CN203094442U - Tilting four-rotor aircraft - Google Patents
Tilting four-rotor aircraft Download PDFInfo
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- CN203094442U CN203094442U CN 201320033248 CN201320033248U CN203094442U CN 203094442 U CN203094442 U CN 203094442U CN 201320033248 CN201320033248 CN 201320033248 CN 201320033248 U CN201320033248 U CN 201320033248U CN 203094442 U CN203094442 U CN 203094442U
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- rotor steering
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Abstract
The utility model discloses a tilting four-rotor aircraft. The tilting four-rotor aircraft comprises an aircraft body, wherein a first fixed wing and a second fixed wing are symmetrically arranged at the front end of the aircraft body; a third fixed wing and a fourth fixed wing are symmetrically arranged at the rear end of the aircraft body, wherein a first rotor steering gear, a second rotor steering gear, a third rotor steering gear and a fourth rotor steering gear are correspondingly arranged on the end parts of the first fixed wing, the second fixed wing, the third fixed wing and the fourth fixed wing, respectively; a set of rotors are arranged on each of the first rotor steering gear, the second rotor steering gear, the third rotor steering gear and the fourth rotor steering gear, respectively. According to the tilting four-rotor aircraft, the rotator steering devices with the rotors are arranged on the four fixed wings, so that the rotors are driven to rotate when the rotor steering gears are tilted, and therefore, the conversion between a horizontal forward flight mode and a vertical lifting flight mode of the aircraft is realized. Besides, the rotor steering gears are high in working reliability and reasonable in space position arrangement of the rotors, so that the aircraft is large in cruising lift force, stable in flight, simple in mechanical structure and capable of improving the working reliability.
Description
Technical field
The utility model relates to space travel power machine field, relates in particular to a kind of four rotor crafts that vert.
Background technology
Verting forward or backward all can not take place in tradition four rotor crafts four rotors, on the one hand, it flies when doing before the realization level, two gyroplane rotate speeds that requirement is in front fuselage reduce, increase and be in two gyroplane rotate speeds of back body, it is poor to produce lift owing to the front and back end gyroplane rotate speed is different like this, and then inevitably causes fuselage generation luffing, makes to fly to influence each other with vertical lifting before the aircraft level; On the other hand, therefore traditional four rotor crafts four rotor crafts that can incline occurred because the restriction of its Design Mechanism is difficult to reach cruising speed higher as fixed-wing.
Four rotor crafts that can incline have the advantage of helicopter and fixed wing aircraft simultaneously, when vertical takeoff and landing, provide lift by four rotors, when cruising flight, provide lift by the fixed wing that is fixed in fuselage.Existing four rotor crafts that incline, its four rotors are arranged in the same plane, four rotors are identical with respect to the vertical dimension on fuselage plane, this just makes aircraft when doing cruising flight, the front fuselage rotor go out the gas that becomes a mandarin that the gas body inevitably becomes back body rotor and fixed wing, cause the coupling on leading portion rotor and rear end rotor and the rear end fixed wing generation fluid dynamics, influence flight quality, the lift that may cause the nosing fixed wing to produce under the serious situation is unequal with the lift that the back body fixed wing produces, and makes body that big pitching action take place when cruising and the fly problem of unstability of appearance; Simultaneously, the existing four rotor craft rotor reclining device project organization complexity of inclining, stability are difficult to guarantee.Just because of the application of feasible four rotor crafts that can incline of above shortcoming is subjected to very big restriction.
The utility model content
At above-mentioned defective or deficiency, the utility model provides that a kind of cruising flight is steady, physical construction simply can vert four rotor crafts.
The utility model is to be achieved through the following technical solutions:
Comprise fuselage, the front end of fuselage is symmetrically installed with first, second fixed wing, the rear end of fuselage is symmetrically installed with the 3rd, the 4th fixed wing, wherein, the end of first, second, third, fourth fixed wing correspondence respectively is equipped with first, second, third, fourth rotor steering hardware, and a cover rotor respectively is installed on the first, second, third, fourth rotor steering hardware.
Described first, second, third, fourth rotor steering hardware structure is identical, wherein, the 3rd rotor steering hardware comprises: the rotor motor cabinet that can vert, the rotor motor cabinet is installed on the end of the 3rd fixed wing, is equipped with on the rotor motor cabinet to drive the torque motor that the rotor motor cabinet rotates.
The end of described the 3rd fixed wing is provided with anchor shaft, and on anchor shaft, key is connected with turbine to the rotor motor cabinet on the anchor shaft, and the worm screw of matching with turbine is installed in the rotating shaft of torque motor by clutch shaft bearing and second bearing installation.
The level height of described first, second fixed wing is lower than the level height of the 3rd, the 4th fixed wing.
Described first, second, third, fourth fixed wing all is fixed on the body by two axles.
The hand of rotation of described adjacent rotor is opposite in twos.
Four rotor crafts that vert that the utility model provides, by the rotor steering hardware that carries rotor is installed on four fixed wings, when the rotor steering hardware verts, drive rotor and rotate, and then realized flying before the level of aircraft conversion with the vertical lifting offline mode; In addition, because rotor steering hardware functional reliability height, the locus connection and reasonable arrangement of rotor makes that the aircraft lift that cruises is big, has a smooth flight, and physical construction is simple, and functional reliability improves.
Further, the rotor steering hardware is made up of a torque motor, one group of turbine and worm pair and rotor motor cabinet in the utility model, torque motor provides the power that verts, after the turbine and worm auxiliary driving, drive the rotation of rotor motor cabinet generation with respect to anchor shaft, and can produce self-locking effect, make rotor steering hardware functional reliability improve.
In addition, the level height of first, second fixed wing of the utility model middle machine body front end is lower than the level height of rear end the 3rd, the 4th fixed wing, avoided the gas that becomes a mandarin that the gas body becomes back body rotor and fixed wing that of front fuselage rotor, reduce the coupling of body aerodynamics, improved the flight quality of aircraft.
Description of drawings
Fig. 1 is the utility model four rotor craft structural representations that can vert;
Fig. 2 is the utility model four rotor craft lateral plans that can vert;
Fig. 3 is can the vert rotor steering hardware structural representation of four rotor crafts of the utility model.
Among the figure, 1 is fuselage, and 2 is the 3rd fixed wing, 3 is primary shaft, and 4 is the rotor motor cabinet, and 5 is clutch shaft bearing, 6 is the 3rd rotor, and 7 is anchor shaft, and 8 is the 3rd rotor steering hardware, 9 is second bearing, 10 is torque motor, and 11 is turbine, and 12 is worm screw, 13 is second, 14 is first rotor, and 15 is the first rotor steering hardware, and 16 is first fixed wing, 17 is second fixed wing, 18 is the second rotor steering hardware, and 19 is second rotor, and 20 is the 4th rotor steering hardware, 21 is the 4th rotor, and 22 is the 4th fixed wing.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is done detailed description.
With reference to shown in Figure 1, the utility model provides a kind of four rotor crafts that vert, comprise fuselage 1, the front end of fuselage 1 is symmetrically installed with first fixed wing 16 and second fixed wing 17, the rear end of fuselage 1 is symmetrically installed with the 3rd fixed wing 2 and the 4th fixed wing 22, first fixed wing 16, second fixed wing 17, the 3rd fixed wing 2 and the 4th fixed wing 22 all are fixed on the body 1 by two axles, for example, the 3rd fixed wing 2 is fixing with fuselage 1 by primary shaft 3 and second 13, wherein, primary shaft 3, second spool 13 are anchor shaft; In addition, the level height of first fixed wing 16 and second fixed wing 17 is lower than the level height of the 3rd fixed wing 2 and the 4th fixed wing 22.Wherein, the end of first fixed wing 16 is equipped with on the first rotor steering hardware, 15, the first rotor steering hardwares 15 and by fix screw first rotor 14 is installed; The end of second fixed wing 17 is equipped with on the second rotor steering hardware, 18, the second rotor steering hardwares 18 and by fix screw second rotor 19 is installed; The end of the 3rd fixed wing 2 is equipped with on the 3rd rotor steering hardware 8, the three rotor steering hardwares 8 and by fix screw the 3rd rotor 6 is installed; The 4th fixed wing 22 ends are equipped with the 4th rotor steering hardware 20, by fix screw the 4th rotor 21 is installed on the 4th rotor steering hardware 20, wherein, the hand of rotation of adjacent rotor is opposite in twos, promptly first rotor 14 is identical with the 3rd rotor 6 hand of rotation, second rotor 19 is identical with the 4th rotor 21 hand of rotation, and first rotor 14 is opposite with the 4th rotor 21 hand of rotation with the 3rd rotor 6 hand of rotation and second rotor 19, and this design makes adjacent two rotor hand of rotation on the contrary to offset reactive torque.
The first rotor steering hardware 15 in the utility model, the second rotor steering hardware 18, the 3rd rotor steering hardware 8, the 4th rotor steering hardware 20 structures are identical, are that example describes with the 3rd rotor steering hardware 8 below.Shown in figure 2,3, the 3rd rotor steering hardware 8 comprises: the rotor motor cabinet 4 that can vert, rotor motor cabinet 4 is installed on the end of the 3rd fixed wing 2, is equipped with on the rotor motor cabinet 4 to drive the torque motor 10 that rotor motor cabinet 4 rotates.Further, the end of the 3rd fixed wing 2 is provided with anchor shaft 7, rotor motor cabinet 4 is installed on the anchor shaft 7 by the clutch shaft bearing 5 and second bearing 9, and key is connected with turbine 11 on the anchor shaft 7, and the worm screw 12 of matching with turbine 11 is installed in the rotating shaft of torque motor 10.The 3rd rotor steering hardware 8 working processs are: torque motor 10 provides the power driven worm screw 12 of verting to rotate, owing to be fixed on the anchor shaft 7 and can not rotate with worm screw 12 ingear turbines 11, worm screw will drive the rotation that rotor motor cabinet 4 takes place with respect to anchor shaft 7, and can produce self-locking effect, therefore, the 3rd rotor 6 that is fixedly mounted on the rotor motor cabinet 4 can vert with rotor steering hardware 8.
Principle of work of the present utility model is:
When the utility model aircraft vertical takeoff and landing, first rotor 14, second rotor 19, the 3rd rotor 6 and the 4th rotor 21 parallel with the place fixed wing, as residing position among Fig. 1, for aircraft provides rising lift.In the vertical takeoff and landing process, when needing to adjust course angle, increase the rotating speed of (or reducing) second rotor 19, the 3rd rotor 6 simultaneously, and reduce the rotating speed of (or increasing) first rotor 14, the 4th rotor 21; In the vertical takeoff and landing process, when needing body to produce the pitching action, then increase the rotating speed of (or reducing) first rotor 14, second rotor 19 simultaneously, and reduce the rotating speed of (or increasing) the 3rd rotor 6, the 4th rotor 21; In the vertical takeoff and landing process, when needing body to produce the roll action, then increase the rotating speed of (or reducing) first rotor 14, the 3rd rotor 6 simultaneously, and reduce the rotating speed of (or increasing) second rotor 19, the 4th rotor 21.
When the cruising flight of the utility model aircraft, 90 ° of first rotor 14, second rotor 19, the 3rd rotor 6 and the 4th rotor 21 rotated position during with vertical takeoff and landing, as present position among Fig. 2, produce lift by first fixed wing 16, second fixed wing 17, the 3rd fixed wing 2 and the 4th fixed wing 22.In the cruising flight process, need to adjust course angle, then increase the rotating speed of (or reducing) rotor second rotor 19, the 4th rotor 21 simultaneously, and reduce the rotating speed of (or increasing) first rotor 14, the 3rd rotor 6.
The fuselage front and back end rotor motor that verted four rotor craft reasonable Arrangement of the present utility model has effectively reduced the aerodynamics coupled problem of existing four rotor crafts that can incline; Designed rotor reclining device can be realized the forward swing that rotor is reliable and stable; Adopt four fixed wings that lift is provided, guaranteed big cruising flight lift, and the feasible four rotor craft physical constructions that can vert are simple, it is high that functional reliability provides.
Claims (6)
1. four rotor crafts that can vert, it is characterized in that: comprise fuselage (1), the front end of fuselage (1) is symmetrically installed with first, second fixed wing (16,17), the rear end of fuselage (1) is symmetrically installed with the 3rd, the 4th fixed wing (2,22), wherein, first, second, the 3rd, the 4th fixed wing (16,17,2,22) end correspondence respectively is equipped with first, second, the 3rd, the 4th rotor steering hardware (15,18,8,20), first, second, the 3rd, the 4th rotor steering hardware (15,18,8, one cover rotor respectively is installed 20).
2. four rotor crafts that vert according to claim 1, it is characterized in that: described first, second, third, fourth rotor steering hardware (15,18,8,20) structure is identical, wherein, the 3rd rotor steering hardware (8) comprising: the rotor motor cabinet (4) that can vert, rotor motor cabinet (4) is installed on the end of the 3rd fixed wing (2), is equipped with on the rotor motor cabinet (4) to drive the torque motor (10) that rotor motor cabinet (4) rotates.
3. four rotor crafts that vert according to claim 2, it is characterized in that: the end of described the 3rd fixed wing (2) is provided with anchor shaft (7), rotor motor cabinet (4) is installed on the anchor shaft (7) by clutch shaft bearing (5) and second bearing (9), anchor shaft (7) is gone up key and is connected with turbine (11), and the worm screw (12) of matching with turbine (11) is installed in the rotating shaft of torque motor (10).
4. four rotor crafts that vert according to claim 1 is characterized in that: the level height of described first, second fixed wing (16,17) is lower than the level height of the 3rd, the 4th fixed wing (2,22).
5. four rotor crafts that vert according to claim 1 is characterized in that: described first, second, third, fourth fixed wing (16,17,2,22) all is fixed on the body (1) by two axles.
6. four rotor crafts that vert according to claim 1, it is characterized in that: the hand of rotation of described adjacent rotor is opposite in twos.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320033248 CN203094442U (en) | 2013-01-22 | 2013-01-22 | Tilting four-rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320033248 CN203094442U (en) | 2013-01-22 | 2013-01-22 | Tilting four-rotor aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203094442U true CN203094442U (en) | 2013-07-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320033248 Expired - Fee Related CN203094442U (en) | 2013-01-22 | 2013-01-22 | Tilting four-rotor aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203094442U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN103935511A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilt-three-rotor craft |
| CN104627360A (en) * | 2013-11-07 | 2015-05-20 | 李宏富 | Helicopter of H-shaped structure |
| CN105836119A (en) * | 2016-03-09 | 2016-08-10 | 龙全洪 | Airplane provided with swinging impellers |
| CN106005372A (en) * | 2016-07-01 | 2016-10-12 | 周小勇 | Four-rotor aircraft and control system thereof |
| CN111516869A (en) * | 2020-04-30 | 2020-08-11 | 北京航空航天大学 | Layout and control method of tilt rotor-wing vertical take-off and landing aircraft |
| CN112407265A (en) * | 2020-11-20 | 2021-02-26 | 浙江工业大学 | Tilting rotor four-axis unmanned aerial vehicle and tilting flight method thereof |
| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
-
2013
- 2013-01-22 CN CN 201320033248 patent/CN203094442U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN104627360A (en) * | 2013-11-07 | 2015-05-20 | 李宏富 | Helicopter of H-shaped structure |
| CN103935511A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilt-three-rotor craft |
| CN105836119A (en) * | 2016-03-09 | 2016-08-10 | 龙全洪 | Airplane provided with swinging impellers |
| CN106005372A (en) * | 2016-07-01 | 2016-10-12 | 周小勇 | Four-rotor aircraft and control system thereof |
| CN111516869A (en) * | 2020-04-30 | 2020-08-11 | 北京航空航天大学 | Layout and control method of tilt rotor-wing vertical take-off and landing aircraft |
| CN112407265A (en) * | 2020-11-20 | 2021-02-26 | 浙江工业大学 | Tilting rotor four-axis unmanned aerial vehicle and tilting flight method thereof |
| CN112896485A (en) * | 2021-02-24 | 2021-06-04 | 河南大学 | Two-shaft inclined wing aircraft with streamlined fuselage and control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130731 Termination date: 20180122 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |