CN206871358U - Drive mechanism in a kind of tilt rotor aircraft wing - Google Patents
Drive mechanism in a kind of tilt rotor aircraft wing Download PDFInfo
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- CN206871358U CN206871358U CN201720317780.1U CN201720317780U CN206871358U CN 206871358 U CN206871358 U CN 206871358U CN 201720317780 U CN201720317780 U CN 201720317780U CN 206871358 U CN206871358 U CN 206871358U
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Abstract
It the utility model is related to spacecraft field of power machinery, there is provided drive mechanism in a kind of tilt rotor aircraft wing, drive mechanism are bifurcated, be symmetricly set in inside the wing of fuselage both sides, and every drive mechanism includes main body load gearing frame, gear unit；Main body load gearing frame includes carbon fiber crossbeam, fixed deckle board, flange；Gear unit includes T-shaped commutator, T-shaped commutator output shaft, shaft coupling subelement, the power output shaft being sequentially connected；Power output shaft and flange pass through bearing fit and fixation；Gear unit is fixed in the middle part of the main body load gearing frame；On the carbon fiber crossbeam axis direction, drive mechanism acts synergistically with wing；On the carbon fiber crossbeam axis direction, drive mechanism does not limit mutually with wing.The utility model uses the scheme of engine in front of rear wheel mid-engine, in the case where ensureing to be driven in wing, effectively simplifies wing structure, mitigates wing weight, improves effective commercial transport of tiltrotor aircraft.
Description
Technical field
Spacecraft field of power machinery is the utility model is related to, transmission knot in more particularly to a kind of tilt rotor aircraft wing
Structure.
Background technology
Tilting rotor：A kind of aircraft form, aircraft can produce the rotation that lift makees similar helicopter upwards by propeller
The wing flies；Propeller can also be verted and make fixed-wing flight to horizontal level.
Tiltrotor aircraft technology, rise earliest in the U.S. in last century 5, the sixties.Comparative maturity verts at present
Gyroplane, the large-scale osprey for having the U.S., medium-sized hawkeye, small-sized black panther for having Israel etc..Above-mentioned project is effective
Improve fighting efficiency in certain circumstances.Above-mentioned technology concentrates on transporter field that can be manned, and design redundancy is big, is available for
The design space of performance is well-to-do；And for the small and medium size unmanned aerial vehicles of big voyage endurance, it is all more sensitive to weight and space, it is existing
The excessive Redundancy Design of technology causes the waste of effective commercial transport.
The domestic research in terms of unmanned plane at present is in blowout state, and unmanned plane is different from transporter, technology impetus
Difference, domestic Patents, the dynamic correlation that is also not carried out verting of oil, although electronic have the advantages that easy to control, phase
Closing Patent design does not have the shortcomings that direct, but before battery capacity makes a breakthrough, made aircraft can not realize heavy－duty,
Big voyage, the work of high request can not be adapted to.
The existing electric tilting rotor wing patent closest to the design（Patent name：Tilting four-rotor-wing aircraft；Patent is public
The number of opening：103072688A）Occur, but because electronic scheme does not have a power transmission, it is simple in construction a lot；The dynamic tilting rotor of oil nobody
Machine has subversiveness meaning in terms of big load and big voyage, though domestic in this respect have many concept types to show, not yet sends out
The case and the similar patent formula for being directed to concrete technical problems that real border is successful.
Utility model content
The purpose of this utility model is exactly the defects of overcoming prior art, there is provided is driven in a kind of tilt rotor aircraft wing
Structure, in the case where ensureing to be driven in wing, effectively simplify wing structure, mitigate wing weight, improve the rotor aircraft that verts
Effective commercial transport.
The utility model mainly solves the problems, such as three Practical Projects：
1st, the loss of weight of engine in front of rear wheel mid-engine carries effect drive technology.The electronic multi-rotor unmanned aerial vehicle of main flow takes in battery energy storage technology
The problems such as long voyage endurance and heavy－duty can not be broken through before must breaking through, being driven respectively using multiple oil machines needs solve gross weight mistake
Greatly, efficiency caused by rotary inertia is low and revolution speed of propeller matching problem.Oil machine driving aircraft uses the utility model side
Case, such issues that can effectively solve；
2nd, the problem of wing deformation is with internal reliable transmission.Bending deformation, but scheme can occur under different loads for wing
Design is needed in wing internal drive, thus needs to solve because propeller shaft length adaptability problem, side caused by wing deformation
The efficiency transmitted to adaptability problem and power；
3rd, propeller power transmission problem.Because the rotational power of propeller needs to be passed on out of wing, propeller
The velocity of following will necessarily be produced when verting, how to handle this velocity of following, how effectively by moment of torsion in the mechanism of " revolution "
Propeller is transferred to, will be resolved in the utility model.
Drive mechanism in a kind of tilt rotor aircraft wing of the utility model, the drive mechanism are bifurcated, are symmetricly set in
Inside the wing of fuselage both sides, every drive mechanism includes main body load gearing frame, gear unit；
The main body load gearing frame includes carbon fiber crossbeam, fixed deckle board, flange；The carbon fiber crossbeam passes through solid
Determine deckle board to be fixedly connected with fuselage, the flange is arranged at the main body load gearing frame end；
The gear unit includes T-shaped commutator, T-shaped commutator output shaft, shaft coupling subelement, the power being sequentially connected
Output shaft；The power output shaft and the flange pass through bearing fit and fixation；
The gear unit is fixed in the middle part of the main body load gearing frame；
On the carbon fiber crossbeam axis direction, the drive mechanism acts synergistically with wing；In the carbon
On fiber crossbeam axis direction, the drive mechanism does not limit mutually with wing.
Further, the shaft coupling subelement be sequentially connected first shaft coupling, intermediate propeller shaft, the second shaft coupling
Device, the first shaft coupling also with T-shaped commutator export axis connection, the second shaft coupling also with power output axis connection.
Further, the shaft coupling subelement is flexible clutch.
Further, the first shaft coupling, second shaft coupling are Hooks coupling universal coupling.
Further, the main body load gearing frame is collectively formed by carbon fiber crossbeam, fixed deckle board, flange
" mesh " font structure.
Further, the length of the main body load gearing frame is slightly longer than wing length, leaves gap delta.
The utility model additionally provides one kind and verted wing unmanned plane, including above-mentioned drive mechanism.
The beneficial effects of the utility model are：Wing and the complementary architectural feature of framework, i.e. wing and framework pass through
Carbon fibre crossbeam contacts, and in crossbeam radially strong interaction each other, is taken off with satisfaction needed for the stress such as landing；Wing and
Framework is all fixed on fuselage, but in the axial direction, is not limited each other, and leaves axial float space；Outside wing
Framework and transmission scheme, it is allowed to a small amount of elastic deformation of crossbeam, power input shaft and output shaft are fixed；By flange and fixation
" mesh " character form structure that deckle board and carbon fibre crossbeam collectively form, the position and shape control of input shaft and output shaft can connect
By within the scope of；Using the scheme of engine in front of rear wheel mid-engine, in the case where ensureing to be driven in wing, effectively simplify wing structure,
Mitigate wing weight, improve effective commercial transport of tiltrotor aircraft.
Brief description of the drawings
It is total that Fig. 1 show drive mechanism and wing, propeller in a kind of tilt rotor aircraft wing of the utility model embodiment
Into position relationship schematic diagram.
Fig. 2 show wing and main body load gearing frame interstitial site schematic diagram.
Fig. 3 show drive mechanism schematic diagram in a kind of tilt rotor aircraft wing of the utility model embodiment.
Fig. 4 show main body load gearing frame structural representation.
In figure：1- wings, 2- screw propeller assemblies, 3- main body loads gearing frame, 4-T types commutator, 5- first shaft couplings,
6- intermediate propeller shafts, 7- second shaft couplings, 8- power output shafts, 9- flanges, 10- fix deckle board, 11- carbon fiber crossbeams.
Embodiment
The utility model specific embodiment is described in detail below in conjunction with specific accompanying drawing.It should be noted that following implementations
Example described in technical characteristic or technical characteristic combination be not construed as it is isolated, they can be mutually combined from
And reach superior technique effect.In the accompanying drawing of following embodiments, the identical label that each accompanying drawing occurs represents identical spy
Sign or part, can be applied in different embodiments.
As Figure 1-4, drive mechanism bifurcates in a kind of tilt rotor aircraft wing of the utility model embodiment, symmetrically sets
It is placed in inside the wing 1 of fuselage both sides, every drive mechanism includes main body load gearing frame 3, gear unit；
The main body load gearing frame 3 includes carbon fiber crossbeam 11, fixed deckle board 10, flange 9；The carbon fiber crossbeam
11 are fixedly connected by fixed deckle board 10 with fuselage（Carbon fiber crossbeam 11 is fixed on fixed deckle board 10, fixed deckle board 10 and machine
Body connects）；The flange 9 is arranged at the end of main body load gearing frame 3（In the present embodiment, flange 9 is fixed on carbon fiber
The end of crossbeam 11）；Preferably, the main body load gearing frame 3 is common by carbon fiber crossbeam 11, fixed deckle board 10, flange 9
" mesh " font structure formed.
It is T-shaped commutator 4 that the gear unit includes being sequentially connected, T-shaped commutator output shaft, shaft coupling subelement, dynamic
Power output shaft 8；The power output shaft 8 and the flange 9 pass through bearing fit and fixation；The power output shaft 8 is used for handle
Shaft end head of the torque drive of engine to the transmission shaft end, i.e. installation propeller end of the both ends propeller of wing 1；The power
Output shaft 8 is constrained by the bearing on flange 9, can be with bearing 8 relative to the high-speed rotation of flange 9, when wing 1, carbon fiber crossbeam
During 11 respective deformation, the power output shaft 8 moves with carbon fiber crossbeam 11, and wing 1 is not related, so as to avoid wing 1
Dimensional variations caused by deformation.
The gear unit is fixed on the middle part of main body load gearing frame 3；
On the axis direction of carbon fiber crossbeam 11, the drive mechanism acts synergistically with wing 1；Described
On the axis direction of carbon fiber crossbeam 11, the drive mechanism does not limit mutually with wing 1.One of specific implementation is：The carbon
Fiber crossbeam 11 contacts with the rib in wing 1, rib central aperture, and the carbon fiber crossbeam 11 passes through out of hole, the carbon fiber
Radial forces interact between crossbeam 11 and fuselage, but are axially allowing play.
Preferably, the shaft coupling subelement is first shaft coupling 5, intermediate propeller shaft 6, the second shaft coupling being sequentially connected
7, the first shaft coupling 5 also exports axis connection with T-shaped commutator 4, and the second shaft coupling 7 is also connected with power output shaft 8；
The first shaft coupling 5, second shaft coupling 7 are Hooks coupling universal coupling.
The shaft coupling subelement can also be flexible clutch.
The length of the main body load gearing frame 3 is slightly longer than the length of wing 1, and gap delta is left in centre.
In practical application, as shown in figure 1, screw propeller assembly 2 is arranged on the both ends of wing 1, thin-walled composite structure is used
Make the structure of wing 1 and covering.To ensure load and transmission, the structure of main body load gearing frame 3 is built by carbon fibre tube（Call in the following text
" framework "）, realize that the installation of propeller is fixed, and transmission is realized in framework.During tilt rotor aircraft ground static, propeller
Isostructural weight make it that frame stressing is curved to downwarp, drives the corresponding deformation of wing 1；When taking off, propeller provides lift, framework
Stress is bent upwards, and drives the corresponding deformation of wing 1；In flight course, vibrated by the lift of wing 1, airflow influence and propeller
Deng influence, wing 1 deforms under alternate stress effect, drives framework corresponding deformation.
The flexural deformation of wing 1 drives framework 3 to bend, and forms axial float at both ends.Calculated with reference to deflection deformation, design
The length of frame structure is slightly longer than wing, unilateral to leave gap delta, it is ensured that in the most adverse case the deformation of frame structure not by
The influence of wing deformation, as shown in Figure 2.
As shown in figure 3, to ensure that stable drive is smooth, the utility model embodiment uses following structure：Power passes through portion
The T-shaped commutator 4 of part is incoming, identical to the both ends output speed of T-shaped commutator 4 respectively, turns to opposite rotary power；It is T-shaped to change
Fixed to the device output shaft of 4 two with T-shaped commutator 4；Power passes through first shaft coupling 5（Hooks coupling universal coupling）, intermediate propeller shaft 6
With second shaft coupling 7（Hooks coupling universal coupling）Three parts, it is delivered to the method for power output shaft 8, power output shaft 8 and framework termination
Orchid 9 passes through bearing fit and fixation.
Preferably, the structure of framework is as shown in figure 4, main body load-carrying construction is fine by flange 9 and fixed deckle board 10 and carbon
Crossbeam 11 collectively forms, and into " mesh " font structure to fall, configuration is symmetrically and stably；Input shaft and output due to power transmission
Axle is fixed with " mesh " character form structure, and wing 1 and framework carbon fibre crossbeam 11 deform caused bending, and axial float can pass through
First shaft coupling 5（Hooks coupling universal coupling）, intermediate propeller shaft 6 and second shaft coupling 7（Hooks coupling universal coupling）Three parts absorb.So as to
Ensure that rack construction is reliable, transmission is accurate.
The utility model additionally provides one kind and verted wing unmanned plane, including above-mentioned drive mechanism.
The beneficial effects of the utility model are：Wing and the complementary architectural feature of framework, i.e. wing and framework pass through
Carbon fibre crossbeam contacts, and in crossbeam radially strong interaction each other, is taken off with satisfaction needed for the stress such as landing；Wing and
Framework is all fixed on fuselage, but in the axial direction, is not limited each other, and leaves axial float space；Outside wing
Framework and transmission scheme, it is allowed to a small amount of elastic deformation of crossbeam, power input shaft and output shaft are fixed；By flange and fixation
" mesh " character form structure that deckle board and carbon fibre crossbeam collectively form, the position and shape control of input shaft and output shaft can connect
By within the scope of；Using the scheme of engine in front of rear wheel mid-engine, in the case where ensureing to be driven in wing, effectively simplify wing structure,
Mitigate wing weight, improve effective commercial transport of tiltrotor aircraft.
Although having been presented for several embodiments of the present utility model herein, those skilled in the art should manage
Solution, in the case where not departing from the utility model spirit, can be changed to the embodiments herein.Above-described embodiment simply shows
Example property, restriction that should not using the embodiments herein as the utility model interest field.
Claims (7)
1. drive mechanism in a kind of tilt rotor aircraft wing, it is characterised in that the drive mechanism bifurcates, and is symmetricly set in machine
Inside the wing of body both sides, every drive mechanism includes main body load gearing frame, gear unit；
The main body load gearing frame includes carbon fiber crossbeam, fixed deckle board, flange；The carbon fiber crossbeam passes through fixed frame
Plate is fixedly connected with fuselage, and the flange is arranged at the main body load gearing frame end；
The gear unit include be sequentially connected T-shaped commutator, T-shaped commutator output shaft, shaft coupling subelement, power output
Axle；The power output shaft and the flange pass through bearing fit and fixation；
The gear unit is fixed in the middle part of the main body load gearing frame；
On the carbon fiber crossbeam axis direction, the drive mechanism acts synergistically with wing；In the carbon fiber
On crossbeam axis direction, the drive mechanism does not limit mutually with wing.
2. drive mechanism in the tilt rotor aircraft wing as claimed in claim 1, it is characterised in that the shaft coupling subelement is
First shaft coupling, intermediate propeller shaft, the second shaft coupling being sequentially connected, the first shaft coupling also with T-shaped commutator output shaft
Connection, the second shaft coupling also with power output axis connection.
3. drive mechanism in the tilt rotor aircraft wing as claimed in claim 1, it is characterised in that the shaft coupling subelement is
Flexible clutch.
4. drive mechanism in the tilt rotor aircraft wing as claimed in claim 2, it is characterised in that the first shaft coupling,
Two shaft couplings are Hooks coupling universal coupling.
5. drive mechanism in the tilt rotor aircraft wing as claimed in claim 1, it is characterised in that the main body load is driven frame
Frame is " mesh " font structure collectively formed by carbon fiber crossbeam, fixed deckle board, flange.
6. drive mechanism in the tilt rotor aircraft wing as described in claim any one of 1-5, it is characterised in that the main body is held
The length of power gearing frame is slightly longer than wing length.
7. a kind of tilting rotor wing unmanned aerial vehicle, it is characterised in that including the drive mechanism as described in claim any one of 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720317780.1U CN206871358U (en) | 2017-03-29 | 2017-03-29 | Drive mechanism in a kind of tilt rotor aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720317780.1U CN206871358U (en) | 2017-03-29 | 2017-03-29 | Drive mechanism in a kind of tilt rotor aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206871358U true CN206871358U (en) | 2018-01-12 |
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ID=61327060
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720317780.1U Active CN206871358U (en) | 2017-03-29 | 2017-03-29 | Drive mechanism in a kind of tilt rotor aircraft wing |
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| Country | Link |
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| CN (1) | CN206871358U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021008310A1 (en) * | 2019-07-12 | 2021-01-21 | 李维农 | Flapping wing aircraft |
-
2017
- 2017-03-29 CN CN201720317780.1U patent/CN206871358U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021008310A1 (en) * | 2019-07-12 | 2021-01-21 | 李维农 | Flapping wing aircraft |
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