CN108622426B - A kind of unmanned plane impact protector equipment - Google Patents
A kind of unmanned plane impact protector equipment Download PDFInfo
- Publication number
- CN108622426B CN108622426B CN201810383742.5A CN201810383742A CN108622426B CN 108622426 B CN108622426 B CN 108622426B CN 201810383742 A CN201810383742 A CN 201810383742A CN 108622426 B CN108622426 B CN 108622426B
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- dish type
- surge bunker
- buffer
- fender bracket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
-
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
Abstract
The present invention relates to unmanned plane fields, in particular to a kind of unmanned plane impact protector equipment, the anti-striker being successively arranged along the clockwise direction of the fuselage of unmanned plane including the dish type fender bracket that can be wrapped up the fuselage of unmanned plane and all wings and at least four, all anti-strikers pass through a shock absorber part and connect with dish type fender bracket, the bottom of dish type fender bracket is equipped with the undercarriage for unmanned plane being capable of exposed notch, the fuselage roof of unmanned plane is fixed with attachment base, the top of dish type fender bracket is equipped with can be with the bolted support arm of attachment base, anti- striker includes surge bunker, the triggering inductor being arranged in surge bunker and the idler wheel part being arranged in outside surge bunker, the bottom of dish type fender bracket is equipped with several miniature adjustment fans, sheet is practical can be effectively to in-flight without aircraft progress Anti-bumping protection, and nobody can be compensated Machine is prevented unmanned plane from turning on one's side in the sky and is fallen due to unbalance after being impacted.
Description
Technical field
The present invention relates to unmanned plane field, in particular to a kind of unmanned plane impact protector equipment.
Background technique
UAV is to utilize radio remote-controlled telemetry equipment and the presetting apparatus provided for oneself referred to as " unmanned plane "
The not manned aircraft of manipulation.Without cockpit on machine, but be equipped with navigation and flight control, presetting apparatus and power and
The equipment such as power supply.Ground remote control telemetry station personnel track it, are positioned, are remotely controlled, telemetering sum number by equipment such as data-links
Word transmission.Compared with manned aircraft, it has the characteristics that small in size, easy to use, a variety of flight environment of vehicle requirements of adaptation, therefore can
It is widely used in air remote sensing, meteorological research, agriculture plant seeds by airplane and the prevention and control of plant diseases, pest control.
Unmanned plane can distinguish plurality of classes, wherein having a classification is multi-rotor unmanned aerial vehicle, while can also be called multiaxis without
It is man-machine, according to propeller quantity, and quadrotor, six rotors, eight rotors can be subdivided into etc..It is generally believed that propeller quantity is more,
It flies more steady, it is easier to operate.
Multi-rotor unmanned aerial vehicle is although small in size, but its manufacturing cost is not low, and common is all thousands of members, expensive
Being being capable of member up to ten thousand；Multi-rotor unmanned aerial vehicle it is daily in-flight, since ground control person to remote barrier and is flying
Distance is grasped bad between capable unmanned plane, if operation is not proper, unmanned plane may be struck on the barrier, this
When will damage multiple wings on unmanned plane, will result in body damage in this way, and even if wing does not damage, it is also possible to
Unbalance deviation after touching, the deviation can result in unmanned plane rollover and fall.
Summary of the invention
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of unmanned plane impact protector equipment.
To solve the above problems, the present invention the following technical schemes are provided:
A kind of unmanned plane impact protector equipment, including the dish type that can be wrapped up the fuselage of unmanned plane and all wings
For fender bracket and at least four successively along the anti-striker of the clockwise direction setting of the fuselage of unmanned plane, all anti-strikers pass through one
A shock absorber part is connect with dish type fender bracket, and the bottom of dish type fender bracket exposed can be lacked equipped with the undercarriage for unmanned plane
Mouthful, the fuselage roof of unmanned plane is fixed with attachment base, and the top of dish type fender bracket is equipped with can be bolted with attachment base
Support arm, anti-striker include surge bunker, the triggering inductor being arranged in surge bunker and the idler wheel part being arranged in outside surge bunker,
The bottom of dish type fender bracket is equipped with several miniature adjustment fans.
Further, all shock absorber parts include damping block and cross sliding block, and one end of damping block and dish type are protected
The outer peripheral surface of retaining frame is fixedly connected, and the other end offers cruciform groove, and cross sliding block movable can be arranged cross
In groove, and four ends of cross sliding block pass through a damping spring respectively and the inner wall elasticity of cruciform groove connects
It connects.
Further, one end of all surge bunkers is connect with all cross sliding blocks correspondingly respectively, and
The other end of all surge bunkers is open setting.
Further, the orlop in surge bunker is arranged in the triggering inductor, is equipped with buffer arm, buffer arm in surge bunker
One end it is hinged by torsional spring and the roof in surge bunker, buffer arm is hollow structure, can be movable in the free end of buffer arm
Be inserted with extension arm, be additionally provided in surge bunker can horizontally toward its open-mouth sliding buffer board, extension arm far from buffering
One end of arm and the top of buffer board connect, and the extension arm one end and the top of buffer board can level be slidably matched.
Further, all idler wheel parts are located at the buffering front edge of board in respective position surge bunker, idler wheel part packet
Two buffer bars are included, two buffer bars are in that horizontal and the two the same end is fixedly connected with buffer board, and two buffer bars are another
One end is hinged with a buffering wheel.
Further, all buffer boards are equipped with a touching far from one end of respective position surge bunker open-mouth
Bar.
Further, the indentation, there be symmetrically arranged with two can respectively with the bolted fixed strip of undercarriage, dish type
Fender bracket is cell structure.
Further, all miniature adjustment fans are successively arranged along the clockwise direction of fuselage, and all miniature
Fan is adjusted to correspond with all surge bunkers respectively.
The utility model has the advantages that a kind of unmanned plane impact protector equipment of the invention, by all triggering inductors and all miniature tune
Rectification campaign fan is connect with the control handle of multi-rotor unmanned aerial vehicle, and wireless module and control mainboard are equipped in control handle, then more
Rotor wing unmanned aerial vehicle flies, after barrier to be contacted, dish type fender bracket preferential contact barrier, and its face or close barrier
The buffering wheel of the surge bunker of object location is hindered to contradict barrier, rotation occurs for buffering wheel, and release portion divides frictional impact dynamics, and should
Impact force makes buffer board carry out horizontal movement in surge bunker by extension arm and buffer arm, that is, towards in the surge bunker
Triggering inductor direction, and the touching bar of the buffer board can touch the induction end of triggering inductor, and signal passes to control
Wireless module in handle processed, then control miniature adjustment fan corresponding with the triggering inductor is carried out by control mainboard and is carried out
Work, caused unbalance due to hitting to compensate with this, the time of the miniature adjustment fan work can be adjusted to 5S-8S in advance,
And buffer board in surge bunker due to hitting in dynamics movement, cross sliding block cooperation damping spring in cruciform groove into
Row is alleviated, and influence of the impact force to unmanned plane is greatly reduced, this it is practical can effectively to in-flight carry out anticollision without aircraft
Protection, and unmanned plane can be compensated due to unbalance after being impacted, it prevents unmanned plane from turning on one's side in the sky and falls.
Detailed description of the invention
Fig. 1 is installation condition schematic diagram one of the invention；
Fig. 2 is schematic perspective view of the invention；
Fig. 3 is the enlarged drawing in Fig. 2 at A；
Fig. 4 is installation condition schematic diagram two of the invention；
Fig. 5 is installation condition schematic diagram three of the invention；
Fig. 6 is the cross-sectional view of surge bunker；
Fig. 7 is the schematic perspective view of unmanned plane；
Description of symbols: dish type fender bracket 1, notch 1a, fixed strip 1b, support arm 1c, anti-striker 2, surge bunker 2a delay
Arm 2b, extension arm 2c, buffer board 2d, buffer bar 2e, buffering wheel 2f are rushed, bar 2g is touched, triggers inductor 2h, shock absorber part 3, damping
Block 3a, cruciform groove 3b, damping spring 3c, cross sliding block 3d, attachment base 4, unmanned plane 5, wing 5a, undercarriage 5b are micro-
Type adjusts fan 6.
Specific embodiment
With reference to the accompanying drawings of the specification and embodiment, specific embodiments of the present invention are described in further detail:
A kind of unmanned plane impact protector equipment shown in referring to Figure 1 to Figure 7, including can by the fuselage of unmanned plane 5 and
What the dish type fender bracket 1 and at least four that all wing 5a are wrapped up successively were arranged along the clockwise direction of the fuselage of unmanned plane 5
Anti- striker 2, all anti-strikers 2 are connect by a shock absorber part 3 with dish type fender bracket 1, and the bottom of dish type fender bracket 1, which is equipped with, to be supplied
The undercarriage 5b of unmanned plane 5 can exposed notch 1a, the fuselage roof of unmanned plane 5 is fixed with attachment base 4, and dish type is protected
The top of retaining frame 1, which is equipped with, to be buffered with the bolted support arm 1c of attachment base 4, anti-striker 2 including surge bunker 2a, setting
Triggering inductor 2h in the 2a of storehouse and the idler wheel part being arranged in outside surge bunker 2a, the bottom of dish type fender bracket 1 is equipped with several micro-
Type adjusts fan 6.
All shock absorber parts 3 include that one end of damping block 3a and cross sliding block 3d, damping block 3a and dish type are protected
The outer peripheral surface of frame 1 is fixedly connected, and the other end offers cruciform groove 3b, and cross sliding block 3d movable can be arranged in cross
In type groove 3b, and four ends of cross sliding block 3d pass through the interior of a damping spring 3c and cruciform groove 3b respectively
Wall elastic connection, after anti-striker 2 collides with the external world, impact force is by cross sliding block 3d by damping spring 3c cross
Irregularly shaken in groove 3b and to buffer.
One end of all surge bunker 2a is connect with all cross sliding block 3d correspondingly respectively, and all slow
The other end for rushing storehouse 2a is open setting, and surge bunker 2a gives cross sliding block 3d to transmit extraneous impact force.
The orlop in surge bunker 2a is arranged in the triggering inductor 2h, is equipped with buffer arm 2b, buffer arm in surge bunker 2a
One end of 2b is hinged by torsional spring and the roof in surge bunker 2a, and buffer arm 2b is hollow structure, in the free end of buffer arm 2b
Movable can be inserted with extension arm 2c, be additionally provided in surge bunker 2a can horizontally toward its open-mouth sliding buffer board 2d,
The one end of extension arm 2c far from buffer arm 2b is connect with the top of buffer board 2d, and the one end extension arm 2c is with buffer board 2d's
Top can level be slidably matched, illustrate: under normal conditions, buffer arm 2b and extension arm 2c make buffer board 2d close to slow to torsional spring
Rush storehouse 2a opening one end be it is a large amount of exposed in the external world, then exposed part is taking the lead in contacting extraneous buildings, also
It is that receiving impact force, the impact force make buffer board 2d in surge bunker 2a by buffer arm 2b with extension arm 2c at first
Horizontal movement, extension arm 2c and the cooperation of buffer board 2d top slide give the movement travel of buffer board 2d, and subsequently through
Torsional spring, buffer board 2d can continue to reset, make its front end largely continue it is exposed outside.
All idler wheel parts are located at the front end buffer board 2d in respective position surge bunker 2a, and idler wheel part includes two
Buffer bar 2e, two buffer bar 2e are in that horizontal and the two the same end is fixedly connected with buffer board 2d, two buffer bar 2e
The other end is hinged with a buffering wheel 2f, due to end in contact external world buildings before buffer board 2d, preferentially uses buffering wheel 2f,
By buffering wheel 2f rotation, alleviate part impact force.
All buffer board 2d are equipped with a touching bar 2g far from one end of respective position surge bunker 2a open-mouth, delay
Punching 2d is by the movement of external impact power, and touching bar 2g connected to it is moved therewith, and its end can contradict triggering
In the induction end of inductor 2h.
Be symmetrically arranged at the notch 1a two can respectively with the bolted fixed strip 1b of undercarriage 5b, dish type protection
Frame 1 is cell structure, and fixed strip 1b is for cooperating support arm 1c to be detachably connected dish type fender bracket 1 and unmanned plane 5, just
In subsequent maintenance and maintenance, and it is plastic construction that dish type fender bracket 1 is whole, so cooperation fixed strip 1b is installed
When, it opposite can move, fixed strip 1b is connect by bolt with undercarriage 5b.
All miniature adjustment fans 6 are successively arranged along the clockwise direction of fuselage, and all miniature adjustment fans 6
It is corresponded respectively with all surge bunker 2a, when the buffering wheel 2f outside a surge bunker 2a in 1 outside of dish type fender bracket strikes
After barrier, miniature adjustment fan 6 corresponding with surge bunker 2a is started turning, with this come compensate due to hit after, relatively
The rolling power of the impingement position other end, that is, hit part and shake upward, the other end shakes downward.
Working principle: by the control hand of all triggering inductor 2h and all miniature adjustment fans 6 and multi-rotor unmanned aerial vehicle 5
Handle connection, control handle is interior to be equipped with wireless module and control mainboard, and then multi-rotor unmanned aerial vehicle 5 is flown, barrier to be contacted
After hindering object, 1 preferential contact barrier of dish type fender bracket, and the buffering wheel 2f of some surge bunker 2a by opposite Obstacle Position
Barrier, then buffering wheel 2f rotation are contradicted, release portion divides frictional impact, and the impact force makes buffer board 2d by extension
Arm 2c and buffer arm 2b carries out horizontal movement in surge bunker 2a, that is, towards the triggering inductor side 2h in surge bunker 2a
To, and the touching bar 2g of buffer board 2d can touch the induction end of triggering inductor 2h, and signal passes in control handle
Wireless module, then corresponding with the triggering inductor 2h miniature adjustment wind of control is carried out by the control mainboard in control handle
Fan 6 works, which can adjust in advance to 5S-8S, is caused with this to compensate unmanned plane 5 since shock is too quickly
It is unbalance, and buffer board 2d in surge bunker 2a due to hitting in dynamics movement, cross sliding block 3d cooperates damping spring 3c
Alleviated in cruciform groove 3b, greatly reduces influence of the impact force to unmanned plane 5.
The above described is only a preferred embodiment of the present invention, not making any limit to technical scope of the invention
System, therefore any subtle modifications, equivalent variations and modifications to the above embodiments according to the technical essence of the invention,
In the range of still falling within technical solution of the present invention.
Claims (7)
1. a kind of unmanned plane impact protector equipment, it is characterised in that: including can be by the fuselage and all wings of unmanned plane (5)
The dish type fender bracket (1) and at least four that (5a) is wrapped up successively are arranged along the clockwise direction of the fuselage of unmanned plane (5) anti-
Striker (2), all anti-strikers (2) are connect by a shock absorber part (3) with dish type fender bracket (1), the bottom of dish type fender bracket (1)
Portion be equipped with for unmanned plane (5) undercarriage (5b) can exposed notch (1a), unmanned plane (5) fuselage roof fixation sets
Have attachment base (4), the top of dish type fender bracket (1) is equipped with can be with attachment base (4) bolted support arm (1c), anti-striker
It (2) include that surge bunker (2a), the triggering inductor (2h) being arranged in surge bunker (2a) and setting are external in surge bunker (2a)
The bottom of idler wheel part, dish type fender bracket (1) is equipped with several miniature adjustment fans (6)；
All shock absorber parts (3) include damping block (3a) and cross sliding block (3d), one end of damping block (3a) and dish type
The outer peripheral surface of fender bracket (1) is fixedly connected, and the other end offers cruciform groove (3b), and cross sliding block (3d) can be movable
Setting in the cruciform groove (3b), and four ends of cross sliding block (3d) pass through respectively a damping spring (3c) with
The inner wall elastic connection of cruciform groove (3b).
2. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that: all surge bunkers (2a)
One end connect correspondingly with all cross sliding blocks (3d) respectively, and the other end of all surge bunkers (2a) is spacious
Mouth setting.
3. a kind of unmanned plane impact protector equipment according to claim 2, it is characterised in that: the triggering inductor (2h)
Orlop in surge bunker (2a) is set, is equipped with buffer arm (2b) in surge bunker (2a), one end of buffer arm (2b) passes through torsional spring
Hinged with the roof in surge bunker (2a), buffer arm (2b) is hollow structure, can be movable in the free end of buffer arm (2b)
It is inserted with extension arm (2c), the buffer board (2d) for capableing of horizontally toward its open-mouth sliding is additionally provided in surge bunker (2a), is extended
Arm (2c) is connect far from the one end of buffer arm (2b) with the top of buffer board (2d), and the one end extension arm (2c) and buffer board
The top of (2d) can level be slidably matched.
4. a kind of unmanned plane impact protector equipment according to claim 3, it is characterised in that: all idler wheel part difference
Front end buffer board (2d) in respective position surge bunker (2a), idler wheel part include two buffer bars (2e), two buffer bars
(2e) is fixedly connected with buffer board (2d) in horizontal and the two the same end, and two buffer bar (2e) other ends are hinged with
One buffering wheel (2f).
5. a kind of unmanned plane impact protector equipment according to claim 4, it is characterised in that: all buffer boards (2d)
One end far from respective position surge bunker (2a) open-mouth is equipped with a touching bar (2g).
6. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that: symmetrical at the notch (1a)
If dish type fender bracket (1) is cell structure there are two can be respectively with undercarriage (5b) bolted fixed strip (1b).
7. a kind of unmanned plane impact protector equipment according to claim 1, it is characterised in that: all miniature adjustment wind
Fan (6) successively along fuselage clockwise direction arrange, and all miniature adjustment fans (6) respectively with all surge bunkers (2a) one
One is corresponding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383742.5A CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810383742.5A CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
Publications (2)
| Publication Number | Publication Date |
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| CN108622426A CN108622426A (en) | 2018-10-09 |
| CN108622426B true CN108622426B (en) | 2019-11-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810383742.5A Active CN108622426B (en) | 2018-04-26 | 2018-04-26 | A kind of unmanned plane impact protector equipment |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110015419A (en) * | 2019-04-18 | 2019-07-16 | 广州供电局有限公司 | Distribution network cable corridor inspection device |
| CN113650778B (en) * | 2021-09-02 | 2023-07-21 | 浙江图盛输变电工程有限公司温州科技分公司 | Power grid inspection unmanned aerial vehicle adapting to complex environment |
| CN113734431B (en) * | 2021-09-24 | 2023-09-01 | 南京拓恒无人系统研究院有限公司 | Unmanned aerial vehicle anti-collision structure and application method thereof |
| CN114044153B (en) * | 2022-01-11 | 2022-03-15 | 云奕智创航空科技(南通)有限公司 | A special anticollision locking equipment for unmanned aerial vehicle transportation |
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