CN203666981U - Aircraft provided with double rotors - Google Patents
Aircraft provided with double rotors Download PDFInfo
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- CN203666981U CN203666981U CN201320677018.6U CN201320677018U CN203666981U CN 203666981 U CN203666981 U CN 203666981U CN 201320677018 U CN201320677018 U CN 201320677018U CN 203666981 U CN203666981 U CN 203666981U
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- rotor
- double
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- aerobat
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- 238000002485 combustion reaction Methods 0.000 claims description 3
- 230000000712 assembly Effects 0.000 claims description 2
- 238000000429 assembly Methods 0.000 claims description 2
- 239000003381 stabilizer Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
An aircraft provided with double rotors comprises a fixed-wing aircraft body and two groups of autorotation double-rotor systems, wherein pre-swirl devices are mounted on rotor heads. All that is needed is to change windward angles of rotor surfaces at two ends of an aerofoil to control the flying attitude of the aircraft, and advantages of a fixed-wing aircraft and a rotorcraft are combined.
Description
Technical field
The utility model relates to a kind of rotor craft, especially a kind of double-rotor aerobat.
Background technology
Rotor craft appears at Europe with the form of a rotor the earliest, belongs to aviette, and load carrying ability is little.It is advantageous that simple in structure, easily manipulation, low cost of manufacture.In addition, cyclogyro also has the advantages such as the required ground run distance of landing is short, and low speed is good, is difficult for stall, and load-carrying ability is strong, and wind loading rating is strong, and therefore safety is higher.The shortcoming of rotor craft is to be difficult to improve flying speed, and the asymmetry that the aircraft rotor of single rotor is rotated also can produce certain anti-twisted moment, affects the stability of aircraft.In prior art, although also there is the aircraft of the bispin wing, two rotor wing rotation opposite directions, for balancing torque, improve the stability of aircraft, still do not solve the technical matters that improves double-rotor aerobat speed.
Utility model content
In order to solve the technical matters that rotor craft speed is not high, the utility model provides a kind of double-rotor aerobat, specifically comprises:
A kind of double-rotor aerobat, comprises fuselage, is arranged on the screw propeller of fuselage head, is connected in a pair of wing on fuselage, is respectively provided with a rotor assembly on the wing of both sides.
In order further to solve and to manipulate the other technologies problems such as convenient, double-rotor aerobat of the present utility model can also comprise: the empennage that is arranged at afterbody; Screw propeller adopts combustion engine or motor to drive.
In addition,, in order to facilitate the control of flight attitude, above-mentioned rotor assembly can carry out with respect to wing the rotation of horizontal direction and vertical direction.
Further, on rotor assembly, be also provided with spin motor.
Above-mentioned spin motor is connected with rotor by power-transfer clutch.
Further, in wing, be provided with reinforced pipe.
Further, in order to realize landing by land, double-rotor aerobat also comprises alighting gear, and the angle of alighting gear two side stands and horizontal surface is set to 50-70 °, especially 53 °.
Owing to having adopted the technical solution of the utility model, this double-rotor aerobat has the high speed performance of fixed wing aircraft, has taken into account again the low-speed performance of cyclogyro.Simultaneously simple in structure, manipulation is convenient, and cost is low, safe, can also realize even vertical takeoff and landing of very short takeoff and landing, has outstanding technique effect.
Brief description of the drawings
Fig. 1 is the schematic top plan view of the utility model bispin wing aircraft.
Fig. 2 is the front schematic view of the utility model bispin wing aircraft.
Fig. 3 is the schematic diagram of alighting gear.
Detailed description of the invention
In order to make the purpose of this utility model, technical scheme and advantage clearer, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein is only in order to explain the utility model, and be not used in restriction the utility model.
Disclosed arbitrary feature in this specification sheets (comprising any accessory claim, summary and accompanying drawing), unless narration especially all can be replaced by other equivalences or the alternative features with similar object.,, unless narration especially, each feature is an example in a series of equivalences or similar characteristics.
Embodiment mono-
As shown in Figure 1, 2, double-rotor aerobat of the present utility model comprises fuselage 4, is arranged on the screw propeller 1 of fuselage head, is connected in a pair of wing 2 on fuselage, is respectively provided with a rotor assembly 3 on the wing of both sides.It is pointed out that the various flight attitudes that can adjust by the rotation of two rotor assemblies aircraft due to this double-rotor aerobat, keep having a smooth flight, therefore the empennage 5 in afterbody is not necessary, can cancel.For example, can control by changing the angle windward of rotor face the flight attitude of aircraft.Change the wing both sides rotor face difference size at angle windward, be equal to and allow wing both sides have lift poor, roll attitude when difference positive and negative just can be controlled aircraft flight etc.In like manner, allow the angle windward of rotor face on both sides increase simultaneously or to reduce, the pitch attitude just can control aircraft flight time.Like this, as long as the size of angle windward of control break rotor face just can realize the control to aircraft flight attitude.Meanwhile, also can realize the switching of high low-speed operations.And in order to realize better flight attitude control, rotor can be with respect to wing in the horizontal direction and/or on vertical direction, carry out the rotation of certain angle.
Embodiment bis-
As shown in Figure 1, 2, as a more excellent embodiment, can on embodiment mono-basis, adopt high mounted wing, rear 3 the fixed wing aircraft bodies carrier as bispin wing assembly 3, retain the normal arrangement of fixed wing aircraft, adopt tailplane and vertical tail, remove the lifting rudder face on aileron and horizontal stabilizer.And adopt A-frame that rotor assembly 3 is fixed on above wing 2, and in wing 2, install reinforced rib additional and strengthen the strengthening and fixing of rotor device, allow wing bear hardly the gravity that rotor device increases, reach the effect of protection wing.In the present embodiment, above-mentioned reinforced rib adopts the carbon pipe of low-density and high-strength.
Further, carry out on land landing in order to realize, double-rotor aerobat of the present utility model can also arrange alighting gear 6.Alighting gear 6 adopts symmetric design, substantially be as shown in Figure 3 U-shaped, wherein the angle 61 of two side stands and horizontal surface is 50-70 °, preferably 53 °, because in the time of this angular range, alighting gear two side stand roots moment in when landing suffered limit stress less, make alighting gear more reliable, greatly reducing fault may.
Double-rotor aerobat of the present utility model, in the time taking off, can first pass through motor or internal combustion engine drive screw propeller 1, makes its high speed rotating produce air-flow, promotes aircraft and advances.In the time that aircraft advances, when reaching certain speed, air-flow can drive rotor to carry out autobiography, produces lift, and now the lift of aircraft is produced jointly by rotor and wing, but is mainly provided by rotor.Rotor produces a kind of power rotor thrust, and this comprises two parts, i.e. lift (normal component) and resistance (horizontal component).Can reach by rotating rotor assembly the angle changing between relative wind and chord line, i.e. the object of angle size windward, just can change rotor provides the size of lift.The size of lift depends on the speed of rotating speed, the relative wind of rotor, angle etc. windward, in general increases angle windward and just can increase lift.Like this, in the time that lift exceedes the gravity of aircraft, aircraft can take off in liftoff realization.Because the lift of this aircraft is mainly provided by two rotors, therefore its take off required minimum speed and distance shorter than common screw propeller fixed wing aircraft.
Aircraft, in the process of flight, by changing the angle of rotor assembly 3 and wing 2, can be controlled the flight attitude of aircraft, for example, climb, and turns to, and dives etc.Aircraft is in the time of low-speed operations, and lift is mainly provided by two rotors, and along with the raising of speed, the shared ratio of lift that wing 2 provides also rises gradually.Therefore, such aircraft can be taken into account the high speed performance of fixed wing aircraft, also can have the vulgar performance of cyclogyro, kills two birds with one stone.Meanwhile, because two rotors are rotating always, can continue to provide lift; therefore in the time that aero-engine breaks down shutdown; the lift that this aircraft also can provide by rotor, slowly pulsation-free is realized the forced landing of gliding, and safety significantly improves than common fixed wing aircraft.
Embodiment tri-
As far as possible consistent in order to ensure both sides gyroplane rotate speed, the inconsistent situation that when solution is taken off, both sides rotating speed may occur, it is also conceivable that and on rotor assembly 3, install the motor of prewhirling (not shown) additional, make rotor produce in advance rotation, eliminate the phenomenon that rollover occurs when wing both sides lift is in different size to be caused taking off.Meanwhile, due to the effect of the motor of prewhirling, even can make this aircraft realize and taking off vertically as autogyro.And after taking off vertically, when aircraft reaches minimum flight when above, can close the motor of prewhirling, and make rotor realize spin, therefore it is also conceivable that and between motor and rotor, adopt power-transfer clutch to connect prewhirling.
Same, in the time of landing, if because place reason need to realize the short distance even vertical landing of landing, also can open the motor of prewhirling before landing, realize above-mentioned purpose.
Claims (9)
1. a double-rotor aerobat, comprise fuselage, be arranged on the screw propeller of fuselage head, be connected in a pair of wing on fuselage, it is characterized in that: on the wing of both sides, be respectively provided with a rotor assembly, above-mentioned two rotor assemblies all do not possess power, also comprise tailplane and vertical tail, do not comprise the lifting rudder face on aileron and horizontal stabilizer.
2. double-rotor aerobat as claimed in claim 1, is characterized in that: above-mentioned screw propeller adopts motor or internal combustion engine drive.
3. double-rotor aerobat as claimed in claim 1 or 2, is characterized in that: above-mentioned each rotor assembly can carry out with respect to above-mentioned wing the rotation of horizontal direction and/or vertical direction.
4. double-rotor aerobat as claimed in claim 3, is characterized in that: on above-mentioned each rotor assembly, be also provided with spin motor.
5. double-rotor aerobat as claimed in claim 4, is characterized in that: above-mentioned spin motor is connected with rotor by power-transfer clutch.
6. double-rotor aerobat as claimed in claim 1, is characterized in that: above-mentioned wing inside is provided with reinforced rib.
7. the double-rotor aerobat as described in claim 5 or 6, is characterized in that: also comprise alighting gear.
8. double-rotor aerobat as claimed in claim 7, is characterized in that: the angle of above-mentioned alighting gear two side stands and horizontal surface is 50-70 °.
9. double-rotor aerobat as claimed in claim 8, is characterized in that: the angle of above-mentioned alighting gear two side stands and horizontal surface is 53 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320677018.6U CN203666981U (en) | 2013-10-31 | 2013-10-31 | Aircraft provided with double rotors |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320677018.6U CN203666981U (en) | 2013-10-31 | 2013-10-31 | Aircraft provided with double rotors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203666981U true CN203666981U (en) | 2014-06-25 |
Family
ID=50963301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320677018.6U Expired - Fee Related CN203666981U (en) | 2013-10-31 | 2013-10-31 | Aircraft provided with double rotors |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203666981U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691759A (en) * | 2015-02-13 | 2015-06-10 | 金陵科技学院 | Intelligent unmanned plane of improved structure |
-
2013
- 2013-10-31 CN CN201320677018.6U patent/CN203666981U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104691759A (en) * | 2015-02-13 | 2015-06-10 | 金陵科技学院 | Intelligent unmanned plane of improved structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151230 Address after: 610041 Sichuan Province, Chengdu Tianfu Street 69 No. 1 Building 1 unit 16 floor No. 1610 Patentee after: Sichuan nine ancient cooking vessel intelligence intellectual property operation far away Co., Ltd Address before: Nanchang Lu Luo town of Guanghan City, Sichuan province 618307 four Deyang City No. 46 Patentee before: Xia Guishu |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140625 Termination date: 20161031 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |