CN105346709A - Multi-rotor craft capable of transforming combination - Google Patents
Multi-rotor craft capable of transforming combination Download PDFInfo
- Publication number
- CN105346709A CN105346709A CN201510751465.5A CN201510751465A CN105346709A CN 105346709 A CN105346709 A CN 105346709A CN 201510751465 A CN201510751465 A CN 201510751465A CN 105346709 A CN105346709 A CN 105346709A
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- Prior art keywords
- fuselage
- rotor
- transmission module
- horn
- wireless
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radio Relay Systems (AREA)
- Studio Devices (AREA)
Abstract
The invention discloses a multi-rotor craft capable of transforming combination. Two arms or three arms are installed on a machine body. The arms are connected with the machine body through screws. An electronic speed regulator is installed on each arm. Motors are installed at two ends of each arm. The motor is loaded with a propeller. A flight control module, a wireless image transmission module, a wireless digital transmission module and a remote control reception module are installed at the upper part of the central position of the machine body. A sensor is mounted at the bottom of the central position of the machine body. An undercarriage is installed at two sides of the bottom of the machine body. A polymer lithium battery is mounted on the undercarriage. The multi-rotor craft can be transformed into a four-rotor or a six-rotor structure to meet requirements of different situations. The four-rotor structure meets the small-load requirement and is light and flexible. The six-rotor structure is stable, achieves large load and can be loaded with single-lens reflex cameras and heavy sensors.
Description
Technical field
The invention belongs to aircraft field, particularly relate to the multi-rotor aerocraft of a kind of deformable combination.
Background technology
Quadrotor, can meet less load requirement, and feature is light, flexible; Six rotorcraft feature be stablize, realize load comparatively large, meet and carry single anti-, heavier sensor;
Existing multi-rotor aerocraft array mode underaction, carry inconvenience, load is single, can not meet the demand of different occasion.
Summary of the invention
The multi-rotor aerocraft that the object of the present invention is to provide a kind of deformable to combine, be intended to solve existing multi-rotor aerocraft array mode underaction, carry inconvenience, load is single, can not meet the problem of the demand of different occasion.
The present invention realizes like this, the fuselage of the multi-rotor aerocraft of deformable combination is provided with two horns or three horns, specifically comprises electronic governor, motor, screw propeller, gps antenna, flight control modules, wireless image transmission module, wireless digital transmission module, remote control reception module, remote controller, poly-lithium battery carry, sensor carry, alighting gear;
Flight control modules comprises Inertial Measurement Unit, gyroscope, accelerometer, magnetometer, pneumatics meter, and this flight control modules, for monitoring flight attitude, controls electronic governor and exports;
Wireless image transmission module is used for the video by Airborne Camera or sensor, is wirelessly transferred to ground station;
Wireless digital transmission module, by wireless transmission method, by the flight attitude data of aircraft, comprises the parameter of coordinate, inclination angle, orientation, flying speed, mode of operation, is real-time transmitted to ground station;
The flight control command that remote control reception module sends for receiving ground remote control equipment, controls offline mode and flight attitude;
Described horn is connected with fuselage by screw, and horn installs electronic governor, and at horn two ends mounted motor, motor carries screw propeller;
Described flight control modules, wireless image transmission module, wireless digital transmission module, remote control reception module are arranged on the top of described fuselage midway location, described sensor carry is arranged on the bottom of described fuselage midway location, described alighting gear is arranged on the both sides of described fuselage bottom, and described poly-lithium battery carry is arranged on described alighting gear;
Further, every bar horn center, is provided with the groove holding another horn.
Further, fuselage is installed two horns and form four rotor mechanisms.
Further, fuselage is installed three horns and form six rotor mechanisms.
The present invention is the multi-rotor aerocraft of deformable combination, and aircraft adopts assembling mode flexibly, may be combined with into four rotors, six rotor structures, meets the demand of different occasion, four rotors, and meet less load requirement, feature is light, flexible; Six rotor features be stablize, realize load comparatively large, meet and carry single anti-, heavier sensor; Owing to adopting modularity flexibly, two kinds of structures can fast be changed.In data acquisition operation in the wild, in order to obtain longer airborne period, alleviating fuselage weight, adopting the structure of four rotors, carry light-duty sensor; When needing to carry the larger sensor of weight, needing the load-carrying ability that flying instrument is standby stronger, now can be converted to six rotor structures of heavy－duty; The multi-rotor aerocraft of deformable combination, can fast dismounting, and after taking apart, volume is very little, easy to carry, follows and carries four rotors respectively, six rotors are compared from two aircraft, greatly improve portability.
Accompanying drawing explanation
Fig. 1 is the structural representation of the quadrotor that the embodiment of the present invention provides.
Fig. 2 is the front elevation of the quadrotor that the embodiment of the present invention provides.
Fig. 3 is the left view of the quadrotor that the embodiment of the present invention provides.
Fig. 4 is the front elevation of the six rotorcraft that the embodiment of the present invention provides.
Fig. 5 is the front elevation of the six rotorcraft that the embodiment of the present invention provides.
Fig. 6 is the left view of the six rotorcraft that the embodiment of the present invention provides.
Fig. 7 is the structural representation of the horn that the embodiment of the present invention provides.
In figure: 1, electronic governor; 2, motor; 3, screw propeller; 4, gps antenna; 5, flight control modules; 6, wireless image transmission module; 7, wireless digital transmission module; 8, remote control reception module; 9, poly-lithium battery carry; 10, sensor carry; 11, alighting gear.
Detailed description of the invention
In order to make object of the present invention, technical scheme and advantage clearly understand, below in conjunction with embodiment, the present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
Below in conjunction with accompanying drawing, application principle of the present invention is further described.
Refer to Fig. 1-Fig. 7:
The fuselage of the multi-rotor aerocraft of a kind of deformable combination of the embodiment of the present invention is provided with two horns or three horns, specifically comprises electronic governor 1, motor 2, screw propeller 3, gps antenna 4, flight control modules 5, wireless image transmission module 6, wireless digital transmission mould 7 pieces, remote control reception module 8, remote controller, poly-lithium battery carry 9, sensor carry 10, alighting gear 11;
Flight control modules 5 comprises Inertial Measurement Unit, gyroscope, accelerometer, magnetometer, pneumatics meter, and this flight control modules, for monitoring flight attitude, controls electronic governor and exports;
Wireless image transmission module 6, for the video by Airborne Camera or sensor, is wirelessly transferred to ground station;
Wireless digital transmission module 7, by wireless transmission method, by the flight attitude data of aircraft, comprises the parameter of coordinate, inclination angle, orientation, flying speed, mode of operation, is real-time transmitted to ground station;
The flight control command that remote control reception module 8 sends for receiving ground remote control equipment, controls offline mode and flight attitude;
Described horn is connected with fuselage by screw, horn is installed electronic governor 1, and at horn two ends mounted motor 2, motor 2 carries screw propeller 3, for aircraft provides flying power;
Described flight control modules 5, wireless image transmission module 6, wireless digital transmission module 7, remote control reception module 8 are arranged on the top of described fuselage midway location, described sensor carry 10 is arranged on the bottom of described fuselage midway location, described alighting gear 11 is arranged on the both sides of described fuselage bottom, and described poly-lithium battery carry 9 is arranged on described alighting gear 11;
Further, every bar horn center, is provided with the groove holding another horn.
Further, fuselage is installed two horns and form four rotor mechanisms.
Further, fuselage is installed three horns and form six rotor mechanisms.
The present invention is the multi-rotor aerocraft of deformable combination, and aircraft adopts assembling mode flexibly, may be combined with into four rotors, six rotor structures, meets the demand of different occasion, four rotors, and meet less load requirement, feature is light, flexible; Six rotor features be stablize, realize load comparatively large, meet and carry single anti-, heavier sensor.
Owing to adopting modularity flexibly, two kinds of structures can fast be changed.In data acquisition operation in the wild, in order to obtain longer airborne period, alleviating fuselage weight, adopting the structure of four rotors, carry light-duty sensor; When needing to carry the larger sensor of weight, as multispectral camera, silent frame camera etc., needing the load-carrying ability that flying instrument is standby stronger, now can be converted to six rotor structures of heavy－duty.
The multi-rotor aerocraft of deformable combination, can fast dismounting, after taking apart, volume is very little, can be placed in packsack easily, with carrying four rotors respectively, six rotors are compared from two aircraft, greatly improve portable capability, usually an aircraft is carried, all need the chest that outfit one is special, adopt the multi-rotor aerocraft that this deformable is combined, can together with other article, put into a packsack, and relative to two complete equipments, decrease four motors and four cover electronic governor configurations, no matter in economy and portability, all there is good innovation.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, all any amendments done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. a multi-rotor aerocraft for deformable combination, is characterized in that, the fuselage of the multi-rotor aerocraft of described deformable combination is provided with two horns or three horns; Comprise electronic governor, motor, screw propeller, gps antenna, flight control modules, wireless image transmission module, wireless digital transmission module, remote control reception module, remote controller, poly-lithium battery carry, sensor carry, alighting gear.
Flight control modules comprises Inertial Measurement Unit, gyroscope, accelerometer, magnetometer, pneumatics meter, and this flight control modules, for monitoring flight attitude, controls electronic governor and exports;
Wireless image transmission module is used for the video by Airborne Camera or sensor, is wirelessly transferred to ground station;
Wireless digital transmission module, by wireless transmission method, by the flight attitude data of aircraft, comprises the parameter of coordinate, inclination angle, orientation, flying speed, mode of operation, is real-time transmitted to ground station;
The flight control command that remote control reception module sends for receiving ground remote control equipment, controls offline mode and flight attitude;
Described horn is connected with fuselage by screw, and horn installs electronic governor, and at horn two ends mounted motor, motor carries screw propeller;
Described flight control modules, wireless image transmission module, wireless digital transmission module, remote control reception module are arranged on the top of described fuselage midway location, described sensor carry is arranged on the bottom of described fuselage midway location, described alighting gear is arranged on the both sides of described fuselage bottom, and described poly-lithium battery carry is arranged on described alighting gear.
2. the multi-rotor aerocraft of deformable combination as claimed in claim 1, is characterized in that, every bar horn center, is provided with the groove holding another horn.
3. the multi-rotor aerocraft of deformable combination as claimed in claim 1, is characterized in that, fuselage is installed two horns and forms four rotor mechanisms.
4. the multi-rotor aerocraft of deformable combination as claimed in claim 1, is characterized in that, fuselage is installed three horns and forms six rotor mechanisms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510751465.5A CN105346709B (en) | 2015-11-05 | 2015-11-05 | A kind of multi-rotor aerocraft of deformable combination |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510751465.5A CN105346709B (en) | 2015-11-05 | 2015-11-05 | A kind of multi-rotor aerocraft of deformable combination |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105346709A true CN105346709A (en) | 2016-02-24 |
| CN105346709B CN105346709B (en) | 2018-06-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510751465.5A Active CN105346709B (en) | 2015-11-05 | 2015-11-05 | A kind of multi-rotor aerocraft of deformable combination |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857587A (en) * | 2016-03-31 | 2016-08-17 | 英华达（上海）科技有限公司 | Multi-axis unmanned aerial vehicle and flight method thereof |
| CN106314779A (en) * | 2016-09-19 | 2017-01-11 | 深圳电航空技术有限公司 | Drone and drone control method |
| CN106314782A (en) * | 2016-10-22 | 2017-01-11 | 钟贵洪 | Remote control aerial camera |
| CN106403958A (en) * | 2016-10-27 | 2017-02-15 | 广东容祺智能科技有限公司 | Unmanned plane aircraft intelligent course indication system |
| CN108513639A (en) * | 2017-07-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Motor drives and flight control method, electricity tune, dynamical system and UAV system |
| CN109187102A (en) * | 2018-09-30 | 2019-01-11 | 广州地理研究所 | A kind of UAV system air enthalpy method sampling apparatus |
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| EP1262403A2 (en) * | 2001-05-23 | 2002-12-04 | ZF Luftfahrttechnik GmbH | Individual rotor blade control device |
| CN204197292U (en) * | 2014-08-07 | 2015-03-11 | 金卫红 | A kind of Multi-axis aircraft |
| CN204489175U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | A kind of many rotor wing unmanned aerial vehicles connecting rod fold mechanism |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
-
2015
- 2015-11-05 CN CN201510751465.5A patent/CN105346709B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1262403A2 (en) * | 2001-05-23 | 2002-12-04 | ZF Luftfahrttechnik GmbH | Individual rotor blade control device |
| CN204197292U (en) * | 2014-08-07 | 2015-03-11 | 金卫红 | A kind of Multi-axis aircraft |
| CN204489175U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | A kind of many rotor wing unmanned aerial vehicles connecting rod fold mechanism |
| CN104859853A (en) * | 2015-06-01 | 2015-08-26 | 姚龙江 | Six-rotor hybrid aircraft |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857587A (en) * | 2016-03-31 | 2016-08-17 | 英华达（上海）科技有限公司 | Multi-axis unmanned aerial vehicle and flight method thereof |
| CN106314779A (en) * | 2016-09-19 | 2017-01-11 | 深圳电航空技术有限公司 | Drone and drone control method |
| CN106314779B (en) * | 2016-09-19 | 2020-02-18 | 深圳一电航空技术有限公司 | Unmanned aerial vehicle and unmanned aerial vehicle control method |
| CN106314782A (en) * | 2016-10-22 | 2017-01-11 | 钟贵洪 | Remote control aerial camera |
| CN106403958A (en) * | 2016-10-27 | 2017-02-15 | 广东容祺智能科技有限公司 | Unmanned plane aircraft intelligent course indication system |
| CN106403958B (en) * | 2016-10-27 | 2019-04-02 | 广东容祺智能科技有限公司 | A kind of unmanned plane during flying device intelligence bearing indication system |
| CN108513639A (en) * | 2017-07-28 | 2018-09-07 | 深圳市大疆创新科技有限公司 | Motor drives and flight control method, electricity tune, dynamical system and UAV system |
| CN109187102A (en) * | 2018-09-30 | 2019-01-11 | 广州地理研究所 | A kind of UAV system air enthalpy method sampling apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105346709B (en) | 2018-06-26 |
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Address after: 510075 one of the compound No. 100, Xianlie Middle Road, Yuexiu District, Guangzhou City, Guangdong Province Patentee after: Guangzhou Institute of geography, Guangdong Academy of Sciences Address before: 510070 No. 100 martyrs Middle Road, Guangzhou, Guangdong, Yuexiu District Patentee before: GUANGZHOU INSTITUTE OF GEOGRAPHY |
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