CN116750227B - Portable multi-rotor folding unmanned aerial vehicle - Google Patents
Portable multi-rotor folding unmanned aerial vehicle Download PDFInfo
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- CN116750227B CN116750227B CN202310863892.7A CN202310863892A CN116750227B CN 116750227 B CN116750227 B CN 116750227B CN 202310863892 A CN202310863892 A CN 202310863892A CN 116750227 B CN116750227 B CN 116750227B
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- 230000005540 biological transmission Effects 0.000 claims description 23
- 238000010438 heat treatment Methods 0.000 claims description 12
- PXIPVTKHYLBLMZ-UHFFFAOYSA-N Sodium azide Chemical compound [Na+].[N-]=[N+]=[N-] PXIPVTKHYLBLMZ-UHFFFAOYSA-N 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims 2
- 239000013585 weight reducing agent Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 description 19
- 230000008569 process Effects 0.000 description 16
- 239000007789 gas Substances 0.000 description 12
- 230000006378 damage Effects 0.000 description 7
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 230000009471 action Effects 0.000 description 4
- 229910001873 dinitrogen Inorganic materials 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 3
- 208000034656 Contusions Diseases 0.000 description 2
- 230000009519 contusion Effects 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
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- 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
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/30—Constructional aspects of UAVs for safety, e.g. with frangible components
-
- 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
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/299—Rotor guards
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Air Bags (AREA)
Abstract
The invention discloses a portable multi-rotor folding unmanned aerial vehicle, which relates to the technical field of aircrafts and comprises a fuselage shell, wherein a working host is welded at the bottom of the fuselage shell, a supporting foot rest is welded on the surface of the fuselage shell, an organic top cover is welded on the upper surface of the fuselage shell, a supporting foot rest is arranged on the side wall of the fuselage shell, a containing component is arranged in the middle of the fuselage shell, a flying collision sensing component is arranged on the side wall of the fuselage shell, a flying protection component is welded at the bottom of the working host, a plurality of wings can be controlled to synchronously stretch and retract through a knob, the weight of the device is reduced, the portability of the device is improved, the device is easy to carry, the problem that the wings are not completely contracted when being contained by a user, so that the wing is different in unfolding length, the situation that the wing is completely contracted by mistake when being contained is easy to cause collision or broken is avoided, and the endurance time is also improved through weight reduction.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a portable multi-rotor folding unmanned aerial vehicle.
Background
The unmanned aerial vehicle is equipment utilizing radio remote control equipment to operate the motion, can realize the demand in the aspect of daily life and the military industry through the unmanned aerial vehicle, traditional unmanned aerial vehicle structure is complicated, thereby unmanned aerial vehicle's whole weight is heavier, can not accept the instruction in a flexible way when flying and change fly height and flight direction, simultaneously when accomodating unmanned aerial vehicle, because unmanned aerial vehicle wing quantity is many and the structure is accurate, manual operation folding unmanned aerial vehicle wing can make the wing shrink inaccurate, and then lead to each wing position different, can appear simultaneously when accomodating carrying unmanned aerial vehicle, the problem that the wing slides and stretches out, if to touching the rupture that the wing leads to the wing, finally cause equipment damage, can lead to the fuselage unstable because the wind is scraped suddenly in unmanned aerial vehicle motion process, or operating personnel operate inappropriately, make unmanned aerial vehicle collide hard object such as building in the flight process easily, cause unmanned aerial vehicle local or whole damage, and then be difficult to guarantee unmanned aerial vehicle's security and safety landing in the flight process.
Therefore, a portable multi-rotor folding unmanned aerial vehicle is provided.
Disclosure of Invention
The invention aims to provide a portable multi-rotor folding unmanned aerial vehicle so as to solve the problems in the background technology.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides a portable many rotors folding unmanned aerial vehicle, includes the fuselage shell, the bottom welding of fuselage shell has the work host computer, the surface welding of fuselage shell has the support foot rest, the upper surface welding of fuselage shell has the organic top cap, the support foot rest has been seted up to the lateral wall of fuselage shell, the middle part of fuselage shell is provided with the subassembly of accomodating, the lateral wall of fuselage shell is provided with flight collision response subassembly, the bottom welding of work host computer has flight protection subassembly;
the storage assembly comprises a first circular positioning plate, a first sliding groove, a second circular positioning plate, a second sliding groove and a first circular positioning plate, wherein the first circular positioning plate is arranged in the machine body shell;
the flying collision sensing assembly comprises a first collision baffle, a second collision baffle, a transmission block and a spring rod, the flying driver is positioned on the side wall of the machine body shell, the second collision baffle is arranged on the side of the machine body shell, the transmission block is connected in the first collision baffle in a sliding manner, the spring rod is welded on one side, close to the second collision baffle, of the transmission block, the bottom of the spring rod is positioned below the positioning rod, and the spring rod slides in the sensing bin;
the flight protection assembly comprises an inflation reactor, heating wires, an air bag bin and a working host, wherein the inflation reactor is arranged at the bottom of the working host, the heating wires are arranged inside the inflation reactor, and the air bag bin is arranged at the bottom of the working host.
Preferably, the storage assembly comprises a cross sliding groove, a positioning column and a rotating rod, wherein the cross sliding groove is welded at the bottom of an inner cavity of the machine body shell, the positioning column is welded at the bottom of the inner cavity of the machine body shell, and the rotating rod is rotatably connected to the upper surface of the circular positioning plate.
Preferably, the storage assembly further comprises a control console, a ratchet wheel, a rotating pawl, an electromagnet and a knob, wherein the control console is welded on the upper surface of the machine body shell, the ratchet wheel is welded on the outer wall of the rotating rod positioned inside the control console, the rotating pawl is rotationally connected to the bottom of an inner cavity of the control console, the inner side end of the pawl is connected with the ratchet wheel in a clamping mode, the electromagnet is welded on the side wall of the inner cavity of the control console, and the knob is welded on the top of the rotating rod positioned inside the control console.
Preferably, the flying collision sensing assembly further comprises a sliding rod, a guide rod, a positioning rod, a flying driver and a wing, wherein the sliding rod is in sliding connection with the cross sliding groove, the guide rod is welded at one end of the sliding rod, which is positioned inside the body shell, and penetrates through the first sliding groove and the second sliding groove at the same time, the flying driver is fixedly connected with one end, which is far away from the body shell, of the sliding rod, the positioning rod is fixedly connected with the side wall of the flying driver, and the wing is rotationally connected with the top of the flying driver.
Preferably, the flight collision sensing assembly further comprises a limiting plate, a sliding cavity, a third sliding groove, a sensing bin and an electric connection block I, wherein the limiting plate is welded in the inner cavity of the positioning rod, the third sliding groove is formed in the bottom of the positioning rod, the sensing bin is welded on the side wall of the flight driver, the electric connection block I is welded on the side wall of the inner cavity of the sensing bin, and one end, close to the electric connection block I, of the spring rod is provided with electric conductivity.
Preferably, the flight protection assembly further comprises a positioning shell, a connecting rod, an inflating cylinder, a gas transmission hole, a protection negative plate and a second electric connection block, wherein the positioning shell is welded at the bottom of the working host, the connecting rod is welded at the bottom of the positioning shell, the inflating cylinder is welded at the bottom of an inner cavity of the positioning shell, the gas transmission hole is formed in the bottom of the side wall of the inflating cylinder, the protection negative plate is adhered to the lower surface of the connecting rod, and the second electric connection block is arranged on the upper surface of the inner cavity of the inflating cylinder.
Preferably, the heating wire has an electrical connection relation with the second electrical connection block, the gas transmission hole is arranged between the gas bag bin and the gas charging cylinder, the first electrical connection block has an electrical connection relation with the electromagnet, and the first electrical connection block has an electrical connection relation with the second electrical connection block.
Preferably, an airbag is arranged in the airbag cabin, and the material of the inflatable reactor is sodium azide.
Compared with the prior art, the invention has the beneficial effects that:
1. the device has the advantages that the synchronous expansion and contraction of a plurality of wings can be controlled through the knob, the weight of the device is reduced, the portability of the device is improved, the device is easy to carry, the problem that the wing expansion length is different due to the fact that a single wing cannot be fully contracted when a user is stored, the problem that collision or breakage of the wing is easily caused when the wing is completely contracted by mistake when the user is stored is avoided, and the endurance time is also improved through the reduction of the weight;
2. the device can timely sense when the obstacle is collided in the flight process, the sliding rod can be controlled to be contracted immediately, damage to device components caused by collision of the obstacle in the flight process is avoided, the body is prevented from being damaged due to continuous collision of the obstacle in the flight process due to inertia, and contusion to internal parts in the collision process is reduced;
3. when unmanned aerial vehicle descends, strut this unmanned aerial vehicle of parcel by air bag, when unmanned aerial vehicle falls to ground, protection fuselage slows down violent striking, avoids fuselage internals to cause the damage owing to the whereabouts crash, conveniently overhauls unmanned aerial vehicle after picking up unmanned aerial vehicle, reduces the crash loss.
Drawings
FIG. 1 is a schematic perspective view of the structure of the present invention;
FIG. 2 is a schematic perspective view of a cross-shaped chute according to the present invention;
FIG. 3 is a schematic perspective view of a straight slot sliding structure according to the present invention;
FIG. 4 is a schematic perspective view of an arc-shaped groove structure of the present invention;
FIG. 5 is a schematic perspective view of a switch locking mechanism of the present invention;
FIG. 6 is a schematic cross-sectional view of the structure of the present invention;
FIG. 7 is an enlarged schematic view of a portion of the structure of FIG. 5A in accordance with the present invention;
FIG. 8 is a partially enlarged schematic illustration of the structure of FIG. 5B in accordance with the present invention;
FIG. 9 is a schematic perspective view of the flight protection assembly of the present invention;
FIG. 10 is a schematic perspective view of a cross-sectional view of the flight protection assembly of the present invention;
fig. 11 is a schematic side perspective view of the structure of the present invention.
In the figure:
1. a working host; 101. a fuselage housing; 102. a sliding hole; 103. a top cover; 104. a support foot rest;
2. a receiving assembly; 201. a cross sliding groove; 202. positioning columns; 203. a circular positioning plate I; 204. a first chute; 205. a rotating lever; 206. a circular positioning plate II; 207. a second chute; 208. a console; 209. a ratchet wheel; 210. a pawl; 211. an electromagnet; 212. a knob;
3. a flight collision sensing assembly; 301. a slide bar; 302. a guide rod; 303. a positioning rod; 304. a flight driver; 305. a wing; 306. an anti-collision baffle I; 307. an anti-collision baffle II; 308. a transmission block; 309. a spring rod; 310. a limiting plate; 311. a sliding chamber; 312. a third chute; 313. an induction bin; 314. an electrical connection block I;
4. a flight protection assembly; 401. positioning the shell; 402. a connecting rod; 403. an inflation cylinder; 404. a gas-filled reactor; 405. generating a heating wire; 406. an air bag bin; 407. a gas delivery hole; 408. a protective backsheet; 409. and an electrical connection block II.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
Referring to fig. 1 to 11, the present invention provides a technical solution:
examples
Referring to fig. 1 to 11, the portable air conditioner comprises a main body shell 101, a working host 1 is welded at the bottom of the main body shell 101, a supporting foot stand 104 is welded on the surface of the main body shell 101, an organic top cover 103 is welded on the upper surface of the main body shell 101, the supporting foot stand 104 is arranged on the side wall of the main body shell 101, a storage component 2 is arranged in the middle of the main body shell 101, a flying collision sensing component 3 is arranged on the side wall of the main body shell 101, and a flying protection component 4 is welded at the bottom of the working host 1.
The storage assembly 2 comprises a first circular positioning plate 203, a first chute 204, a second circular positioning plate 206, a second chute 207, wherein the first circular positioning plate 203 is disposed inside the housing 101, the first chute 204 is disposed through the first circular positioning plate 203, the second circular positioning plate 206 is disposed at the top of the first circular positioning plate 203, and the second chute 207 is disposed through the second circular positioning plate 206.
The flying collision sensing assembly 3 comprises a first collision baffle 306, a second collision baffle 307, a transmission block 308 and a spring rod 309, the flying driver 304 is located on the side wall of the body shell 101, the second collision baffle 307 is arranged on the side of the body shell 101, the transmission block 308 is slidably connected in the first collision baffle 306, the spring rod 309 is welded on one side, close to the second collision baffle 307, of the transmission block 308, the bottom of the spring rod 309 is located below the positioning rod 303, the spring rod 309 slides in the sensing bin 313, and one end, close to the first electrical connection block 314, of the spring rod 309 is conductive.
The flight protection assembly 4 comprises an inflatable reactor 404, heating wires 405, an air bag bin 406, wherein the inflatable reactor 404 is arranged at the bottom of the working host 1, the heating wires 405 are arranged inside the inflatable reactor 404, and the air bag bin 406 is arranged at the bottom of the working host 1.
The storage assembly 2 further comprises a cross sliding groove 201, a positioning column 202 and a rotating rod 205, wherein the cross sliding groove 201 is welded at the bottom of the inner cavity of the machine body shell 101, the positioning column 202 is welded at the bottom of the inner cavity of the machine body shell 101, and the rotating rod 205 is rotatably connected to the upper surface of the first circular positioning plate 203.
The accommodating assembly 2 further comprises a control console 208, a ratchet 209, a rotating pawl 210, an electromagnet 211 and a knob 212, wherein the control console 208 is welded on the upper surface of the machine body shell 101, the ratchet 209 is welded on the outer wall of the inside of the control console 208, the rotating pawl 210 is rotationally connected to the bottom of an inner cavity of the control console 208, the inner side end of the pawl 210 is clamped with the ratchet 209, the electromagnet 211 is welded on the side wall of the inner cavity of the control console 208, the knob 212 is welded on the top of the inside of the control console 208, the rotating rod 205, the round locating plate two 206, the ratchet 209 and the knob 212 can synchronously rotate when the knob 212 is driven by external force, and the rotating rod 205 and the round locating plate two 206 synchronously rotate when the knob 212 is manually rotated, and the guide rod 302 can slide in the second slide groove 207 and the first slide groove 204.
The flying collision sensing assembly 3 further comprises a sliding rod 301, a guide rod 302, a positioning rod 303, a flying driver 304 and a wing 305, wherein the sliding rod 301 is slidably connected in the cross sliding groove 201, the guide rod 302 is welded at one end of the sliding rod 301 positioned in the fuselage housing 101, the guide rod 302 simultaneously penetrates through the first sliding groove 204 and the second sliding groove 207, the flying driver 304 is fixedly connected at one end of the sliding rod 301 far away from the fuselage housing 101, the positioning rod 303 is fixedly connected to the side wall of the flying driver 304, and the wing 305 is rotatably connected to the top of the flying driver 304.
The flying collision sensing assembly 3 further comprises a limiting plate 310, a sliding cavity 311, a third sliding groove 312, a sensing bin 313 and a first electrical connection block 314, wherein the limiting plate 310 is welded to the inner cavity of the positioning rod 303, the third sliding groove 312 is formed in the bottom of the positioning rod 303, the sensing bin 313 is welded to the side wall of the flying driver 304, the first electrical connection block 314 is welded to the side wall of the inner cavity of the sensing bin 313, when the second circular positioning plate 206 rotates, the guiding rod 302 is pushed to slide, the guiding rod 302 enables the sliding rod 301 to stretch and retract in the cross sliding groove 201, when the spring rod 309 is extruded, the spring rod 309 contracts, the bottom of the spring rod 309 moves in the third sliding groove 312, the spring rod 309 contacts the first electrical connection block 314, an electrical connection relationship exists between the first electrical connection block 314 and the electromagnet 211, and an electrical connection relationship exists between the first electrical connection block 314 and the second electrical connection block 409.
The flight protection assembly 4 further comprises a positioning shell 401, a connecting rod 402, an inflating cylinder 403, a gas transmission hole 407, a protection negative film 408 and a second electrical connection block 409, wherein the positioning shell 401 is welded at the bottom of the working host 1, the connecting rod 402 is welded at the bottom of the positioning shell 401, the inflating cylinder 403 is welded at the bottom of an inner cavity of the positioning shell 401, the gas transmission hole 407 is formed at the bottom of the side wall of the inflating cylinder 403, the protection negative film 408 is adhered to the lower surface of the connecting rod 402, the second electrical connection block 409 is arranged on the upper surface of the inner cavity of the inflating cylinder 403, the heating wire 405 is electrically connected with the second electrical connection block 409, the gas transmission hole 407 is arranged between the airbag cabin 406 and the inflating cylinder 403, an airbag is arranged in the airbag cabin 406, the material of the inflating reactor 404 is sodium azide, a large amount of nitrogen gas is generated by the high temperature during electrifying, the airbag can be rapidly filled with the sodium azide, the airbag 408 is rapidly ejected out, and the adhered airbag 408 is ejected, so that the safety protection device is expanded to the bottom of the whole device, and the safety device is landed.
Working principle: in the initial state, the working host 1 is not started, the sliding rod 301 is located at the innermost side of the cross sliding groove 201, the guide rod 302 is located at the innermost side of the first sliding groove 204, meanwhile, the guide rod 302 is located at the innermost side of the second sliding groove 207, one end of the rotating pawl 210 is clamped in a tooth groove of the ratchet 209, the electromagnet 211 is not electrified, the spring rod 309 is not compressed, the spring rod 309 is not contacted with the second electrical connection block 409, the second electrical connection block 409 is in an open circuit state, the second electrical connection block 409 is not electrified, the protective negative film 408 is adhered to the lower surface of the connection rod 402, and the airbag cabin 406 is not inflated into the airbag.
During operation, the knob 212 is manually rotated, the knob 212 drives the rotating rod 205 to rotate, the ratchet 209 welded on the rotating rod 205 synchronously rotates under the drive of the rotating rod 205, the second circular positioning plate 206 welded at the bottom end of the rotating rod 205 follows the rotating rod 205 to rotate, when the second circular positioning plate 206 rotates, under the guiding action of the second sliding groove 207, the second circular positioning plate 206 pushes the guide rod 302 to gradually slide to the outermost side of the second sliding groove 207 from one side close to the rotating rod 205 through the first sliding groove 204, the guide rod 302 synchronously slides outwards in the first sliding groove 204, the guide rod 302 drives the sliding rod 301 to slide outwards in the cross sliding groove 201 in the process of moving outwards, the guide rod 302 can control the synchronous expansion of the wings 305 through the knob 212, the weight of the device is reduced, the portability of the device is improved, the device is easy to carry, the problem that the wings 305 are not damaged due to complete shrinkage when being stored by personnel, the fact that the wings 305 are completely contracted by mistake is easy to be broken when being stored is avoided, the problem that the wings 305 are knocked or broken is damaged is gradually, and simultaneously, the wings 305 are gradually damaged by lifting weight is gradually, and the shell is gradually extended from the inner part of the sliding rod 101 through the shell 102.
When the device flies in the air, if the device encounters a collision problem in the working process after the weather of strong wind or improper operation exists, when the device contacts an obstacle, the second anti-collision baffle 307 contacts the obstacle first, the transmission block 308 presses the spring rod 309 when the device is collided, so that the spring rod 309 moves inwards in the third sliding groove 312, the transmission block 308 moves the spring rod 309 inwards in the third sliding groove 312, the inner side end of the spring rod 309 is in electrical contact with the first electrical connection block 314 in the inner cavity of the induction bin 313, at the moment, the electromagnet 211 in the control console 208 is electrified, the electromagnet 211 generates magnetic attraction and magnetic attraction to the rotating pawl 210 after being electrified, so that the rotating pawl 210 between tooth grooves of the ratchet 209 rotates until the rotating pawl 210 is adsorbed on the electromagnet 211, at the moment, the ratchet 209 is not limited by the rotating pawl 210 and can rotate reversely, during the collision, the obstacle continuously collides against the transmission block 308, when the transmission block 308 is extruded, the transmission block 308 pushes the anti-collision baffle II 307 to move towards the machine body shell 101, the sliding rod 301 moves towards the machine body shell 101 under the pushing of the anti-collision baffle II 307, the guide rod 302 welded on the sliding rod 301 moves in the first sliding groove 204 and gradually pushes the first sliding groove 204 to the end close to the first round positioning plate 203 under the continuous pushing, during the pushing, the guide rod 302 gradually moves to the end close to the rotating rod 205 through the movement in the second sliding groove 207, during the moving, the guide rod 302 drives the second round positioning plate 206 to rotate, the second round positioning plate 206 drives the rotating rod 205 to synchronously rotate, the ratchet 209 welded on the rotating rod 205 rotates along with the driving direction of the rotating rod 205 while the rotating rod 205 rotates, when the guide rod 302 moves to one end close to the central part of the first round locating plate 203 in the first chute 204, the sliding rod 301 is contracted;
the electromagnet 211 does not absorb the rotating pawl 210 any more, the rotating pawl 210 swings into the notch of the ratchet 209, the ratchet 209 is blocked to enable the ratchet 209 not to reversely rotate, the device can timely sense when the device collides with an obstacle in the flying process, the sliding rod 301 can be controlled to immediately shrink, damage to device components caused by the collision of the obstacle in the flying process is avoided, the body damage caused by the continuous collision of the obstacle due to inertia in the flying process is prevented, and contusion to internal parts in the collision process is reduced.
When spring bar 309 and first 314 electrical contact of electrical connection piece, because spring bar 309 is close to the one end of first 314 electrical connection piece and has conductivity, make first 314 passageway of electrical connection piece, because first 314 and second 409 electrical connection piece of electrical connection piece, and then make second 409 electrical connection piece circular telegram, because second 409 and heating wire 405 electrical connection, produce huge electric current after the circular telegram of heating wire 405, the electric current produces high temperature in heating wire 405, under the effect of high temperature, the sodium azide that sets up in the gas-filled reactor 404 can produce a large amount of nitrogen gas rapidly, the nitrogen gas that produces in gas-filled cylinder 403 constantly gushes into in the gasbag storehouse 406 through gas-supply hole 407, make the air bag aerify rapidly, after having rushed into sufficient nitrogen gas in the air bag, thereby the roof-open bonds the protective film 408 at connecting rod 402 lower surface, expand to the bottom and all around, when unmanned aerial vehicle descends downwards, strut parcel unmanned aerial vehicle, when unmanned aerial vehicle falls to ground, the protective body violently bumps, avoid the fuselage internals to cause the damage because the whereabouts falls down, after picking up unmanned aerial vehicle and the maintenance loss is reduced.
It is noted that relational terms such as first and second, and the like are 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. Moreover, 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. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The utility model provides a folding unmanned aerial vehicle of lightweight many rotors, includes fuselage shell (101), its characterized in that: the device comprises a main body (101), a working host (1) is welded at the bottom of the main body (101), a supporting foot rest (104) is welded on the surface of the main body (101), an organic top cover (103) is welded on the upper surface of the main body (101), a supporting foot rest (104) is arranged on the side wall of the main body (101), a storage component (2) is arranged in the middle of the main body (101), a flying collision sensing component (3) is arranged on the side wall of the main body (101), and a flying protection component (4) is welded at the bottom of the main body (1);
the storage assembly (2) comprises a first circular positioning plate (203), a first sliding groove (204), a second circular positioning plate (206) and a second sliding groove (207), wherein the first circular positioning plate (203) is arranged in the machine body shell (101), the first sliding groove (204) is arranged on the first circular positioning plate (203) in a penetrating way, the second circular positioning plate (206) is arranged at the top of the first circular positioning plate (203), and the second sliding groove (207) is arranged on the second circular positioning plate (206) in a penetrating way;
the storage assembly (2) further comprises a cross sliding groove (201), a positioning column (202) and a rotating rod (205), wherein the cross sliding groove (201) is welded at the bottom of an inner cavity of the machine body shell (101), the positioning column (202) is welded at the bottom of the inner cavity of the machine body shell (101), and the rotating rod (205) is rotatably connected to the upper surface of the first circular positioning plate (203);
the accommodating assembly (2) further comprises a control console (208), a ratchet wheel (209), a rotating pawl (210), an electromagnet (211) and a knob (212), wherein the control console (208) is welded on the upper surface of the machine body shell (101), the ratchet wheel (209) is welded on the outer wall of the rotating rod (205) positioned inside the control console (208), the rotating pawl (210) is rotationally connected to the bottom of an inner cavity of the control console (208), the inner side end of the pawl (210) is clamped with the ratchet wheel (209), the electromagnet (211) is welded on the side wall of the inner cavity of the control console (208), and the knob (212) is welded on the top of the rotating rod (205) positioned inside the control console (208);
the flying collision sensing assembly (3) comprises a flying driver (304), a first collision baffle (306), a second collision baffle (307), a transmission block (308) and a spring rod (309), wherein the flying driver (304) is positioned on the side wall of the machine body shell (101), the second collision baffle (307) is arranged on the side of the machine body shell (101), the transmission block (308) is slidably connected in the first collision baffle (306), the spring rod (309) is welded on one side, close to the second collision baffle (307), of the transmission block (308), the bottom of the spring rod (309) is positioned below the positioning rod (303), and the spring rod (309) slides in the sensing bin (313);
the flying collision sensing assembly (3) further comprises a sliding rod (301), a guide rod (302), a positioning rod (303) and a wing (305), wherein the sliding rod (301) is connected in the cross sliding groove (201) in a sliding mode, the guide rod (302) is welded at one end of the sliding rod (301) located in the machine body shell (101), the guide rod (302) penetrates through the first sliding groove (204) and the second sliding groove (207) respectively and is connected in a sliding mode, the flying driver (304) is fixedly connected to one end, far away from the machine body shell (101), of the sliding rod (301), the positioning rod (303) is fixedly connected to the side wall of the flying driver (304), and the wing (305) is connected to the top of the flying driver (304) in a rotating mode;
the flight protection assembly (4) comprises an inflation reactor (404), heating wires (405), an air bag bin (406) and a control unit, wherein the inflation reactor (404) is arranged at the bottom of the working host (1), the heating wires (405) are arranged in the inflation reactor (404), and the air bag bin (406) is arranged at the bottom of the working host (1);
the flying collision sensing assembly (3) further comprises a limiting plate (310), a sliding cavity (311), a third sliding groove (312), a sensing bin (313) and an electric connection block I (314), wherein the limiting plate (310) is welded inside the positioning rod (303), the third sliding groove (312) is formed in the bottom of the positioning rod (303), the sensing bin (313) is welded on the side wall of the flying driver (304), the electric connection block I (314) is welded on the side wall of the inner cavity of the sensing bin (313), and one end, close to the electric connection block I (314), of the spring rod (309) is conductive.
2. The portable multi-rotor folding drone of claim 1, wherein: the flight protection assembly (4) further comprises a positioning shell (401), a connecting rod (402), an inflating cylinder (403), a gas transmission hole (407), a protection negative film (408) and a second electric connection block (409), wherein the positioning shell (401) is welded at the bottom of the working host machine (1), the connecting rod (402) is welded at the bottom of the positioning shell (401), the inflating cylinder (403) is welded at the bottom of an inner cavity of the positioning shell (401), the gas transmission hole (407) is formed in the bottom of the side wall of the inflating cylinder (403), the protection negative film (408) is adhered to the lower surface of the connecting rod (402), and the second electric connection block (409) is arranged on the upper surface of the inner cavity of the inflating cylinder (403).
3. The portable multi-rotor folding drone of claim 2, wherein: there is electric connection between wire (405) and the second of electrical connection piece (409), there is electric connection between first of electrical connection piece (314) and electro-magnet (211), there is electric connection between first of electrical connection piece (314) and the second of electrical connection piece (409), gas-supply hole (407) set up between gasbag storehouse (406) and inflatable cylinder (403).
4. The portable multi-rotor folding drone of claim 1, wherein: an airbag is arranged in the airbag cabin (406), and the material of the inflatable reactor (404) is sodium azide.
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| CN202310863892.7A CN116750227B (en) | 2023-07-13 | 2023-07-13 | Portable multi-rotor folding unmanned aerial vehicle |
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| CN116750227A (en) | 2023-09-15 |
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