CN110001979A - A kind of unmanned vehicle for the anti-crash that can quickly rise - Google Patents
A kind of unmanned vehicle for the anti-crash that can quickly rise Download PDFInfo
- Publication number
- CN110001979A CN110001979A CN201910273597.XA CN201910273597A CN110001979A CN 110001979 A CN110001979 A CN 110001979A CN 201910273597 A CN201910273597 A CN 201910273597A CN 110001979 A CN110001979 A CN 110001979A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- crash
- unmanned vehicle
- gasbag
- quickly rise
- 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.)
- Withdrawn
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 24
- 239000002184 metal Substances 0.000 claims abstract description 11
- 229910052751 metal Inorganic materials 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 238000001179 sorption measurement Methods 0.000 claims description 11
- 230000000694 effects Effects 0.000 claims description 7
- 230000005389 magnetism Effects 0.000 claims description 6
- SZVJSHCCFOBDDC-UHFFFAOYSA-N iron(II,III) oxide Inorganic materials O=[Fe]O[Fe]O[Fe]=O SZVJSHCCFOBDDC-UHFFFAOYSA-N 0.000 claims description 5
- 239000003292 glue Substances 0.000 claims description 3
- 206010030110 Oedema mouth Diseases 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 206010057071 Rectal tenesmus Diseases 0.000 abstract description 2
- 208000012271 tenesmus Diseases 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 230000003139 buffering effect Effects 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000005273 aeration Methods 0.000 description 2
- 238000013016 damping Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 230000035699 permeability Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000010338 mechanical breakdown Methods 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses the unmanned vehicles for the anti-crash that one kind can quickly rise, including fuselage, wing, airflow hole, buoyant device and plugging mechanism, the equidistant surrounding for being mounted on fuselage of the wing, the airflow hole is provided with the two sides of fuselage roof respectively, the buoyant device is mounted on the two sides of fuselage inner cavity, and the inner cavity of airflow hole is arranged in the plugging mechanism；Buoyant device includes gasbag, traction rope, sheet metal and cutting-off mechanism, one end of the traction rope is fixedly connected with the sealing end of gasbag, the sheet metal is fixedly connected with traction rope far from one end of gasbag, the top of gasbag is arranged in the cutting-off mechanism, the unmanned vehicle of the anti-crash that can quickly rise, flowed backward using the air-flow that unmanned plane itself tenesmus generates versus high motion, the air bag that expanse has been opened stretches the wing for forming two entities outward, the buoyancy of generation can slow down to the machine to fall, unmanned plane is able to maintain balance when being unable to control autonomous travel, reduce the probability of air crash.
Description
Technical field
The present invention relates to air vehicle technique field, specially a kind of unmanned vehicle for the anti-crash that can quickly rise.
Background technique
In the past few years, with the continuous development of science and technology and electronic technology, unmanned air vehicle technique has also obtained very big hair
Exhibition, is gradually developed to by military unmanned air vehicle commercial and civilian, and small drone has been also applied to each production and living
Field suffers, and has also appeared a large amount of intelligent and multi-functional unmanned vehicles, primarily serves transmitting information and detection
Effect, unmanned vehicle have the advantages that flexibly, reaction is fast, unmanned flight and operating technology require it is relatively low, its own
It is the new concept aircraft in rapidly developing, is also increasingly taken seriously, described unmanned plane refers to family mostly instantly
Outer sporting a kind of electronic equipment, this class of electronic devices are usually to have certain flight control range, pass through wireless signal
It is controlled, with the continuous development and progress of unmanned plane, the data of flying distance and flying height are also increasing.
Currently, the flying distance and flying height of most of unmanned vehicle have the upper limit, and daily institute
The unmanned vehicle used is to use battery to provide power for it, so cruising ability is also to limit unmanned plane performance
A key factor, after runawaying, unmanned plane will have a risk of breaking-up, and high-altitude flight when
It waits, aerial environment is also complex, has more complicated air-flow, floating material and flying bird etc., is all to influence whether unmanned plane
Flight, when unmanned plane uses up in high aerial electricity, it is high in the air by hit occur mechanical breakdown or unmanned plane during flying away from
From too far and it is excessively high in the case where departing from remote control control range will cause unmanned vehicle occur air crash accident.
If Chinese patent discloses " a kind of anti-crash unmanned plane " (patent No.: CN107097961A), which includes nothing
Man-machine, air bag, catapult-launching gear, parachute, controller, acceleration transducer install landing at the unmanned plane top center
Pack, above-mentioned technical solution mainly pop up parachute by catapult-launching gear, reduce the decrease speed of unmanned plane, gas generator
Gas is generated, and delivers gas to air bag, air bag expands, and plays buffer function in unmanned plane landing, protects nobody
Machine is added to various although above-mentioned technical solution can play the role of fall-retarding buffering in unmanned vehicle
Device, the production cost on the one hand increasing aircraft are not suitable for being popularized, and on the other hand increase the whole of unmanned vehicle
Weight, not only will affect the flight of aircraft, and also add the energy consumption of aircraft, at the same be detached from remote range with
And it not can guarantee various devices at all in the case where power-off and can operate normally.
Summary of the invention
(1) the technical issues of solving
In view of the deficiencies of the prior art, the unmanned vehicle for the anti-crash that can quickly rise the present invention provides one kind, solves
Unmanned vehicle breaks down in the sky has landing or air crash damage.
(2) technical solution
In order to achieve the above object, the present invention is achieved by the following technical programs: the nothing for the anti-crash that one kind can quickly rise
People's aircraft, including fuselage, wing, airflow hole, buoyant device and plugging mechanism, the wing is equidistant to be mounted on the four of fuselage
Week, the airflow hole are provided with the two sides of fuselage roof respectively, and the buoyant device is mounted on the two sides of fuselage inner cavity, the envelope
The inner cavity of airflow hole is arranged in stifled mechanism.
Buoyant device includes gasbag, traction rope, sheet metal and cutting-off mechanism, and the port section of the gasbag passes through glue
Hydropexis is mounted on the two sides of fuselage inner cavity, and one end of the traction rope is fixedly connected with the sealing end of gasbag, the metal
Piece is fixedly connected with traction rope far from one end of gasbag, and the top of gasbag is arranged in the cutting-off mechanism.
Preferably, the plugging mechanism includes electromagnet, plugging block, flow deflector, smooth rail, reset spring and magnetic adsorption plate,
The electromagnet is fixedly mounted on the inner wall of fuselage by screw, and the top of the smooth rail and the inner wall of fuselage pass through bolt
It is fixedly connected, the plugging block is movably arranged between two smooth rails by protrusion, and the flow deflector is fixedly mounted on closure
The side of block, the reset spring are fixedly mounted on the left side of plugging block, and the magnetic adsorption plate is fixedly bonded to the right side of plugging block.
Preferably, the cutting-off mechanism includes by means of power plate, truncation piece, propelling spring and positioning ring, the top by means of power plate
The inner wall of portion and fuselage is fixedly welded, and the positioning ring is fixedly mounted on the right side by means of power plate, the truncation piece activity clamping
Bottom on the left of the inner cavity of positioning ring, the truncation piece is fixedly welded with positive stop strip, and the propelling spring is socketed in positive stop strip
Outer ring.
Preferably, the two sides of the fuselage offer expansion hatch, and cutout is offered above the expansion hatch, described
Vertical cassette is fixedly welded with above expansion hatch.
Preferably, the opposite side of the wing is fixedly installed with magnetite block, and the middle part of the fuselage roof two sides is passed through
It wears and is connected with fixing bolt.
Preferably, the piecemeal activity that the truncation piece is located at fuselage outer side is connected to the inner cavity of vertical cassette, the truncation piece
Side far from fuselage is fixedly connected with sliding piece, and the surface of the truncation piece is equidistant to offer location hole.
Preferably, be fixedly connected at the top of the bottom of the propelling spring and positive stop strip, the top of the propelling spring with
It is fixedly connected by means of the bottom of power plate.
Preferably, it is identical to generate magnetic magnetic pole for the magnetism of the magnetic adsorption plate and electromagnet, the length of the plugging block with
Width is all larger than the length and width of airflow hole.
(3) beneficial effect
The present invention provides the unmanned vehicles for the anti-crash that one kind can quickly rise.Have it is following the utility model has the advantages that
(1), the unmanned vehicle of the anti-crash that can quickly rise is dropped using unmanned plane itself and generates versus high motion
Air-flow is flowed backward, come with this so that air bag expansion protrude outward, increase the surface area of unmanned plane, the buoyancy of generation can be right
The machine to fall slows down.
(2), the unmanned vehicle of the anti-crash that can quickly rise, the use of aeration position can be closed to be set with penetrating
Meter, sealing state when can carry out guiding to the gas poured into allows air bag expansion to increase buoyancy, keeps permeability status
When, can ascent stage keep air-flow unimpeded reduction unmanned plane air drag, uphill process can faster, energy consumption
It is lower.
(3), the unmanned vehicle of the anti-crash that can quickly rise, air bag use since internal inflation up to prolonging
The outside for extending to unmanned body, the part on the outside of body can increase whole surface area and increase buoyancy, be in unmanned plane
Internal cavity segment after inflation, can provide good damping and buffering when air crash for the components of inner cavity, avoid
Internal component is impaired, and shell will not be occurred excessive deformation by impact and squeeze inside when being mainly reflected in air crash
Components.
(4), the unmanned vehicle of the anti-crash that can quickly rise, the air bag that expanse has been opened stretch to be formed outward
The wing of two entities, can carry out simulation gliding flight in the case where there is wind, and unmanned plane is being unable to control autonomous travel
When be able to maintain balance, reduce the probability of air crash.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is plugging block side view of the present invention；
Fig. 3 is fuselage cross-sectional view of the present invention；
Fig. 4 is gasbag top view of the present invention.
In figure: 1 fuselage, 101 expansion hatches, 102 cutouts, 103 vertical cassettes, 104 fixing bolts, 2 wings, 201 magnetite blocks, 3
Power plate, 4042 sections are borrowed in airflow hole, 4 buoyant devices, 401 gasbags, 402 traction ropes, 403 sheet metals, 404 cutting-off mechanisms, 4041
Part, 4043 propelling springs, 4044 positioning rings, 4045 positive stop strips, 4046 sliding pieces, 4047 location holes, 5 plugging mechanisms, 501 electricity
Magnet, 502 plugging blocks, 503 flow deflectors, 504 smooth rails, 505 reset springs, 506 magnetic adsorption plates.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, can also can be in two elements indirectly connected through an intermediary
The interaction relationship of the connection in portion or two elements.It for the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
Fig. 1-4 is please referred to, the present invention provides a kind of technical solution: the unmanned flight for the anti-crash that one kind can quickly rise
Device, including fuselage 1, wing 2, airflow hole 3, buoyant device 4 and plugging mechanism 5, the equidistant surrounding for being mounted on fuselage 1 of wing 2,
Airflow hole 3 is provided with the two sides at 1 top of fuselage respectively, and buoyant device 4 is mounted on the two sides of 1 inner cavity of fuselage, and plugging mechanism 5 is arranged
In the inner cavity of airflow hole 3, the two sides of fuselage 1 offer expansion hatch 101, and the top of expansion hatch 101 offers cutout 102,
The top of expansion hatch 102 is fixedly welded with vertical cassette 103, and the opposite side of wing 2 is fixedly installed with magnetite block 201, and fuselage 1 pushes up
The middle part of portion two sides, which is run through, is connected with fixing bolt 104, plugging mechanism 5 include electromagnet 501, plugging block 502, flow deflector 503,
Smooth rail 504, reset spring 505 and magnetic adsorption plate 506, electromagnet 501 are fixedly mounted on the inner wall of fuselage 1 by screw, are put down
The top of sliding rail 504 and the inner wall of fuselage 1 are bolted to connection, and plugging block 502 is movably arranged on two by protrusion and puts down
Between sliding rail 504, flow deflector 503 is fixedly mounted on the side of plugging block 502, and reset spring 505 is fixedly mounted on plugging block 502
Left side, magnetic adsorption plate 506 is fixedly bonded to the right side of plugging block 502, and magnetism and the electromagnet 501 of magnetic adsorption plate 506 generate magnetism
Magnetic pole it is identical, the length and width of plugging block 502 is all larger than the length and width of airflow hole 3, and buoyant device 4 includes gasbag
401, traction rope 402, sheet metal 403 and cutting-off mechanism 404, the port section of gasbag 401 are fixedly mounted on machine by glue
One end of the two sides of 1 inner cavity of body, traction rope 402 is fixedly connected with the sealing end of gasbag 401, sheet metal 403 and traction rope 402
One end far from gasbag 401 is fixedly connected, and the top of gasbag 401 is arranged in cutting-off mechanism 404, and cutting-off mechanism 404 includes
By means of power plate 4041, truncation piece 4042, propelling spring 4043 and positioning ring 4044, the inner wall at top and fuselage 1 by means of power plate 4041
It is fixedly welded, positioning ring 4044 is fixedly mounted on the right side by means of power plate 4041, and truncation 4042 activity of piece is connected to positioning ring
The bottom of 4044 inner cavity, 4042 left side of truncation piece is fixedly welded with positive stop strip 4045, and propelling spring 4043 is socketed in positive stop strip
4045 outer ring, the piecemeal activity that truncation piece 4042 is located at 1 outside of fuselage are connected to the inner cavity of vertical cassette 103, piece 4042 are truncated
Side far from fuselage 1 is fixedly connected with sliding piece 4046, and the surface of truncation piece 4042 is equidistant to offer location hole 4047, pushes away
It is fixedly connected into the bottom of spring 4043 with the top of positive stop strip 4045, the top of propelling spring 4043 and the bottom for borrowing power plate 4041
Portion is fixedly connected.
When (or when using) the unmanned vehicle work of the anti-crash that can quickly rise, start unmanned plane first, nobody
After component inside machine is powered, electromagnet 501 also powers on, and electromagnet 501 becomes the stronger magnetic of band after being powered
The magnetic patch of property, electromagnet 501 is identical as the side magnetic pole that magnetic adsorption plate 506 is opposite, in this way, which electromagnet 501 is powering on
During be in the movement for push away magnetic adsorption plate 506 itself, with this act progress, plugging block 502 also by
Gradually mobile up to reset spring 505 is compressed into extreme position, plugging block 502 at this time will be directly by airflow hole blocking portion
It exposes, the top and bottom of fuselage 1 are in the state communicated, and the movement of plugging block 502 also drives flow deflector 503 to transport
Dynamic, when extreme position, flow deflector directly blocks the opening of gasbag 401, avoids air from pouring into, at this time airflow hole
It is transparent, it can accomplish to reduce air drag during unmanned plane rises, accelerate soaring speed, the same day encounters electricity
When amount exhausts or unmanned plane breaks down, multiple propellers stop working, and de-energizing actions also can directly occur for unmanned plane,
With the generation of de-energizing actions, electromagnet 501 goes magnetism when powering off, it is multiple that reset spring 505 pushes directly on plugging block 502
Position, flow deflector 503 at this time also expose the port section of gasbag 401, and the unmanned plane of power-off is during decline, greatly
The air of amount pours into the inner cavity of fuselage 1 via airflow hole 3, since the airflow hole 3 of upper end is blocked by plugging block, the sky poured at this time
Gas will enter directly into the inner cavity of gasbag 401, and air bag ancient times are poured into air and expanded and along expansion hatch later
101 are stretched over the outside of fuselage 1, and traction rope 402 and sheet metal 403 also float on the outside, and sheet metal 403 at this time is subject to
The attraction of magnetite block 201 adheres to, and gasbag 401 will tile and come, as the air that pours into of continuing to fall of unmanned plane is more next
More, gasbag 401 continues expansion until press fixing bolt 104, forces it to be separated from each other with location hole 4047, propelling spring
4043 will direct pull truncation piece 4042 move down and press gasbag 401, one end is squeezed and is fastened, air bag at this time
Biggish surface area is formed between bag 401 exterior portions tiling expansion and wing 2, the part positioned at 1 inner cavity of fuselage will be pressed
Contracting is in the inner cavity of fuselage 1.
In conclusion the unmanned vehicle of the anti-crash that can quickly rise, is generated opposite using unmanned plane itself tenesmus
The air-flow of high-speed motion is flowed backward, come with this so that air bag expansion protrude outward, increase the surface area of unmanned plane, generation
Buoyancy can slow down to the machine to fall, aeration position using can be closed with penetrating design, sealing state when
Time can carry out guiding to the gas poured into allows air bag expansion to increase buoyancy, when keeping permeability status, can rise
Stage keeps the air drag of the unimpeded reduction unmanned plane of air-flow, uphill process can faster, energy consumption it is lower, air bag is used from interior
Portion starts inflation until extending to the outside of unmanned body, the part on the outside of body can increase whole surface area
Increase buoyancy, after inflation in cavity segment in unmanned plane body, can be provided very for the components of inner cavity when air crash
Good damping and buffering avoids internal component impaired, and shell will not be occurred by impact when being mainly reflected in air crash
Excessive deformation and squeeze internal components, the air bag that expanse has been opened stretch the wing of two entities of formation outward,
Simulation gliding flight can be carried out in the case where there is wind, and unmanned plane is able to maintain flat when being unable to control autonomous travel
Weighing apparatus, reduces the probability of air crash.
The foregoing is only a preferred embodiment of the present invention, but scope of protection of the present invention is not limited thereto,
Anyone skilled in the art in the technical scope disclosed by the present invention, according to the technique and scheme of the present invention and its
Inventive concept is subject to equivalent substitution or change, should be covered by the protection scope of the present invention.
Claims (8)
1. the unmanned vehicle for the anti-crash that one kind can quickly rise, it is characterised in that: including fuselage (1), wing (2), air-flow
Hole (3), buoyant device (4) and plugging mechanism (5), the equidistant surrounding for being mounted on fuselage (1) of wing (2), the air-flow
Hole (3) is provided with the two sides at the top of fuselage (1) respectively, and the buoyant device (4) is mounted on the two sides of fuselage (1) inner cavity, described
Plugging mechanism (5) is arranged in the inner cavity of airflow hole (3)；
Buoyant device (4) includes gasbag (401), traction rope (402), sheet metal (403) and cutting-off mechanism (404), the gas
The port section of pouch (401) is fixedly mounted on the two sides of fuselage (1) inner cavity, one end of the traction rope (402) by glue
Be fixedly connected with the sealing end of gasbag (401), the sheet metal (403) and traction rope (402) far from gasbag (401) one
End is fixedly connected, top of cutting-off mechanism (404) setting in gasbag (401).
2. the unmanned vehicle for the anti-crash that one kind according to claim 1 can quickly rise, it is characterised in that: the envelope
Stifled mechanism (5) include electromagnet (501), plugging block (502), flow deflector (503), smooth rail (504), reset spring (505) and
Magnetic adsorption plate (506), the electromagnet (501) are fixedly mounted on the inner wall of fuselage (1) by screw, the smooth rail (504)
Top and the inner wall of fuselage (1) be bolted to connection, the plugging block (502) by protrusion be movably arranged on two it is flat
Between sliding rail (504), the flow deflector (503) is fixedly mounted on the side of plugging block (502), and the reset spring (505) is solid
Dingan County is mounted in the left side of plugging block (502), and the magnetic adsorption plate (506) is fixedly bonded to the right side of plugging block (502).
3. the unmanned vehicle for the anti-crash that one kind according to claim 1 can quickly rise, it is characterised in that: described section
Breaking mechanism (404) includes by means of power plate (4041), piece (4042), propelling spring (4043) and positioning ring (4044) is truncated, described to borrow
The top of power plate (4041) and the inner wall of fuselage (1) are fixedly welded, and the positioning ring (4044) is fixedly mounted on by means of power plate
(4041) right side, described truncation piece (4042) activity are connected to the inner cavity of positioning ring (4044), the truncation piece (4042)
The bottom in left side is fixedly welded with positive stop strip (4045), and the propelling spring (4043) is socketed in the outer ring of positive stop strip (4045).
4. the unmanned vehicle for the anti-crash that one kind according to claim 1 can quickly rise, it is characterised in that: the machine
The two sides of body (1) offer expansion hatch (101), offer cutout (102) above the expansion hatch (101), described swollen
Vertical cassette (103) are fixedly welded with above swollen mouth (102).
5. the unmanned vehicle for the anti-crash that one kind according to claim 1 can quickly rise, it is characterised in that: the machine
The opposite side of the wing (2) is fixedly installed with magnetite block (201), and the middle part of two sides, which is run through, at the top of the fuselage (1) is connected with admittedly
Determine bolt (104).
6. the unmanned vehicle for the anti-crash that one kind according to claim 3 can quickly rise, it is characterised in that: described section
The piecemeal activity that part (4042) is located on the outside of fuselage (1) is connected to the inner cavity of vertical cassette (103), and the truncation piece (4042) is remote
The disembark side of body (1) is fixedly connected with sliding piece (4046), and the surface of truncation piece (4042) is equidistant to offer positioning
Hole (4047).
7. the unmanned vehicle for the anti-crash that one kind according to claim 3 can quickly rise, it is characterised in that: described to push away
Be fixedly connected at the top of into the bottom and positive stop strip (4045) of spring (4043), the top of the propelling spring (4043) with borrow power
The bottom of plate (4041) is fixedly connected.
8. the unmanned vehicle for the anti-crash that one kind according to claim 2 can quickly rise, it is characterised in that: the magnetic
The magnetism of suction piece (506) is identical as the magnetic pole that electromagnet (501) generate magnetism, and the length and width of the plugging block (502) is equal
Greater than the length and width of airflow hole (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910273597.XA CN110001979A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned vehicle for the anti-crash that can quickly rise |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910273597.XA CN110001979A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned vehicle for the anti-crash that can quickly rise |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110001979A true CN110001979A (en) | 2019-07-12 |
Family
ID=67170117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910273597.XA Withdrawn CN110001979A (en) | 2019-04-06 | 2019-04-06 | A kind of unmanned vehicle for the anti-crash that can quickly rise |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110001979A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588998A (en) * | 2019-08-14 | 2019-12-20 | 国网安徽省电力有限公司检修分公司 | Prevent weighing down unmanned aerial vehicle |
| CN110920887A (en) * | 2019-11-28 | 2020-03-27 | 航天时代飞鸿技术有限公司 | Autonomous water-landing detection and safety protection system and method for small unmanned aerial vehicle |
| CN111661335A (en) * | 2020-06-24 | 2020-09-15 | 王振清 | Self-stabilizing agricultural unmanned aerial vehicle |
| CN112550729A (en) * | 2021-02-23 | 2021-03-26 | 成都飞航智云科技有限公司 | Aircraft with pneumatic appearance is impaired later to prevent weighing down function |
| CN112776983A (en) * | 2021-03-01 | 2021-05-11 | 赵堇涵 | Unmanned aerial vehicle terrain detection device for aerospace |
| CN115214888A (en) * | 2022-08-18 | 2022-10-21 | 江苏英拓动力科技有限公司 | Hybrid power driven unmanned aerial vehicle |
| CN116002068A (en) * | 2023-03-22 | 2023-04-25 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Impact water-entering sliding track of water high-speed dragging system and design and use method thereof |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180022310A1 (en) * | 2016-03-24 | 2018-01-25 | Rhombus Systems Group, Inc. | Airbag system for use with unmanned aerial vehicles |
| CN206984324U (en) * | 2017-07-18 | 2018-02-09 | 昊翔电能运动科技(昆山)有限公司 | Rotor wing unmanned aerial vehicle |
| CN108058835A (en) * | 2017-12-20 | 2018-05-22 | 郑州康晓科技有限公司 | Unmanned plane fortuitous event fall arrest damages device |
| US10137986B1 (en) * | 2015-03-25 | 2018-11-27 | Amazon Technologies, Inc. | Airlift package protection airbag container |
| CN109272600A (en) * | 2018-08-30 | 2019-01-25 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane cloud black box subsystem and its auxiliary device based on big data |
-
2019
- 2019-04-06 CN CN201910273597.XA patent/CN110001979A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10137986B1 (en) * | 2015-03-25 | 2018-11-27 | Amazon Technologies, Inc. | Airlift package protection airbag container |
| US20180022310A1 (en) * | 2016-03-24 | 2018-01-25 | Rhombus Systems Group, Inc. | Airbag system for use with unmanned aerial vehicles |
| CN206984324U (en) * | 2017-07-18 | 2018-02-09 | 昊翔电能运动科技(昆山)有限公司 | Rotor wing unmanned aerial vehicle |
| CN108058835A (en) * | 2017-12-20 | 2018-05-22 | 郑州康晓科技有限公司 | Unmanned plane fortuitous event fall arrest damages device |
| CN109272600A (en) * | 2018-08-30 | 2019-01-25 | 芜湖翼讯飞行智能装备有限公司 | A kind of unmanned plane cloud black box subsystem and its auxiliary device based on big data |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588998A (en) * | 2019-08-14 | 2019-12-20 | 国网安徽省电力有限公司检修分公司 | Prevent weighing down unmanned aerial vehicle |
| CN110920887A (en) * | 2019-11-28 | 2020-03-27 | 航天时代飞鸿技术有限公司 | Autonomous water-landing detection and safety protection system and method for small unmanned aerial vehicle |
| CN111661335A (en) * | 2020-06-24 | 2020-09-15 | 王振清 | Self-stabilizing agricultural unmanned aerial vehicle |
| CN111661335B (en) * | 2020-06-24 | 2024-06-07 | 中开丝路生态产业集团有限公司 | Self-stabilizing type agricultural unmanned aerial vehicle |
| CN112550729A (en) * | 2021-02-23 | 2021-03-26 | 成都飞航智云科技有限公司 | Aircraft with pneumatic appearance is impaired later to prevent weighing down function |
| CN112776983A (en) * | 2021-03-01 | 2021-05-11 | 赵堇涵 | Unmanned aerial vehicle terrain detection device for aerospace |
| CN115214888A (en) * | 2022-08-18 | 2022-10-21 | 江苏英拓动力科技有限公司 | Hybrid power driven unmanned aerial vehicle |
| CN115214888B (en) * | 2022-08-18 | 2024-06-11 | 江苏英拓动力科技有限公司 | Hybrid power driven unmanned aerial vehicle |
| CN116002068A (en) * | 2023-03-22 | 2023-04-25 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Impact water-entering sliding track of water high-speed dragging system and design and use method thereof |
| CN116002068B (en) * | 2023-03-22 | 2023-05-26 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Impact water-entering sliding track of water high-speed dragging system and design and use method thereof |
| CN117885923A (en) * | 2024-03-14 | 2024-04-16 | 航大汉来（天津）航空技术有限公司 | Long-endurance patrol unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110001979A (en) | A kind of unmanned vehicle for the anti-crash that can quickly rise | |
| US8910903B2 (en) | Aircraft generating a lift from an interior thereof | |
| CN201678037U (en) | Natural power levitation platform | |
| CN204776011U (en) | Many rotor unmanned aerial vehicle that can entry | |
| EP2760739A1 (en) | An unmanned aerial vehicle | |
| CN109760848B (en) | Unmanned aerial vehicle descends unmanned ship and uses anti-skidding locking mechanical system | |
| CN107364575A (en) | A kind of flapping wing aircraft | |
| CN108482685A (en) | Unmanned plane recovery system, unmanned plane and recovery method | |
| JP2011255892A (en) | Fluid machine using parallel rotary wing | |
| CN103991549A (en) | High-intensity rotary ornithopter | |
| CN101973395A (en) | Electric anti-collision safety unmanned helicopter | |
| CN104787331B (en) | Double-wing ornithopter provided with controllable buoyancy wings and power wings and operation method of double-wing ornithopter | |
| CN212313298U (en) | Small-sized solar unmanned aerial vehicle | |
| CN107364576A (en) | One kind vibration rotor aircraft | |
| CN203864997U (en) | High-strength rotary flapping wing air vehicle | |
| CN219133766U (en) | Unmanned aerial vehicle with amphibious tilting rotor | |
| CN206606352U (en) | A kind of strong unmanned plane of endurance | |
| CN109250082A (en) | A kind of multiaxis low latitude manned vehicle | |
| CN212906659U (en) | Parachute landing simulator for parachute landing simulation training | |
| CN104648671A (en) | Manned flying saucer | |
| CN203581383U (en) | Manned flying saucer | |
| CN203845010U (en) | Small ornithopter | |
| CN204056295U (en) | Pneumatic structure four rotor unmanned aircraft | |
| CN210149580U (en) | Composite wing unmanned aerial vehicle stop device | |
| CN201842257U (en) | Electric collision-preventive safe unmanned helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190712 |
|
| WW01 | Invention patent application withdrawn after publication |