CN108513569B - Aircraft launcher - Google Patents
Aircraft launcher Download PDFInfo
- Publication number
- CN108513569B CN108513569B CN201780005123.6A CN201780005123A CN108513569B CN 108513569 B CN108513569 B CN 108513569B CN 201780005123 A CN201780005123 A CN 201780005123A CN 108513569 B CN108513569 B CN 108513569B
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- China
- Prior art keywords
- base
- support frame
- aircraft
- telescopic structure
- supporting
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- 238000003825 pressing Methods 0.000 claims description 7
- 230000013011 mating Effects 0.000 claims 3
- 238000010276 construction Methods 0.000 abstract 1
- 238000007689 inspection Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000000034 method Methods 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
- 230000002265 prevention Effects 0.000 description 1
- 239000004575 stone Substances 0.000 description 1
Images
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
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- 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 utility model provides an aircraft launcher of new construction, draw together the base and with the support frame that the base rotates to be connected, the base is used for placing the aircraft, the support frame is used for supporting after rotating base one end makes base and ground become certain angle. The support frame is including locating the supporting part of base one side, and locate the base opposite side and with the location portion that the supporting part is connected, location portion be used for with the aircraft is fixed the base, wherein the supporting part with location portion follows the length direction of support frame is connected.
Description
Technical Field
The utility model relates to an aircraft firing equipment technical field especially relates to an aircraft launcher.
Background
The aircraft is widely applied to the present society, and has extremely wide application prospects in aerial photography, forest fire prevention inspection, geological survey, high-voltage transmission line inspection, oil field pipeline inspection, highway management, emergency rescue and rescue.
At present, the aircraft is placed on the ground before being controlled, and during takeoff, the aircraft needs to vertically fly away from the ground for a certain distance before flying back and forth, so that the takeoff needs a long time. Alternatively, the aircraft may simply be leaned against a stone at an angle to the ground to take off at a faster rate, but this approach does not allow easy adjustment of the angle of the aircraft to the ground.
Disclosure of Invention
The present disclosure provides an aircraft launcher to address deficiencies in the related art.
The invention provides an aircraft launcher, which comprises a base and a support frame rotationally connected with the base, wherein the base is used for placing an aircraft, and the support frame is used for supporting one end of the base after rotation so that the base and the ground form a certain angle;
the support frame is including locating the supporting part of base one side, and locate the base opposite side and with the location portion that the supporting part is connected, location portion be used for with the aircraft is fixed the base, wherein the supporting part with location portion follows the length direction of support frame is connected.
Optionally, the supporting frame further includes a pivoting portion connecting the supporting portion and the positioning portion, and the pivoting portion is rotatably connected with the base.
Optionally, the base is provided with an accommodating portion for accommodating the support frame, the accommodating portion is formed in the base, and the support frame can be accommodated in the base by rotating the support frame.
Optionally, the base is provided with a fixing portion for fixing the support frame, the support frame is provided with a matching portion matched with the fixing portion, and when the support frame is accommodated in the base, the fixing portion is in contact fit with the matching portion.
Optionally, one of the fixing portion and the matching portion is a clamping groove, the other is a buckle, and the fixing portion is connected with the matching portion in a clamping manner.
Optionally, a first limiting part is arranged at a position of the base, which is close to the positioning part; when the support frame is rotated to a preset angle, the first limiting part can be in contact with the positioning part to prevent the support frame from continuing to rotate.
Optionally, one end of the base in the length direction is provided with a telescopic structure, and the telescopic structure can stretch along the length direction of the base.
Optionally, the base includes a receiving portion for receiving the telescopic structure, and the telescopic structure is slidable in the receiving portion.
Optionally, the accommodating portion is a sliding groove formed in the base, and the telescopic structure is a U-shaped rod with a preset width.
Optionally, an elastic member is disposed at a terminal end of the telescopic structure, and the elastic member is disposed in the accommodating portion.
Optionally, a second limiting portion is arranged on the telescopic structure, a pressing portion matched with the second limiting portion is arranged on the support frame, and when the telescopic structure is accommodated in the accommodating portion, the pressing portion is matched with the second limiting portion to fix the telescopic structure in the accommodating portion.
Optionally, the base is provided with a fixed clamping position, the second limiting portion is movable to the fixed clamping position, and when the support frame is accommodated in the base, the pressing portion is pressed on the second limiting portion, so that the telescopic structure accommodated in the accommodating portion is fixed.
The technical scheme provided by the disclosure can comprise the following beneficial effects:
this is disclosed through the cooperation of the support frame of rotating the connection and base, the inclination of adjustable base is in order to satisfy the demand of taking off of aircraft. The angle of aircraft and ground can easily be adjusted to the rotation support frame, has changed the difficult problem of adjusting after launcher aircraft put on the shelf in the tradition.
Drawings
FIG. 1 is an exploded view of an aircraft launcher illustrating one embodiment of the present disclosure;
FIG. 2 is a view of the aircraft launcher of FIG. 1 in a first orientation;
FIG. 3 is a second directional view of the aircraft launcher of FIG. 1;
fig. 4 is a schematic view of an aircraft launcher in cooperation with an aircraft.
Detailed Description
Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The implementations described in the exemplary embodiments below are not intended to represent all implementations consistent with the present disclosure. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present disclosure, as detailed in the appended claims.
The terminology used in the present disclosure is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used in this disclosure and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
It is to be understood that although the terms first, second, third, etc. may be used herein to describe various information, such information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present disclosure. The word "if" as used herein may be interpreted as "at … …" or "when … …" or "in response to a determination", depending on the context.
FIG. 1 is an exploded view of an aircraft launcher illustrating one embodiment of the present disclosure; FIG. 2 is a view of the aircraft launcher of FIG. 1 in a first orientation; FIG. 3 is a second directional view of the aircraft launcher of FIG. 1; the first direction and the second direction are respectively the front side and the back side of the aircraft launcher. As shown in fig. 1 to 3, the aircraft launcher includes a base 1 and a support frame 2, wherein the base 1 is rotatably connected with the support frame 2. The base 1 is used for placing an aircraft, the support frame 2 is used for supporting one end of the base 1 after rotating, so that the base 1 forms a certain angle (for example, 30-150 degrees) with the ground, one end of the base 1 and one end of the support frame 2 are fulcrums, and one end of the support frame 2 serving as the fulcrums is far away from the base 1. The base 1 is composed of a plurality of rod-shaped cylinders and is provided with a supporting seat with a certain supporting area, and the area of the supporting seat can be slightly larger than the supporting area of the aircraft.
The supporting frame 2 includes a supporting portion 22, a positioning portion 21 and a pivoting portion. The supporting portion 22 is disposed on one side of the base 1, the positioning portion 21 is disposed on the other side of the base 1 and connected to the supporting portion 22, and the supporting portion 22 and the positioning portion 21 are connected along the length direction of the supporting frame 2. The pivoting part (not shown) is rotatably connected to the base 1, and the pivoting part connects the supporting part 22 and the positioning part 21.
In the present embodiment, the supporting frame 2 is composed of two columnar structures and a connecting rod connected between the two columnar structures. The pivot joint part is through holes (formed on two columnar structures) arranged on the support frame 2, correspondingly, the base 1 is also provided with through holes 16, and a rotating shaft penetrates through the two through holes to realize the rotating connection of the support frame 2 and the base 1. The pivot portion divides the two columnar structures into two parts, namely, a supporting portion 22 and a positioning portion 21. Since the pivot joint is located between the supporting portion 22 and the positioning portion 21, when the supporting frame 2 rotates around the rotating shaft, the rotating directions of the supporting portion 22 and the positioning portion 21 are opposite. Therefore, when the support frame 2 is rotated, the free end of the support part 22 is far away from the base 1, the positioning part 21 protrudes out of the surface of the base 1, and the aircraft can be placed on the base 1 with a certain inclination angle by means of the positioning part 21. The positioning part 21 can fix the aircraft on the base 1, for example, the positioning part 21 cooperates with an empty space of the aircraft to fix the aircraft, so as to prevent the aircraft from sliding down on the base 1.
Referring to fig. 1 to 4, the base 1 is provided with an accommodating portion 13 for accommodating the supporting frame 2, the accommodating portion 13 is formed in the base 1, and the supporting frame 2 can be accommodated in the base 1 by rotating the supporting frame 2. In one embodiment, the receiving portion 13 is a slotted hole and is disposed near two sides of the base 1. The free end of the supporting portion 22 rotates towards the base 1, and when the plane of the supporting frame 2 coincides with the plane of the base 1, the supporting frame 2 is accommodated in the accommodating portion 13. Therefore, the aircraft launcher is simple in structure, the size of the aircraft launcher is reduced by fully utilizing the slotted hole structure, and the aircraft launcher is convenient to carry.
Further, the base 1 is provided with a fixing portion 14 for fixing the support frame 2, the support frame 2 is provided with a matching portion 23 matched with the fixing portion 14, and when the support frame 2 is accommodated in the base 1, the fixing portion 14 is in contact fit with the matching portion 23. In the embodiment of the present disclosure, the fixing portion 14 is a slot and is disposed near the bottom end of the base 1; the matching part 23 is a buckle and is arranged near the bottom end of the support frame 2 (on a support rod at the lower end of the support frame 2). When the aircraft launcher needs to be stored, the support frame 2 is rotated, the support frame 2 is stored in the storage portion 13, the fixing portion 14 is clamped with the matching portion 23, and the support frame 2 is fixed. When in use, the lower end of the support frame 2 and the lower end of the base 1 are directly dragged to separate the engaged fixing part 14 from the engaging part 23. Of course, in other embodiments, the fixing portion 14 is a snap and the engaging portion 23 is a slot.
The base 1 is further provided with a first limiting part 12, and the position of the first limiting part 12 on the base 1 is close to the positioning part 21. In the embodiment of the present disclosure, the first stopper 12 is disposed in the accommodating portion 13 and located below the rotating shaft. After the supporting frame 2 is rotated to a predetermined angle, the first position-limiting portion 12 may contact the positioning portion 21 to prevent the supporting frame 2 from rotating continuously. The first position-limiting portion 12 includes a notch with a specific depth, the positioning portion 21 rotates from the plane of the base 1 until contacting the first position-limiting portion 12, and the depth of the notch is related to the rotatable angle of the positioning portion 21.
Further, a telescopic structure 3 is arranged at one end of the base 1 in the length direction, and the telescopic structure 3 can stretch along the length direction of the base 1. The length of the aircraft launcher is increased by the arrangement of the telescopic structure 3 so as to adapt to aircrafts 5 (see fig. 4) with different lengths, and the effect of stable placement of different aircrafts can be achieved. In the embodiment of the present disclosure, the telescopic structure 3 is a U-shaped bar having a predetermined width.
To simplify the structure and achieve the extension and retraction of the telescopic structure 3 relative to the base 1, a receiving portion 11 is provided on the base 1, the receiving portion 11 can receive the telescopic structure 3, and the telescopic structure 3 can slide in the receiving portion 11. In the embodiment of the present disclosure, the accommodating portion 11 is a chute formed in the base 1. Of course, the structure of the sliding groove formed on the surface of the base 1 is also possible.
The end of the telescopic structure 3 is provided with an elastic part 4, and the elastic part 4 is arranged in the accommodating part 11. In one embodiment, the elastic member 4 can be compressed by sliding the telescopic structure 3 into the receiving portion 11. The elastic element 4 may assist in ejecting the telescopic structure 3 when it is desired to take out the telescopic structure 3. One end of the elastic element 4 can be connected with the base 1, and the other end is connected with the telescopic structure 3. In the present embodiment, the elastic member 4 is a spring.
The telescopic structure 3 is provided with a second limiting part 12, and the support frame 2 is provided with a press-fit part 24 matched with the second limiting part 12. The second limiting portion 12 is a groove formed on the telescopic structure 3, and the press-fit portion 24 is a connecting rod arranged on the support frame 2. When the telescopic structure 3 is accommodated in the accommodating part 11 and the accommodating length of the telescopic structure 3 is the maximum, the connecting rod is clamped into the press-fit part 24, and the press-fit part 24 is matched with the second limiting part 12 to fix the telescopic structure 3 in the accommodating part 11.
The base 1 is provided with a fixing clip 15, the fixing clip 15 is a strip-shaped groove formed on the base 1, and the pressing part 24 can be accommodated in the strip-shaped groove (the support frame 2 is accommodated in the base 1). When the length of the telescopic structure 3 is the maximum when it is accommodated in the accommodating portion 11, the second position-limiting portion 12 can move to the fixed position-limiting position 15 and be exposed from the accommodating portion 13. When the supporting frame 2 is accommodated in the base 1, the pressing portion 24 is pressed on the second limiting portion 12, so that the telescopic structure 3 accommodated in the accommodating portion 11 is fixed. When the support frame 2 rotates to separate from the receiving portion 13, the elastic member 4 may eject a portion of the telescopic structure 3 out of the receiving portion 11. The structure optimization of the aircraft launcher and the full utilization of the volume are realized.
The above description is only exemplary of the present disclosure and should not be taken as limiting the disclosure, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.
Claims (9)
1. The aircraft launcher is characterized by comprising a base and a support frame rotatably connected with the base, wherein the base is used for placing an aircraft, and the support frame is used for supporting one end of the base after rotating so that the base and the ground form a certain angle;
the supporting frame comprises a supporting part arranged on one side of the base and a positioning part arranged on the other side of the base and connected with the supporting part, the positioning part is used for fixing the aircraft on the base, and the supporting part and the positioning part are connected along the length direction of the supporting frame;
one end of the base in the length direction is provided with a telescopic structure, and the telescopic structure can be telescopic along the length direction of the base;
the base comprises an accommodating part for accommodating the telescopic structure, and the telescopic structure can slide in the accommodating part;
the telescopic structure is provided with a second limiting part, the support frame is provided with a pressing part matched with the second limiting part, and when the telescopic structure is accommodated in the accommodating part, the pressing part is matched with the second limiting part to ensure that the telescopic structure is fixed in the accommodating part.
2. The aircraft launcher according to claim 1, wherein the support frame further comprises a pivot portion connecting the support portion and the positioning portion, the pivot portion being rotatably connected to the base.
3. The aircraft launcher according to claim 1, wherein the base has a receptacle for receiving the support frame, the receptacle being formed in the base, and rotation of the support frame allows the support frame to be received in the base.
4. The aircraft launcher according to claim 3, wherein the base has a fixing portion for fixing the support frame, the support frame has a mating portion for mating with the fixing portion, and the fixing portion is in contact with the mating portion when the support frame is received in the base.
5. The aircraft launcher according to claim 4, wherein one of said securing portion and said engagement portion is a snap-fit slot, and the other of said securing portion and said engagement portion is a snap-fit connection.
6. The aircraft launcher according to claim 1, wherein the base has a first limiting portion disposed at a position adjacent to the positioning portion; when the support frame is rotated to a preset angle, the first limiting part can be in contact with the positioning part to prevent the support frame from continuing to rotate.
7. The aircraft launcher according to claim 1, wherein the receptacle is a chute formed in the base, and the telescoping structure is a U-shaped bar having a predetermined width.
8. The aircraft launcher according to claim 1, wherein the telescoping structure terminates with an elastic member disposed within the receptacle.
9. The aircraft launcher according to claim 1, wherein the base has a fixed detent, the second limiting portion is movable to the fixed detent, and when the support frame is received in the base, the press fit portion presses on the second limiting portion, such that the retractable structure received in the receiving portion 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 CN108513569A (en) | 2018-09-07 |
| CN108513569B true 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)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (6)
| 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 |
| WO2015073091A1 (en) * | 2013-08-27 | 2015-05-21 | 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 |
-
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 |
|---|---|
| CN108513569A (en) | 2018-09-07 |
| WO2019127565A1 (en) | 2019-07-04 |
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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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