CN105059539A - Novel efficient drone - Google Patents
Novel efficient drone Download PDFInfo
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- CN105059539A CN105059539A CN201510410912.0A CN201510410912A CN105059539A CN 105059539 A CN105059539 A CN 105059539A CN 201510410912 A CN201510410912 A CN 201510410912A CN 105059539 A CN105059539 A CN 105059539A
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- unmanned plane
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- stop platform
- piston engine
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Abstract
The invention relates to a novel efficient drone which comprises a take-off and landing platform, a drone body and a control system, wherein the take-off and landing platform comprises a positioning support frame, a traveling mechanism and an unmanned aerial vehicle take-off and landing platform, and at least three positioning electromagnets and at least one homeward voyage guided radar are uniformly distributed on the unmanned aerial vehicle take-off and landing platform; the drone body comprises undercarriages, a fuselage, fixed wings, spiral wings, a turbofan engine, a piston engine and driving propellers; the control system comprises a flight attitude control unit, a wireless data communication unit, a function expansion unit, a data processing unit, a flight navigation unit and a landing navigation unit; and the undercarriages and the fixed wings are installed at the outer side of the fuselage. According to the invention, on one hand, the transport capacity of the unmanned aerial vehicle system is improved, and on the other hand, the operation efficiency of the drone can be effectively improved, thereby greatly improving the service performance of the drone and widening the range of application of the drone.
Description
Technical field
The present invention relates to unmanned air vehicle technique, is exactly a kind of new and effective unmanned plane.
Background technology
Survey at map at present, in the industry field that forest detection etc. are numerous, unmanned plane obtains and uses very widely, but find in actual use, current Unmanned Aircraft Systems (UAS) operationally, the power system of unmanned plane is moved by piston engine by driving screw propeller or rotary wings and is obtained often, although this power system structure is simple, and unmanned plane can be made to obtain good flight attitude control ability and flying power, but result in maneuvering performance and the high speed performance wretched insufficiency of unmanned plane simultaneously, thus make the range of use of unmanned plane limited, simultaneously, in order to the unmanned plane obtaining high maneuverability and high speed performance can exist again the drawback of flight attitude control ability and flying power deficiency simultaneously, simultaneously, current unmanned plane operates relatively simple when launch, but when unmanned plane landing is turned one's head, then often difficulty is larger, and often cause unmanned plane to collide with ground etc. in descent, thus cause unmanned plane damaged phenomenon to occur, and these above drawbacks, significantly limit the range of use of Unmanned Aircraft Systems (UAS) and the stability of operation, therefore for this present situation, in the urgent need to developing a kind of brand-new Unmanned Aircraft Systems (UAS), with the needs that satisfied reality uses.
Summary of the invention
For the deficiency that prior art exists, the invention provides a kind of new and effective unmanned plane, this invention knot concision and compact, rationally distributed, gesture discrimination power and identification precision is high, run that degree of automation is high, place and adaptive capacity to environment strong, separately can automatically adjust best gesture identification angle according to position of human body simultaneously, thus improve accuracy of identification and the efficiency of gesture on the one hand, greatly improve the convenience of gesture identification on the other hand.
To achieve these goals, the present invention realizes by the following technical solutions:
A kind of new and effective unmanned plane, comprise start-stop platform, unmanned plane body and control system, wherein start-stop platform comprises positioning supporting frame, traveling gear and unmanned plane start-stop platform, wherein positioning supporting frame lower surface is connected with traveling gear, upper surface is connected with unmanned plane start-stop platform, unmanned plane start-stop platform is platy structure, and separately uniform at least three positioning electromagnets and at least one guided radar that makes a return voyage on unmanned plane start-stop platform, and positioning electromagnet is all uniform around the guided radar that makes a return voyage, unmanned plane start-stop platform upper surface separately establishes elastic buffer plate, and be connected with unmanned plane body by elastic buffer plate, unmanned plane body comprises alighting gear, fuselage, fixed wing, spiral wing, fanjet, piston engine and driving screw propeller, wherein fanjet, all at least one and be positioned at fuselage interior, piston engine, and the axis of fanjet and piston engine output shaft all with fuselage axis line parallel, fuselage corresponding to fanjet separately establishes admission port and exhausr port, piston engine is connected with driving screw propeller by output shaft, and each piston engine all drives screw propeller to be connected with at least one, screw propeller is driven to be positioned at outside fuselage and fixed wing, spiral wing to be positioned at directly over fuselage and by transmission device respectively with fanjet, piston engine connects, control system comprises and lays respectively in start-stop platform and unmanned plane body, and connected by wireless data communication, control system comprises flight attitude control unit, wireless data communication unit, functions expanding unit, data processing unit, flight navigation unit and landing navigation elements, wherein data processing unit respectively with flight attitude control unit, wireless data communication unit, functions expanding unit, flight navigation unit and the electrical connection of landing navigation elements, alighting gear and fixed wing are installed in fuselage outer side.
Further, the another and control system of described traveling gear is electrically connected.
Further, described spiral wing at least one.
Further, described flight attitude control unit comprises handle operational module, keyboard operational module and gesture operational module, and handle operational module, keyboard operational module and gesture operational module are in parallel, and be electrically connected by change-over switch and data processing unit.
Further, described fuselage is separately established at least one Function Extension frame
The present invention is rationally distributed, diverse in function, improve the turn-over capacity of Unmanned Aircraft Systems (UAS) on the one hand, on the other hand can improve the Operating ettectiveness of unmanned plane by actv., and simplify the control system of unmanned plane, make unmanned plane obtain high maneuverability, long battery life, vertical takeoff and landing and hover capabilities and landing ability of automatically making a return voyage simultaneously, thus greatly improve the in-use performance of unmanned plane, widen the Applicable scope of unmanned plane.
Accompanying drawing explanation
The present invention is described in detail below in conjunction with the drawings and specific embodiments;
Fig. 1 is structural representation of the present invention;
Fig. 2 is control system electrical schematic diagram.
Detailed description of the invention
The technological means realized for making the present invention, creation characteristic, reaching object and effect is easy to understand, below in conjunction with detailed description of the invention, setting forth the present invention further.
The new and effective unmanned plane of one as described in Figure 1, comprise start-stop platform, unmanned plane body and control system, wherein start-stop platform comprises positioning supporting frame 1, traveling gear 2 and unmanned plane start-stop platform 3, wherein positioning supporting frame 1 lower surface is connected with traveling gear 2, upper surface is connected with unmanned plane start-stop platform 3, unmanned plane start-stop platform 3 is platy structure, and separately uniform at least three positioning electromagnets 4 and at least one guided radar 5 that makes a return voyage on unmanned plane start-stop platform 3, and positioning electromagnet 4 is all uniform around the guided radar 5 that makes a return voyage, unmanned plane start-stop platform upper surface separately establishes elastic buffer plate 6, and be connected with unmanned plane body by elastic buffer plate 6, unmanned plane body comprises alighting gear 7, fuselage 8, fixed wing 9, spiral wing 10, fanjet 11, piston engine 12 and driving screw propeller 13, wherein fanjet 11, all at least one and to be positioned at fuselage 8 inner, piston engine 12, and the axis of fanjet 11 and piston engine 12 output shaft all with fuselage 8 axis being parallel, fuselage 8 corresponding to fanjet 11 is separately established admission port 101 and exhausr port 102, piston engine 12 machine is connected with driving screw propeller 13 by output shaft 120, and each piston engine 12 all drives screw propeller 13 to be connected with at least one, screw propeller 13 is driven to be positioned at outside fuselage 8 and fixed wing 9, spiral wing 10 to be positioned at directly over machine 8 body and by transmission device 14 respectively with fanjet 10, piston engine 11 connects, alighting gear 7 and fixed wing 9 are installed in outside fuselage 8.
As shown in Figure 2, control system described in the present embodiment comprises and lays respectively in start-stop platform and unmanned plane body, and connected by wireless data communication, control system comprises flight attitude control unit, wireless data communication unit, functions expanding unit, data processing unit, flight navigation unit and landing navigation elements, and wherein data processing unit is electrically connected with flight attitude control unit, wireless data communication unit, functions expanding unit, flight navigation unit and navigation elements of landing respectively.
In the present embodiment, the another and control system of described traveling gear 2 is electrically connected.
In the present embodiment, described spiral wing 10 at least one.
In the present embodiment, described flight attitude control unit comprises handle operational module, keyboard operational module and gesture operational module, and handle operational module, keyboard operational module and gesture operational module are in parallel, and be electrically connected by change-over switch and data processing unit.
In the present embodiment, described fuselage 8 is separately established at least one Function Extension frame 15.
The present invention is rationally distributed, diverse in function, improve the turn-over capacity of Unmanned Aircraft Systems (UAS) on the one hand, on the other hand can improve the Operating ettectiveness of unmanned plane by actv., and simplify the control system of unmanned plane, make unmanned plane obtain high maneuverability, long battery life, vertical takeoff and landing and hover capabilities and landing ability of automatically making a return voyage simultaneously, thus greatly improve the in-use performance of unmanned plane, widen the Applicable scope of unmanned plane.
More than show and describe groundwork of the present invention and principal character and advantage of the present invention.The technical personnel of the industry should be understood; the present invention is not restricted to the described embodiments; what describe in above-described embodiment and specification sheets just illustrates principle of the present invention; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications, and these changes and improvements all fall in the claimed scope of the invention.Application claims protection domain is defined by appending claims and equivalent thereof.
Claims (5)
1. a new and effective unmanned plane, it is characterized in that: described new and effective unmanned plane comprises start-stop platform, unmanned plane body and control system, wherein said start-stop platform comprises positioning supporting frame, traveling gear and unmanned plane start-stop platform, wherein said positioning supporting frame lower surface is connected with traveling gear, upper surface is connected with unmanned plane start-stop platform, described unmanned plane start-stop platform is platy structure, and separately uniform at least three positioning electromagnets and at least one guided radar that makes a return voyage on unmanned plane start-stop platform, and described positioning electromagnet is all uniform around the guided radar that makes a return voyage, described unmanned plane start-stop platform upper surface separately establishes elastic buffer plate, and be connected with unmanned plane body by elastic buffer plate, described unmanned plane body comprises alighting gear, fuselage, fixed wing, spiral wing, fanjet, piston engine and driving screw propeller, wherein said fanjet, all at least one and be positioned at fuselage interior, piston engine, and the axis of fanjet and piston engine output shaft all with fuselage axis line parallel, fuselage corresponding to described fanjet separately establishes admission port and exhausr port, described piston engine is connected with driving screw propeller by output shaft, and each piston engine all drives screw propeller to be connected with at least one, described driving screw propeller is positioned at outside fuselage and fixed wing, described spiral wing to be positioned at directly over fuselage and by transmission device respectively with fanjet, piston engine connects, described control system comprises and lays respectively in start-stop platform and unmanned plane body, and connected by wireless data communication, described control system comprises flight attitude control unit, wireless data communication unit, functions expanding unit, data processing unit, flight navigation unit and landing navigation elements, wherein said data processing unit respectively with flight attitude control unit, wireless data communication unit, functions expanding unit, flight navigation unit and the electrical connection of landing navigation elements, described alighting gear and fixed wing are installed in fuselage outer side.
2. the new and effective unmanned plane of one according to claim 1, is characterized in that, the another and control system of described traveling gear is electrically connected.
3. the new and effective unmanned plane of one according to claim 1, is characterized in that, described spiral wing at least one.
4. the new and effective unmanned plane of one according to claim 1, it is characterized in that, described flight attitude control unit comprises handle operational module, keyboard operational module and gesture operational module, and handle operational module, keyboard operational module and gesture operational module are in parallel, and be electrically connected by change-over switch and data processing unit.
5. the new and effective unmanned plane of one according to claim 1, is characterized in that, described fuselage is separately established at least one Function Extension frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510410912.0A CN105059539B (en) | 2015-07-14 | 2015-07-14 | A kind of efficient unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510410912.0A CN105059539B (en) | 2015-07-14 | 2015-07-14 | A kind of efficient unmanned plane |
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| CN105059539A true CN105059539A (en) | 2015-11-18 |
| CN105059539B CN105059539B (en) | 2017-03-01 |
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| CN201510410912.0A Expired - Fee Related CN105059539B (en) | 2015-07-14 | 2015-07-14 | A kind of efficient unmanned plane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105667768A (en) * | 2015-12-31 | 2016-06-15 | 歌尔科技有限公司 | Unmanned aerial vehicle take-off or landing control system and control method |
| CN106564610A (en) * | 2016-10-26 | 2017-04-19 | 中国电子科技集团公司第四十八研究所 | Auxiliary taking-off and landing system for rotor unmanned plane |
| CN106840107A (en) * | 2016-12-31 | 2017-06-13 | 郑州双杰科技股份有限公司 | Unmanned aerial vehicle group intelligent scheduling monitoring system |
| CN109388146A (en) * | 2017-08-04 | 2019-02-26 | 上海裕芮信息技术有限公司 | A kind of unmanned plane core flight control system |
| CN109760828A (en) * | 2019-01-22 | 2019-05-17 | 浙江理工大学 | A kind of high maneuverability unmanned plane during flying system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105667768A (en) * | 2015-12-31 | 2016-06-15 | 歌尔科技有限公司 | Unmanned aerial vehicle take-off or landing control system and control method |
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| CN106564610A (en) * | 2016-10-26 | 2017-04-19 | 中国电子科技集团公司第四十八研究所 | Auxiliary taking-off and landing system for rotor unmanned plane |
| CN106564610B (en) * | 2016-10-26 | 2019-02-15 | 中国电子科技集团公司第四十八研究所 | A kind of rotor wing unmanned aerial vehicle auxiliary landing system |
| CN106840107A (en) * | 2016-12-31 | 2017-06-13 | 郑州双杰科技股份有限公司 | Unmanned aerial vehicle group intelligent scheduling monitoring system |
| CN109388146A (en) * | 2017-08-04 | 2019-02-26 | 上海裕芮信息技术有限公司 | A kind of unmanned plane core flight control system |
| CN109760828A (en) * | 2019-01-22 | 2019-05-17 | 浙江理工大学 | A kind of high maneuverability unmanned plane during flying system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105059539B (en) | 2017-03-01 |
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Inventor after: Xu Shuang Inventor before: The inventor has waived the right to be mentioned |
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Effective date of registration: 20170106 Address after: Nanshan District city of Shenzhen province Guangdong Taoyuan street 518000 Liuxian Avenue No. 1213 Zhongguan honghualing Industrial District 2 District 4 Building 4 floor, 8 floor of building 3 Applicant after: Shenzhen Shengxiang Technology Development Co., Ltd. Address before: The middle Tianfu Avenue in Chengdu city Sichuan province 610041 No. 1388 1 8 storey building No. 866 Applicant before: CHENGDU YUYA SCIENCE & TECHNOLOGY CO., LTD. |
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Granted publication date: 20170301 Termination date: 20200714 |