CN112357104A - High-performance temperature sensor for unmanned aerial vehicle - Google Patents
High-performance temperature sensor for unmanned aerial vehicle Download PDFInfo
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- CN112357104A CN112357104A CN202110049663.2A CN202110049663A CN112357104A CN 112357104 A CN112357104 A CN 112357104A CN 202110049663 A CN202110049663 A CN 202110049663A CN 112357104 A CN112357104 A CN 112357104A
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- aerial vehicle
- unmanned aerial
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- mounting groove
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- 239000007787 solid Substances 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 9
- 230000000979 retarding effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 4
- 230000001681 protective effect Effects 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 21
- 239000000428 dust Substances 0.000 description 6
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 230000003139 buffering effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 239000000463 material Substances 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
- 239000000575 pesticide Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Classifications
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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
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20145—Means for directing air flow, e.g. ducts, deflectors, plenum or guides
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20136—Forced ventilation, e.g. by fans
- H05K7/20181—Filters; Louvers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
Abstract
The invention discloses a high-performance temperature sensor for an unmanned aerial vehicle, which belongs to the technical field of sensors, and adopts the technical scheme that the high-performance temperature sensor for the unmanned aerial vehicle comprises an unmanned aerial vehicle main body and a cover, wherein the cover is positioned above the unmanned aerial vehicle main body and is hinged with the unmanned aerial vehicle main body, the inner wall of the unmanned aerial vehicle main body is provided with a mounting groove, a sensor body is movably mounted on the inner wall of the mounting groove, the top of the unmanned aerial vehicle main body is provided with a mounting port communicated with the mounting groove, the surface of the cover is fixedly connected with a fixing block matched with the mounting port, an engaging block fixedly connected with the surface of a clamping rod can be clamped into the inside of the engaging port, so that the sensor body is preliminarily limited and fixed, meanwhile, the protective block is contacted with the sensor body, a preliminary buffer effect can, the sensor body is damaged under the action of vibration, and the normal operation of the sensor body is influenced.
Description
Technical Field
The invention relates to the technical field of sensors, in particular to a high-performance temperature sensor for an unmanned aerial vehicle.
Background
A drone is an unmanned aerial vehicle that is operated by a radio remote control device or by its own programmed control means. At present, in the civil field, the research and application of mapping unmanned aerial vehicle, geological survey unmanned aerial vehicle, disaster monitoring unmanned aerial vehicle, meteorological detection unmanned aerial vehicle, air traffic control unmanned aerial vehicle, border control unmanned aerial vehicle, communication relay unmanned aerial vehicle, pesticide spraying unmanned aerial vehicle are in continuous development at home and abroad.
Wherein temperature sensor is important sensor among the unmanned aerial vehicle, owing to receive fuselage structure's restriction, temperature sensor sets up the process on the unmanned aerial vehicle comparatively loaded down with trivial details, and its stability after the installation can not be guaranteed to the leakproofness after the temperature sensor installation is mostly not good, consequently, technical personnel in the field provide a high performance temperature sensor for unmanned aerial vehicle, in order to solve the problem that proposes in the above-mentioned background art.
Disclosure of Invention
1. Technical problem to be solved
In view of the problems in the prior art, an object of the present invention is to provide a high performance temperature sensor for an unmanned aerial vehicle, which has advantages of improving convenience in installation and stability after installation, and having good sealing performance.
2. Technical scheme
In order to solve the problems, the invention adopts the following technical scheme: the utility model provides a high performance temperature sensor for unmanned aerial vehicle, includes unmanned aerial vehicle main part and cover, the cover is located the top of unmanned aerial vehicle main part and articulates mutually with the unmanned aerial vehicle main part, the mounting groove has been seted up to the inner wall of unmanned aerial vehicle main part, the inner wall movable mounting of mounting groove has the sensor body, the installing port that is linked together with the mounting groove is seted up at the top of unmanned aerial vehicle main part, the fixed surface of cover is connected with and installing port assorted fixed block, the outer fringe and the inner wall of fixed block contact with the inner edge of installing port and the surface of sensor body respectively, the inner wall sliding connection of mounting groove has the buffer board, the top of buffer board articulates the kelly that is two and with sensor body looks joint, the air duct that is linked together and is evenly distributed with the mounting groove.
Furthermore, the top fixedly connected with of buffer board and the articulated seat of kelly bottom looks articulated, the surface of sensor body is seted up quantity and is four meshing mouths, two the equal fixedly connected with meshing piece of opposite side of kelly and the protection piece that contacts with the sensor body surface, meshing piece and meshing mouth phase-match.
Further, the inner wall fixedly connected with torsional spring of articulated seat, two the hinge groove has all been seted up to the inner wall of kelly, the both ends of torsional spring run through articulated seat respectively and with the inner wall fixed connection in both sides hinge groove.
Further, the fixed slot that quantity is two is seted up on the surface of sensor body, the inner wall both sides of mounting groove all are provided with solid fixed ring, gu fixed ring runs through the buffer board and overlaps the surface of locating sensor body, and gu fixed ring's inner edge and the inner wall looks joint of fixed slot.
Furthermore, the vertex height of the fixing ring is lower than that of the sensor main body, and the fixing ring is a rubber component.
Further, fixedly connected with evenly distributed's spring between the bottom of buffer board and the inner wall bottom of mounting groove, the equal fixedly connected with slider in both ends of buffer board, the spout that is linked together with slider phase-match and with the mounting groove is seted up to the inner wall of unmanned aerial vehicle main part.
Furthermore, the both ends opening part of wind groove is the arc, and the wind groove is located the buffer board under, fixedly connected with filter screen between wind groove and the mounting groove.
Further, the surface of cover is fixedly connected with sealing strip and quantity in proper order by left to right and is two joint piece, the inner wall both sides of unmanned aerial vehicle main part have been seted up respectively with sealing strip and joint piece assorted seal groove and bayonet socket.
Furthermore, the inner wall of the cover is provided with two retarding grooves which are matched with the fixing rings and can be contacted with the fixing rings.
3. Advantageous effects
Compared with the prior art, the invention has the advantages that:
(1) according to the scheme, the clamping rod is arranged, the sensor body is firstly placed on the surface of the clamping rod, the sensor body is downwards pressed to displace for a distance, the meshing block fixedly connected with the surface of the clamping rod can be clamped into the meshing port during displacement, preliminary limiting and fixing are carried out on the sensor body, the protection block is in contact with the sensor body during clamping, preliminary buffering effect can be achieved on the sensor body through the protection block, the unmanned aerial vehicle main body is prevented from being damaged under the action of vibration due to vibration of the body during operation, and normal operation of the sensor body is influenced;
(2) by arranging the torsion spring and matching the hinge seat and the two hinge grooves, the sensor body can be ensured to have good clamping force when placed on the surface of the clamping rod, and the sensor body is prevented from being loosened when installed in the installation groove through the meshing port;
(3) by arranging the fixing ring, when the sensor body is installed in the installation groove through the clamping rod and the meshing port matched with the meshing block, the fixing ring can be sleeved on the surface of the sensor body and clamped into the fixing groove, so that the sensor body is limited and fixed again, and the stability of the sensor body during installation is improved;
(4) by arranging the buffer plate, the unmanned aerial vehicle main body can generate a reverse impact force when the unmanned aerial vehicle finishes operation and falls to the ground, and the buffer plate can be displaced up and down in the sliding groove through the sliding block through the spring, so that the reverse impact force generated when the unmanned aerial vehicle falls to the ground is relieved, and the phenomenon that the sensor body is damaged due to overlarge impact and the normal operation of the sensor body is influenced is avoided;
(5) through setting up wind groove and filter screen, through the wind groove that arc opening design and be linked together with the mounting groove, the unmanned aerial vehicle main part can make the wind flow lead to the inside of mounting groove when moving, from this to the inside cooling of unmanned aerial vehicle main part, the filter screen that sets up between wind groove and the mounting groove simultaneously can filter the dust that contains in the wind flow, avoids the normal function that the high temperature and dust are too much influences the sensor body.
Drawings
FIG. 1 is a perspective view of the present invention;
FIG. 2 is a top view of the present invention;
FIG. 3 is a right side sectional view of the present invention;
FIG. 4 is an elevational, cross-sectional view of the present invention;
FIG. 5 is an enlarged view taken at A in FIG. 3 according to the present invention;
FIG. 6 is a perspective view of a sensor body of the present invention;
fig. 7 is a top view of a sensor body of the present invention.
The reference numbers in the figures illustrate:
1. an unmanned aerial vehicle main body; 2. a machine cover; 3. a fixed block; 4. a sealing strip; 5. a sensor body; 6. a fixing ring; 7. mounting grooves; 8. a bayonet; 9. an engagement port; 10. fixing grooves; 11. a buffer plate; 12. a clamping rod; 13. an air duct; 14. a spring; 15. a hinged seat; 16. a hinge slot; 17. a filter screen; 18. a protection block; 19. a torsion spring.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention.
Referring to fig. 1-7, in the embodiment of the invention, a high-performance temperature sensor for an unmanned aerial vehicle comprises an unmanned aerial vehicle main body 1 and a cover 2, the cover 2 is located above the unmanned aerial vehicle main body 1 and is hinged to the unmanned aerial vehicle main body 1, an installation groove 7 is formed in the inner wall of the unmanned aerial vehicle main body 1, a sensor body 5 is movably installed on the inner wall of the installation groove 7, an installation opening communicated with the installation groove 7 is formed in the top of the unmanned aerial vehicle main body 1, a fixed block 3 matched with the installation opening is fixedly connected to the surface of the cover 2, the outer edge and the inner wall of the fixed block 3 are respectively contacted with the inner edge of the installation opening and the surface of the sensor body 5, a buffer plate 11 is slidably connected to the inner wall of the installation groove 7, two clamping rods 12 which are clamped to the sensor body 5 are hinged to the top of the buffer plate 11.
The top of the buffer plate 11 is fixedly connected with an articulated seat 15 hinged with the bottom end of the clamping rod 12, the surface of the sensor body 5 is provided with four engaging ports 9, the opposite sides of the two clamping rods 12 are fixedly connected with an engaging block and a protecting block 18 contacted with the surface of the sensor body 5, the engaging block is matched with the engaging ports 9, when the sensor body 5 is required to be installed inside the installation groove 7, the sensor body 5 is firstly placed on the surface of the clamping rod 12, the sensor body 5 is downwards displaced for a certain distance by downwards pressing the sensor body 5, the engaging block fixedly connected with the surface of the clamping rod 12 can be clamped inside the engaging ports 9 during displacement, therefore, the sensor body 5 is preliminarily limited and fixed, the protecting block 18 is contacted with the sensor body 5 during clamping, and preliminary buffer effect can be achieved on the sensor body 5 through the protecting block 18, prevent that unmanned aerial vehicle main part 1 from leading to sensor body 5 to damage under the effect of vibrations because the vibrations of fuselage in the operation process, influencing sensor body 5's normal function.
Articulated seat 15's inner wall fixedly connected with torsional spring 19, hinge groove 16 has all been seted up to the inner wall of two kellies 12, 19 both ends of torsional spring run through articulated seat 15 respectively and with the inner wall fixed connection in both sides hinge groove 16, through the articulated seat 15 of 19 cooperation of torsional spring and two hinge grooves 16, can guarantee that sensor body 5 is placing when putting in kellies 12 surfaces, have good clamping-force to sensor body 5, prevent that sensor body 5 from producing when installing in mounting groove 7 inside through meshing mouth 9 and becoming flexible.
The fixed slot 10 that quantity is two is seted up on sensor body 5's surface, the inner wall both sides of mounting groove 7 all are provided with solid fixed ring 6, gu fixed ring 6 runs through buffer board 11 and overlaps the surface of locating sensor body 5, and gu fixed ring 6's inner edge and the inner wall of fixed slot 10 joint mutually, sensor body 5 through kelly 12 with mesh piece assorted meshing mouth 9 installation with mounting groove 7 when inside, can locate sensor body 5's surface with solid fixed ring 6 cover, and with solid fixed ring 6 inside of blocking to fixed slot 10, carry out spacing fixed once more to sensor body 5 from this, and increase the stability of sensor body 5 when the installation.
The summit height of solid fixed ring 6 is less than the summit height of sensor body 5, and solid fixed ring 6 is the rubber material component, through the solid fixed ring 6 that is less than sensor body 5, when needs locate solid fixed ring 6 cover on the surface of sensor body 5, draw solid fixed ring 6 upwards to draw to keep the level with the central point of sensor body 5, alright locate the surface of sensor body 5 with solid fixed ring 6 cover, give sensor body 5 one downward pulling power from this, it is more firm when making the installation of sensor body 5 and kelly 12 surface.
Fixedly connected with evenly distributed's spring 14 between the bottom of buffer board 11 and the inner wall bottom of mounting groove 7, the equal fixedly connected with slider in both ends of buffer board 11, the spout that is linked together with slider phase-match and with mounting groove 7 is seted up to unmanned aerial vehicle main part 1's inner wall, unmanned aerial vehicle main part 1 can produce the reverse impact force of one when the operation is accomplished and falls to the ground, can make buffer board 11 pass through the slider and take place the displacement about the inside of spout through spring 14, slow down the reverse impact force that produces when falling to the ground from this, avoid assaulting excessively, lead to sensor body 5 to damage, influence sensor body 5's normal function.
Both ends opening part of wind groove 13 is the arc, and wind groove 13 is located buffer board 11 under, fixedly connected with filter screen 17 between wind groove 13 and the mounting groove 7, unmanned aerial vehicle main part 1 when aerial operating duration is longer, the 1 inside temperature of unmanned aerial vehicle main part can rise, through the design of arc opening and with the wind groove 13 that mounting groove 7 is linked together, unmanned aerial vehicle main part 1 can make the wind flow lead to the inside of mounting groove 7 when the operation, from this to the 1 inside cooling of unmanned aerial vehicle main part, the filter screen 17 that sets up between wind groove 13 and the mounting groove 7 simultaneously, can filter the dust that contains in the wind flow, avoid the too high and dust normal operating that influences sensor body 5 too much of temperature.
The inner wall of cover 2 is seted up quantity and is two and with solid fixed ring 6 phase-match and can contact with solid fixed ring 6 slow down the groove, cover 2 upset and with unmanned aerial vehicle main part 1 between the closure, gu fixed ring 6's top can enter into to the inside that slows down the groove, cover 2 gives solid fixed ring 6 pressure simultaneously, increase the fixed action to sensor body 5, can prevent cover 2 and sensor body 5 direct contact simultaneously again, damage sensor body 5.
The working principle of the invention is as follows: when the sensor body 5 needs to be installed inside the installation groove 7, the sensor body 5 is firstly placed on the surface of the clamping rod 12, the sensor body 5 is downwards displaced by a distance by pressing the sensor body 5 downwards, the meshing block fixedly connected with the surface of the clamping rod 12 can be clamped inside the meshing port 9 during displacement, the sensor body 5 is preliminarily limited and fixed, the protection block 18 is in contact with the sensor body 5 during clamping, the protection block 18 can play a preliminary buffering role for the sensor body 5, the damage of the sensor body 5 under the action of vibration caused by the vibration of the body of the unmanned aerial vehicle main body 1 during operation is prevented, the normal operation of the sensor body 5 is influenced, when the sensor body 5 is installed inside the installation groove 7 through the clamping rod 12 and the meshing port 9 matched with the meshing block, the fixing ring 6 can be sleeved on the surface of the sensor body 5, and the fixing ring 6 is caught to the inside of the fixing groove 10, thereby performing the position-limiting fixing of the sensor body 5 again, and the stability of the sensor body 5 during installation is increased, a reverse impact force can be generated when the unmanned aerial vehicle main body 1 is operated and falls to the ground, the buffer plate 11 can be displaced up and down in the chute by the slide block through the spring 14, thereby slowing down the reverse impact force generated when the unmanned aerial vehicle falls to the ground, avoiding the damage of the sensor body 5 caused by overlarge impact and influencing the normal operation of the sensor body 5, leading the wind flow to the inside of the mounting groove 7 when the unmanned aerial vehicle main body 1 operates, thereby cooling the interior of the unmanned aerial vehicle main body 1, meanwhile, a filter screen 17 is arranged between the air duct 13 and the mounting groove 7, the dust contained in the wind flow can be filtered, and the normal operation of the sensor body 5 is prevented from being influenced by overhigh temperature and excessive dust.
The foregoing is only a preferred embodiment of the present invention; the scope of the invention is not limited thereto. Any person skilled in the art should be able to cover the technical scope of the present invention by equivalent or modified solutions and modifications within the technical scope of the present invention.
Claims (9)
1. The utility model provides a high performance temperature sensor for unmanned aerial vehicle, includes unmanned aerial vehicle main part (1) and cover (2), cover (2) are located the top of unmanned aerial vehicle main part (1) and are articulated mutually with unmanned aerial vehicle main part (1), its characterized in that: mounting groove (7) have been seted up to the inner wall of unmanned aerial vehicle main part (1), the inner wall movable mounting of mounting groove (7) has sensor body (5), the installing port that is linked together with mounting groove (7) is seted up at the top of unmanned aerial vehicle main part (1), the fixed surface of cover (2) is connected with installing port assorted fixed block (3), the outer fringe and the inner wall of fixed block (3) contact with the surface of the inner edge of installing port and sensor body (5) respectively, the inner wall sliding connection of mounting groove (7) has buffer board (11), the top of buffer board (11) articulates have card pole (12) that quantity is two and with sensor body (5) looks joint, air duct (13) that are linked together and are evenly distributed with mounting groove (7) are seted up to the inner wall bottom of unmanned aerial vehicle main part (1).
2. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 1, wherein: the sensor is characterized in that the top of the buffer plate (11) is fixedly connected with a hinged seat (15) hinged to the bottom end of the clamping rod (12), the surface of the sensor body (5) is provided with four engaging openings (9), two opposite sides of the clamping rod (12) are fixedly connected with an engaging block and a protecting block (18) contacted with the surface of the sensor body (5), and the engaging block is matched with the engaging openings (9).
3. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 2, wherein: articulated seat (15)'s inner wall fixedly connected with torsional spring (19), two articulated groove (16) have all been seted up to the inner wall of kelly (12), the both ends of torsional spring (19) run through articulated seat (15) respectively and with the inner wall fixed connection in both sides articulated groove (16).
4. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 1, wherein: the sensor body (5) the surface seted up quantity be two fixed slot (10), the inner wall both sides of mounting groove (7) all are provided with solid fixed ring (6), gu fixed ring (6) run through buffer board (11) and the cover locate the surface of sensor body (5), and the inner edge of solid fixed ring (6) and the inner wall looks joint of fixed slot (10).
5. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 4, wherein: the vertex height of the fixing ring (6) is lower than that of the sensor body (5), and the fixing ring (6) is a rubber component.
6. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 1, wherein: fixedly connected with evenly distributed's spring (14) between the bottom of buffer board (11) and the inner wall bottom of mounting groove (7), the equal fixedly connected with slider in both ends of buffer board (11), the spout that is linked together with slider phase-match and with mounting groove (7) is seted up to the inner wall of unmanned aerial vehicle main part (1).
7. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 1, wherein: the both ends opening part of wind groove (13) is the arc, and wind groove (13) are located buffer board (11) under, fixedly connected with filter screen (17) between wind groove (13) and mounting groove (7).
8. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 1, wherein: cover (2) the surperficial from left to right fixedly connected with sealing strip (4) and quantity be two joint piece in proper order, the inner wall both sides of unmanned aerial vehicle main part (1) seted up respectively with sealing strip (4) and joint piece assorted seal groove and bayonet socket (8).
9. The high-performance temperature sensor for the unmanned aerial vehicle according to claim 8, wherein: the inner wall of the machine cover (2) is provided with two retarding grooves which are matched with the fixing ring (6) and can be contacted with the fixing ring (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110049663.2A CN112357104B (en) | 2021-01-14 | 2021-01-14 | High-performance temperature sensor for unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110049663.2A CN112357104B (en) | 2021-01-14 | 2021-01-14 | High-performance temperature sensor for unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN112357104A true CN112357104A (en) | 2021-02-12 |
| CN112357104B CN112357104B (en) | 2021-05-21 |
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| CN202110049663.2A Active CN112357104B (en) | 2021-01-14 | 2021-01-14 | High-performance temperature sensor for unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113525664A (en) * | 2021-09-16 | 2021-10-22 | 南京钢果电子科技有限公司 | Modularized sensor and unmanned aerial vehicle adaptive to same |
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2021
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| CN206514864U (en) * | 2016-11-29 | 2017-09-22 | 上海拓攻机器人有限公司 | A kind of unmanned plane inertial measuring unit and the unmanned plane containing it |
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| CN112357104B (en) | 2021-05-21 |
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