CN209814325U - Orientation device of launcher - Google Patents
Orientation device of launcher Download PDFInfo
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- CN209814325U CN209814325U CN201920369759.5U CN201920369759U CN209814325U CN 209814325 U CN209814325 U CN 209814325U CN 201920369759 U CN201920369759 U CN 201920369759U CN 209814325 U CN209814325 U CN 209814325U
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- launcher
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- rod
- adjusting rod
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Abstract
The utility model discloses an orienting device of launcher, including two tail-support poles, a connecting rod, two stabilizer bars, a head regulation pole, two tail-support pole symmetries are vertical places, two tail-support pole upper ends to the both ends of connecting a connecting rod of a bit connection in the mid point, two tail-support poles of connecting rod perpendicular to, two stabilizer bars are connected respectively to two tail-support pole upper ends, two stabilizer bar lower extremes all are connected on launcher under bracing structure's front end, head regulation pole connection launcher under bracing structure front end and launcher head bearing structure, head regulation pole can angle regulation. The problem of current fixed wing unmanned aerial vehicle launcher structure comparatively simple, it is not good to unmanned aerial vehicle's supporting effect, and the level of launcher when can't adjusting the transmission, only can use in flat region, be unfavorable for open-air transmission is solved.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle launches field, in particular to orienting device of launcher.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
Fixed wing drones are a subclass of drones, and the wings of drones of this class have adopted a fixed design and are therefore called fixed wing drones. The fixed-wing unmanned aerial vehicle has the advantages of long endurance time, high flight efficiency, stable flight attitude, strong wind resistance, high operation efficiency and large load. The application is mainly applied to the fields of forestry and grassland monitoring, mine resource monitoring, marine environment monitoring, urban and rural junction and land utilization monitoring, water conservancy, electric power and the like. Although the unmanned aerial vehicle has the characteristics of long endurance, high efficiency and the like, the fixed-wing unmanned aerial vehicle has obvious defects in the past. Fixed wing drones primarily rely on the wind flowing over the wings to provide lift. However, the take-off and recovery problems of the fixed-wing unmanned aerial vehicle are two major difficulties which plague the fixed-wing unmanned aerial vehicle. The take-off mode of the fixed-wing unmanned aerial vehicle mainly comprises the following three modes: rocket boosters, wheeled taxis, hand-thrown versions, and the like. The rocket booster is difficult to launch and guarantee, the rocket projectile is safe to store, store and use, the launcher is needed, the preparation time is long, and the guarantee work is complex.
The existing launcher for fixed-wing unmanned aerial vehicles is simple in structure, poor in supporting effect on unmanned aerial vehicles, and capable of adjusting the level of the launcher during launching, and can only be used in a flat area, so that field launching is not facilitated.
Disclosure of Invention
The utility model aims to provide a: the utility model provides a orienting device of launcher, it is comparatively simple to have solved current fixed wing unmanned aerial vehicle launcher structure, and is not good to unmanned aerial vehicle's supporting effect, and the level of launcher when unable regulation transmission, only can use in flat region, is unfavorable for the problem of open-air transmission.
The utility model adopts the technical scheme as follows:
the utility model provides an orienting device of launcher, includes two tail-support poles, a connecting rod, two stabilizer bars, a head regulation pole, two tail-support pole symmetries are vertical places, two tail-support pole upper ends to the both ends of a connecting rod of a bit connection in the mid point, two tail-support pole of connecting rod perpendicular to, two stabilizer bars are connected respectively to two tail-support pole upper ends, and two stabilizer bar lower extremes all are connected on launcher under bracing structure's front end, under bracing structure includes the sleeve that is on a parallel with the tail-support pole with the axis that the stabilizer bar is connected, still includes the screw rod that sets up in the sleeve, the upper end of screw rod is provided with the limit structure who is greater than the sleeve internal diameter, the lower extreme of screw rod is the tip, and launcher under bracing structure front end and launcher head. The level of transmitter can be adjusted through adjusting the position of screw rod among tail-stock pole or the under bracing structure, has multiunit adjustment mechanism, can adapt to different transmission environment. The problem of current fixed wing unmanned aerial vehicle launcher structure comparatively simple, it is not good to unmanned aerial vehicle's supporting effect, and the level of launcher when can't adjusting the transmission, only can use in flat region, be unfavorable for open-air transmission is solved.
And the two tail support rods are also provided with two stabilizer bars outside and connected with the tail support rods and the lower support structure of the launching frame.
The two stabilizing rods are also rods with adjustable length.
Two tail-stock poles, a connecting rod, two stabilizer bars, a head regulation pole are hollow pole.
The head adjusting rod adjusts the angle of the supporting structure at the upper end of the launching frame by adjusting the length of the head adjusting rod.
The angle of the supporting structure at the upper end of the launching frame is adjusted by adjusting the connecting position of the head adjusting rod and the supporting structure on the launching frame.
The head adjusting rod adjusts the length of the screw inside by using a wheel disc to adjust the length of the head adjusting rod.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
1. the utility model relates to a orienting device of launcher has solved current fixed wing unmanned aerial vehicle launcher structure comparatively simple, and is not good to unmanned aerial vehicle's supporting effect, and the level of launcher when unable regulation transmission, only can be in flat regional use, is unfavorable for the problem of open-air transmission.
2. The utility model relates to an orienting device of launcher is all adjustable between each subassembly, can be applicable to different transmission scenes, satisfies different transmission demands.
Drawings
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
fig. 1 is a schematic structural diagram of the present invention;
in the figure, 1-tail support rod, 2-connecting rod, 3-stabilizing rod, 4-head adjusting rod, 5-lower support structure, 501-sleeve, 502-screw.
Detailed Description
All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
The present invention will be described in detail with reference to fig. 1.
Example 1
As shown in figure 1, the orienting device of the launcher comprises two tail support rods 1, a connecting rod 2, two stabilizing rods 3 and a head adjusting rod 4, wherein the two tail support rods 1 are symmetrically and vertically arranged, one point from the upper end to the middle point of the two tail support rods 1 is connected with two ends of the connecting rod 2, the connecting rod 2 is perpendicular to the two tail support rods 1, the upper ends of the two tail support rods 1 are respectively connected with the two stabilizing rods 3, the lower ends of the two stabilizing rods 3 are both connected with the front end of a lower supporting structure 5 of the launcher, the lower supporting structure 5 comprises a sleeve 501, the axis of which is connected with the stabilizing rods 3 is parallel to the tail support rods 1, and a screw 502 arranged in the sleeve 501, the upper end of the screw 502 is provided with a limiting structure larger than the inner diameter of the sleeve 501, the lower end of the screw 502 is a pointed end, and the head adjusting rod, the head adjusting rod 4 can adjust the angle.
Example 2
The difference between this embodiment and embodiment 1 is that two stabilizer bars are further arranged near the two tail support rods 1 to connect the tail support rods and the lower support structure of the launcher.
The two stabilizer bars 3 are also adjustable in length.
Two tail-support poles 1, a connecting rod 2, two stabilizer bars 3, a head adjusting lever 4 are hollow pole.
The head adjusting rod 4 adjusts the angle of the upper end supporting structure of the launching cradle by adjusting the length of the head adjusting rod.
The angle of the supporting structure at the upper end of the launching frame is adjusted by adjusting the connecting position of the head adjusting rod 4 and the supporting structure on the launching frame.
The head adjusting rod 4 adjusts the length of the screw inside by using a wheel disc to adjust the length of the head adjusting rod.
The above description is only for the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can be covered within the protection scope of the present invention without the changes or substitutions conceived by the inventive work within the technical scope disclosed by the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope defined by the claims.
Claims (7)
1. The utility model provides a orienting device of launcher, includes two tail-support poles (1), a connecting rod (2), two stabilizer bars (3), a head regulation pole (4), its characterized in that: the two tail support rods (1) are symmetrically and vertically arranged, one point from the upper ends to the middle point of the two tail support rods (1) is connected with two ends of a connecting rod (2), the connecting rod (2) is perpendicular to the two tail support rods (1), the upper ends of the two tail support rods (1) are respectively connected with two stabilizer bars (3), the lower ends of the two stabilizer bars (3) are connected with the front end of a lower support structure (5) of the launching cradle, the lower supporting structure comprises a sleeve (501) which is connected with the stabilizing rod (3) and the axis of which is parallel to the tail supporting rod (1), and also comprises a screw (502) which is arranged in the sleeve (501), the upper end of the screw rod (502) is provided with a limit structure which is larger than the inner diameter of the sleeve (501), the lower end of the screw rod (502) is a pointed end, the head adjusting rod (4) is connected with the front end of the lower supporting structure of the launching frame and the head supporting structure of the launching frame, and the head adjusting rod (4) can adjust the angle.
2. An orienting device for a launcher according to claim 1, wherein: the two tail support rods (1) are also provided with two stabilizer bars outside and connected with the tail support rods and the lower support structure of the launching frame.
3. An orienting device for a launcher according to claim 1, wherein: the two stabilizing rods (3) are also rods with adjustable length.
4. An orienting device for a launcher according to claim 1, wherein: the two tail support rods (1), the connecting rod (2), the two stabilizer bars (3) and the head adjusting rod (4) are hollow rods.
5. An orienting device for a launcher according to claim 1, wherein: the head adjusting rod (4) adjusts the angle of the supporting structure at the upper end of the launching frame by adjusting the length of the head adjusting rod.
6. An orienting device for a launcher according to claim 1, wherein: the angle of the supporting structure at the upper end of the launching frame is adjusted by adjusting the connecting position of the head adjusting rod (4) and the supporting structure on the launching frame.
7. An orienting device for a launcher according to claim 5, wherein: the head adjusting rod (4) adjusts the length of the screw inside by using a wheel disc to adjust the length of the head adjusting rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920369759.5U CN209814325U (en) | 2019-03-22 | 2019-03-22 | Orientation device of launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920369759.5U CN209814325U (en) | 2019-03-22 | 2019-03-22 | Orientation device of launcher |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209814325U true CN209814325U (en) | 2019-12-20 |
Family
ID=68876691
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920369759.5U Active CN209814325U (en) | 2019-03-22 | 2019-03-22 | Orientation device of launcher |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209814325U (en) |
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2019
- 2019-03-22 CN CN201920369759.5U patent/CN209814325U/en active Active
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