CN105442960B - Quick-locking device for hatch cover of unmanned aerial vehicle - Google Patents
Quick-locking device for hatch cover of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105442960B CN105442960B CN201510993670.2A CN201510993670A CN105442960B CN 105442960 B CN105442960 B CN 105442960B CN 201510993670 A CN201510993670 A CN 201510993670A CN 105442960 B CN105442960 B CN 105442960B
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- CN
- China
- Prior art keywords
- hatchcover
- bearing pin
- mounting seat
- locking device
- unmanned plane
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- E—FIXED CONSTRUCTIONS
- E05—LOCKS; KEYS; WINDOW OR DOOR FITTINGS; SAFES
- E05C—BOLTS OR FASTENING DEVICES FOR WINGS, SPECIALLY FOR DOORS OR WINDOWS
- E05C19/00—Other devices specially designed for securing wings, e.g. with suction cups
- E05C19/007—Latches with wedging action
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
- B64C1/1446—Inspection hatches
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Seats For Vehicles (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention discloses a quick-locking device for a hatch cover of an unmanned aerial vehicle. The quick-locking device comprises a hatch cover installation seat, a lock cylinder, and a body installation seat, wherein the lock cylinder comprises a pin shaft arranged in the hatch cover installation seat in a penetrating manner, springs arranged on the pin shaft in a penetrating manner, and lock pins detachably installed on the pin shaft, a spring seat is arranged on the pin shaft, and the springs are installed between the spring seat and the lock pins; a seat hole, and lock grooves for penetration of the pin shaft and the lock pins are sequentially formed in the inner wall of the body installation seat from one end to the other end; a return step is formed between the seat hole and the lock grooves; and one end close to the lock pins, of the hatch cover installation seat, is inserted in the seat hole, the lock pins are clockwise rotated 90 degrees, the springs are abutted between the spring seat and the return step, and the lock pins are abutted in concave grooves of the lock grooves under actions of restoring forces of the springs. According to the invention, locking and unlocking steps are simplified, time is saved, and the operation is more convenient and rapid.
Description
Technical field
The present invention relates to unmanned air vehicle technique, the especially a kind of fast locking device of unmanned plane hatchcover.
Background technology
At present, the mounting means of the hatchcover of Small Civil unmanned plane, generally based on screw fastening means, this hatchcover
Fastening means is required for using instrument, directly affects system rapidity so that the take-down time of hatchcover is longer.Unmanned plane is in debugging
In the operation process of outfield, need Jing often to open hatchcover, changed and safeguarded battery, check Aerial Electronic Equipment, download flight number
According to etc., for bolt connection, Jing often dismountings easily cause hatchcover covering and damage and the pre-buried screw thread damage of fuselage, need to carry out
Maintenance；Simultaneously this bolted mode dismounts inconvenience, needs specific purpose tool to carry out the fastening of bolt and disassemble, ordinary circumstance
Under, the locking of hatchcover and fuselage or disassemble to separate and need 3-5 minutes.
The application advantage of unmanned plane is that it is compared someone's aircraft utilization and gets up convenient and swift, safe and reliable, but cabin
Lid is not enough with the loaded down with trivial details, reliability of the existing connected mode assembling of fuselage etc., and the deficiency of these operability performances hinders nobody
The category and prospect of machine application.Therefore we need hatchcover and the connected mode of fuselage accomplish as much as possible it is simple, fast with can
Lean on, be to open fixed-wing unmanned plane the offer in market is provided effectively to ensure.
The content of the invention
The present invention provides a kind of unmanned plane hatchcover fast locking device, for overcoming defect of the prior art, simple structure, behaviour
Make quick, reliable in action.
The present invention provides a kind of unmanned plane hatchcover fast locking device, including：
Hatchcover mounting seat, on hatchcover, is cylindrical in shape；
Lock core, including the bearing pin being located in the hatchcover mounting seat, the spring being located on the bearing pin and detachable
On the bearing pin and the lock pin that the hatchcover mounting seat comes off from the bearing pin is prevented, there is spring on the bearing pin
Seat, the spring is arranged between the spring base and lock pin；
Fuselage mounting seat, on the fuselage, is cylindrical in shape, and inwall has and the cabin successively from one end to the other end
Bore that lid mounting seat outer wall is adapted and the locked groove penetrated for the bearing pin and lock pin；Shape between the bore and the locked groove
Into there is reset step；
The hatchcover mounting seat is inserted in the bore near one end of the lock pin, and the spring is contradicted in the spring
Between seat and the reset step, the lock pin contradicts the end face extended in the locked groove under the restoring force effect of the spring
On.
Wherein, it is additionally provided with along the end face that the locked groove extends in the fuselage mounting seat and turns for limiting the lock pin
The stopper slot of dynamic angle, the cross section of the stopper slot includes the centre bore being adapted with the bearing pin and two with regard in described
Two sectors that the center of circle in heart hole is symmetric, the fan-shaped diameter is identical with the length of the lock pin.
Further, the fan-shaped central angle is 90 degree.
Particularly, it is provided with along the end face that the locked groove extends in the fuselage mounting seat and turns for limiting the lock pin
Dynamic groove, the angle between the groove and the locked groove is 90 degree.
Wherein, described bearing pin one end has the rotary head for being easy to rotate, and the protruding hatchcover of the rotary head is installed
Seat.
Further, the rotary head is in regular prism shape.
Wherein, the rotary head is provided in the sliding piece on the bearing pin.
Further, the hatchcover mounting seat has end cap near one end of the rotary head, has on the end cap
The perforating coordinated with the bearing pin.
Particularly, the spring base is provided in the limited step on the bearing pin, and in the hatchcover mounting seat.
The fast locking device of unmanned plane hatchcover that the present invention is provided, when using, bearing pin is installed first one end insertion cabin of lock pin
In lid mounting seat, then spring is penetrated on bearing pin from hatchcover mounting seat bottom opening end, then lock pin is installed to into bearing pin bottom
Hole in, complete the installation of fast locking device, during locking, hatchcover is fastened on fuselage, hatchcover mounting seat bottom fall into fuselage peace
In the bore of dress seat, rotating pin so that lock pin is aligned with locked groove promotes bearing pin to cause in lock pin and bearing pin insertion locked groove, this
When, spring is compressed between spring base and the reset step of locked groove upper end, treats that lock pin and bearing pin pass through locked groove, again rotational pin
Axle causes lock pin and locked groove staggered positions, unclamps bearing pin, and lock pin is stuck under the action of the spring fuselage mounting seat bottom, locks cabin
Lid and fuselage；When needing unblock, press down on and rotating pin so that lock pin coordinates with locked groove, and in the effect of spring-return power
Under, locked groove is upward through automatically；Hatchcover mounting seat departs from fuselage mounting seat；Whole process is only needed to tens seconds, relative to
Prior art, simplifies locking and unlocked step, has saved the time, more convenient, quick.
Description of the drawings
Fig. 1 is the stereogram of the fast locking device of unmanned plane hatchcover that the embodiment of the present invention one is provided；
Fig. 2 is the front view of the fast locking device of unmanned plane hatchcover that the embodiment of the present invention provides；
Fig. 3 is the right view of Fig. 2；
Fig. 4 is to sectional view in Fig. 3 along A-A；
Fig. 5 is the stereogram one of the fast locking device of unmanned plane hatchcover that the embodiment of the present invention two is provided；
Fig. 6 is the stereogram two of the fast locking device of unmanned plane hatchcover that the embodiment of the present invention provides two；
Fig. 7 is the front view of the fast locking device of unmanned plane hatchcover that the embodiment of the present invention provides two；
Fig. 8 is the left view of Fig. 7；
Fig. 9 is the right view of Fig. 7；
Figure 10 is along B-B direction sectional view in Fig. 7.
Specific embodiment
Embodiment one
Referring to Fig. 1-4, the present invention provides a kind of unmanned plane hatchcover fast locking device, including：
Hatchcover mounting seat 1, it is cylindrical on hatchcover；Open at one end, the other end has end cap 11, in end cap 11
The heart has the hole worn for bearing pin 21, is tight fit between end cap 11 and bearing pin 21, can prevent dust and in short-term rainproof function；
Lock core 2, including the bearing pin 21 being located in hatchcover mounting seat 1, the spring 22 being located on bearing pin 21 and detachable
Lock pin 23 on bearing pin 21, has spring base 24 on bearing pin 21, spring 22 is arranged between spring base 24 and lock pin 23；
The one end of bearing pin 21 has the rotary head 21a for being easy to rotate, the protruding hatchcover mounting seats 1 of rotary head 21a, and rotary head 21a is in just
It is prismatic, it is annular knurl in positive six prismsby, or outer wall compacting in the present embodiment, it is easy to artificial operation, can be with bearing pin 21
The sliding piece of upper setting, drives bearing pin 21 to rotate by rotating sliding piece；
Spring base 24 is located in hatchcover mounting seat, may be mounted on bearing pin 21, it is also possible to by arranging on bearing pin 21
Limited step, by limited step movement of the spring 22 on bearing pin 21 is limited, and the latter is adopted in the present embodiment, is installed more square
Just.
Fuselage mounting seat 3, on fuselage, is cylindrical in shape, and inwall has successively from one end to the other end to be installed with hatchcover
Bore 31 that 1 outer wall of seat is adapted, the locked groove 32 penetrated for bearing pin 21 and lock pin 23, be formed between bore 31 and locked groove 32 it is multiple
Position step 3a；The shape of locked groove 32 is adapted in oblateness, the global shape after installing with lock pin 23 and bearing pin 21, lock pin 23 and
In the insertion locked groove 32 of bearing pin 21, it is impossible to rotate, can only be along the axial movement of locked groove 32；
In addition reset step may also be arranged on the inside of hatchcover mounting seat 1, and such spring 22 will be compressed in spring base
Between 24 and the reset step of hatchcover mounting seat, when bearing pin 21 is pressed, spring 22 further receives compression, the insertion locked groove of lock pin 23
After 32, rotating pin 21 causes lock pin 23 to turn over an angle, staggers with the angle of locked groove 32, unclamps bearing pin 21, and lock pin 23 exists
The restoring force effect of spring 22 is lower to be contradicted on the end face 3b extended in locked groove 32.
In the open one end insertion bore 31 of hatchcover mounting seat 21, spring 22 contradict spring base 24 and reset step 3a it
Between, lock pin 23 spring 22 restoring force effect under contradict locked groove 32 extend end face 3b on, in order to prevent vibration processes in
Lock pin 23 and the relative motion of fuselage mounting seat 1, cause unblock, can arrange and the shape of lock pin 23 on the end face 3b that locked groove 32 extends
The groove being adapted, after lock pin 23 is passed from locked groove 32, unclamps bearing pin 21, and lock pin 23 blocks and set under the effect of the restoring force of spring 22
In groove.
The fast locking device of unmanned plane hatchcover that the present invention is provided, when using, bearing pin 21 is installed first one end of lock pin 23 from
Insert in hatchcover mounting seat 1 in hole with end cap 11, then spring 22 is penetrated into bearing pin from the opening end of the bottom of hatchcover mounting seat 1
On 21, then lock pin 23 is installed in the hole of the bottom of bearing pin 21, completes the installation of fast locking device, during locking, hatchcover is fastened
On fuselage, the opening end of the bottom of hatchcover mounting seat 1 and the bottom of lock pin 23 and bearing pin 21 both fall within the seat of fuselage mounting seat
Kong Zhong, rotating pin 21 so that lock pin 23 is aligned with locked groove 32, promote bearing pin 21 to cause lock pin 23 and the insertion locked groove 32 of bearing pin 21
Interior, now, spring 22 is compressed between spring base 24 and the reset step 3a of the upper end of locked groove 32, treats that lock pin 23 and bearing pin 21 are worn
Locked groove 32 is crossed, again rotating pin 21 causes lock pin 23 and the staggered positions of locked groove 32, unclamp bearing pin 21, lock pin 23 is in spring 22
It is pressed under effect in the groove on the end face 3b that fuselage mounting seat 1 extends along locked groove 32, locks hatchcover and fuselage；Need unblock
When, press down on and rotating pin 21 so that lock pin 23 departs from the groove on locked groove 32, and under the effect of the restoring force of spring 22,
Automatically it is upward through locked groove 32；And be pressed on reset step 3a, hatchcover mounting seat 1 departs from fuselage mounting seat 3；Whole process is only
Several seconds are needed, relative to prior art, locking and unlocked step is simplified, has been saved the time, it is more convenient, quick.
Embodiment two
Referring to Fig. 5-10, on the basis of embodiment one, the one end extended along locked groove 32 in fuselage mounting seat 3 also sets up
There is the stopper slot 33 for limiting the rotational angle of lock pin 23, the cross section of stopper slot 33 includes the centre bore being adapted with bearing pin 21
Two sector 33b that 33a and two center of circle with regard to centre bore is symmetric, the diameter of fan-shaped 33b and the length of lock pin 23
It is identical.The central angle of fan-shaped 33b between 60 degree～120 degree, preferably 90 degree.The end face extended along locked groove in fuselage mounting seat 3
The groove 3c for limiting the rotation of lock pin 23 is provided with 3b, the angle between groove 3c and locked groove 32 is 90 degree.
Pressure bearing pin 21 simultaneously rotates clockwise 90 °, and locked soon, bearing pin 21 rotates counterclockwise 90 ° and upsprings, and fast lock is opened.
When needing to lock hatchcover, hatchcover mounting seat 1 is directed at into fuselage mounting seat 3 and is inserted so that hatchcover is tight with fuselage
Contact；Then manual depression bearing pin 21 is passed through from locked groove 32 in fuselage mounting seat 3, is turned clockwise 90 ° and is put down lock pin 23 bottom of to,
Upspring using the elastic force of spring 22, during the groove 3c of coil insertion device body mounting seat is at this moment corrected under lock pin 23, realize fast lock locking.When
When needing to unlock, manual depression bearing pin 21 so that lock pin 23 leaves groove 3c turns counterclockwise 90 °, using the elastic force bullet of spring 22
Go out so that lock pin 23 leaves locked groove 32, realize unlocking.
The locking design of stopper slot 33 of fuselage mounting seat 3, by devise in the fuselage mounting seat 3 90 degree spacing and
One stopper slot with the half of the length of lock pin 23 as radius, when dexterously allowing bearing pin 21 and lock pin 23 to move to locked position from
In being so absorbed in groove 3c, the elastic force protection of compression spring is added, serve the spacing fixation to bearing pin 21, prevented because unmanned plane
During wide-angle flight in the air, cause the positional deviation of bearing pin 21 and lock pin 23, occur without unblock, hatchcover departs from fuselage.
Existing small and medium size unmanned aerial vehicles hatchcover adopts the mode being bolted connection with the connection majority of fuselage, when needing
Check the reliability of locking quarter, and need specific purpose tool auxiliary to be attached locking and disassemble separation, it is complicated, time-consuming (usual
In 3-5 minutes), effort.But the connected mode of lock pin plug of the present invention, it is only necessary to manual rotation bearing pin so as to by 90 °
Lower rotary motion is just capable of achieving, and locking and tear down operations are usually no more than 30 seconds, it is simple, save time, it is laborsaving.
The invention is verified through practical application, applied in the model optimization of certain type multi-rotor unmanned aerial vehicle, exists so far
More than 1 year used in more than five framves remodeling unmanned plane, according to the testing experiment sum man that more than 100 sorties, more than 40 hours are navigated at present
Type unmanned plane user's is actually used, feeds back the equipment safety reliability, convenient and swift, and assembling is compared original bolt with hatchcover and connected
The mode time-consuming 3-5 minutes for connecing are reduced to 30 seconds, but also without being aided in using instrument, connection reliability, more convenient and quicker.
Test and practice result show that quick locking structure realizes that hatchcover is safe and reliable with fuselage, conveniently and efficiently locks or disassemble and separate
Purpose.
Claims (9)
1. the fast locking device of a kind of unmanned plane hatchcover, it is characterised in that include：
Hatchcover mounting seat, on hatchcover, is cylindrical in shape；
Lock core, including the bearing pin being located in the hatchcover mounting seat, the spring being located on the bearing pin and detachable installation
On the bearing pin and the lock pin that the hatchcover mounting seat comes off from the bearing pin is prevented, there is spring base on the bearing pin,
The spring is arranged between the spring base and lock pin；
Fuselage mounting seat, on the fuselage, is cylindrical in shape, and inwall has successively and hatchcover peace from one end to the other end
The dress seat outer wall bore being adapted and the locked groove penetrated for the bearing pin and lock pin；It is formed between the bore and the locked groove
Reset step；
The hatchcover mounting seat is inserted in the bore near one end of the lock pin, the spring contradict the spring base with
Between the reset step, the lock pin is contradicted on the end face extended in the locked groove under the restoring force effect of the spring.
2. the fast locking device of unmanned plane hatchcover according to claim 1, it is characterised in that along described in the fuselage mounting seat
The stopper slot for limiting the key rotation angle, the transversal bread of the stopper slot are additionally provided with the end face that locked groove extends
Two sectors that the centre bore that is adapted with the bearing pin and two centers of circle with regard to the centre bore are symmetric are included, it is described
Fan-shaped diameter is identical with the length of the lock pin.
3. the fast locking device of unmanned plane hatchcover according to claim 2, it is characterised in that the fan-shaped central angle is 90
Degree.
4. the fast locking device of unmanned plane hatchcover according to claim 3, it is characterised in that along described in the fuselage mounting seat
The groove for limiting the key rotation, the angle between the groove and the locked groove are provided with the end face that locked groove extends
It is 90 degree.
5. the fast locking device of unmanned plane hatchcover according to claim 4, it is characterised in that described bearing pin one end has is easy to rotation
The rotary head for turning, the protruding hatchcover mounting seat of the rotary head.
6. the fast locking device of unmanned plane hatchcover according to claim 5, it is characterised in that the rotary head is in regular prism shape.
7. the fast locking device of unmanned plane hatchcover according to claim 6, it is characterised in that the rotary head is provided in described
Sliding piece on bearing pin.
8. according to the arbitrary described fast locking device of unmanned plane hatchcover of claim 5-7, it is characterised in that the hatchcover mounting seat is leaned on
One end of the nearly rotary head has end cap, has the perforating coordinated with the bearing pin on the end cap.
9. the fast locking device of unmanned plane hatchcover according to claim 8, it is characterised in that the spring base is provided in described
Limited step on bearing pin, and in the hatchcover mounting seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510993670.2A CN105442960B (en) | 2015-12-25 | 2015-12-25 | Quick-locking device for hatch cover of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510993670.2A CN105442960B (en) | 2015-12-25 | 2015-12-25 | Quick-locking device for hatch cover of unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105442960A CN105442960A (en) | 2016-03-30 |
| CN105442960B true CN105442960B (en) | 2017-05-10 |
Family
ID=55553548
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510993670.2A Active CN105442960B (en) | 2015-12-25 | 2015-12-25 | Quick-locking device for hatch cover of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105442960B (en) |
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| CN107444607A (en) * | 2017-08-14 | 2017-12-08 | 北京奇正数元科技股份有限公司 | The rotation fast-open type hatchcover of small-sized unmanned plane |
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| CN111086620B (en) * | 2019-12-24 | 2022-09-20 | 中国航空工业集团公司西安飞机设计研究所 | Multi-position integrated handle control mechanism |
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| CN112591075B (en) * | 2021-01-04 | 2023-03-07 | 航天时代飞鸿技术有限公司 | Airborne antenna folding transportation and fast-assembling locking mechanism and unmanned aerial vehicle |
| CN113417920B (en) * | 2021-06-30 | 2022-09-06 | 重庆建安仪器有限责任公司 | But multipurpose auto-lock quick detach device |
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| EP1249570A1 (en) * | 2001-04-12 | 2002-10-16 | bulthaup GmbH & Co. KG | Closure device |
| CN102348861A (en) * | 2009-03-11 | 2012-02-08 | 布尔加建筑业和贸易有限公司 | Lockable handle/grip system with coupling for sliding windows |
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| Publication number | Publication date |
|---|---|
| CN105442960A (en) | 2016-03-30 |
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