CN103171765A - Aircraft - Google Patents
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- CN103171765A CN103171765A CN2012104063161A CN201210406316A CN103171765A CN 103171765 A CN103171765 A CN 103171765A CN 2012104063161 A CN2012104063161 A CN 2012104063161A CN 201210406316 A CN201210406316 A CN 201210406316A CN 103171765 A CN103171765 A CN 103171765A
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- aerocraft
- sided wing
- aircraft
- wing
- control cabinet
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Abstract
The invention discloses an aircraft which comprises a unilateral wing used for rotatablely generating lift force, and a thrust device used for pushing the unilateral wing to rotate around the barycenter of the aircraft, wherein an aileron used for controlling a fly direction is arranged on the unilateral wing; and the thrust device is connected onto the unilateral wing, and the barycenter of the aircraft deviates from the center position of the unilateral wing along the length direction. The unilateral wing rotates around the barycenter of the aircraft to generate the lift force, so that the aircraft can vertically rise. Therefore, the aircraft disclosed by the invention has the advantage of vertical take-off and landing. Meanwhile, according to the aircraft, the lift force of the aircraft is generated by the rotation of the unilateral wing, and the front-and-back as well as the left-and-right fly direction is controlled by the aileron, so that the aircraft has the advantage of being simple in structure. According to the gyroscopic effect generated by the means that the unilateral wing rotates around the barycenter of the aircraft, the wind resistance of the aircraft and the stability of fly can be effectively improved.
Description
Technical field
The present invention relates to a kind of aerocraft.
Background technology
Aerocraft is aerial main means of delivery, mainly comprises fixed wing aircraft and autogyro.
Fixed wing aircraft has that flying speed is fast, the flight efficiency advantages of higher.But fixed wing aircraft need to have long runway for landing, and is harsher to the conditional request of landing, can't vertical takeoff and landing.
Autogyro can be done the constant maneuvering flight of low latitude, low speed and heading, and outstanding feature is the function that autogyro possesses vertical takeoff and landing.But autogyro structure very complex, airborne period is short, the Maintenance and Repair work capacity is larger.
Therefore, have temporarily at present the advantage of fixed wing aircraft and autogyro concurrently without a kind of aerocraft, not only possess the function of vertical takeoff and landing, and simple in structure.
Summary of the invention
The invention provides a kind of aerocraft, not only simple in structure, and possess the function of vertical takeoff and landing.The technical solution adopted for the present invention to solve the technical problems is:
A kind of aerocraft, it comprises:
Be used for the one-sided wing that rotation produces lift, described one-sided wing is provided with for the aileron of controlling heading;
Be used for promoting the thruster of the center of gravity rotation of described one-sided wing deviation from voyage route pocket, described thruster is connected on described one-sided wing, the described one-sided wing of the deviation of gravity center of described aerocraft center along its length.
Among one preferred embodiment: the center of gravity of described aerocraft is positioned at outside described one-sided wing end or end along its length.
Among one preferred embodiment: described thruster is screw propeller or jet engine or rocket socket.
Among one preferred embodiment: when described thruster was screw propeller, described screw propeller was front pull-type screw propeller or back-pushed screw propeller.
Among one preferred embodiment: also comprise alighting gear, described alighting gear is connected to the bottom of described one-sided wing.
Among one preferred embodiment: the dihedral angle of described one-sided wing is at the 0-50 degree, and the angle of attack of described one-sided wing is at the 0-50 degree.
Among one preferred embodiment: also comprise control cabinet, described control cabinet is connected with described one-sided wing.
Among one preferred embodiment: described control cabinet is connected to a described one-sided wing end along its length, and the center of gravity of described aerocraft is between described control cabinet and described one-sided wing.
Among one preferred embodiment: also comprise control cabinet, described control cabinet is connected with described one-sided wing.
Among one preferred embodiment: described control cabinet is connected to a described one-sided wing end along its length, and the center of gravity of described aerocraft is between described control cabinet and described one-sided wing.
The technical program is compared with background technology, and it has following advantage:
1. the described one-sided wing of the deviation of gravity center of described aerocraft center along its length, described one-sided wing produces lift after the center of gravity rotation of described aerocraft, described aerocraft is vertically risen.Therefore, aerocraft of the present invention has advantages of vertical takeoff and landing.Simultaneously, produce lift because aerocraft of the present invention utilizes the rotation of described one-sided wing, and utilize described aileron to control all around heading, have advantages of simple in structure.
In addition, described one-sided wing has effectively improved the wind loading rating of described aerocraft and the stability of flight around the gyro effect of the center of gravity rotation generation of described aerocraft, makes described aerocraft to be applied in scounting aeroplane.
2. the center of gravity of described aerocraft is positioned at outside described one-sided wing end or end along its length, increases the lift that makes progress that described one-sided wing rotation produces, and described one-sided wing just can make described aerocraft rise under less rotating speed.
3. described alighting gear is connected to the bottom of described one-sided wing, the rotation when starting of convenient described one-sided wing.Simultaneously, the existence of described alighting gear makes an end and the ground butt of described aerocraft, keeps certain friction force, avoids described aerocraft to go hither and thither in the moment that starts.
4. described control cabinet is connected with described one-sided wing, and described control cabinet can be used in lays power supply, controller etc.In addition, described control cabinet can also play the effect of counterweight, makes the center of gravity of described aerocraft between described control cabinet and described one-sided wing, thus the lift that makes progress that has farthest utilized described one-sided wing rotation to produce.
Description of drawings
The invention will be further described below in conjunction with drawings and Examples.
Fig. 1 has illustrated the overall schematic of the first embodiment of a kind of aerocraft of the present invention.
Fig. 2 has illustrated the principle of work schematic diagram of a kind of aerocraft shown in Figure 1.
Fig. 3 has illustrated the overall schematic of the second embodiment of a kind of aerocraft of the present invention.
The master that Fig. 4 has illustrated a kind of aerocraft shown in Figure 3 looks schematic diagram.
Fig. 5 has illustrated the left side of a kind of aerocraft shown in Figure 3 and has looked schematic diagram.
Fig. 6 has illustrated the overall schematic of the 3rd embodiment of a kind of aerocraft of the present invention.
Fig. 7 has illustrated the overall schematic of the 4th embodiment of a kind of aerocraft of the present invention.
Fig. 8 has illustrated the overall schematic of the 5th embodiment of a kind of aerocraft of the present invention.
The specific embodiment
Please refer to Fig. 1 and Fig. 2, it is depicted as the first embodiment of a kind of aerocraft of the present invention.Described aerocraft 100 comprises an one-sided wing 10 and a thruster 20.The center of gravity G of described aerocraft 100 is positioned at described one-sided wing 10 inner end position along its length.
Described one-sided wing 10 is used for producing lift around the center of gravity G of described aerocraft 100 rotation.The rear end of described one-sided wing 10 broad wayss is provided with one for the aileron 11 of controlling heading.
Described thruster 20 is used for promoting described one-sided wing 10 around the center of gravity G of described aerocraft 100 rotation.Described thruster 20 can be screw propeller or jet engine or rocket socket etc.Described thruster 20 is connected on described one-sided wing 10, is positioned at described one-sided wing 10 outer end along its length, and is connected to the front end of described one-sided wing 10 broad wayss.The center of gravity G of described aerocraft 100 departs from described one-sided wing 10 center along its length, and, can rotate in order to make described one-sided wing 10, the center of gravity G of described aerocraft 100 also will depart from the position of described thruster 20.
Please refer to Fig. 2, open and produce thrust F when described thruster 20 and promote described one-sided wing 10 after the center of gravity G of described aerocraft 100 rotates in the counterclockwise direction, described one-sided wing 10 cutting air produce lift, and described lift vertically rises described aerocraft 100.Then, described aileron 11 requires pendulum angle according to flight, and described aerocraft 100 is all around flown.
Please refer to Fig. 3 to Fig. 5, it is depicted as the second embodiment of a kind of aerocraft of the present invention.The difference of described aerocraft 100a and the first embodiment is: described thruster 20 is front pull-type screw propeller; Described aerocraft 100a also comprises an alighting gear 30, and described alighting gear 30 is connected to the bottom of described one-sided wing 10.
Please refer to Fig. 4, the dihedral angle θ of described one-sided wing 10 is at the 0-50 degree.
Please refer to Fig. 5, the angle of attack β of described one-sided wing is at the 0-50 degree.
Please refer to Fig. 6, it is depicted as the 3rd embodiment of a kind of aerocraft of the present invention.The difference of described aerocraft 100b and the second embodiment is: described thruster 20b is the back-pushed screw propeller, and described screw propeller 20b is connected on the end face of described one-sided wing 10.
Please refer to Fig. 7, it is depicted as the 4th embodiment of a kind of aerocraft of the present invention.The difference of described aerocraft 100c and the second embodiment is: described aerocraft 100c also comprises a control cabinet 40, and described control cabinet 40 is connected with described one-sided wing 10.Described control cabinet 40 is connected with described one-sided wing 10 inner end along its length; The center of gravity G of described aerocraft 100c is between described control cabinet 40 and described one-sided wing 10.
Please refer to Fig. 8, it is depicted as the 5th embodiment of a kind of aerocraft of the present invention.The difference of described aerocraft 100d and the 3rd embodiment is: described aerocraft 100d also comprises a control cabinet 40, and described control cabinet 40 is connected with described one-sided wing 10.Described control cabinet 40 is connected with described one-sided wing 10 inner end along its length; The center of gravity G of described aerocraft 100d is between described control cabinet 40 and described one-sided wing 10.
The above, only for preferred embodiment of the present invention, therefore can not limit according to this scope of the invention process, the equivalence of namely doing according to the scope of the claims of the present invention and description changes and modifies, and all should still belong in the scope that the present invention contains.
Claims (10)
1. an aerocraft, is characterized in that, it comprises:
Be used for the one-sided wing that rotation produces lift, described one-sided wing is provided with for the aileron of controlling heading;
Be used for promoting the thruster of the center of gravity rotation of described one-sided wing deviation from voyage route pocket, described thruster is connected on described one-sided wing, the described one-sided wing of the deviation of gravity center of described aerocraft center along its length.
2. a kind of aerocraft according to claim 1 is characterized in that: the center of gravity of described aerocraft is positioned at outside described one-sided wing end or end along its length.
3. a kind of aerocraft according to claim 2, it is characterized in that: described thruster is screw propeller or jet engine or rocket socket.
4. a kind of aerocraft according to claim 3, it is characterized in that: when described thruster was screw propeller, described screw propeller was front pull-type screw propeller or back-pushed screw propeller.
5. according to claim 1 and 2 or 3 or 4 described a kind of aerocrafts, it is characterized in that: also comprise alighting gear, described alighting gear is connected to the bottom of described one-sided wing.
6. a kind of aerocraft according to claim 5, it is characterized in that: the dihedral angle of described one-sided wing is at the 0-50 degree, and the angle of attack of described one-sided wing is at the 0-50 degree.
7. a kind of aerocraft according to claim 6, it is characterized in that: also comprise control cabinet, described control cabinet is connected with described one-sided wing.
8. a kind of aerocraft according to claim 7, it is characterized in that: described control cabinet is connected to a described one-sided wing end along its length, and the center of gravity of described aerocraft is between described control cabinet and described one-sided wing.
9. according to claim 1 and 2 or 3 or 4 described a kind of aerocrafts, it is characterized in that: also comprise control cabinet, described control cabinet is connected with described one-sided wing.
10. a kind of aerocraft according to claim 9, it is characterized in that: described control cabinet is connected to a described one-sided wing end along its length, and the center of gravity of described aerocraft is between described control cabinet and described one-sided wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104063161A CN103171765A (en) | 2012-10-22 | 2012-10-22 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104063161A CN103171765A (en) | 2012-10-22 | 2012-10-22 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103171765A true CN103171765A (en) | 2013-06-26 |
Family
ID=48632062
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104063161A Pending CN103171765A (en) | 2012-10-22 | 2012-10-22 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103171765A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN104477374A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | High-lift-wing aircraft |
| CN105480406A (en) * | 2015-12-31 | 2016-04-13 | 歌尔科技有限公司 | Single-axis aircraft |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202358299U (en) * | 2011-11-04 | 2012-08-01 | 深圳市大疆创新科技有限公司 | Detachable multi-rotor type aircraft |
| CN202879794U (en) * | 2012-10-22 | 2013-04-17 | 厦门同嘉信息科技有限公司 | Aircraft |
-
2012
- 2012-10-22 CN CN2012104063161A patent/CN103171765A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202358299U (en) * | 2011-11-04 | 2012-08-01 | 深圳市大疆创新科技有限公司 | Detachable multi-rotor type aircraft |
| CN202879794U (en) * | 2012-10-22 | 2013-04-17 | 厦门同嘉信息科技有限公司 | Aircraft |
Non-Patent Citations (1)
| Title |
|---|
| KINGSLEY FREGENE ET AL: "Dynamics and Control of a Biomimetic Single-Wing Nano Air Vehicle", 《2010 AMERICAN CONTROL CONFERENCE》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN104477374A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | High-lift-wing aircraft |
| CN105480406A (en) * | 2015-12-31 | 2016-04-13 | 歌尔科技有限公司 | Single-axis aircraft |
| CN105480406B (en) * | 2015-12-31 | 2017-07-21 | 歌尔科技有限公司 | A kind of single shaft aircraft |
| US10336434B2 (en) | 2015-12-31 | 2019-07-02 | Goertek Technology Co., Ltd. | Single-shaft aerial vehicle |
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Application publication date: 20130626 |