CN108513569A - Vehicle launch frame - Google Patents
Vehicle launch frame Download PDFInfo
- Publication number
- CN108513569A CN108513569A CN201780005123.6A CN201780005123A CN108513569A CN 108513569 A CN108513569 A CN 108513569A CN 201780005123 A CN201780005123 A CN 201780005123A CN 108513569 A CN108513569 A CN 108513569A
- Authority
- CN
- China
- Prior art keywords
- pedestal
- vehicle launch
- support frame
- support
- stretching structure
- 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.)
- Granted
Links
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 83
- 238000010276 construction Methods 0.000 abstract 1
- 238000007689 inspection Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000686 essence Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
Abstract
The disclosure provides a kind of vehicle launch frame of new construction, the supporting rack for including pedestal and being connect with the base rotation, and the pedestal is used to support described pedestal one end for placing aircraft, after support frame as described above rotation and makes the pedestal and ground angled.Support frame as described above includes the support portion set on the pedestal side, and set on the pedestal other side and the positioning region that is connect with the support portion, the positioning region is used to the aircraft being fixed on the pedestal, and wherein length direction of the support portion with the positioning region along support frame as described above is connected.
Description
Technical field
This disclosure relates to vehicle launch equipment technical field more particularly to a kind of vehicle launch frame.
Background technology
Aircraft is widely used in society now, take pictures in aviation, forest fire protection inspection, geological survey, high voltage power transmission
Line inspection, oil filed pipeline inspection, freeway management, emergency management and rescue and rescue application prospect are extremely wide.
Currently, before manipulating aircraft being placed it on ground, when taking off, aircraft needs vertically fly away from ground
Front and back flight is just proceeded by after certain distance, this, which causes to take off, needs the long period.Alternatively, simply aircraft is leant against
On one block of stone, make its with ground at an angle, so that quickly speed is liftoff takes off for it, still, this method can not be light
Loose ground adjusts the angle of aircraft and ground.
Invention content
The disclosure provides a kind of vehicle launch frame, to solve deficiency in the related technology.
The disclosure provides a kind of vehicle launch frame, including pedestal and the supporting rack that is connect with the base rotation, described
Pedestal is used to support described pedestal one end and makes the pedestal with ground at one for placing aircraft after support frame as described above rotation
Determine angle；
Support frame as described above includes the support portion set on the pedestal side, and set on the pedestal other side and with it is described
The positioning region of support portion connection, the positioning region are used to the aircraft being fixed on the pedestal, wherein support portion with it is described
Positioning region is connected along the length direction of support frame as described above.
Optionally, support frame as described above further includes the articulated section for connecting the support portion and the positioning region, the articulated section
It is connect with the base rotation.
Optionally, the pedestal is equipped with the receiving portion for accommodating support frame as described above, and the receiving portion is formed in the bottom
In seat, rotation institute supporting rack can will support frame as described above receiving in the pedestal.
Optionally, the pedestal is equipped with to the fixed part of fixed support frame as described above, and support frame as described above is equipped with and institute
The auxiliary section of fixed part cooperation is stated, when support frame as described above is contained in the pedestal, the fixed part is contacted with the auxiliary section
Cooperation.
Optionally, the fixed part and one among the auxiliary section are card slot, another is buckle, the fixed part
It is connected together with the auxiliary section.
Optionally, the pedestal is equipped with the first limiting section close to the position of the positioning region；When rotation support frame as described above extremely
After predetermined angle, first limiting section with the positioning region can contact that support frame as described above is prevented to be rotated further.
Optionally, one end on the length direction of the pedestal is equipped with stretching structure, and the stretching structure can be along described
The length direction of pedestal is flexible.
Optionally, the pedestal includes the holding part for housing the stretching structure, and the stretching structure can be described
Sliding in holding part.
Optionally, the holding part is the sliding slot being formed in the pedestal, and the stretching structure is with predetermined width
U-shaped bar.
Optionally, the end of the stretching structure is equipped with elastic component, and the elastic component is placed in the holding part.
Optionally, the stretching structure is equipped with the second limiting section, and support frame as described above is equipped with and second limiting section
The nip portion of cooperation, when the stretching structure is contained in the holding part, the nip portion makes with second limiting section cooperation
The stretching structure is obtained to be fixed in the holding part.
Optionally, the pedestal is equipped with fixed screens, and second limiting section is movable to the fixed screens, works as institute
When stating supporting rack and being contained in the pedestal, the nip portion is pressed together on second limiting section so that is contained in the appearance
The stretching structure set in portion is fixed.
Technical solution provided by the present disclosure can include the following benefits：
The disclosure is by the cooperation of the supporting rack and pedestal of rotation connection, and the angle of inclination of adjustable frames is to meet flight
The demand of taking off of device.Rotary support frame can change traditionally launcher flight with the angle of easy adjustment aircraft and ground
Difficult problem is adjusted after device restocking.
Description of the drawings
Fig. 1 is the explosive view that the disclosure one implements a kind of vehicle launch frame exemplified；
Fig. 2 is the view of the first direction of vehicle launch frame in Fig. 1；
Fig. 3 is the view of the second direction of vehicle launch frame in Fig. 1；
Fig. 4 is the schematic diagram of vehicle launch frame and aircraft cooperation.
Specific implementation mode
Example embodiments are described in detail here, and the example is illustrated in the accompanying drawings.Following description is related to
When attached drawing, unless otherwise indicated, the same numbers in different drawings indicate the same or similar elements.Following exemplary embodiment
Described in embodiment do not represent all implementations consistent with this disclosure.On the contrary, they be only with it is such as appended
The example of the consistent device and method of some aspects be described in detail in claims, the disclosure.
It is the purpose only merely for description specific embodiment in the term that the disclosure uses, is not intended to be limiting the disclosure.
The "an" of singulative used in disclosure and the accompanying claims book, " described " and "the" are also intended to including majority
Form, unless context clearly shows that other meanings.It is also understood that term "and/or" used herein refers to and wraps
Containing one or more associated list items purposes, any or all may be combined.
It will be appreciated that though various information, but this may be described using term first, second, third, etc. in the disclosure
A little information should not necessarily be limited by these terms.These terms are only used for same type of information being distinguished from each other out.For example, not departing from
In the case of disclosure range, the first information can also be referred to as the second information, and similarly, the second information can also be referred to as
One information.Depending on context, word as used in this " if " can be construed to " ... when " or " when ...
When " or " in response to determination ".
Fig. 1 is the explosive view that the disclosure one implements a kind of vehicle launch frame exemplified；Fig. 2 is that aircraft is sent out in Fig. 1
Penetrate the view of the first direction of frame；Fig. 3 is the view of the second direction of vehicle launch frame in Fig. 1；The first direction and
Two directions are respectively front and the reverse side of vehicle launch frame.As shown in Figure 1 to Figure 3, vehicle launch frame includes pedestal 1 and branch
Support 2, the pedestal 1 are rotatablely connected with supporting rack 2.The pedestal 1 is used for placing aircraft, support frame as described above 2 after rotating
Make the pedestal 1 and ground angled (such as 30 ° -150 °) in described 1 one end of pedestal of support, the one of the pedestal 1
End and one end of support frame as described above 2 are fulcrum, and one end of the support frame as described above 2 as fulcrum is far from the pedestal 1.The pedestal
1 is made of the support base formed and with certain bearing area multiple rod-shaped cylinders, and area may be slightly larger than the support of aircraft
Area.
Support frame as described above 2 includes support portion 22, positioning region 21 and articulated section.The support portion 22 is set to the pedestal 1 one
Side, the positioning region 21 are connect set on 1 other side of the pedestal with the support portion 22, and the support portion 22 with it is described fixed
Position portion 21 is connected along the length direction of support frame as described above 2.The articulated section (not shown) is rotatablely connected with the pedestal 1, should
Articulated section connects the support portion 22 and the positioning region 21.
In the present embodiment, support frame as described above 2 is by two column structures and the company being connected between two column structures
Extension bar forms.Wherein articulated section is the through-hole (being formed on two column structures) on support frame as described above 2, corresponding, institute
It states and is again provided with through-hole 16 on pedestal 1, shaft is used to pass through two through hole to realize the rotation of support frame as described above 2 and the pedestal 1
Connection.Two column structure is divided into two parts, i.e. support portion 22 and positioning region 21 by the articulated section.Due to the articulated section
Between the support portion 22 and the positioning region 21, when support frame as described above 2 rotates around the axis, the support portion 22 and institute
The rotation direction for stating positioning region 21 is opposite.Therefore, when rotating support frame as described above 2, the free end of the support portion 22 is the bottom of far from
Seat 1, the positioning region 21 then protrude from the surface of the pedestal 1, and aircraft can be placed in by the positioning region 21 with certain
On the pedestal 1 at angle of inclination.The aircraft can be fixed on the pedestal 1, such as the positioning region 21 by the positioning region 21
Coordinate to fix aircraft with the clearance position of aircraft, prevents aircraft from gliding on pedestal 1.
Shown in please referring to Fig.1 to Fig.4, the pedestal 1 is equipped with the receiving portion 13 for accommodating support frame as described above 2, the receipts
Appearance portion 13 is formed in the pedestal 1, rotation institute supporting rack 2 can will the receiving of support frame as described above 2 in the pedestal 1.It is real one
It applies in mode, the receiving portion 13 is bar shape trench hole, is arranged respectively close to the both sides of the pedestal 1.The support portion 22 from
It is rotated by holding towards the pedestal 1, until when 2 place plane of support frame as described above is overlapped with 1 place plane of the pedestal, the support
Frame 2 is placed in the receiving portion 13.Not only make the vehicle launch frame simple in structure in this way, also makes full use of slot knot
Structure reduces the volume of vehicle launch frame, easy to carry.
Further, the pedestal 1 is equipped with to fix the fixed part 14 of support frame as described above 2, is set on support frame as described above 2
Have the auxiliary section 23 coordinated with the fixed part 14, when support frame as described above 2 is contained in the pedestal 1, the fixed part 14 with
The auxiliary section 23 is engaged.In embodiment of the disclosure, the fixed part 14 is card slot, is set close to the bottom end of pedestal 1
It sets；The auxiliary section 23 is buckle, (is located on the supporting rod of 2 lower end of supporting rack) close to the setting of the bottom end of support frame as described above 2.When
When need to store the vehicle launch frame, support frame as described above 2, when support frame as described above 2 is contained in the receiving portion 13, institute are rotated
It states fixed part 14 with the auxiliary section 23 to engage, realizes the fixation of supporting rack 2.When in use, it directly drags under supporting rack 2
End detaches the fixed part 14 of engaging with auxiliary section 23 with the lower end of pedestal 1.Certainly in other implementations, described
Fixed part 14 uses card slot using buckle, auxiliary section 23.
The first limiting section 12 is additionally provided on the pedestal 1, which, which is located on the pedestal 1, is located proximate to
The positioning region 21 is arranged.In embodiment of the present disclosure, first limiting section 12 is arranged in the receiving portion 13, and
Positioned at the lower section of the shaft.After rotating support frame as described above 2 to predetermined angle, first limiting section 12 can be with the positioning
Portion 21 contacts that support frame as described above 2 is prevented to be rotated further.First limiting section 12 includes one with certain depth notch, institute
Positioning region 21 is stated from 1 place Plane Rotation of the pedestal, until contacted with first limiting section 12, the depth of the notch with
21 rotatable angle of the positioning region is related.
Further, one end on the length direction of the pedestal 1 is equipped with stretching structure 3, and the stretching structure 3 can edge
The length direction of the pedestal 1 is flexible.The length for increasing the vehicle launch frame is arranged in the stretching structure 3, to adapt to
The aircraft 5 (see Fig. 4) of different length can reach different aircraft and stablize the effect placed.In embodiment of the present disclosure,
The stretching structure 3 is the U-shaped bar with predetermined width.
To simplify structure, the stretching structure 3 is completed relative to the flexible of the pedestal 1, is provided on the pedestal 1
Holding part 11, the holding part 11 can holding part 11 divide the stretching structure 3, the stretching structure 3 can be in the holding part 11
Sliding.In embodiment of the present disclosure, the holding part 11 is the sliding slot being formed in the pedestal 1.Can certainly be
The sliding groove structure being formed on 1 surface of the pedestal.
The end of the stretching structure 3 is equipped with elastic component 4, and the elastic component 4 is placed in the holding part 11.Implement one
In mode, the stretching structure 3 is slided into the holding part 11, the compressible elastic component 4.It is needing described to stretch
When structure 3 is taken out, the elastic component 4 can assist popping up stretching structure 3.The elastic component 4 can one end connect the pedestal 1,
The other end connects the stretching structure 3.In the present embodiment, the elastic component 4 is spring.
The stretching structure 3 is equipped with the second limiting section 12, and support frame as described above 2 is equipped with matches with second limiting section 12
The nip portion 24 of conjunction.Second limiting section 12 is the groove being formed on the stretching structure 3, and the nip portion 24 is setting
Connecting rod on 2 structure of support frame as described above.When the stretching structure 3 is contained in the holding part 11, and the stretching structure 3 is received
When holding length maximum, the connecting rod is caught in the nip portion 24, and the nip portion 24 coordinates with second limiting section 12
So that the stretching structure 3 is fixed in the holding part 11.
The pedestal 1 is equipped with fixed screens 15, which is the bar-shaped trough being formed on the pedestal 1, institute
Stating nip portion 24 can be housed in the bar slot (supporting rack 2 is housed in pedestal 1).The stretching structure 3 is housed in accommodating
In portion 11 when length maximum, second limiting section 12 is movable to the fixed screens 15, and the dew from the receiving portion 13
Go out.When support frame as described above 2 is contained in the pedestal 1, the nip portion 24 is pressed together on second limiting section 12 so that
The stretching structure 3 being contained in the holding part 11 is fixed.It is described when support frame as described above 2, which rotates, is detached from the receiving portion 13
The part stretching structure 3 can be popped up the holding part 11 by elastic component 4.The structure optimization of vehicle launch frame is realized, and
Volume makes full use of.
The foregoing is merely the preferred embodiments of the disclosure, not limiting the disclosure, all essences in the disclosure
With within principle, any modification, equivalent substitution, improvement and etc. done should be included within the scope of the disclosure protection god.
Claims (12)
1. a kind of vehicle launch frame, which is characterized in that the supporting rack being connect including pedestal and with the base rotation, the bottom
Seat is used to support described pedestal one end for placing aircraft, after support frame as described above rotation and makes the pedestal with ground at certain
Angle；
Support frame as described above includes the support portion set on the pedestal side, and set on the pedestal other side and with the support
The positioning region of portion's connection, the positioning region are used to the aircraft being fixed on the pedestal, wherein support portion and the positioning
Portion is connected along the length direction of support frame as described above.
2. vehicle launch frame according to claim 1, which is characterized in that support frame as described above further includes the connection support
The articulated section in portion and the positioning region, the articulated section are connect with the base rotation.
3. vehicle launch frame according to claim 1, which is characterized in that the pedestal is equipped with for accommodating the support
The receiving portion of frame, the receiving portion are formed in the pedestal, and rotation institute supporting rack can accommodate support frame as described above and the bottom
In seat.
4. vehicle launch frame according to claim 3, which is characterized in that the pedestal is equipped with to the fixation branch
The fixed part of support, support frame as described above are equipped with the auxiliary section coordinated with the fixed part, and support frame as described above is contained in the bottom
When in seat, the fixed part is engaged with the auxiliary section.
5. vehicle launch frame according to claim 4, which is characterized in that among the fixed part and the auxiliary section
One is card slot, another is buckle, and the fixed part is connected together with the auxiliary section.
6. vehicle launch frame according to claim 1, which is characterized in that position of the pedestal close to the positioning region
Equipped with the first limiting section；After rotating support frame as described above to predetermined angle, first limiting section can be contacted with the positioning region
To prevent support frame as described above from being rotated further.
7. vehicle launch frame according to claim 1, which is characterized in that one end on the length direction of the pedestal
Equipped with stretching structure, the stretching structure can be flexible along the length direction of the pedestal.
8. vehicle launch frame according to claim 7, which is characterized in that the pedestal includes described flexible for housing
The holding part of structure, the stretching structure can slide in the holding part.
9. vehicle launch frame according to claim 8, which is characterized in that the holding part is to be formed in the pedestal
Sliding slot, the stretching structure be the U-shaped bar with predetermined width.
10. vehicle launch frame according to claim 8, which is characterized in that the end of the stretching structure is equipped with elasticity
Part, the elastic component are placed in the holding part.
11. vehicle launch frame according to claim 8, which is characterized in that the stretching structure is equipped with the second limit
Portion, support frame as described above are equipped with the nip portion coordinated with second limiting section, and the stretching structure is contained in the holding part
When, the nip portion coordinates with second limiting section so that the stretching structure is fixed in the holding part.
12. vehicle launch frame according to claim 11, which is characterized in that the pedestal is equipped with fixed screens, institute
It states the second limiting section and is movable to the fixed screens, when support frame as described above is contained in the pedestal, the nip portion pressure
It closes on second limiting section so that the stretching structure being contained in the holding part is fixed.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/120386 WO2019127565A1 (en) | 2017-12-30 | 2017-12-30 | Aircraft launcher |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108513569A true CN108513569A (en) | 2018-09-07 |
| CN108513569B CN108513569B (en) | 2021-06-18 |
Family
ID=63375246
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780005123.6A Active CN108513569B (en) | 2017-12-30 | 2017-12-30 | Aircraft launcher |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108513569B (en) |
| WO (1) | WO2019127565A1 (en) |
Citations (6)
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| CN203094463U (en) * | 2013-01-09 | 2013-07-31 | 碳基科技股份有限公司 | Folding launching frame |
| US8662441B2 (en) * | 2011-02-16 | 2014-03-04 | Sparton Corporation | Unmanned aerial vehicle launch system |
| CN104608937A (en) * | 2015-02-03 | 2015-05-13 | 河南省汇隆精密设备制造有限公司 | Hydraulic pressure energy storage catapult of multi-plane type unmanned plane |
| CN106043731A (en) * | 2016-06-22 | 2016-10-26 | 浙江大学 | Improved aircraft launching cradle |
| CN205872508U (en) * | 2016-05-26 | 2017-01-11 | 江西洪都国际机电有限责任公司 | Adjustable and automatic emitter who avoids formula shears mechanism |
| CN206238747U (en) * | 2016-08-31 | 2017-06-13 | 杭州利帆实业有限公司 | A kind of desk |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7165745B2 (en) * | 2003-01-17 | 2007-01-23 | The Insitu Group, Inc. | Methods and apparatuses for launching unmanned aircraft, including releasably gripping aircraft during launch and braking subsequent grip motion |
| US8511607B2 (en) * | 2010-07-14 | 2013-08-20 | Arcturus UAV LLC | UAV launch attachment assembly and launch system |
| US9783322B2 (en) * | 2013-08-27 | 2017-10-10 | Engineered Arresting Systems Corporation | Electric unmanned aerial vehicle launcher |
| CN204956949U (en) * | 2015-09-22 | 2016-01-13 | 上海南迅航空科技有限公司 | Light foldable unmanned aerial vehicle launcher |
| CN107176310B (en) * | 2017-06-27 | 2023-09-15 | 安徽国援智能科技有限公司 | Unmanned aerial vehicle launching cradle |
| CN108039165B (en) * | 2017-10-31 | 2020-10-02 | 广西一带一路科技有限公司 | Supporting frame |
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2017
- 2017-12-30 WO PCT/CN2017/120386 patent/WO2019127565A1/en active Application Filing
- 2017-12-30 CN CN201780005123.6A patent/CN108513569B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8662441B2 (en) * | 2011-02-16 | 2014-03-04 | Sparton Corporation | Unmanned aerial vehicle launch system |
| CN203094463U (en) * | 2013-01-09 | 2013-07-31 | 碳基科技股份有限公司 | Folding launching frame |
| CN104608937A (en) * | 2015-02-03 | 2015-05-13 | 河南省汇隆精密设备制造有限公司 | Hydraulic pressure energy storage catapult of multi-plane type unmanned plane |
| CN205872508U (en) * | 2016-05-26 | 2017-01-11 | 江西洪都国际机电有限责任公司 | Adjustable and automatic emitter who avoids formula shears mechanism |
| CN106043731A (en) * | 2016-06-22 | 2016-10-26 | 浙江大学 | Improved aircraft launching cradle |
| CN206238747U (en) * | 2016-08-31 | 2017-06-13 | 杭州利帆实业有限公司 | A kind of desk |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019127565A1 (en) | 2019-07-04 |
| CN108513569B (en) | 2021-06-18 |
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Effective date of registration: 20200716 Address after: Building 3, west side, huangjiangyuan Industrial Zone, Qiaoli Beimen village, Changping Town, Dongguan City, Guangdong Province 523000 Applicant after: Dongguan Flysky RC Model Technology Co.,Ltd. Address before: 518000 Guangdong Shenzhen Futian District Xinzhou Road overpass northwest side Xinzhou Plaza Huafeng Building 16 floor Applicant before: FLYSKY TECHNOLOGY Co.,Ltd. |
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