CN109969401A - Mechanical multi-rotor aerocraft is in the air from release device and method for releasing - Google Patents
Mechanical multi-rotor aerocraft is in the air from release device and method for releasing Download PDFInfo
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- CN109969401A CN109969401A CN201910232112.2A CN201910232112A CN109969401A CN 109969401 A CN109969401 A CN 109969401A CN 201910232112 A CN201910232112 A CN 201910232112A CN 109969401 A CN109969401 A CN 109969401A
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- spring
- ejection
- rotor aerocraft
- clamping device
- rotor
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 230000008602 contraction Effects 0.000 claims abstract description 10
- 230000005484 gravity Effects 0.000 claims description 10
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000007599 discharging Methods 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 4
- 238000003756 stirring Methods 0.000 description 3
- 230000009187 flying Effects 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/20—Launching, take-off or landing arrangements for releasing or capturing UAVs in flight by another aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Remote Sensing (AREA)
- Clamps And Clips (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of mechanical multi-rotor aerocrafts in the air from release device and method for releasing, and mechanical multi-rotor aerocraft therein is in the air from release device, including support platform, clamping device, trigger mechanism and locking and relieving mechanism；Locking and relieving mechanism include the first spring mountings, the first spring and lock device；Trigger mechanism includes frizzen, articulation piece and bar；Clamping device lower end is fixedly connected with aircraft, and clamping device upper end is equipped with locking hole；The mechanical multi-rotor aerocraft is in the air from method for releasing, comprising: A. aircraft rotor rotary dial frizzen is rotated around articulation piece；B. bar leaves the first spring；C. the first spring contraction drives lock device to leave locking hole.The present invention can be carried remotely, discharge multi-rotor aerocraft.The present invention is suitable for using when multi-rotor aerocraft executes flight time longer aerial mission, for mechanically discharging the multi-rotor aerocraft being fixed on Fixed Wing AirVehicle.
Description
Technical field
The invention belongs to the aerial release tech field of multi-rotor aerocraft, specifically a kind of mechanical more rotor flyings
Device is in the air from release device and method for releasing.
Background technique
Multi-rotor aerocraft has structure simple, the advantages of flexible operation, can be advanced, be retreated, gone up and down, translate etc. and is winged
Row state can complete the aerial mission of numerous complicated.But since the flight time of multi-rotor aerocraft is usually at 15 minutes
To between 1 hour, the flight time is limited, for mission area beyond be not available in the case where air mileage (such as to traffic every
The case where disconnected remote disaster area detects, the investigation of remote battle field etc.).Existing multi-rotor aerocraft, which takes off, is all ground
Face is horizontal positioned to be discharged, and delivery mode is single, the case where for exceeding multi-rotor aerocraft air mileage, can not pass through it
Its mode carries out long-range aerial dispensing.
Summary of the invention
It is existing in the prior art above insufficient to solve, the present invention is intended to provide a kind of mechanical multi-rotor aerocraft is empty
In from release device and method for releasing, to achieve the purpose that remotely to carry, discharge multi-rotor aerocraft.
To achieve the above object, the technical solution adopted in the present invention is as follows: a kind of mechanical multi-rotor aerocraft is aerial
It including the support platform being placed in above aircraft further include clamping device, trigger mechanism and locking and release from release device
Mechanism；
One, locking and relieving mechanism
Locking and relieving mechanism include the first spring mountings, the first spring and lock device, and the first spring one end is fixedly connected on
On first spring mountings, the first spring other end is fixedly connected with locking device；
Two, trigger mechanism
Trigger mechanism includes frizzen, articulation piece and the bar for being fixed on frizzen upper end, and frizzen is placed in aircraft rotor
Between blade, the articulation piece being fixed in support platform is articulated on frizzen, and bar, which passes through the first spring, protects the first spring
Tensional state is held, bar drives bar to leave the first spring around hinged place rotation makes the first spring contraction；
Three, clamping device
Clamping device lower end is fixedly connected with aircraft, and clamping device upper end is equipped with the locking hole being laterally extended, and locking hole can make
It is passed through with the lock device being connected in the first spring of tensional state, lock device leaves locking when the first spring is in contraction state
Hole.
It as an improvement of the present invention, further include the ejection mechanism being placed in above clamping device, ejection mechanism includes ejection bullet
Spring and the ejection-spring fixing piece being fixedly connected with ejection-spring upper end；When lock device passes through locking hole, ejection-spring lower end
It is in contact with clamping device, ejection-spring is in compressive state and is placed in above clamping device.
As a further improvement of the present invention, clamping device is placed on ejection-spring fixing piece lower part, and ejection-spring is fixed
Part is equipped with the second through-hole corresponding with locking hole, and lock device can pass through locking hole through the second through-hole；First spring mountings
It is equipped with the first through hole for making bar pass through the first spring.
Improved as another kind of the invention, clamping device passes through support platform and extends up and down along the vertical direction, locking with
Relieving mechanism and locking hole are placed in above support platform and left and right extends in the horizontal direction, the bar being placed in above support platform
Extending direction and the first telescopic spring direction are perpendicular, and frizzen passes through support platform and extends up and down along the vertical direction.
As other improvement of the invention, clamping device is rod-shaped, the first spring mountings and ejection bullet with lock device
Spring fixing piece is tubulose, and articulation piece is pin shaft, and pin shaft axis direction is parallel to the first telescopic spring direction.
It from release device and is realized in the air the present invention also provides a kind of using above-mentioned mechanical multi-rotor aerocraft
Mechanical multi-rotor aerocraft is in the air from method for releasing, and its technical solution is as follows:
A kind of mechanical multi-rotor aerocraft is in the air from method for releasing, comprising the following steps:
A. aircraft rotor rotary dial frizzen is rotated around articulation piece；
B. articulation piece drives bar rotation, is in the bar of the first spring of tensional state to make to have passed through and leaves the first spring；
C. the first spring contraction drives the lock device for having passed through locking hole to leave locking hole, clamping device and aircraft and makees in gravity
With lower release.
It as an improvement of the present invention, further include that lock device leaves locking hole in step C, ejection-spring stretches downwards promotion
Clamping device, clamping device and aircraft discharge under ejection-spring elastic force and gravity.
As a further improvement of the present invention, the frizzen that A. aircraft rotor rotary dial vertical direction extends is around hinged
Part rotates backward；
B. articulation piece drives bar to rotate forward, is in the bar of the first spring of tensional state to make to have passed through and leaves the first bullet
Spring；
C. the first spring contraction drives the lock device for having passed through locking hole to leave locking hole, and ejection-spring stretches downwards promotion clamping
Mechanism, clamping device and aircraft discharge under ejection-spring elastic force and gravity.
It improves as another kind of the invention, in step A, is fixed in the air from release device through mechanical multi-rotor aerocraft
Multi-rotor aerocraft rotor rotational on Fixed Wing AirVehicle, the rotor wing rotation of multi-rotor aerocraft stir frizzen around hinged
Part rotation.
Due to the adoption of the above technical solution, mechanical multi-rotor aerocraft of the invention from release device and is released in the air
Put method compared with prior art, acquired beneficial effect is:
The present invention makes the mechanically voluntarily triggering release of more rotor Fixed Wing AirVehicles, in the same of multi-rotor aerocraft starting
When discharge aircraft itself, guarantee that aircraft security is detached from release, can realize long-range carrying, release multi-rotor aerocraft
Purpose；
The present invention can fix multi-rotor aerocraft by setting clamping device in the sky；The lock being laterally arranged in clamping device
Only hole, when lock device can be made to pass through locking hole, limitation multi-rotor aerocraft is in longitudinal movement, with the more rotor flyings of fixation
Device；
The present invention can be rotated automatic trigger frizzen by multi-rotor aerocraft paddle, be recycled by setting trigger mechanism
Lever principle makes bar be detached from locking and relieving mechanism, and multi-rotor aerocraft flight starting and the release of aircraft can be made same
Shi Jinhang；
The present invention makes lock device be detached from locking hole by setting locking and relieving mechanism under the effect of the first spring contraction power, with
Multi-rotor aerocraft is discharged in the sky, is not necessarily to power supply, release is voluntarily triggered using mechanical system, it is safe and reliable, practical；
The present invention can guarantee multi-rotor aerocraft in ejection-spring bullet by setting ejection mechanism using ejection-spring elastic force
It is smoothly discharged under power and gravity；
The present invention carries multi rack multi-rotor aerocraft using long-range Fixed Wing AirVehicle and reaches mission area overhead, discharges in the sky
Multi-rotor aerocraft, then the scheme for making multi-rotor aerocraft carry out aerial mission；By such manner, more rotors are not only solved
Aircraft can not distance flight the problem of, also overcome Fixed Wing AirVehicle can not flexible flight the shortcomings that.
The present invention is suitable for using when multi-rotor aerocraft executes flight time longer aerial mission, for that will be fixed on
Multi-rotor aerocraft on Fixed Wing AirVehicle mechanically discharges.
Detailed description of the invention
With reference to the accompanying drawing and specific embodiment makees more detailed description to the present invention.
Fig. 1 is the schematic perspective view of the embodiment of the present invention 1；
Fig. 2 is the main view of the embodiment of the present invention 1；
Fig. 3 is the top view of the embodiment of the present invention 1.
In figure: 1, support platform；2, clamping device；4, the first spring mountings；5, the first spring；6, lock device；7, it touches
Send out bar；8, bar；9, articulation piece；10, ejection-spring；11, ejection-spring fixing piece；12, multi-rotor aerocraft ontology；13, more
Rotor craft blade.
Specific embodiment
A kind of mechanical multi-rotor aerocraft of embodiment 1 is in the air from release device
As shown in Figure 1 to Figure 3, the present embodiment include support platform 1, clamping device 2, ejection mechanism, trigger mechanism and locking with
Relieving mechanism, support platform 1 are the rectangle tabular being placed in above multi-rotor aerocraft, and support platform 1 is fixedly attached to solid
Determine below rotor aircraft.
One, clamping device 2
Clamping device 2 is for fixing multi-rotor aerocraft ontology 12.Clamping device 2 passes through support through the centre bore of support platform 1
Platform 1, clamping device 2 are the rod-shaped of (gravity direction) extension along the vertical direction, and the lower end of clamping device 2 is fixedly connected on more rotations
On rotor aircraft ontology 12, the upper end of clamping device 2 offers locking hole, and locking hole is to extend transversely (i.e. perpendicular to gravity
Direction) through-hole, be placed in the top of support platform 1 and left and right extend the locking hole energy in (with reference to the direction in Fig. 1) in the horizontal direction
Pass through lock device 6.
Two, ejection mechanism
Ejection mechanism, which is used to pop up multi-rotor aerocraft using ejection elastic force, to be discharged.Ejection mechanism is placed in 2 top of clamping device,
Ejection mechanism includes the ejection-spring fixing piece 11 of ejection-spring 10 and fixed ejection-spring 10.
Ejection-spring fixing piece 11 is circular tube shaped, and the upper end of clamping device 2 is placed on 11 lower part of ejection-spring fixing piece, bullet
Spring mountings 11 are penetrated equipped with the second through-hole corresponding with locking hole, lock device can pass through locking hole through the second through-hole, make
Lock device 6 is also cross ejection-spring fixing piece 11 and clamping device 2.
When lock device 6 passes through the second through-hole, locking hole, place is equipped between clamping device 2 and ejection-spring fixing piece 11
In the ejection-spring 10 of compressive state.That is, ejection-spring 10 is flexible along the vertical direction (gravity direction), ejection-spring 10
Upper end be fixedly connected on the upper end of ejection-spring fixing piece 11, the lower end of ejection-spring 10 connects with the top surface of clamping device 2
Touching.And when lock device 6 leaves the second through-hole, locking hole, i.e., lock device 6 no longer fixing and holding mechanism 2 when, clamping device 2 exists
It is discharged downwards under 10 elastic force of ejection-spring and self gravitation effect.
Three, trigger mechanism
Trigger mechanism is used to trigger the movement of the first spring 5 in locking and relieving mechanism.Trigger mechanism includes frizzen 7, bar 8
And articulation piece 9.
Frizzen 7 passes through support platform 1 and extends up and down along the vertical direction, and 7 lower end of frizzen is placed in multi-rotor aerocraft paddle
Between piece 13, when rotor rotational, multi-rotor aerocraft blade 13 can stir frizzen 7.Frizzen 7 is hinged by articulation piece 9
In in support platform 1, articulation piece 9 is placed in the middle and upper part of frizzen 7, and frizzen 7 is enable to rotate around articulation piece 9.The present embodiment
Middle articulation piece 9 is using the pin shaft being fixed in support platform 1, and left and right extends the central axis of pin shaft in the horizontal direction, i.e. pin shaft
Central axial direction and frizzen 7 and 8 extending direction of bar it is all vertical, the central axial direction of pin shaft is also parallel with the first bullet
The telescopic direction of spring 5.
Bar 8 is placed in the top of support platform 4, and bar 8 is vertically fixed on the upper end of frizzen 7, with 7 one of frizzen at
Type.Front and back extends bar 8 in the horizontal direction, and the extending direction of bar 8 and the telescopic direction of the first spring 5 are perpendicular.In this way, working as
When multi-rotor aerocraft blade 13 rotates and stirs frizzen 7 around the rotation of articulation piece 9, lever principle is utilized, frizzen 7 drives gear
Bar 8 is rotated around articulation piece 9, so that making to pass through the first spring 5 originally makes the first spring 5 that the bar 8 of tensional state be kept to leave the
One spring 5 no longer limits the first spring 5, and shrinks the first spring 5.
Four, locking and relieving mechanism
Locking and relieving mechanism are for locking, discharging clamping device 8.Locking and relieving mechanism are placed in 1 top of support platform, including
First spring mountings 4, the first spring 5 and lock device 6.
First spring mountings 4 are circular tube shaped for fixing the first spring 5, the first spring mountings 4, and the first spring is fixed
Part 4 is fixedly attached in support platform 1, and the first spring 5 is fixedly connected in the first spring mountings 4.The one of first spring 5
End is fixed on the first spring mountings 4, and the other end of the first spring 5 is fixedly connected with lock device 6, and lock device 6 is that can be inserted into
Being laterally extended in locking hole is rod-shaped.The central axis of first spring mountings 4, the central axis of the first spring 5, lock device
6 central axis is conllinear and left and right extends in the horizontal direction, and in other words, locking and relieving mechanism extend along horizontal cross, can join
Examine the direction in Fig. 1.Offering on first spring mountings 4 perpendicular to 5 direction of the first spring passes through trigger mechanism central stop lever 8
First through hole, bar 8 passes through the first spring mountings 4 and the first spring 5 for being placed in the first spring mountings 4, can limit
First spring 5 keeps tensional state, and certainly, bar 8 can be wrapped on the first spring 5 in tensional state, so that the first bullet
Spring 5 keeps stretching, and passes through the locking of clamping device 2 with the lock device 6 that the first spring 5 is connected when being in tensional state at this time
Hole.
In this way, when the bar 8 in trigger mechanism passes through the first spring 5 and the first spring mountings 4 through first through hole, the
One spring 5 is in tensional state, and lock device 6 passes through locking hole so that clamping device 5 to be fixed；And when in trigger mechanism
When bar 8 leaves the first through hole of the first spring 5 and the first spring mountings 4, i.e., bar 8 is no longer to the in tensional state
One spring 5 is limited, and the first spring 5 is shunk under the effect of elasticity, is driven lock device 6 to leave locking hole, is made lock device 6 no longer
Clamping device 2 is fixed, to discharge clamping device 2.
The method for releasing of the present embodiment is shown in embodiment 2.
A kind of mechanical multi-rotor aerocraft of embodiment 2 is in the air from method for releasing
The present embodiment realized from release device in the air using the mechanical multi-rotor aerocraft in embodiment 1, the present embodiment packet
Include following steps:
A. the multi-rotor aerocraft paddle being fixed in the air from release device through mechanical multi-rotor aerocraft on Fixed Wing AirVehicle
Piece 13 rotates, and the frizzen 7 that the rotor blade rotary dial vertical direction of multi-rotor aerocraft extends turns round around articulation piece 9
It is dynamic；
B. articulation piece 9 drives bar 8 to rotate forward, is in the bar 8 of the first spring of tensional state 5 to make to have passed through and leaves the
One spring 5, bar 8 no longer limit the position of the first spring 5, shrink the first spring 5 from tensional state to former long status；
C. the first spring 5, which is shunk, drives the lock device 6 for having passed through locking hole to leave locking hole, and lock device 6 no longer limits clamping machine
The position of structure 2,2 top of clamping device also no longer limit ejection-spring 10, and ejection-spring 10 restores former length；It is now in compression shape
State ejection-spring 10 stretches push clamping device 2 downwards, and clamping device 2 and multi-rotor aerocraft are in 10 elastic force of ejection-spring and again
The lower release of power effect.
Claims (9)
1. a kind of mechanical multi-rotor aerocraft is in the air from release device, special including the support platform being placed in above aircraft
Sign is: further including clamping device, trigger mechanism and locking and relieving mechanism；
One, locking and relieving mechanism
Locking and relieving mechanism include the first spring mountings, the first spring and lock device, and the first spring one end is fixedly connected on
On first spring mountings, the first spring other end is fixedly connected with locking device；
Two, trigger mechanism
Trigger mechanism includes frizzen, articulation piece and the bar for being fixed on frizzen upper end, and frizzen is placed in aircraft rotor
Between blade, the articulation piece being fixed in support platform is articulated on frizzen, and bar, which passes through the first spring, protects the first spring
Tensional state is held, bar drives bar to leave the first spring around hinged place rotation makes the first spring contraction；
Three, clamping device
Clamping device lower end is fixedly connected with aircraft, and clamping device upper end is equipped with the locking hole being laterally extended, and locking hole can make
It is passed through with the lock device being connected in the first spring of tensional state, lock device leaves locking when the first spring is in contraction state
Hole.
2. mechanical multi-rotor aerocraft according to claim 1 is in the air from release device, it is characterised in that: further include setting
Ejection mechanism above clamping device, ejection mechanism include ejection-spring and the ejection bullet being fixedly connected with ejection-spring upper end
Spring fixing piece；When lock device passes through locking hole, ejection-spring lower end is in contact with clamping device, and ejection-spring is in compression shape
State is placed in above clamping device.
3. mechanical multi-rotor aerocraft according to claim 2 is in the air from release device, it is characterised in that: clamping device
It is placed on ejection-spring fixing piece lower part, ejection-spring fixing piece is equipped with the second through-hole corresponding with locking hole, lock device
Locking hole can be passed through through the second through-hole；First spring mountings are equipped with the first through hole for making bar pass through the first spring.
4. mechanical multi-rotor aerocraft described in any one of -3 is in the air from release device, feature according to claim 1
Be: clamping device passes through support platform and extends up and down along the vertical direction, and locking and relieving mechanism and locking hole are placed in support
Above platform and left and right extension in the horizontal direction, the bar extending direction being placed in above support platform and the first telescopic spring direction
Perpendicular, frizzen passes through support platform and extends up and down along the vertical direction.
5. mechanical multi-rotor aerocraft according to claim 2 or 3 is in the air from release device, it is characterised in that: clamping
Mechanism with lock device be it is rod-shaped, the first spring mountings and ejection-spring fixing piece are tubulose, and articulation piece is pin shaft, pin shaft
Axis direction is parallel to the first telescopic spring direction.
6. a kind of mechanical multi-rotor aerocraft is in the air from method for releasing, it is characterised in that: utilize any one in claim 1-5
Mechanical multi-rotor aerocraft described in is realized from release device in the air, comprising the following steps:
A. aircraft rotor rotary dial frizzen is rotated around articulation piece；
B. articulation piece drives bar rotation, is in the bar of the first spring of tensional state to make to have passed through and leaves the first spring；
C. the first spring contraction drives the lock device for having passed through locking hole to leave locking hole, clamping device and aircraft and makees in gravity
With lower release.
7. mechanical multi-rotor aerocraft according to claim 6 is in the air from method for releasing, it is characterised in that: in step C
It further include that lock device leaves locking hole, ejection-spring, which stretches downwards, pushes clamping device, clamping device and aircraft in ejection bullet
It is discharged under spring force and gravity.
8. mechanical multi-rotor aerocraft according to claim 7 is in the air from method for releasing, it is characterised in that:
A. the frizzen that aircraft rotor rotary dial vertical direction extends rotates backward around articulation piece；
B. articulation piece drives bar to rotate forward, is in the bar of the first spring of tensional state to make to have passed through and leaves the first bullet
Spring；
C. the first spring contraction drives the lock device for having passed through locking hole to leave locking hole, and ejection-spring stretches downwards promotion clamping
Mechanism, clamping device and aircraft discharge under ejection-spring elastic force and gravity.
9. the mechanical multi-rotor aerocraft according to any one of claim 6-8 is in the air from method for releasing, feature
It is: in step A, is fixed on more rotors on Fixed Wing AirVehicle from release device in the air through mechanical multi-rotor aerocraft and flies
Row device rotor rotational, the rotor wing rotation of multi-rotor aerocraft are stirred frizzen and are rotated around articulation piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910232112.2A CN109969401A (en) | 2019-03-26 | 2019-03-26 | Mechanical multi-rotor aerocraft is in the air from release device and method for releasing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910232112.2A CN109969401A (en) | 2019-03-26 | 2019-03-26 | Mechanical multi-rotor aerocraft is in the air from release device and method for releasing |
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| Publication Number | Publication Date |
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| CN109969401A true CN109969401A (en) | 2019-07-05 |
Family
ID=67080637
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910232112.2A Pending CN109969401A (en) | 2019-03-26 | 2019-03-26 | Mechanical multi-rotor aerocraft is in the air from release device and method for releasing |
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| CN109146377A (en) * | 2018-08-21 | 2019-01-04 | 钱文娟 | A kind of Intelligent logistics delivery system based on unmanned plane |
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Application publication date: 20190705 |