeller coaxial helicopter |
| US20090057482A1 (en) * | 2007-08-29 | 2009-03-05 | Charles Lin | Transmission Device for a Twin-Rotor Helicopter |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103552686A (en) * | 2013-10-21 | 2014-02-05 | 北京航空航天大学 | Combined type ducted aerial reconnaissance robot |
| CN103552686B (en) * | 2013-10-21 | 2015-10-28 | 北京航空航天大学 | A kind of compound type duct aerial reconnaissance machine people |
| CN107117288A (en) * | 2017-05-18 | 2017-09-01 | 郝思阳 | A kind of twin shaft rotatable mechaninism based on driving cog ring structure |
| CN107311094A (en) * | 2017-06-21 | 2017-11-03 | 常州沃米尔智能机械设备有限公司 | PET bottle automatic filling line air conveyance devices with sliver adjusting means |
| CN108313284A (en) * | 2018-03-14 | 2018-07-24 | 长沙市云智航科技有限公司 | Rotor for the vehicle that carries people to fly |
| CN108313285A (en) * | 2018-03-15 | 2018-07-24 | 中国人民解放军国防科技大学 | Propeller tilting mechanism |
| CN109130743A (en) * | 2018-07-03 | 2019-01-04 | 北京海空行科技有限公司 | A kind of rotor inclining rotary mechanism of close coupled type hovercar |
| CN109130743B (en) * | 2018-07-03 | 2021-01-15 | 北京海空行科技有限公司 | Rotor wing tilting mechanism of coaxial type flying automobile |
| CN111522356A (en) * | 2020-03-27 | 2020-08-11 | 北京航空航天大学 | Strong-robustness full-envelope integrated control method for tilt rotor unmanned aerial vehicle |
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Application publication date: 20111207 |