CN108557076B - Unmanned aerial vehicle based on full protection skeleton - Google Patents
Unmanned aerial vehicle based on full protection skeleton Download PDFInfo
- Publication number
- CN108557076B CN108557076B CN201810045789.0A CN201810045789A CN108557076B CN 108557076 B CN108557076 B CN 108557076B CN 201810045789 A CN201810045789 A CN 201810045789A CN 108557076 B CN108557076 B CN 108557076B
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- Prior art keywords
- unmanned aerial
- aerial vehicle
- fixedly connected
- shell
- vehicle shell
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
- B64C1/062—Frames specially adapted to absorb crash loads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention discloses an unmanned aerial vehicle based on a full-protection framework, which comprises an unmanned aerial vehicle shell, wherein one side of the unmanned aerial vehicle shell is provided with a charging port, the top and the bottom of the unmanned aerial vehicle shell are fixedly connected with a supporting platform, the surface of the supporting platform is fixedly connected with a protection framework, balancing machines are respectively arranged on the periphery of the unmanned aerial vehicle shell, an aircraft is rotatably connected inside the unmanned aerial vehicle shell, the top end of a fixing support is rotatably connected with a shock-absorbing rod, the section of the shock-absorbing rod is fixedly connected with the fixing support through a thrust spring, and the end face of the shock-absorbing rod is fixedly connected with a supporting leg. This unmanned aerial vehicle based on protect skeleton entirely, protection skeleton can realize the support that falls to the ground to unmanned aerial vehicle, lie in the shock attenuation that can be abundant when the object bumps, reduce the impact that the collision caused to unmanned aerial vehicle, protection skeleton cooperation rotary device can be so that the positive and negative can change at will of unmanned aerial vehicle, is favorable to the adjustment after the unmanned aerial vehicle collision.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle based on a full-protection framework.
Background
The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, or is completely or intermittently and autonomously operated by an on-board computer, the unmanned aerial vehicle can be divided into military and civil aspects according to the application field, the unmanned aerial vehicle is divided into a reconnaissance plane and a target plane, the civil aspect and the unmanned aerial vehicle + industry application are really needed by the unmanned aerial vehicle, and the unmanned aerial vehicle is currently applied in the fields of aerial photography, agriculture, plant protection, micro self-timer, express delivery transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection, disaster relief, movie and television shooting, romantic manufacturing and the like, so that the purposes of the unmanned aerial vehicle are greatly expanded, and the developed countries also actively expand the industry application and develop the unmanned aerial vehicle technology.
Present unmanned aerial vehicle does not all have corresponding safeguard measure, collides when carrying out the work easily, leads to equipment to damage, can not in time adjust after the collision, and stability is not strong.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides an unmanned aerial vehicle based on a full-protection framework, and solves the problem of poor stability of the unmanned aerial vehicle during operation.
In order to achieve the purpose, the invention is realized by the following technical scheme:
an unmanned aerial vehicle based on a full-protection framework comprises an unmanned aerial vehicle shell, wherein a charging port is formed in one side of the unmanned aerial vehicle shell, supporting platforms are fixedly connected to the top and the bottom of the unmanned aerial vehicle shell, a protection framework is fixedly connected to the surface of each supporting platform, balancing machines are respectively arranged on the periphery of the unmanned aerial vehicle shell, and an aircraft is rotatably connected to the inside of the unmanned aerial vehicle shell;
the protective framework comprises a fixed support, a shock absorption rod is rotatably connected to the top end of the fixed support, the section of the shock absorption rod is fixedly connected with the fixed support through a thrust spring, a supporting leg is fixedly connected to the end face of the shock absorption rod, and a sponge block is fixedly connected to one end, far away from the fixed support, of the shock absorption rod;
the balancing machine comprises a rotating device, the bottom of the rotating device is fixedly connected with an unmanned aerial vehicle shell, one end of an output shaft of the rotating device is fixedly connected with a rotating support, the bottom of the rotating support is fixedly connected with a gyroscope, one side of the rotating support is fixedly connected with a first driving device, and one end of an output shaft of the first driving device is fixedly connected with a fan blade;
the right side of the inner wall of the unmanned aerial vehicle shell is fixedly connected with a fixed block, the right side of the top of the fixed block is fixedly connected with a control plate, the left side of the top of the fixed block is fixedly connected with an adjusting device, one end of an output shaft of the adjusting device penetrates through the unmanned aerial vehicle shell and extends to the outside of the unmanned aerial vehicle shell, one end of the output shaft of the adjusting device, which is positioned outside the unmanned aerial vehicle shell, is fixedly connected with an aircraft, and the left side of the inner wall of the unmanned aerial vehicle shell is fixedly connected with a lithium battery;
the aircraft includes protecting sheathing, one side of protecting sheathing and the one end fixed connection of adjusting device output shaft, one side that adjusting device was kept away from to protecting sheathing rotates with the unmanned aerial vehicle shell through the pivot to be connected, the inner wall of protecting sheathing passes through dead lever fixedly connected with second drive arrangement, the one end fixedly connected with screw of second drive arrangement output shaft.
Preferably, the bottom end of the fixed support is fixedly connected with the supporting platform through a bolt, and a limiting block matched with the bottom end of the fixed support is arranged at the bottom end of the fixed support.
Preferably, the lithium battery is connected with the charging port through a wire.
Preferably, the first driving device and the second driving device are both brushless direct current motors, and output shafts are arranged at the top and the bottom of the second driving device.
Preferably, the rotating device and the adjusting device are both hybrid stepping motors.
Preferably, an a/D converter is arranged inside the control board, and the control board is connected with the first driving device, the second driving device, the rotating device, the adjusting device and the gyroscope through wires.
Preferably, the protective framework is made of magnesium-aluminum alloy, and the supporting legs are fixedly connected with the damping rods in a hot melt adhesive adhesion mode.
Advantageous effects
The invention provides an unmanned aerial vehicle based on a full-protection framework. The method has the following beneficial effects:
(1) this unmanned aerial vehicle based on protect skeleton entirely can realize the support that falls to the ground to unmanned aerial vehicle through protecting the skeleton, lie in the shock attenuation that can be abundant when the object bumps, reduce the impact that the collision caused to unmanned aerial vehicle, also prevent simultaneously that the fan from hitting the object or artificially becoming the unnecessary injury, protection skeleton cooperation rotary device can make the positive and negative of unmanned aerial vehicle change at will, is favorable to the adjustment after the unmanned aerial vehicle collision.
(2) This unmanned aerial vehicle based on protect skeleton entirely helps improving unmanned aerial vehicle's flying speed through embedded aircraft, and cooperation adjusting device can in time adjust when unmanned aerial vehicle takes place the skew for unmanned aerial vehicle is difficult for receiving the wind-force influence, and stability is stronger.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view of the present invention without a protective frame;
FIG. 3 is a schematic perspective view of the protective framework of the present invention;
FIG. 4 is a schematic perspective view of the balancer of the present invention;
FIG. 5 is an enlarged view of a portion of the invention at A in FIG. 3;
fig. 6 is a schematic structural diagram of the unmanned aerial vehicle shell and the aircraft.
In the figure: the automatic control system comprises an unmanned aerial vehicle shell 1, a charging port 101, an adjusting device 102, a supporting platform 103, a fixing block 104, a control board 105, a lithium battery 106, a protective framework 2, a fixing support 201, a shock absorption rod 202, a supporting foot 203, a protective rod 204, a sponge block 205, a balancing machine 3, a rotating device 301, a first driving device 302, a gyroscope 303, a rotating support 304, fan blades 305, an aircraft 4, a protective shell 401, a second driving device 402, a fixing rod 403 and a propeller 404.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, the present invention provides a technical solution: an unmanned aerial vehicle based on a full-protection framework comprises an unmanned aerial vehicle shell 1, wherein one side of the unmanned aerial vehicle shell 1 is provided with a charging port 101, the top and the bottom of the unmanned aerial vehicle shell 1 are fixedly connected with a supporting platform 103, the surface of the supporting platform 103 is fixedly connected with a protection framework 2, the periphery of the unmanned aerial vehicle shell 1 is respectively provided with a balancing machine 3, the interior of the unmanned aerial vehicle shell 1 is rotatably connected with an aircraft 4, the protection framework 2 comprises a fixed support 201, the bottom end of the fixed support 201 is fixedly connected with the supporting platform 103 through bolts, the bottom end of the fixed support 201 is provided with a limiting block matched with the damping rod 202, the top end of the fixed support 201 is rotatably connected with a damping rod 202, the section of the damping rod 202 is fixedly connected with the fixed support 201 through a thrust spring 206, the thrust spring 206 is used for stress damping when the supporting foot 203 contacts the ground, and the end face of the damping rod 202 is fixedly connected with the supporting foot 203, the end of the shock absorption rod 202 far away from the fixed support 201 is fixedly connected with a sponge block 205, the protective framework 2 is made of magnesium aluminum alloy, the supporting leg 203 and the shock absorption rod 202 are fixedly connected in a hot melt adhesive adhesion manner, the balancing machine 3 comprises a rotating device 301, the bottom of the rotating device 301 is fixedly connected with the unmanned aerial vehicle shell 1, one end of an output shaft of the rotating device 301 is fixedly connected with a rotating support 304, the bottom of the rotating support 304 is fixedly connected with a gyroscope 303, one side of the rotating support 304 is fixedly connected with a first driving device 302, one end of an output shaft of the first driving device 302 is fixedly connected with a fan blade 305, the right side of the inner wall of the unmanned aerial vehicle shell 1 is fixedly connected with a fixed block 104, the right side of the top of the fixed block 104 is fixedly connected with a control plate 105, the left side of the top of the fixed block 104 is fixedly connected with an adjusting device 102, one end of an output shaft of the adjusting device 102 penetrates through the unmanned aerial vehicle shell 1 and extends to the outside of the unmanned aerial vehicle shell 1, one end of an output shaft of the adjusting device 102, which is positioned outside the unmanned aerial vehicle shell 1, is fixedly connected with the aircraft 4, the left side of the inner wall of the unmanned aerial vehicle shell 1 is fixedly connected with the lithium battery 106, the lithium battery 106 is connected with the charging port 101 through a lead, the aircraft comprises a protective shell 401, one side of the protective shell 401 is fixedly connected with one end of the output shaft of the adjusting device 102, one side of the protective shell 401, which is far away from the adjusting device 102, is rotatably connected with the unmanned aerial vehicle shell 1 through a rotating shaft, the rotating device 301 and the adjusting device 102 are both hybrid stepping motors, the inner wall of the protective shell 401 is fixedly connected with a second driving device 402 through a fixing rod 403, the first driving device 302 and the second driving device 402 are both brushless direct current motors, output shafts are arranged at the top and the bottom of the second driving device 402, one end of the output shaft of the second driving device 402 is fixedly connected with a propeller 404, and an A/D converter is arranged inside the control panel 105, the control board 105 is connected to the first driving device 302, the second driving device 402, the rotating device 301, the adjusting device 102, and the gyroscope 303 through wires, respectively.
During operation, place unmanned aerial vehicle on ground, supporting legs 203 and ground contact, inside control panel 105 was transmitted through the AD converter to the analog signal that gyroscope 303 will detect perpendicular ground direction, control panel 105 control rotary device 301 rotation adjustment, make one side of gyroscope 303 perpendicular to ground all the time in the balancing machine 3, control panel 105 control first drive arrangement 302 and the operation of second drive arrangement 402, unmanned aerial vehicle rises the flight, if unmanned aerial vehicle shell 1 takes place the skew, three gyroscope 303 is not on a horizontal plane, control panel 105 control adjustment adjusting device 102 adjusts, make aircraft 4 take place to deflect and adjust.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides an unmanned aerial vehicle based on protect skeleton entirely, includes unmanned aerial vehicle shell (1), its characterized in that: a charging port (101) is formed in one side of the unmanned aerial vehicle shell (1), a supporting platform (103) is fixedly connected to the top and the bottom of the unmanned aerial vehicle shell (1), a protective framework (2) is fixedly connected to the surface of the supporting platform (103), balancing machines (3) are respectively arranged on the periphery of the unmanned aerial vehicle shell (1), and an aircraft (4) is rotatably connected to the interior of the unmanned aerial vehicle shell (1);
the protective framework (2) comprises a fixed support (201), the top end of the fixed support (201) is rotatably connected with a shock absorption rod (202), the section of the shock absorption rod (202) is fixedly connected with the fixed support (201) through a thrust spring (206), the end face of the shock absorption rod (202) is fixedly connected with a supporting leg (203), and one end, far away from the fixed support (201), of the shock absorption rod (202) is fixedly connected with a sponge block (205);
the balancing machine (3) comprises a rotating device (301), the bottom of the rotating device (301) is fixedly connected with the unmanned aerial vehicle shell (1), one end of an output shaft of the rotating device (301) is fixedly connected with a rotating support (304), the bottom of the rotating support (304) is fixedly connected with a gyroscope (303), one side of the rotating support (304) is fixedly connected with a first driving device (302), and one end of the output shaft of the first driving device (302) is fixedly connected with a fan blade (305);
a fixed block (104) is fixedly connected to the right side of the inner wall of the unmanned aerial vehicle shell (1), a control plate (105) is fixedly connected to the right side of the top of the fixed block (104), an adjusting device (102) is fixedly connected to the left side of the top of the fixed block (104), one end of an output shaft of the adjusting device (102) penetrates through the unmanned aerial vehicle shell (1) and extends to the outside of the unmanned aerial vehicle shell (1), one end of the output shaft of the adjusting device (102) located outside the unmanned aerial vehicle shell (1) is fixedly connected with an aircraft (4), and a lithium battery (106) is fixedly connected to the left side of the inner wall of the unmanned aerial vehicle shell (1);
the aircraft comprises a protective shell (401), one side of the protective shell (401) is fixedly connected with one end of an output shaft of an adjusting device (102), one side of the protective shell (401), which is far away from the adjusting device (102), is rotatably connected with the unmanned aerial vehicle shell (1) through a rotating shaft, the inner wall of the protective shell (401) is fixedly connected with a second driving device (402) through a fixing rod (403), and one end of the output shaft of the second driving device (402) is fixedly connected with a propeller (404).
2. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: the bottom end of the fixed support (201) is fixedly connected with the supporting platform (103) through a bolt, and the bottom end of the fixed support (201) is provided with a limiting block matched with the supporting platform (202).
3. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: the lithium battery (106) is connected with the charging port (101) through a lead.
4. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: the first driving device (302) and the second driving device (402) are both brushless direct current motors, and output shafts are arranged at the top and the bottom of the second driving device (402).
5. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: the rotating device (301) and the adjusting device (102) are both hybrid stepping motors.
6. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: an A/D converter is arranged in the control board (105), and the control board (105) is connected with the first driving device (302), the second driving device (402), the rotating device (301), the adjusting device (102) and the gyroscope (303) through wires.
7. The unmanned aerial vehicle based on full protection skeleton of claim 1, characterized in that: the material of protection skeleton (2) is magnesium aluminum alloy, the fixed connection mode of supporting legs (203) and shock attenuation pole (202) is that the hot melt adhesive adhesion is fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810045789.0A CN108557076B (en) | 2018-01-17 | 2018-01-17 | Unmanned aerial vehicle based on full protection skeleton |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810045789.0A CN108557076B (en) | 2018-01-17 | 2018-01-17 | Unmanned aerial vehicle based on full protection skeleton |
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| CN108557076A CN108557076A (en) | 2018-09-21 |
| CN108557076B true CN108557076B (en) | 2021-10-29 |
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| CN106043673A (en) * | 2016-08-12 | 2016-10-26 | 成都恒胜达科技有限公司 | Unmanned plane landing in random terrain |
| CN107380467A (en) * | 2017-07-31 | 2017-11-24 | 重庆晓微城企业孵化器有限公司 | A kind of information display device and its application method based on unmanned plane cluster |
| CN107380439A (en) * | 2017-08-31 | 2017-11-24 | 广州市妙伊莲科技有限公司 | A kind of rotor wing unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104554724B (en) * | 2014-11-14 | 2016-05-04 | 山东农业大学 | A kind of plant protection dedicated unmanned machine and driving method of low cost high capacity |
| US9650134B2 (en) * | 2015-06-05 | 2017-05-16 | Dana R. CHAPPELL | Unmanned aerial rescue system |
| KR101585650B1 (en) * | 2015-09-11 | 2016-01-14 | 주식회사 나라항공기술 | Safety apparatus for unmanned aerial vehicles and method for sensing and avoiding of obstacles thereof |
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2018
- 2018-01-17 CN CN201810045789.0A patent/CN108557076B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416589A (en) * | 2015-11-26 | 2016-03-23 | 中国计量学院 | Rope pulling type control device and control method for quad-rotor unmanned aerial vehicle |
| CN106043673A (en) * | 2016-08-12 | 2016-10-26 | 成都恒胜达科技有限公司 | Unmanned plane landing in random terrain |
| CN107380467A (en) * | 2017-07-31 | 2017-11-24 | 重庆晓微城企业孵化器有限公司 | A kind of information display device and its application method based on unmanned plane cluster |
| CN107380439A (en) * | 2017-08-31 | 2017-11-24 | 广州市妙伊莲科技有限公司 | A kind of rotor wing unmanned aerial vehicle |
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| CN108557076A (en) | 2018-09-21 |
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