CN210113179U - Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure - Google Patents
Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure Download PDFInfo
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- CN210113179U CN210113179U CN201920375264.3U CN201920375264U CN210113179U CN 210113179 U CN210113179 U CN 210113179U CN 201920375264 U CN201920375264 U CN 201920375264U CN 210113179 U CN210113179 U CN 210113179U
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- 230000003139 buffering effect Effects 0.000 claims abstract description 15
- 230000003028 elevating effect Effects 0.000 claims abstract description 7
- 230000001133 acceleration Effects 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 3
- 239000010409 thin film Substances 0.000 claims 2
- 238000000034 method Methods 0.000 abstract description 2
- 230000002265 prevention Effects 0.000 description 5
- 239000000872 buffer Substances 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 239000006173 Good's buffer Substances 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model relates to an unmanned air vehicle technique field specifically is a reconnaissance unmanned aerial vehicle that falls with second grade floating structure, including frame, wing support frame, screw rotating electrical machines, screw, measuring and control device, second grade relocation mechanism, the mechanism of preventing falling, bottom sleeve, aerify motor, buffering gasbag, the mechanism of preventing falling includes the outer sleeve, the diaphragm, and the parachute body is installed to the upper end of diaphragm, and the through-hole has been seted up at the center of diaphragm, runs through in the through-hole and is equipped with the vaulting pole, and the inside of outer sleeve still is equipped with elevating gear, and the lower extreme fixed mounting of vaulting pole is on elevating gear. When the inflation motor works and inflates towards the interior of the buffering air bag, the buffering air bag begins to expand and breaks the film, so that a good buffering effect can be achieved when the frame falls, when the frame falls out of balance, the lifting device is started, the lifting device can push the parachute body out of the outer sleeve through the support rod and the top plate, the parachute body can be propped open by the influence of air, and the falling speed of the frame is reduced.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is a reconnaissance unmanned aerial vehicle that prevents falling with second grade floating structure.
Background
The unmanned plane is called unmanned plane for short, and is called UAV in English, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. From a technical point of view, the definition can be divided into: unmanned fixed wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane aircraft, and the like. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + industry application is really just needed for the unmanned aerial vehicle, and is currently applied to the fields of aerial photography, agriculture, plant protection, self-photography, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, electric power inspection, disaster relief, movie and television shooting and the like, so that the application of the unmanned aerial vehicle is greatly expanded, and developed countries are also actively expanding the industry application and developing the unmanned aerial vehicle technology.
However, along with unmanned aerial vehicle's application is more and more extensive, unmanned aerial vehicle prevent falling also receive more and more people's attention, because reasons such as trouble, remote control malfunction probably lead to falling of unmanned aerial vehicle, because its impact force that falls the production probably causes the injury to people, thing etc..
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a reconnaissance unmanned aerial vehicle that prevents falling with second grade floating structure to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: an anti-falling reconnaissance unmanned aerial vehicle with a secondary floating structure comprises a frame, wherein wing supporting frames are respectively installed at four corners of the upper end of the frame, a propeller rotating motor is installed at the upper end of each wing supporting frame, a propeller is installed on an output shaft at the upper end of the propeller rotating motor, a measurement and control device is installed at the center of the inner portion of the frame and comprises a height sensor and an acceleration sensor, the height sensor and the acceleration sensor are both connected with a single chip microcomputer, a secondary floating mechanism is also installed in the frame and is installed at the position close to the four corners in the inner portion of the frame, an anti-falling mechanism is installed at the center of the upper end of the frame, a bottom sleeve is installed at the lower end of the frame and is vertical to the frame, an inflation motor is arranged in the bottom sleeve, the upper end of the, buffering gasbag installs in the telescopic inside of bottom, the mechanism of preventing falling includes the outer sleeve, and the lower extreme fixed mounting of outer sleeve is on the upper end center of frame, and the inside of outer sleeve is close to the diaphragm that the open-top portion installed the level and set up, and the parachute body is installed to the upper end of diaphragm, and the through-hole has been seted up at the center of diaphragm, runs through in the through-hole and is equipped with the vaulting pole, the inside of outer sleeve still is equipped with elevating gear, and elevating gear locates the diaphragm below, and the lower extreme fixed mounting of vaulting pole is on elevating gear.
Preferably, a film is arranged at an opening at the lower end of the bottom sleeve, and the film is arranged at one time.
Preferably, the top of vaulting pole is installed the roof, and the roof becomes the arc setting, and the top of roof is tightly supported the parachute body and is set up.
Preferably, elevating gear includes fixed sleeve, and fixed sleeve's lower extreme fixed mounting is on the upper end center of frame, and fixed sleeve and outer sleeve set up with the axle center, and fixed sleeve's upper end is inside to be inserted and is equipped with the inserted bar, and the inside screw hole that sets up of lower extreme of inserted bar installs the lead screw in the screw hole, and fixed sleeve's inside lower extreme still is equipped with positive and negative motor, and positive and negative motor installs on the upper end center of frame, and the lower extreme of lead screw and positive and negative motor's output shaft transmission are connected.
Preferably, the sliding grooves are symmetrically formed in the inner side wall of the fixing sleeve and are parallel to the screw rod, the sliding blocks are symmetrically mounted at the lower end of the outer wall of the inserting rod, and the sliding blocks are arranged in the sliding grooves in a sliding mode.
Compared with the prior art, the beneficial effects of the utility model are that:
1. when the inflation motor works and inflates towards the interior of the buffering air bag, the buffering air bag starts to expand and breaks the film, so that a good buffering effect can be achieved when the rack falls;
2. when the frame loses balance and falls, the lifting device is started, the lifting device can push the parachute out of the outer sleeve through the support rod and the top plate, the parachute body can be unfolded under the influence of air, and the falling speed of the frame is reduced.
Drawings
Fig. 1 is a schematic structural view of a falling prevention reconnaissance unmanned aerial vehicle with a secondary floating structure;
fig. 2 is a schematic structural diagram of a falling prevention mechanism in a falling prevention reconnaissance unmanned aerial vehicle with a two-stage floating structure;
fig. 3 is a schematic structural diagram of a lifting device in a falling prevention reconnaissance unmanned aerial vehicle with a two-stage floating structure.
In the figure: the device comprises a rack 1, a wing support frame 2, a propeller rotating motor 3, a propeller 4, a measurement and control device 5, a height sensor 6, an acceleration sensor 7, a single chip microcomputer 8, a two-stage floating structure 9, a falling prevention mechanism 10, a bottom sleeve 11, an inflation motor 12, a buffer air bag 13, a film 14, an outer sleeve 15, a parachute body 16, a transverse plate 17, a support rod 18, a top plate 19, a lifting device 20, a fixing sleeve 21, an inserted rod 22, a forward and reverse motor 23, a screw rod 24, a threaded hole 25, a sliding groove 26 and a sliding block 27.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides a technical solution: an anti-falling reconnaissance unmanned aerial vehicle with a secondary floating structure comprises a frame 1, wing support frames 2 are mounted at four corners of the upper end of the frame 1, a propeller rotating motor 3 is mounted at the upper end of each wing support frame 2, propellers 4 are mounted on an output shaft of the upper end of the propeller rotating motor 3, a measurement and control device 5 is mounted at the center of the inside of the frame 1, each measurement and control device 5 comprises a height sensor 6 and an acceleration sensor 7, the height sensors 6 and the acceleration sensors 7 are connected with a single chip microcomputer 8, a secondary floating mechanism 9 is further mounted inside the frame 1, the secondary floating mechanism 9 is mounted inside the frame 1 and close to the four corners, an anti-falling mechanism 10 is mounted at the center of the upper end of the frame 1, a bottom sleeve 11 is mounted at the lower end of the frame 1, the bottom sleeve 11 is perpendicular to the frame 1, an inflation motor 12 is arranged, the output end of the inflating motor 12 is connected with a buffering air bag 13, the buffering air bag 13 is installed inside the bottom sleeve 11, a film 14 is arranged at the opening of the lower end of the bottom sleeve 11, the film 14 is arranged at one time, when the inflating motor 12 is inflated towards the buffering air bag 13 in work, the buffering air bag 13 begins to expand and breaks the film 13, and a good buffering effect can be achieved when the rack 1 falls.
The anti-falling mechanism 10 comprises an outer sleeve 15, the lower end of the outer sleeve 15 is fixedly arranged on the center of the upper end of the frame 1, a horizontal plate 17 which is horizontally arranged is arranged inside the outer sleeve 15 and close to the opening of the top part, a parachute body 16 is arranged at the upper end of the horizontal plate 17, a through hole is arranged at the center of the horizontal plate 17, a stay bar 18 penetrates through the through hole, a top plate 19 is arranged at the top end of the stay bar 18, the top plate 19 is arranged in an arc shape, the top end of the top plate 19 is tightly abutted to the parachute body 16, a lifting device 20 is further arranged inside the outer sleeve 15, the lifting device 20 is arranged below the horizontal plate 17, the lower end of the, when the frame 1 is out of balance and falls, the lifting device 20 is started, the lifting device 20 can push the parachute body 16 out of the outer sleeve 15 through the support rod 18 and the top plate 19, the parachute body 16 can be unfolded under the influence of air, and the falling speed of the frame 1 is reduced.
The lifting device 20 comprises a fixed sleeve 21, the lower end of the fixed sleeve 21 is fixedly installed on the center of the upper end of the rack 1, the fixed sleeve 21 and the outer sleeve 15 are coaxially arranged, an insertion rod 22 is inserted into the upper end of the fixed sleeve 21, a threaded hole 25 is formed in the lower end of the insertion rod 22, a screw rod 24 is installed in the threaded hole 25, a forward and reverse motor 23 is further arranged at the lower end of the inner part of the fixed sleeve 21, the forward and reverse motor 23 is installed on the center of the upper end of the rack 1, the lower end of the screw rod 24 is in transmission connection with an output shaft of the forward and reverse motor 23, the forward and reverse motor 23 drives the screw rod 23 to rotate, the screw rod 24 drives the insertion rod 22 to achieve a telescopic function in the fixed sleeve 21 through the threaded hole 25, the turning direction of the forward and reverse motor 23 is specifically required to be seen, sliding grooves 26 are symmetrically, the slide block 27 is slidably disposed in the slide groove 26, and the arrangement of the slide block 27 and the slide groove 26 can ensure that the insert rod 22 does not rotate along with the screw rod 24.
The working principle is as follows: when the inflation motor 12 works and inflates towards the interior of the buffer air bag 13, the buffer air bag 13 starts to expand and burst the film 13, so that a good buffer effect can be achieved when the rack 1 falls, when the rack 1 falls out of balance, the lifting device 20 is started, the lifting device 20 can push the parachute body 16 out of the outer sleeve 15 through the support rod 18 and the top plate 19, the parachute body 16 can be propped open under the influence of air, and the falling speed of the rack 1 is reduced.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a reconnaissance unmanned aerial vehicle that prevents falling with second grade floating structure, includes frame (1), its characterized in that: the aircraft is characterized in that wing support frames (2) are installed at four corners of the upper end of a rack (1), a propeller rotating motor (3) is installed at the upper end of the wing support frames (2), a propeller (4) is installed on an upper end output shaft of the propeller rotating motor (3), a measurement and control device (5) is installed at the inner center of the rack (1), the measurement and control device (5) comprises a height sensor (6) and an acceleration sensor (7), the height sensor (6) and the acceleration sensor (7) are both connected with a single chip microcomputer (8), a secondary floating mechanism (9) is also installed inside the rack (1), the secondary floating mechanism (9) is installed inside the rack (1) and is close to the four corners, an anti-falling mechanism (10) is installed at the center of the upper end of the rack (1), a bottom sleeve (11) is installed at the lower end of the rack (1), and, an inflating motor (12) is arranged in the bottom sleeve (11), the upper end of the inflating motor (12) is fixedly arranged on the center of the bottom of the frame (1), the output end of the inflating motor (12) is connected with a buffering air bag (13), the buffering air bag (13) is arranged in the bottom sleeve (11), the anti-falling mechanism (10) comprises an outer sleeve (15), the lower end of the outer sleeve (15) is fixedly arranged on the center of the upper end of the rack (1), a horizontal transverse plate (17) is arranged in the outer sleeve (15) close to the opening at the top, a parachute body (16) is arranged at the upper end of the transverse plate (17), a through hole is formed in the center of the transverse plate (17), a stay bar (18) penetrates through the through hole, the inner part of the outer sleeve (15) is also provided with a lifting device (20), the lifting device (20) is arranged below the transverse plate (17), and the lower end of the stay bar (18) is fixedly arranged on the top end of the lifting device (20).
2. The unmanned aerial vehicle with secondary floating structure for anti-falling reconnaissance of claim 1, wherein: a thin film (14) is arranged at an opening at the lower end of the bottom sleeve (11), and the thin film (14) is arranged at one time.
3. The unmanned aerial vehicle with secondary floating structure for anti-falling reconnaissance of claim 1, wherein: the top of vaulting pole (18) is installed roof (19), and roof (19) become the arc setting, and the top of roof (19) is tightly supported parachute body (16) and is set up.
4. The unmanned aerial vehicle with secondary floating structure for anti-falling reconnaissance of claim 1, wherein: elevating gear (20) are including fixed sleeve (21), the lower extreme fixed mounting of fixed sleeve (21) is on the upper end center of frame (1), fixed sleeve (21) and outer sleeve (15) set up with the axle center, the inside inserted bar (22) that is equipped with in upper end of fixed sleeve (21), the inside screw hole (25) of seting up of lower extreme of inserted bar (22), install lead screw (24) in screw hole (25), the inside lower extreme of fixed sleeve (21) still is equipped with positive and negative motor (23), positive and negative motor (23) are installed on the upper end center of frame (1), the lower extreme of lead screw (24) and the output shaft transmission of positive and negative motor (23) are connected.
5. The unmanned aerial vehicle with secondary floating structure for anti-falling reconnaissance of claim 4, wherein: the inner side wall of the fixed sleeve (21) is symmetrically provided with sliding grooves (26), the sliding grooves (26) are parallel to the screw rod (24), the lower end of the outer wall of the inserted rod (22) is symmetrically provided with sliding blocks (27), and the sliding blocks (27) are arranged in the sliding grooves (26) in a sliding mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920375264.3U CN210113179U (en) | 2019-03-24 | 2019-03-24 | Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920375264.3U CN210113179U (en) | 2019-03-24 | 2019-03-24 | Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure |
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| Publication Number | Publication Date |
|---|---|
| CN210113179U true CN210113179U (en) | 2020-02-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920375264.3U Active CN210113179U (en) | 2019-03-24 | 2019-03-24 | Prevent reconnaissance unmanned aerial vehicle that falls with second grade floating structure |
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| CN (1) | CN210113179U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678173A (en) * | 2021-01-30 | 2021-04-20 | 江西中建勘察设计有限公司 | Unmanned aerial vehicle is used in survey and drawing |
| CN113135297A (en) * | 2021-05-17 | 2021-07-20 | 宜宾职业技术学院 | Unmanned aerial vehicle anti-falling device |
-
2019
- 2019-03-24 CN CN201920375264.3U patent/CN210113179U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678173A (en) * | 2021-01-30 | 2021-04-20 | 江西中建勘察设计有限公司 | Unmanned aerial vehicle is used in survey and drawing |
| CN113135297A (en) * | 2021-05-17 | 2021-07-20 | 宜宾职业技术学院 | Unmanned aerial vehicle anti-falling device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211202 Address after: 518000 N51, building 1, Bolin Junrui, No. 26, Shaqi Community Center Road, Xinqiao street, Bao'an District, Shenzhen, Guangdong Patentee after: Shenzhen 1008 Technology Co.,Ltd. Address before: Room 406, Block B5, 286 Longtengzhong Road, Xipi Town, Xinluo District, Longyan City, Fujian Province Patentee before: Lin Caihong |
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| TR01 | Transfer of patent right |