CN203127142U - Aircraft - Google Patents
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- CN203127142U CN203127142U CN 201320089966 CN201320089966U CN203127142U CN 203127142 U CN203127142 U CN 203127142U CN 201320089966 CN201320089966 CN 201320089966 CN 201320089966 U CN201320089966 U CN 201320089966U CN 203127142 U CN203127142 U CN 203127142U
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Abstract
The utility model discloses an aircraft which comprises a controller, wherein a lifting propeller I, a lifting propeller II, a lifting propeller III and a lifting propeller IV are uniformly arranged on and connected with the controller; and a horizontal propeller I, a horizontal propeller II, a horizontal propeller III and a horizontal propeller IV are uniformly arranged on and connected with the controller. The lifting of the aircraft is synergically realized by mainly depending on the four lifting propellers, the lifting control of the aircraft can integrally realize intelligentized lifting by independently controlling the lifting propellers through a lifting controller, and thus the aircraft disclosed by the utility model has the advantages of high lifting efficiency and good lifting stability; and the horizontal motion of the aircraft is synergically realized by mainly depending on the four horizontal propellers, so that the requirement for operation and control technology of an operator is not extremely high. Compared with the traditional aircraft, the aircraft disclosed by the utility model is greatly enhanced in horizontal motion flexibility ratio; and the aircraft disclosed by the utility model is enhanced in the flight flexibility ratio and flight stability through the independent and synergic control on the four lifting propellers and the four horizontal propellers.
Description
Technical field
The utility model relates to the airmanship field, relates in particular to a kind of aircraft, particularly flight investigation and camera technique field.
Background technology
Aircraft refers generally to the culture that flies in air or space, the former is called aviation aircraft (comprising aircraft, balloon, flight pick up camera etc.), and the latter is spacecraft.Along with the continuous development of flight art, the multiaxis vertically taking off and landing flyer arises at the historic moment.In numerous multiaxis aircraft that is similar to autogyro, the quantity of axle is how in the majority with even number, there are four, six and eight, the most general with four-axle aircraft now, the axle of four-axle aircraft is " ten " font or " X " and distributes, namely before and after each one, about each one, wherein the screw propeller of antero posterior axis is all left-hand revolution, and the screw propeller of Y-axis is all clickwise.
When aircraft needs to preacceleration, then the screw propeller of front axle slows down, the screw propeller of rear axle accelerates simultaneously, the screw propeller of Y-axis accelerates, described like this aircraft could guarantee equilibrium of torques, according to aerodynamic principle, the pressure that rear axle screw propeller lower surface is subjected to be greater than front axle screw propeller lower surface be subjected to pressure, thereby cause lifting surface to lean forward.According to the mechanics principle, reach the condition of a dynamical equilibrium, four axles of the minimum needs of multiaxis aircraft are controlled simultaneously, and four axles all are that in the aircraft lifting process, the rotation of four axle rotating blades can be played comparatively stable elevating function in the horizontal surface rotation substantially, but when the aircraft horizontal flight, the turning effort power that dependence horizontally rotates blade realizes that horizontal flight efficient is low, and the stationarity of flight course is relatively poor, and these make aircraft flight extremely unstable; Because control operation is comparatively complicated, also flight control personnel are controlled having relatively high expectations of technology simultaneously.
Aircraft moves flexibly owing to it, be subjected to the region less-restrictive, be widely used at present in various flight investigations, the camera technique, because traditional aircraft adopts four axle horizontals to rotate to realize lifting and two kinds of effects of horizontal flight substantially, in the aircraft flight process, vibration is comparatively severe, and degree of having a smooth flight is lower, badly influenced investigation and the pickup quality of aircraft, and its flight alerting ability is affected greatly also.
The utility model content
The purpose of this utility model is to overcome the weak point that existing aircraft stationarity and alerting ability exist, and all aircraft preferably of a kind of stationarity and alerting ability are provided, and can solve the problems of the technologies described above effectively.
The purpose of this utility model is achieved through the following technical solutions:
A kind of aircraft, comprise controller, evenly arrange on the controller to be connected with elevating screw one, elevating screw two, elevating screw three and elevating screw four, also evenly arrange on the described controller to be connected with horizontal propeller one, horizontal propeller two, horizontal propeller three and horizontal propeller four.
In order to realize the utility model better, described elevating screw one, elevating screw two, elevating screw three and elevating screw four are positioned at same horizontal plane A, and described horizontal propeller one, horizontal propeller two, horizontal propeller three and horizontal propeller four are positioned at same horizontal surface B.
The utility model provides a kind of preferred controller architecture technical scheme to be: described controller mainly includes lifting controller, horizontal controller, receiver of remote-control sytem and shock sensor, and described lifting controller is connected with described elevating screw one, elevating screw two, elevating screw three and elevating screw four respectively; Described horizontal controller is connected with horizontal propeller one, horizontal propeller two, horizontal propeller three and horizontal propeller four respectively.
The utility model provides a kind of preferred controller principle technical scheme to be: described controller inside includes CPU module, and CPU module is electrically connected with elevating screw control module, horizontal propeller control module, shock sensor module, gyroscope and remote control control module respectively.
As preferably, described elevating screw control module is made up of elevating screw one module, elevating screw two modules, elevating screw three modules and elevating screw four module.
As preferably, described horizontal propeller control module is made up of horizontal propeller one module, horizontal propeller two modules, horizontal propeller three modules and horizontal propeller four module.
Further optimized technical scheme is: described elevating screw one, elevating screw two, elevating screw three are identical with elevating screw four structures, and electric signal strut bar, lifting drive and rotating blade have been included, described electric signal strut bar one end is fixedly connected on the described lifting controller, the other end of electric signal strut bar is electrically connected with lifting drive, and the output shaft of described lifting drive is captiveed joint with rotating blade.
Further optimized technical scheme is: described lifting drive mainly is made of electric machine casing and motor, and electric machine casing is fixedly connected on the end of electric signal strut bar, and motor is installed in the electric machine casing inner chamber; The centre of gration place of rotating blade is provided with rotary axle box, and the output shaft of described motor closely cooperates and is installed in this rotary axle box.
As preferably, described horizontal propeller one, horizontal propeller two, horizontal propeller three are identical with horizontal propeller four structures, and electric signal strut bar, horizontal drive apparatus and rotating blade have been included, described electric signal strut bar one end is fixedly connected on the described horizontal controller, the other end of electric signal strut bar is electrically connected with horizontal drive apparatus, and the output shaft of described horizontal drive apparatus is captiveed joint with rotating blade.
In order to make this aircraft takeoff and landing more convenient, the bottom of described controller is provided with alighting gear.
The utility model is compared than prior art, has the following advantages and beneficial effect:
(1) lifting of this aircraft mainly relies on the collaborative realization of four elevating screws, because four elevating screws are respectively by four mutual corresponding elevating screw module controls, its lifting control can be controlled separately each elevating screw by lifting controller and comprehensively realize intelligent lifting, and the lifting efficient of aircraft is higher like this, the lifting stationarity will be better.The horizontal motion of this aircraft mainly relies on the collaborative realization of four horizontal propellers, four horizontal propellers are controlled separately by four mutual corresponding horizontal propeller modules respectively simultaneously, when the aircraft left-right and front-back moves, the control principle of aircraft is comparatively simple, just can not be too high to the technical requirements of controlling of operating personal; And four horizontal propellers make this aircraft improve greatly with respect to the horizontal motion flexibility ratio of conventional aircraft.This aircraft has improved flight flexibility ratio and the degree of having a smooth flight of aircraft by the independent and Collaborative Control to four elevating screws and four horizontal propellers.This aircraft can be widely used in military affairs, field such as civilian, during as flight investigation or shooting, microcam can be arranged on the aircraft, realizes investigation or camera operation to object of observation by the control aircraft.
(2) this aircraft is provided with shock sensor, this shock sensor is the flight shock conditions in the sense aircraft flight course in real time, and this shock conditions fed back to controller, controller is by the analysis of data bank, make corresponding shockproof control command, control corresponding screw propeller running and rotary power, realize damping and shockproof purpose.
(3) and, the bottom of controller of aircraft is provided with alighting gear, this alighting gear is conducive to guarantee convenience and the stationarity of this aircraft takeoff and landing.
Description of drawings
Fig. 1 is overlooking surface structural representation of the present utility model;
Fig. 2 is construction profile scheme drawing of the present utility model;
Fig. 3 is the mounting structure scheme drawing of lifting drive of the present utility model and rotating blade;
Fig. 4 is the inside theory structure block diagram of controller of the present utility model.
Wherein, the corresponding name of the Reference numeral in the accompanying drawing is called:
The 1-controller, 2-elevating screw one, 3-elevating screw two, 4-elevating screw three, 5-elevating screw four, 6-electric signal strut bar, the 7-lifting drive, the 8-rotating blade, 9-horizontal propeller one, 10-horizontal propeller two, 11-horizontal propeller three, 12-horizontal propeller four, 13-electric signal strut bar, 14-horizontal drive apparatus, the 15-rotating blade, the 16-lifting controller, 17-horizontal controller, 18-alighting gear, the 19-receiver of remote-control sytem, the 71-electric machine casing, 72-motor, 721-output shaft.
The specific embodiment
Be described in further detail below in conjunction with the utility model of embodiment:
Embodiment
As Fig. 1～shown in Figure 4, a kind of aircraft comprises controller 1, and this controller 1 is comparatively advanced at present dual core processor, can certainly select more advanced treater.Evenly arrange on the controller 1 and be connected with elevating screw 1, elevating screw 23, elevating screw 34 and elevating screw 45; Elevating screw 1, elevating screw 23, elevating screw 34 and elevating screw 45 are positioned at same horizontal plane A.Also evenly arrange on the controller 1 and be connected with horizontal propeller 1, horizontal propeller 2 10, horizontal propeller 3 11 and horizontal propeller 4 12; Horizontal propeller 1, horizontal propeller 2 10, horizontal propeller 3 11 and horizontal propeller 4 12 are positioned at same horizontal surface B.As shown in Figure 2, when concrete the manufacturing, the horizontal surface B of present embodiment is lower than horizontal plane A, and namely the plane of arrangement of all horizontal propellers is lower than the plane of arrangement of all elevating screws.
As shown in Figure 2, controller 1 mainly includes lifting controller 16, horizontal controller 17, receiver of remote-control sytem 19 and shock sensor, lifting controller 16 is connected with elevating screw 1, elevating screw 23, elevating screw 34 and elevating screw 45 respectively, lifting controller 16 be mainly used in controlling each elevating screw startup, close the rotating speed size with screw propeller.Horizontal controller 17 is connected with horizontal propeller 1, horizontal propeller 2 10, horizontal propeller 3 11 and horizontal propeller 4 12 respectively, horizontal controller 17 be mainly used in controlling each horizontal propeller startup, close the rotating speed size with screw propeller.Receiver of remote-control sytem 19 is and the remote signal receiver of the supporting remote controller of this aircraft, can receives the wireless control signal from remote controller or other telecommand equipment.This receiver of remote-control sytem 19 can be supported WIFI or control signals such as bluetooth or radiowave.
As shown in Figure 4, controller 1 inside includes CPU module, and CPU module is electrically connected with elevating screw control module, horizontal propeller control module, shock sensor module, gyroscope and remote control control module respectively.Remote control control module in the controller 1 receives and comes from control of remote controller instruction (comprise anti-shake of lifting instruction, rising or falling speed instruction, parallel motion instruction, the level of control aircraft instruct and horizontal velocity instruction etc.), and its instruction transferred to CPU module, realize purposes such as lifting, rising or falling speed, parallel motion and the level of this aircraft be shockproof through the Coordination Treatment of CPU module.The shock sensor module can detect the shock conditions of this aircraft in real time, and this vibrational feedback signal transferred to CPU module, through the intelligent control of the program of CPU module, and the startup that realizes each horizontal propeller by the horizontal propeller control module with close the shockproof beneficial effect of realization level under the synergy of each horizontal propeller.
Gyroscope can play a part the stabilized flight device in the aircraft flight process, makes aircraft steadily be in the air.Gyroscope can play a part each horizontal propeller of operation or each elevating screw (traditional gyroscope realizes that just present embodiment is not just done concrete principle explanation) simultaneously.
As shown in Figure 4, the elevating screw control module is made up of elevating screw one module, elevating screw two modules, elevating screw three modules and elevating screw four module.The startup of the corresponding control of elevating screw one module elevating screw 1, close and start after speed etc.; The startup of the corresponding control of elevating screw two modules elevating screw 23, close and start after speed etc.; The startup of the corresponding control of elevating screw three modules elevating screw 34, close and start after speed etc.; The startup of the corresponding control of elevating screw four module elevating screw 1, close and start after speed etc.The elevating screw control module can realize control separately to each elevating screw, by the quantity of open and close elevating screw, and the control of the elevating screw speed after having opened, come the collaborative descending operation of realizing this aircraft.
As shown in Figure 4, the horizontal propeller control module is made up of horizontal propeller one module, horizontal propeller two modules, horizontal propeller three modules and horizontal propeller four module.The startup of the corresponding control of horizontal propeller one module horizontal propeller 1, close and start after speed etc.; The startup of the corresponding control of horizontal propeller two modules horizontal propeller 2 10, close and start after speed etc.; The startup of the corresponding control of horizontal propeller three modules horizontal propeller 3 11, close and start after speed etc.; The startup of the corresponding control of horizontal propeller four module horizontal propeller 4 12, close and start after speed etc.The horizontal propeller control module can realize control separately to each horizontal propeller, by opening and closing the quantity of horizontal propeller, and the control of the horizontal propeller speed after having opened, come collaborative intelligent earthquake and the parallel motion operation that realizes this aircraft.
As Fig. 1, shown in Figure 3, elevating screw 1, elevating screw 23, elevating screw 34 are identical with elevating screw 45 structures, and electric signal strut bar 6, lifting drive 7 and rotating blade 8 have been included, electric signal strut bar 6 one ends are fixedly connected on the lifting controller 16, the other end of electric signal strut bar 6 is electrically connected with lifting drive 7, and the output shaft of lifting drive 7 is captiveed joint with rotating blade 8.
As shown in Figure 3, lifting drive 7 is mainly by electric machine casing 71(or combustion engine housing) and motor 72(or combustion engine) constitute, present embodiment preferably adopts motor 72 as engine installation, can certainly adopt other class pseudodynamic devices such as combustion engine.Electric machine casing 71(or combustion engine housing) be fixedly connected on the end of electric signal strut bar 6, motor 72(or combustion engine) install in electric machine casing 71(or combustion engine housing) in the inner chamber; The centre of gration place of rotating blade 8 is provided with rotary axle box 81, motor 72(or combustion engine) output shaft 721 closely cooperate and be installed in this rotary axle box 81.Electric machine casing 71(or combustion engine housing) inside is cavity structure, is laid with power transmission line and signal wire (SW) in its inner chamber.
As shown in Figure 1 and Figure 2, horizontal propeller 1, horizontal propeller 2 10, horizontal propeller 3 11 are identical with horizontal propeller 4 12 structures, and its structure is identical with the structure of each elevating screw, and electric signal strut bar 13, horizontal drive apparatus 14 and rotating blade 15 have been included, electric signal strut bar 13 1 ends are fixedly connected on the horizontal controller 17, the other end of electric signal strut bar 13 is electrically connected with horizontal drive apparatus 14, and the output shaft of horizontal drive apparatus 14 is captiveed joint with rotating blade 15.Wherein the structure of horizontal drive apparatus 14, principle and lifting drive 7 structures, principle are identical substantially.
The control signal transmission principle of aircraft being carried out remote control is:
Receiver of remote-control sytem 19 receive remote signal in the remote control transmitting apparatus (comprise instruction rising, decline are arranged, to left movement, move right etc.), and the intelligent data analyzing and processing by controller 1 CPU module, and the formation control command, namely form the control command of elevating screw control module and the control command of horizontal propeller control module.The elevating screw control module is received the control command signal, by the micro controller system analyzing and processing of self, send control signal for respectively then elevating screw one module, elevating screw two modules, elevating screw three modules and elevating screw four module, just can realize respectively independent control to elevating screw 1, elevating screw 23, elevating screw 34 and elevating screw 45 by these control signals.The elevating screw control module that is positioned at lifting controller 16 transfers to motor 72(or the combustion engine of each elevating screw correspondence by the data line that is positioned at electric signal strut bar 6 to the control signal of each elevating screw), and control motor 72(or combustion engine) switching and operating power size.
The horizontal propeller control module is received the control command signal, by the micro controller system analyzing and processing of self, send control signal for respectively then flat spin oar one module, horizontal propeller two modules, horizontal propeller three modules and horizontal propeller four module, just can realize respectively independent control to horizontal propeller 1, horizontal propeller 2 10, horizontal propeller 3 11 and horizontal propeller 4 12 by these control signals.The horizontal propeller control module that is positioned at horizontal controller 17 transfers to the motor of each horizontal propeller correspondence and switching and the operating power size of control motor to the control signal of each horizontal propeller by the data line that is positioned at electric signal strut bar 13.
The bottom of controller 1 is provided with alighting gear 18, and this alighting gear 18 makes this aircraft takeoff more convenient, steady with landing.
This aircraft can be made small and exquisite, is used for flight investigation, shooting field, during use, installs camera at aircraft and gets final product.
The above only is preferred embodiment of the present utility model; not in order to limit the utility model; all any modifications of within spirit of the present utility model and principle, doing, be equal to and replace and improvement etc., all should be included within the protection domain of the present utility model.
Claims (10)
1. aircraft, it is characterized in that: comprise controller (1), controller (1) arranges evenly upward and is connected with elevating screw one (2), elevating screw two (3), elevating screw three (4) and elevating screw four (5) that described controller (1) is upward gone back even the layout and is connected with horizontal propeller one (9), horizontal propeller two (10), horizontal propeller three (11) and horizontal propeller four (12).
2. according to the described aircraft of claim 1, it is characterized in that: described elevating screw one (2), elevating screw two (3), elevating screw three (4) and elevating screw four (5) are positioned at same horizontal plane A, and described horizontal propeller one (9), horizontal propeller two (10), horizontal propeller three (11) and horizontal propeller four (12) are positioned at same horizontal surface B.
3. according to the described aircraft of claim 2, it is characterized in that: described controller (1) mainly includes lifting controller (16), horizontal controller (17), receiver of remote-control sytem (19) and shock sensor, and described lifting controller (16) is connected with described elevating screw one (2), elevating screw two (3), elevating screw three (4) and elevating screw four (5) respectively; Described horizontal controller (17) is connected with horizontal propeller one (9), horizontal propeller two (10), horizontal propeller three (11) and horizontal propeller four (12) respectively.
4. according to claim 1 or 3 described aircraft, it is characterized in that: described controller (1) inside includes CPU module, and CPU module is electrically connected with elevating screw control module, horizontal propeller control module, shock sensor module, gyroscope and remote control control module respectively.
5. according to the described aircraft of claim 4, it is characterized in that: described elevating screw control module is made up of elevating screw one module, elevating screw two modules, elevating screw three modules and elevating screw four module.
6. according to the described aircraft of claim 4, it is characterized in that: described horizontal propeller control module is made up of horizontal propeller one module, horizontal propeller two modules, horizontal propeller three modules and horizontal propeller four module.
7. according to the described aircraft of claim 4, it is characterized in that: described elevating screw one (2), elevating screw two (3), elevating screw three (4) is identical with elevating screw four (5) structures, and included electric signal strut bar (6), lifting drive (7) and rotating blade (8), described electric signal strut bar (6) one ends are fixedly connected on the described lifting controller (16), the other end of electric signal strut bar (6) is electrically connected with lifting drive (7), and the output shaft of described lifting drive (7) is captiveed joint with rotating blade (8).
8. according to the described aircraft of claim 7, it is characterized in that: described lifting drive (7) mainly is made of electric machine casing (71) and motor (72), electric machine casing (71) is fixedly connected on the end of electric signal strut bar (6), and motor (72) is installed in electric machine casing (71) inner chamber; The centre of gration place of rotating blade (8) is provided with rotary axle box (81), and the output shaft (721) of described motor (72) closely cooperates and is installed in this rotary axle box (81).
9. according to the described aircraft of claim 4, it is characterized in that: described horizontal propeller one (9), horizontal propeller two (10), horizontal propeller three (11) is identical with horizontal propeller four (12) structures, and included electric signal strut bar (13), horizontal drive apparatus (14) and rotating blade (15), described electric signal strut bar (13) one ends are fixedly connected on the described horizontal controller (17), the other end of electric signal strut bar (13) is electrically connected with horizontal drive apparatus (14), and the output shaft of described horizontal drive apparatus (14) is captiveed joint with rotating blade (15).
10. according to the described aircraft of claim 4, it is characterized in that: the bottom of described controller (1) is provided with alighting gear (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320089966 CN203127142U (en) | 2013-02-27 | 2013-02-27 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320089966 CN203127142U (en) | 2013-02-27 | 2013-02-27 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203127142U true CN203127142U (en) | 2013-08-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN 201320089966 Expired - Fee Related CN203127142U (en) | 2013-02-27 | 2013-02-27 | Aircraft |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103112587A (en) * | 2013-02-27 | 2013-05-22 | 曾小敏 | Aircraft |
| CN104648667A (en) * | 2015-02-17 | 2015-05-27 | 何春旺 | Aircraft |
| CN104743107A (en) * | 2015-04-24 | 2015-07-01 | 北京双飞伟业科技有限公司 | Multi-rotor type aircraft |
| CN105711825A (en) * | 2016-03-18 | 2016-06-29 | 吴李海 | Hybrid power unmanned aerial vehicle |
| CN106114851A (en) * | 2015-05-08 | 2016-11-16 | 光州科学技术院 | Many rotary wind types unmanned flight's body |
| CN106585966A (en) * | 2016-12-13 | 2017-04-26 | 天津传承科技有限公司 | Electromechanical integration unmanned aerial vehicle device capable of smoothly taking off and landing |
| CN107140185A (en) * | 2017-05-22 | 2017-09-08 | 程伯儒 | A kind of intelligent multi-rotor unmanned aerial vehicle |
| US10160538B2 (en) | 2013-05-31 | 2018-12-25 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
-
2013
- 2013-02-27 CN CN 201320089966 patent/CN203127142U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103112587A (en) * | 2013-02-27 | 2013-05-22 | 曾小敏 | Aircraft |
| US10160538B2 (en) | 2013-05-31 | 2018-12-25 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US10196138B2 (en) | 2013-05-31 | 2019-02-05 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US10745119B2 (en) | 2013-05-31 | 2020-08-18 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US11267565B2 (en) | 2013-05-31 | 2022-03-08 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| CN104648667A (en) * | 2015-02-17 | 2015-05-27 | 何春旺 | Aircraft |
| CN104743107A (en) * | 2015-04-24 | 2015-07-01 | 北京双飞伟业科技有限公司 | Multi-rotor type aircraft |
| CN106114851A (en) * | 2015-05-08 | 2016-11-16 | 光州科学技术院 | Many rotary wind types unmanned flight's body |
| CN105711825A (en) * | 2016-03-18 | 2016-06-29 | 吴李海 | Hybrid power unmanned aerial vehicle |
| CN106585966A (en) * | 2016-12-13 | 2017-04-26 | 天津传承科技有限公司 | Electromechanical integration unmanned aerial vehicle device capable of smoothly taking off and landing |
| CN107140185A (en) * | 2017-05-22 | 2017-09-08 | 程伯儒 | A kind of intelligent multi-rotor unmanned aerial vehicle |
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Legal Events
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| 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: 20130814 |
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| CF01 | Termination of patent right due to non-payment of annual fee |