CN106494616A - Hybrid lift tilting rotor assault aircraft - Google Patents
Hybrid lift tilting rotor assault aircraft Download PDFInfo
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- CN106494616A CN106494616A CN201510559680.5A CN201510559680A CN106494616A CN 106494616 A CN106494616 A CN 106494616A CN 201510559680 A CN201510559680 A CN 201510559680A CN 106494616 A CN106494616 A CN 106494616A
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- rotor
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- bevel gear
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Abstract
It is an advantage of the invention that employing lifting and the flying method of tilting rotor/lift fan combined type, thus make the type on the basis of eagle machine property indices are maintained substantially, the machine is made more to obtain excellent hybrid lift ability, the stable transfer capability of liter thrust under the conditions of hybrid lift and hybrid lift flight performance, simplify manipulation difficulty and manufacturing process difficulty, the safe yarn number for improving vertical lift load-carrying and aircraft and occupant by a relatively large margin, and with higher flight speed, voyage farther out and multiple load prestowage forms and VTOL, short distance or super-short distance rolling start, the technical performance such as landing ability and good mobility.The design of hybrid lift tilting rotor assault aircraft substantially departing from the design pattern that existing tilting rotor class aircraft is traditional, fundamentally overcomes and solves sternly vertical defect and deficiency of the tilt rotor aircraft in terms of safety and lift from outward appearance to integral layout.
Description
Technical field
A kind of hybrid lift tilting rotor assault aircraft, belongs to technical field of aerospace
Technical background
The tiltrotor aircraft for uniquely producing in the world at present and coming into operation is passed through by the U.S.
MV-22 " osprey " tilt rotor aircraft that develops for many years.But through being used for process
From the point of view of the analysis to relevant information picture, at present the type aircraft also exist many not enough and
Defect, as take off vertically switch transition to flat fly or from flat fly to be transformed into vertical landing when
Balanced capacity is poor, and shifter is complicated, manipulation difficulty is big, deflection rotor steering spindle square compared with
Greatly, the increase of fixed-wing resistance less and that cause because rotor diameter is excessive in horizontal flight,
The shortcomings of fuel consumption height and relatively low safety coefficient.The assault transport of hybrid lift tilting rotor
Machine is exactly studied for solving the problems of existing tilt rotor aircraft under this background
A kind of aircraft of the novel concept topology layout form for going out.
Content of the invention
The purpose of the present invention is exactly for solving the above problems and one kind that is not enough and providing can be vertically
STOL, employ by the wing of fuselage both sides turboaxle motor axle provide power
The double duct lift fan of tandem and be supplied to by turbine wheel shaft simultaneously and be placed at fixed wing
Rotor power on two ends and configuration rotor are verted the hybrid lift tilting rotor assault of device
Transporter.
The mesh ground and solution for realizing the present invention is to be provided with driving cabin 2 in 1 front portion of fuselage,
In fuselage, rear portion be closely semi-circular crew module 3, fuselage bottom front and rear distinguish
The round lift fan trouserss 4 of two longitudinal layouts are provided with, in the upper and lower of trouserss 4
Aperture face is provided with the venetian blind type bucket cover plate 5 of activity, and lower blade cover plate can also left and right pendulum
Dynamic, make aircraft realize lateral motion capability (as shown in Figure 6), in the outer both sides of waist
Two turboshaft engines 7 are installed on fixed wing 6, in the both ends of the surface of fixed wing 6
Square pod apertures 8 and movable wings cover plate 9 is provided with, (front for 9 closure state of cover plate, after
For 9 open mode of cover plate) tailplane 10 and double vertical tails is additionally provided with afterbody
11.
Two turboaxle motors 7 are separately mounted to both sides and fix in wing 6, in electromotor
Driving bevel gear 13 is housed on axle 12, driving bevel gear 13 is engaged with drive bevel gear 14
And the dynamic axis 15 of band cross is rotated, and drive drive bevel gear 16 and longitudinal axiss transmission simultaneously
17 longitudinal lift fan power transmission shaft 18 of bevel gear and drive bevel gear 19 are rotated.Dynamic in cross
Clutch 20 and variator 21 is also equipped with axis 15.
Lift fan vertical pivot 22 is vertically installed on fuselage base plate 23 and lower bracing strut 24, is erected
Lift fan 25 and vertical pivot drive bevel gear 26 is also equipped with axle 22.Vertical pivot is driven umbrella tooth
Wheel 26 is engaged with drive bevel gear 19 and rotates lift fan 25.
Dynamic 15 two ends of axis of cross extend transverse to wing two ends, and vert device from rotor
Pass through in the hole of 27 mother rib lateral rotundum sleeve column 28, at the two ends of the dynamic axis 15 of cross equipped with transmission
Bevel gear 29, bevel gear 29 and the drive bevel gear 31 that starches installed in rotor on vertical pivot 30
Engagement, rotor vertical pivot 30 be longitudinally mounted to rotor vert device 27 top and bottom on perpendicular
In d-axis hole, rotor 32 is installed on the top of rotor vertical pivot 30.It is located at rotor
The vert circular hole sleeve column 28 of device side of oar is sleeved on and is fixed on circular hole sleeve column load-bearing on wing 6
In support set 33, rotor vert the outer bottom of device 27, be provided with semi-circular gear on side
Circle 34, gear ring 34 are engaged and by tooth with the gear 36 installed in 35 two ends of axis of verting
Wheel 36 is rotated, and realizes that Synchronization Control wing two ends rotor starches the tilt angle of the device 27 that verts
Degree, the axis 35 that verts is by the motor 37 in the middle of fuselage by being mounted in motor shaft
The rotation of bar 39 on 38 is mounted in the worm gear 40 verted on axis 35 and realizes that rotor is verted
The tilt synchronous axial system of device 27 and rotor 32.
Accompanying drawing 1 is assault aircraft front view
Accompanying drawing 2 is that assault aircraft is faced and cuts open figure
Accompanying drawing 3 is assault aircraft top view
Accompanying drawing 4 is that full power transmission yarn system topology layout view overlooked by assault aircraft
Accompanying drawing 5 is assault aircraft upward view
Accompanying drawing 6 is assault aircraft side view
Accompanying drawing 7 is assault aircraft side view cutaway drawing
Accompanying drawing 8 is that rotor is verted device three-view diagram
In figure：The closely semi-circular crew module 4- trouserss 5- bucket covers of 1- fuselage 2- driving cabins 3-
Plate 6- fixes wing 7- turboshaft engine 8- square pod apertures 9- movable wings cover plates
10- tailplane 11- vertical tail 12- engine shaft 13- driving bevel gears 14- is passed
The dynamic axis 16- drive bevel gears 17- longitudinal directions axle drivel gear of 15 1 cross of dynamic bevel gear
18 1 longitudinal 19 1 drive bevel gear 20- clutch 21- variators of lift fan power transmission shaft
22 1 lift fan vertical pivot, 23 1 fuselage base plate 24 once 25 1 lift fan 26 of bracing strut
One vertical pivot drive bevel gear 27- rotors vert device 28- circular hole sleeve columns 29- transmission umbrella tooth
Wheel 30- rotor vertical pivot 31- drive bevel gear 32- rotors 33 1 justify load bearing support set
The semi-circular gear rings 35 1 of 34- vert 36 1 gear of axis, 37 1 motor, 38 1 snail
42 1 landing gear compartment of oil pipe, 43 1 wheel 44 1 received by 39 1 worm gear 40- radars 41 1 of bar
47 1 pressure bearing of fuel bunker 45 1 axis support, 46 1 securing member, 48 1 cabin back door
It is an advantage of the invention that employing the lifting of tilting rotor/lift fan combined type and flying
Line mode, thus make the type on the basis of burnt eagle machine property indices are maintained substantially,
The liter thrust for making the machine more obtain under the conditions of excellent hybrid lift ability, hybrid lift is steady
Fixed transfer capability and compound flight performance, simplify manipulation difficulty and manufacturing process difficulty,
Dike by a relatively large margin has risen the safe yarn number of vertical lift load-carrying and aircraft and occupant, and has
Higher flight speed, voyage farther out and multiple load prestowage forms and VTOL, short
Away from or super-short distance rolling start, landing the technical performance such as ability and good mobility.
Specific embodiment
With reference to view, the invention will be further described：
When aircraft vertical takes off, venetian blind type bucket cover plate 5 and then rotate gear is first opened
37 tilting rotor oars vert device 27, and rotor 32 is rotated to horizontal level, while opening
Wing cover 9 in square pod apertures 8, then starts turboaxle motor 7 and by master
Bevel gear 13 starts rotor transmission yarn system, rotates rotor 32, subsequently closes clutch
Device 20, longitudinally starts whole lift fan by 13 travelling gear of driving gear and is driven yarn system,
Lift fan 13 is driven to rotate.At this moment aircraft is in lift fan 25 and tilting rotor oar 32
Hang down under the common lift effect for providing, be achieved that the VTOL and hovering of aircraft.When winged
When machine needs flight forward, just make tilt device 27 vert rotation again, make rotor 32 incline
Upright position is gone to, makes aircraft obtain thrust, aircraft is realized in the air to moving ahead, in the air
Carry out air slip line flight.And the lift of this stage aircraft is mainly by lift fan 25
The lift gradually increased with wing 6 is provided jointly, reaches certain speed, fixed machine in aircraft
The wing 6 can be provided after enough lift for aircraft, at this moment can holdback clutch 20 make lift wind
Fan 25 quits work, and closes upper and lower cover plates 5, aircraft is entered under the promotion of rotor 32
Enter normal level flight condition.When aircraft is arrived at needs vertical landing or hovering,
Upper and lower bucket cover plate can be opened, and is completed by repeating the inverse process of aforesaid operations program.
Also adjustable swing blade of louver window (as shown in Figure 6) in hang.Obtain aircraft
Certain transverse presentation locomotivity.
After variable balance adjustment lift fan 25 with 32 angle of tilting rotor oar, aircraft is just
Different compound landings and load effect can be obtained, such as short distance, short distance and corresponding
Various variable load effects.
The design of hybrid lift tilting rotor assault aircraft base from outward appearance to integral layout
This fundamentally overcomes reconciliation departing from the traditional design pattern of existing tilting rotor class aircraft
Determine sternly vertical defect and deficiency of the tilt rotor aircraft in terms of safety and lift, significantly carried
High every efficiency index, so that the machine obtains many of fixed wing airplane and helicopter
Item combination property advantage, makes the type become a kind of broad-spectrum new the army and the people's multipurpose
Type.
Claims (4)
1. a kind of can VTOL hybrid lift tilting rotor assault aircraft, it is characterised in that：Driving cabin (2) is provided with fuselage (1) front portion, in fuselage, rear portion is closely semi-circular crew module (3), in round lift fan trouserss (4) that the front and rear of fuselage bottom is respectively equipped with two longitudinal layouts, in the upper of trouserss (4), lower aperture face is provided with the venetian blind type bucket cover plate (5) of activity, lower blade cover plate can also swing, aircraft is made to realize lateral motion capability (as shown in Figure 6), two turboshaft engines (7) are installed on the fixed wing (6) of the outer both sides of waist, square pod apertures (8) and movable wings cover plate (9) are provided with the both ends of the surface of fixed wing (6), (front for 9 closure state of cover plate, it is 9 open mode of cover plate afterwards) tailplane (10) and double vertical tails (11) is additionally provided with afterbody.
2. the hybrid lift tilting rotor assault aircraft according to described in claim 1, it is characterised in that：Two turboaxle motors (7) are separately mounted to both sides and fix in wing (6), upper equipped with driving bevel gear (13) in engine shaft (12), driving bevel gear (13) is nibbled the dynamic axis (15) of Merging zone method cross with drive bevel gear (14) and is rotated, and drives drive bevel gear (16) and longitudinal axle drivel gear (17) longitudinal direction lift fan power transmission shaft (18) and drive bevel gear (19) to rotate simultaneously.Clutch (20) and variator (21) are also equipped with the dynamic axis (15) of cross.
3. the hybrid lift tilting rotor assault aircraft according to described in claim 1, it is characterised in that：Lift fan vertical pivot (22) is vertically installed on fuselage base plate (23) and lower bracing strut (24), is also equipped with lift fan (25) and vertical pivot drive bevel gear (26) on vertical pivot (22).Vertical pivot drive bevel gear (26) is engaged with drive bevel gear (19) and rotates lift fan (25).
4. the hybrid lift tilting rotor assault aircraft according to described in claim 1, it is characterised in that：Cross moves axis (15) two ends and extends transverse to wing two ends, and pass through in the hole for verting the mother rib lateral rotundum sleeve column (28) of device (27) from rotor, drive bevel gear (29) is housed at the two ends of cross dynamic axis (15), bevel gear (29) is engaged with the drive bevel gear (31) on rotor slurry vertical pivot (30), rotor vertical pivot (30) be longitudinally mounted to rotor vert device (27) top and bottom on vertical axis hole in, rotor (32) is installed on the top of rotor vertical pivot (30).It is located at the vert circular hole sleeve column (28) of device side of rotor to be sleeved on and be fixed in upper circular hole sleeve column load bearing support set (33) of wing (6), vert the outer bottom of device (27) in rotor, side is provided with semi-circular gear ring (34), gear (34) is engaged with the gear (36) installed in axis (35) two ends of verting and gear 36 is rotated, realize that Synchronization Control wing two ends rotor starches the tilt angle of device (27) of verting, bar (39) of the axis (35) by the motor (37) in the middle of the fuselage by being mounted on motor shaft (38) that vert rotates the worm gear (40) being mounted on the axis that verts (35) and realizes that rotor is verted the synchronously inclining rotation of device (27) and rotor (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510559680.5A CN106494616A (en) | 2015-09-07 | 2015-09-07 | Hybrid lift tilting rotor assault aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510559680.5A CN106494616A (en) | 2015-09-07 | 2015-09-07 | Hybrid lift tilting rotor assault aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106494616A true CN106494616A (en) | 2017-03-15 |
Family
ID=58286528
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510559680.5A Pending CN106494616A (en) | 2015-09-07 | 2015-09-07 | Hybrid lift tilting rotor assault aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106494616A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107089322A (en) * | 2017-04-26 | 2017-08-25 | 浙江点辰航空科技有限公司 | One kind becomes the dynamic multi-rotor unmanned aerial vehicle of lift structure oil |
| CN107985537A (en) * | 2017-11-30 | 2018-05-04 | 吉林大学 | A kind of amphibious submariner device of new culvert type |
| CN108408042A (en) * | 2018-04-12 | 2018-08-17 | 中国计量大学 | A kind of tiltrotor with deformable wing |
| CN110450958A (en) * | 2019-07-18 | 2019-11-15 | 江苏大学 | A kind of unmanned ground effect vehicle of plant protection |
-
2015
- 2015-09-07 CN CN201510559680.5A patent/CN106494616A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107089322A (en) * | 2017-04-26 | 2017-08-25 | 浙江点辰航空科技有限公司 | One kind becomes the dynamic multi-rotor unmanned aerial vehicle of lift structure oil |
| CN107089322B (en) * | 2017-04-26 | 2024-06-11 | 国网新疆电力有限公司奎屯供电公司 | Oil-driven multi-rotor unmanned aerial vehicle with variable lift structure |
| CN107985537A (en) * | 2017-11-30 | 2018-05-04 | 吉林大学 | A kind of amphibious submariner device of new culvert type |
| CN108408042A (en) * | 2018-04-12 | 2018-08-17 | 中国计量大学 | A kind of tiltrotor with deformable wing |
| CN110450958A (en) * | 2019-07-18 | 2019-11-15 | 江苏大学 | A kind of unmanned ground effect vehicle of plant protection |
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| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170315 |
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| WD01 | Invention patent application deemed withdrawn after publication |