CN208070013U - Tiltrotor aircraft - Google Patents
Tiltrotor aircraft Download PDFInfo
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- CN208070013U CN208070013U CN201820380643.7U CN201820380643U CN208070013U CN 208070013 U CN208070013 U CN 208070013U CN 201820380643 U CN201820380643 U CN 201820380643U CN 208070013 U CN208070013 U CN 208070013U
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Abstract
This disclosure relates to a kind of tiltrotor aircraft, including fuselage (1), main wing (2), rotor (61) and strut (3) for installing the rotor (61), the strut (3) is front and back through the main wing (2), and the rotor (61) is mounted on the both ends of the strut (3) by inclining rotary mechanism in which front and back can vert.Pass through above-mentioned technical proposal, Fixed Wing AirVehicle is combined with multi-rotor aerocraft, when aircraft vertical or front and back flight, by inclining rotary mechanism tilting rotor corresponding power can be provided to aircraft, in conjunction with the advantages of Fixed Wing AirVehicle and multi-rotor aerocraft, achieve the effect that voyage is remote, the speed of a ship or plane is high.
Description
Technical field
This disclosure relates to vehicle technology field, and in particular, to a kind of tiltrotor aircraft.
Background technology
Tiltrotor aircraft be one kind can VTOL, hovering as helicopter, and can be as fixed wing aircraft
The aircraft of the same high forward.Suitable for air transport, the related General Aviation field such as take photo by plane, tiltrotor aircraft be
A set of rotor assemblies that can be rotated between horizontal position and upright position are installed on Fixed Wing AirVehicle body, work as rotor assemblies
In blade plane when being in horizontality, rotor shaft is more rotor modes perpendicular to ground, aircraft, can hover in the air,
It is front and back flight and side fly, by change blade climbing power size and blade lift direction of verting so that aircraft keep or
Change of flight state；When blade plane is in vertical state, rotor shaft is horizontal, and blade then makes as pulling force propeller
With aircraft is fixed-wing pattern, and generating lift by main wing can high speed cruise flight.
Utility model content
Purpose of this disclosure is to provide a kind of tiltrotor aircraft, the tiltrotor aircraft combination Fixed Wing AirVehicles
And the characteristics of multi-rotor aerocraft, achieve the effect that voyage is remote, the speed of a ship or plane is high.
To achieve the goals above, the disclosure provides a kind of tiltrotor aircraft, including fuselage, main wing, rotor and use
In the strut for installing the rotor, the strut is front and back through the main wing, and the rotor can anteversion and retroversion by inclining rotary mechanism
Turn the both ends that ground is mounted on the strut.
Optionally, the inclining rotary mechanism includes being fixed on the verting for end of the strut steering engine and to be connected to described vert
The output shaft of motor cabinet on steering engine output shaft, the steering engine that verts be laterally extended so that the motor cabinet can front and back rotation,
The rotor is fixed on by motor on the motor cabinet.
Optionally, the tiltrotor aircraft includes fixed-wing pattern and more rotor modes, in more rotor modes,
The shaft of the rotor is vertical, and the direction that the rotor at both ends is connected before and after the strut is opposite.
Optionally, the angle rotatable of the steering engine output shaft that verts is 0 ° -90 °, so that the rotor is from horizontality
Switch between vertical state.
Optionally, the wingtip in the main wing is arranged in the strut.
Optionally, the strut is hollow pipe to form cable tray.
Optionally, the rear end of the fuselage is provided with two vertical tails of the longitudinal centre line for being symmetrical with the fuselage,
It is provided with rudder on each vertical tail.
Optionally, the bottom of the fuselage is provided with undercarriage, the undercarriage include positioned at front end first leg with
And the second supporting leg and third supporting leg positioned at rear end, the first leg are located on the longitudinal centre line of the fuselage, described
Two supporting legs and the third supporting leg are symmetrical with the longitudinal centre line.
Optionally, second supporting leg and the third supporting leg are in inverted V-arrangement.
Through the above technical solutions, Fixed Wing AirVehicle and the multi-rotor aerocraft that can be verted are combined together, both may be used
With VTOL, hovering such as multi-rotor aerocraft, and can be such as Fixed Wing AirVehicle, cruise fast with cruising speed
The feature of time length, in conjunction with the characteristics of the two, use is more flexible.
Other feature and advantage of the disclosure will be described in detail in subsequent specific embodiment part.
Description of the drawings
Attached drawing is for providing further understanding of the disclosure, and a part for constitution instruction, with following tool
Body embodiment is used to explain the disclosure together, but does not constitute the limitation to the disclosure.In the accompanying drawings：
Fig. 1 is that the axis of the more rotor modes for the tiltrotor aircraft that a kind of illustrative embodiments of the disclosure provide is surveyed
Figure；
Fig. 2 is the vertical view of the more rotor modes for the tiltrotor aircraft that a kind of illustrative embodiments of the disclosure provide
Figure；
Fig. 3 is the forward sight of the more rotor modes for the tiltrotor aircraft that a kind of illustrative embodiments of the disclosure provide
Figure；
Fig. 4 is the strut of the more rotor modes for the tiltrotor aircraft that a kind of illustrative embodiments of the disclosure provide
The structure partial enlarged drawing of one end；
Reference sign
1 fuselage, 2 main wing, 3 strut
4 empennage, 51 first leg, 52 second supporting leg
53 third supporting leg, 61 rotor, 611 first rotor
612 second rotor, 613 third rotor, 614 quadrotor
62 motors 63 vert 64 motor cabinet of steering engine
Specific implementation mode
The specific implementation mode of the disclosure is described in detail below in conjunction with attached drawing.It should be understood that this place is retouched
The specific implementation mode stated is only used for describing and explaining the disclosure, is not limited to the disclosure.
In the disclosure, in the absence of explanation to the contrary, the noun of locality used such as "upper", "lower" refer to that aircraft is flat
It is upper and lower when winged state.It should be noted that the front-rear direction of aircraft flight is defined according to use habit, fuselage
Length extending direction is the front-rear direction of aircraft flight, and specifically in the disclosure, strut extends along fuselage length direction, parallel
In the front-rear direction of aircraft flight." transverse direction ", " longitudinal direction " in a horizontal plane by front-rear direction on the basis of define, have
Body, laterally perpendicular to front-rear direction, longitudinal is front-rear direction.In addition, the term " first " used in the disclosure, " second " etc.
It is not have succession and importance to distinguish an element and another element.
As shown in Figure 1, the tiltrotor aircraft that the disclosure provides, including fuselage 1, main wing 2, rotor 61 and for installing
The strut 3 of rotor 61, strut 3 is front and back through main wing 2, and rotor 61 is mounted on strut 3 with front and back can verting by inclining rotary mechanism
Both ends.In this way, Fixed Wing AirVehicle is combined with multi-rotor aerocraft, when tiltrotor aircraft is vertical or front and back flight
When, corresponding power can be provided to aircraft so that aircraft both can be such as more rotor flyings by inclining rotary mechanism tilting rotor 61
VTOL, hovering as device, and can have the characteristics that cruising speed is fast, cruise time length, knot such as Fixed Wing AirVehicle
The characteristics of closing the two, use is more flexible.Wherein the disclosure is not specifically limited the form of main wing 2, such as can be all-wing aircraft.
In addition, tandem-winged form may be used in main wing 2, in the case where the tandem wing includes two rows of main wing 2, strut 3 can through main wing 2
To be interpreted as the front end that strut 3 passes through front side main wing 2, and across the rear end of rear side main wing 2, the side of fuselage 1 has at this time
Two rotors 61；It is also understood that be both provided with strut 3 on each main wing 2, there are four rotors for the side tool of fuselage 1 at this time
61。
Specifically, as shown in figure 4, inclining rotary mechanism may include vert steering engine 63 and the connection for the end for being fixed on strut 3
It is laterally extended in the output shaft of the motor cabinet 64 on 63 output shaft of steering engine that verts, the steering engine 63 that verts so that motor cabinet front and back can turn
Dynamic, rotor 61 is fixed on by motor 62 on motor cabinet 64.It verts and verts before and after 63 driving motor seat 64 of steering engine, be mounted on motor
Motor 62 on seat 64 can drive rotor 61 to be rotated by assigned direction, to provide corresponding power to aircraft, make aircraft
Not only can VTOL, hovering such as multi-rotor aerocraft, but also such as Fixed Wing AirVehicle, can generate advance thrust or
Pulling force, use are more flexible.
The tiltrotor aircraft that the disclosure provides includes at least fixed-wing pattern and more rotor modes, in fixed-wing mould
Formula, the shaft of rotor 61 is front and back to be extended, and rotor 61 is forward or backwards；Extend vertically in the shaft of more rotor modes, rotor 61, revolves
The wing 61 faces upward or downward.
The tiltrotor aircraft of disclosure offer by taking the quadrotor shown in Fig. 1 to Fig. 4 as an example, will be provided below
Structure.The left side front end of the preceding line direction of fuselage 1 is the first rotor 611, and rear end is the second rotor 612, the forward side of fuselage 1
To right side front be third rotor 613, rear end be quadrotor 614.First rotor 611 and the second rotor 612 are about main wing 2
Front and back symmetrical, third rotor 613 and quadrotor 614 are about symmetrical before and after main wing 2, the first rotor 611 and the pass of third rotor 613
It is symmetrical in the longitudinal centre line of fuselage 1, the longitudinal centre line or so of the second rotor 612 and quadrotor 614 about fuselage 1
Symmetrically, in this way, can make aircraft in the process of running will not run-off the straight, active balance torque.
In embodiment of the present disclosure, as shown in Figure 1, in more rotor modes, the court of the rotor 61 of 3 rear and front end of strut
To opposite.Specifically, referring to Figure 1 and Figure 3, the first rotor 611 and third rotor 613 upward, the second rotor 612 and quadrotor
614 downward.It should be noted that in more rotor modes, four rotors 61 can generate lift straight up, that is,
It says, although the second rotor 612 and quadrotor 614 are downward, the lift generated is still upward, this can be by being arranged blade
Angle of inclination is realized, is not here elaborated.
By this set form, after aircraft is switched to fixed-wing pattern from more rotor modes, rotor 61 can be after
Continuous rotation, can further provide for the power of aircraft advance.Specifically, referring to Figure 1 and Figure 3, in more rotor modes, upward
The first rotor 611 and third rotor 613 generate upward lift, the second rotor 612 directed downwardly and quadrotor 614 generate to
On lift.After aircraft is switched to fixed-wing pattern from more rotor modes, the first rotor 611 and third rotor 613 are facing forward,
Forward pulling force can be generated, the second rotor 612 and quadrotor 614 backwards, can generate forward thrust.In such case
Under, when fixed-wing pattern, four rotors 61 can generate the power for making aircraft forward flight.
Further, vert 63 output shaft of steering engine angle rotatable be 0 ° -90 ° so that rotor 61 from horizontality to
Switch between vertical state, and rotor 61 can be avoided excessively to vert and generate the power of obstruction aircraft operation.With the first rotor 611
For, in more rotor modes, the first rotor 611 generates upward lift, and 0 ° -90 ° are rotated in the output shaft for the steering engine 63 that verts
During, the first rotor 611 can generate the power tilted upward first, finally generate forward power, without will produce downwards
Power.By switching 61 status of rotor, pattern where change of flight device, when rotor 61 is in horizontality, rotor shaft
State in a vertical shape, aircraft are in more rotor modes, at this point, the steering engine that verts rotates 90 °, the 63 driving motor seat 64 of steering engine that verts is same
When vert 90 °, when rotor 61 is in vertical state, rotor shaft is horizontal, and aircraft is in fixed-wing pattern, by verting
The rotational angle of 63 output shaft of steering engine changes rotor state, keeps the use of aircraft more flexible.
In addition, in fixed-wing pattern, the torque in order to balance the generation of four rotors 61 deflects to avoid fuselage 1, four rotations
The rotation direction of the two in the wing 61 is oppositely oriented with other the two.Specifically, in the first embodiment, 611 He of the first rotor
The rotation direction of second rotor 612 is identical, and the rotation direction of third rotor 613 and quadrotor 614 is in contrast；In second embodiment
In, the first rotor 611 is identical with the rotation direction of third rotor 613, and the rotation direction of the second rotor 612 and quadrotor 614 is in contrast；
In the third embodiment, the first rotor 611 is identical with the rotation direction of quadrotor 614, the second rotor 612 and third rotor 613
Rotation direction in contrast.The rotation direction of rotor 61 can be driven by motor 62, not repeated here.
The fixed-wing pattern for the tiltrotor aircraft that the disclosure described in detail above provides and more rotor modes, this flies
Row device can also have the state between fixed-wing pattern and more rotor modes.Specifically, when the shaft of rotor 61 neither
When horizontal also not vertical, a part of component of power that rotor 61 generates can provide the lift of aircraft, and another part component can be with
The power that aircraft advances is provided.
As shown in Figure 1 to Figure 3, the wingtip in main wing 2 can be arranged in strut 3, on the one hand can destroy master as small as possible
This body structure of the wing 2, being on the other hand located at the rotor 61 of wingtip will not wait structural members to generate interference with fuselage 1.
Strut 3 can be hollow pipe to form cable tray, electric wire is connected to by strut 3 in inclining rotary mechanism and aircraft
Control system, aircraft controlling system can control the start and stop of vert state and the motor of inclining rotary mechanism, to
The state of flight of aircraft is controlled, electric wire is arranged in inside strut 3, and can save the device of electric wire arrangement, saves space.
As shown in Figure 1, the rear end of fuselage 1 is provided with two vertical tails 4 of the longitudinal centre line for being symmetrical with fuselage 1, with
The course balance of aircraft is kept, rudder, rudder control aircraft deflection, at other are provided on each vertical tail 4
Embodiment in, the empennage 4 of aircraft can further include tailplane.
The bottom of fuselage 1 is provided with undercarriage, and undercarriage includes positioned at the first leg 51 of front end and positioned at rear end
Second supporting leg 52 and third supporting leg 53, first leg 51 are located on the longitudinal centre line of fuselage 1, the second supporting leg 52 and third supporting leg
53 are symmetrical with longitudinal centre line.Using the undercarriage of three supporting leg forms, there is good directional stability, securely and reliably.The
Two supporting legs 52 and third supporting leg 53 are in inverted V-type, the support aircraft that can more consolidate.In other embodiments, it rises
Fall the undercarriage that frame can also be other forms, such as bicycle type.The disclosure is to the empennage of aircraft and the form of undercarriage, no
Do excessive limitation.
The preferred embodiment of the disclosure is described in detail above in association with attached drawing, still, the disclosure is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out to the technical solution of the disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that specific technical features described in the above specific embodiments, in not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the disclosure to it is various can
The combination of energy no longer separately illustrates.
In addition, arbitrary combination can also be carried out between a variety of different embodiments of the disclosure, as long as it is without prejudice to originally
Disclosed thought equally should be considered as disclosure disclosure of that.
Claims (9)
1. a kind of tiltrotor aircraft, which is characterized in that including fuselage (1), main wing (2), rotor (61) and for installing
The strut (3) of rotor (61) is stated, the strut (3) is front and back through the main wing (2), and the rotor (61) passes through inclining rotary mechanism
It is mounted on the both ends of the strut (3) with front and back can verting.
2. tiltrotor aircraft according to claim 1, which is characterized in that the inclining rotary mechanism is described including being fixed on
The steering engine that verts (63) of the end of strut (3) and it is connected to the motor cabinet (64) to vert on steering engine (63) output shaft, it is described
Vert steering engine (63) output shaft be laterally extended so that the motor cabinet (64) can front and back rotation, the rotor (61) passes through electricity
Machine (62) is fixed on the motor cabinet (64).
3. tiltrotor aircraft according to claim 2, which is characterized in that the tiltrotor aircraft includes fixing
Wing pattern and more rotor modes, it is vertical in the shaft of more rotor modes, the rotor (61), two before and after the strut (3)
The direction of the rotor (61) at end is opposite.
4. tiltrotor aircraft according to claim 3, which is characterized in that the steering engine that verts (63) output shaft can
Rotational angle is 0 ° -90 °, so that the rotor (61) switches between horizontality to vertical state.
5. according to the tiltrotor aircraft described in claim 1, which is characterized in that the strut (3) is arranged in the master
The wingtip of the wing (2).
6. tiltrotor aircraft according to claim 1, which is characterized in that the strut (3) is hollow pipe to be formed
Cable tray.
7. tiltrotor aircraft according to claim 1, which is characterized in that the rear end of the fuselage (1) is provided with pair
Claim in two vertical tails (4) of the longitudinal centre line of the fuselage (1), direction is provided on each vertical tail (4)
Rudder.
8. tiltrotor aircraft according to claim 1, which is characterized in that the bottom of the fuselage (1) has been provided with
Frame is fallen, the undercarriage includes the second supporting leg (52) and third supporting leg positioned at the first leg (51) of front end and positioned at rear end
(53), the first leg (51) is located on the longitudinal centre line of the fuselage (1), second supporting leg (52) and the third
Supporting leg (53) is symmetrical with the longitudinal centre line.
9. tiltrotor aircraft according to claim 8, which is characterized in that second supporting leg (52) and the third
Supporting leg (53) is in inverted V-arrangement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820380643.7U CN208070013U (en) | 2018-03-20 | 2018-03-20 | Tiltrotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820380643.7U CN208070013U (en) | 2018-03-20 | 2018-03-20 | Tiltrotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208070013U true CN208070013U (en) | 2018-11-09 |
Family
ID=64047573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820380643.7U Active CN208070013U (en) | 2018-03-20 | 2018-03-20 | Tiltrotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208070013U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111164011A (en) * | 2019-05-30 | 2020-05-15 | 四川灼识科技股份有限公司 | Power-controlled aircraft thrust steering method and corresponding aircraft |
-
2018
- 2018-03-20 CN CN201820380643.7U patent/CN208070013U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111164011A (en) * | 2019-05-30 | 2020-05-15 | 四川灼识科技股份有限公司 | Power-controlled aircraft thrust steering method and corresponding aircraft |
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