CN203528831U - Ejecting frame for fixed-wing unmanned aerial vehicle - Google Patents
Ejecting frame for fixed-wing unmanned aerial vehicle Download PDFInfo
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- CN203528831U CN203528831U CN201320553937.2U CN201320553937U CN203528831U CN 203528831 U CN203528831 U CN 203528831U CN 201320553937 U CN201320553937 U CN 201320553937U CN 203528831 U CN203528831 U CN 203528831U
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- unmanned plane
- elastic component
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- aerial vehicle
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Abstract
The utility model relates to an ejecting frame for a fixed-wing unmanned aerial vehicle. The ejecting frame is characterized by comprising an unmanned aerial vehicle fixing platform, an elastic component and an elastic component fixing frame. The unmanned aerial vehicle fixing platform comprises a bottom support, a top support and a rotating support. Supporting columns are connected between the top support and the bottom support, and a beam is connected between the adjacent supporting columns. The rotating support is hinged to the inner side of the top support through a hinge pin, and the upper surface of the rotating shaft is provided with an unmanned aerial vehicle fixing clamping groove. The elastic component fixing frame comprises a base with the upper portion fixedly provided with two stand columns, a stand rod is hinged between the stand columns, the same side of the two stand columns is provided with a baffle, and the upper end of the stand rod is provided with a bayonet on which the elastic component is hung. Compared with a traditional fixed type ejecting frame, the ejecting frame for the fixed-wing unmanned aerial vehicle has the advantages of being simple in structure, light in weight, convenient to carry and capable of solving the problems of transportation, storage and the like at the same time; in addition, the ejecting frame for the fixed-wing unmanned aerial vehicle is easy to manufacture, low in cost, convenient to operate and suitable for environments where the geology is floppy.
Description
Technical field
The utility model belongs to the unmanned plane auxiliary device technical field of taking off, and particularly relates to a kind of launching cradle taking off for fixed-wing unmanned plane.
Background technology
Existing unmanned vehicle is when taking off; must as general aircraft, first accelerate to after takeoff speed; can make aircraft produce enough lift makes to take off; for making unmanned aerial vehicle can not be subject to the taking off of restriction of place size or landform; conventionally can utilize launching cradle to give unmanned vehicle auxiliary power, make unmanned vehicle accelerate to takeoff speed at short notice and take off.
When unmanned plane takes off on ground, main employing on car launcher taken off and two kinds of modes of catapult-assisted take-off, while taking off on car launcher, unmanned plane is arranged on car launcher, under the thrust of driving engine, unmanned plane and launch vehicle combination body are run along common slideway is sliding, when accelerating to unmanned plane takeoff speed, discharge unmanned plane, there is complex structure in this launch mode, manufacturing cost is high, the problem of maintenance difficulty, catapult-assisted take-off is that unmanned plane is contained on launching cradle, by elastic component, realize the method that zero-height ejection takes off, existing launching cradle is all heavier, and complicated structure.
Summary of the invention
The utility model for solve the technical matters existing in known technology provide a kind of simple in structure, easy to install, volume is little, the easy to carry launching cradle taking off for fixed-wing unmanned plane.
The technical scheme that the utility model is taked for the technical matters existing in solution known technology is:
A kind of launching cradle taking off for fixed-wing unmanned plane, it is characterized in that: this launching cradle mainly comprises unmanned plane fixed platform, elastic component and elastic component fixed mount, wherein said unmanned plane fixed platform comprises bottom bracket, top-support and swinging strut; Between described top-support and bottom bracket, be connected with pillar stiffener, between described adjacent supports post, be connected with crossbeam, the inner side of described top-support is by the hinged installation swinging strut of hinge, and the upper surface of described swinging strut is provided with unmanned plane fixed card slot; Described elastic component fixed mount comprises base, and the top of described base is installed with two columns, hinged vertical rod between described column, and a side of described two columns is provided with baffle plate, and the upper end of described vertical rod is provided with the bayonet socket that mounts elastic component.
The utility model can also adopt following technical measures:
Between described elastic component fixed mount and unmanned plane fixed platform, be provided with push rod; The front end of described push rod is inserted between two columns and by attaching parts and is connected with column, described attaching parts is inserted in connecting bore, described connecting bore is provided with several, the other end of described push rod extends on the bottom bracket of unmanned plane fixed platform, bottom bracket is provided with positioning convex, and the front end of described push rod is inserted in positioning convex.
Advantage and the good effect that the utlity model has are: because the utility model adopts technique scheme, make the utility model and traditional fixed type launching cradle structure compared simple, lightweight, be easy to carry, solved simultaneously transportation and deposit etc. problem, the utility model also has manufacture of being easy to, with low cost, easy to operate in addition, is also applicable to the environment that geology is softer.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
In figure: 1, unmanned plane fixed platform; 1-1, bottom bracket; 1-2, top-support; 1-3, swinging strut; 1-4, pillar stiffener; 1-5, crossbeam; 1-6, hinge; 1-7, swinging strut; 1-8, unmanned plane fixed card slot; 2, elastic component; 3, elastic component fixed mount; 3-1, base; 3-2, column; 3-3, vertical rod; 3-4, baffle plate; 3-5, bayonet socket; 4, push rod; 5, column; 6, attaching parts; 7, connecting bore.
The specific embodiment
For further understanding summary of the invention of the present utility model, Characteristic, hereby exemplify following examples, and coordinate accompanying drawing to be described in detail as follows:
Refer to Fig. 1, a kind of launching cradle taking off for fixed-wing unmanned plane, this launching cradle mainly comprises unmanned plane fixed platform 1, elastic component 2 and elastic component fixed mount 3, and wherein said unmanned plane fixed platform comprises bottom bracket 1-1, top-support 1-2 and swinging strut 1-3; Between described top-support 1-2 and bottom bracket 1-1, be connected with pillar stiffener 1-4, between described adjacent supports post 1-4, be connected with crossbeam 1-5, the inner side of described top-support 1-2 is by the hinged installation swinging strut of hinge 1-6 1-7, and the upper surface of described swinging strut 1-7 is provided with unmanned plane fixed card slot 1-8; Described elastic component fixed mount 3 comprises base 3-1, the top of described base 3-1 is installed with two column 3-2, hinged vertical rod 3-3 between described column, a side of described two columns is provided with baffle plate 3-4, and the upper end of described vertical rod 3-3 is provided with the bayonet socket 3-5 that mounts elastic component.
Concrete using method: the front end of elastic component is mounted on bayonet socket 3-5, the rear end of elastic component is mounted on unmanned plane, unmanned plane is strained towards unmanned plane fixed platform direction, and unmanned plane fixed card is contained in fixed card slot 1-8, at this moment swinging strut is tending towards level attitude or front end is slightly higher, after waiting for that all standby for takeoff work are ready, upwards lift swinging strut 1-7, after lifting to certain position, unmanned plane will depart from fixed card slot, at this moment under the effect of elastic component, unmanned plane obtains a takeoff speed, coordinate self power to complete takes off simultaneously, after elastic component is lax, vertical rod is leaned forward by inertia, and falls down, thereby has avoided vertical rod interference to unmanned plane when taking off, thereby completes whole take-off process.
In order to meet the utility model, to be applicable to geology softer, badly between elastic component fixed mount 3 and unmanned plane fixed platform 1 fixedly time, between described elastic component fixed mount 3 and unmanned plane fixed platform 1, is provided with push rod 4 with ground; The front end of described push rod 4 is inserted between two columns 5 and by attaching parts 6 and is connected with column 5, described attaching parts is inserted in connecting bore 7, described connecting bore is provided with several, can adjust according to actual needs the height of push rod like this, to be suitable for the differently requirement in ore deposit, the other end of described push rod extends on the bottom bracket of unmanned plane fixed platform, and bottom bracket is provided with positioning convex, and the front end of described push rod is inserted in positioning convex.
The above is only to preferred embodiment of the present utility model, not the utility model is done to any pro forma restriction, every foundation technical spirit of the present utility model is to any simple modification made for any of the above embodiments, equivalent variations and modification, all belong in the scope of technical solutions of the utility model.
Claims (2)
1. the launching cradle taking off for fixed-wing unmanned plane, it is characterized in that: this launching cradle mainly comprises unmanned plane fixed platform, elastic component and elastic component fixed mount, wherein said unmanned plane fixed platform comprises bottom bracket, top-support and swinging strut; Between described top-support and bottom bracket, be connected with pillar stiffener, between described adjacent supports post, be connected with crossbeam, the inner side of described top-support is by the hinged installation swinging strut of hinge, and the upper surface of described swinging strut is provided with unmanned plane fixed card slot; Described elastic component fixed mount comprises base, and the top of described base is installed with two columns, hinged vertical rod between described column, and a side of described two columns is provided with baffle plate, and the upper end of described vertical rod is provided with the bayonet socket that mounts elastic component.
2. the launching cradle taking off for fixed-wing unmanned plane according to claim 1, is characterized in that: between described elastic component fixed mount and unmanned plane fixed platform, be provided with push rod; The front end of described push rod is inserted between two columns and by attaching parts and is connected with column, described attaching parts is inserted in connecting bore, described connecting bore is provided with several, the other end of described push rod extends on the bottom bracket of unmanned plane fixed platform, bottom bracket is provided with positioning convex, and the front end of described push rod is inserted in positioning convex.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320553937.2U CN203528831U (en) | 2013-09-06 | 2013-09-06 | Ejecting frame for fixed-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320553937.2U CN203528831U (en) | 2013-09-06 | 2013-09-06 | Ejecting frame for fixed-wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203528831U true CN203528831U (en) | 2014-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320553937.2U Expired - Fee Related CN203528831U (en) | 2013-09-06 | 2013-09-06 | Ejecting frame for fixed-wing unmanned aerial vehicle |
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| CN (1) | CN203528831U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005467A (en) * | 2016-08-01 | 2016-10-12 | 天峋（常州）智能科技有限公司 | Small fixed wing unmanned aerial vehicle ejector rack |
-
2013
- 2013-09-06 CN CN201320553937.2U patent/CN203528831U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005467A (en) * | 2016-08-01 | 2016-10-12 | 天峋（常州）智能科技有限公司 | Small fixed wing unmanned aerial vehicle ejector rack |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140409 Termination date: 20150906 |
|
| EXPY | Termination of patent right or utility model |