CN216301477U

CN216301477U - Airborne transmitting station and unmanned aerial vehicle

Info

Publication number: CN216301477U
Application number: CN202123112904.8U
Authority: CN
Inventors: 刘庚鹏
Original assignee: Chongqing Yifei Zhilian Technology Co ltd
Current assignee: Chongqing Yifei Zhilian Technology Co ltd
Priority date: 2021-12-10
Filing date: 2021-12-10
Publication date: 2022-04-15
Anticipated expiration: 2031-12-10

Abstract

The application relates to the technical field of unmanned aerial vehicles, in particular to an airborne launching pad and an unmanned aerial vehicle, which comprise a mounting base, a connecting arm assembly and a launching assembly which are sequentially connected; the connecting arm subassembly is including being used for driving the transmission subassembly is relative mount pad pivoted first rotation driving piece, the axis of the output shaft of first rotation driving piece is first axis, the transmission subassembly includes main transmitting tube, the axis of main transmitting tube is the transmission axis, first axis with the transmission axis is crossing. The utility model provides an aim at is great to recoil when launching ammunition to current unmanned aerial vehicle weapon system, can produce great range vibrations by relative motor, and then influences the problem of the accuracy of hitting, provides an airborne launch pad and unmanned aerial vehicle.

Description

Airborne transmitting station and unmanned aerial vehicle

Technical Field

The application relates to the technical field of unmanned aerial vehicles, particularly, relate to an airborne launching pad and unmanned aerial vehicle.

Background

Unmanned aerial vehicles are unmanned aerial vehicles operated by radio remote control equipment and self-contained program control devices, and have been widely used in the military field as a new generation of aerial striking force. Present for military use unmanned aerial vehicle generally is equipped with the airborne launcher, and this airborne launcher is equipped with weapon system, and the output shaft through motor on the airborne launcher drives relative unmanned aerial vehicle organism motion, realizes the change of weapon system shooting direction, because weapon system recoil is great when launching ammunition, can produce great range vibrations by relative motor, and then influences the accuracy of hitting.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aim at is great to recoil when launching ammunition to current unmanned aerial vehicle weapon system, can produce great range vibrations by relative motor, and then influences the problem of the accuracy of hitting, provides an airborne launch pad and unmanned aerial vehicle.

In order to achieve the purpose, the following technical scheme is adopted in the application:

one aspect of the application provides an airborne launching pad, which comprises a mounting seat, a connecting arm assembly and a launching assembly which are sequentially connected; the connecting arm subassembly is including being used for driving the transmission subassembly is relative mount pad pivoted first rotation driving piece, the axis of the output shaft of first rotation driving piece is first axis, the transmission subassembly includes main transmitting tube, the axis of main transmitting tube is the transmission axis, first axis with the transmission axis is crossing.

Optionally, the connecting arm assembly further includes a first connecting arm, the firing assembly is mounted to the first connecting arm, and the first connecting arm is mounted to the mounting base through the first rotary driving member.

The technical scheme has the beneficial effects that: through first connecting arm with main launch tube direct mount in mount pad, the structure is simple relatively, stability when having improved main launch tube launch ammunition.

Optionally, the first connecting arm is an L-shaped rod, and the launching assembly is mounted on the inner side of the L-shaped rod.

The technical scheme has the beneficial effects that: this design, in which the first axis intersects the emission axis, is easier to achieve.

Optionally, the connecting arm assembly further includes a second rotation driving member for driving the launching assembly to rotate relative to the mounting base, an axis of an output shaft of the second rotation driving member is a second axis, and the second axis, the first axis and the launching axis intersect at a point.

The technical scheme has the beneficial effects that: when including first rotation driving piece and second rotation driving piece, make the transmission axis of main shooting pipe all intersect with first axis and second axis, the arm of force between recoil and first axis and the second axis is zero or nearly zero when the ammunition is launched, and this amplitude of oscillation of main shooting pipe relative first rotation driving piece and second rotation driving piece when having reduced the transmission ammunition, and then improve the accuracy of hitting.

Optionally, at least two of the first axis, second axis and the emission axis intersect perpendicularly with each other.

The technical scheme has the beneficial effects that: the installation of first rotation driving piece, second rotation driving piece and main launching tube is convenient for to this kind of position relation, and each relevant part is processed easily relatively, improves the production efficiency of machine-carried launch pad.

Optionally, the connecting arm assembly further comprises a second connecting arm and a second rotary driving member, the second connecting arm is mounted on the mounting seat through the second rotary driving member, and the launching assembly is mounted on the second connecting arm through the first rotary driving member. At this time, the emission axis may intersect only the first axis, or may intersect both the first axis and the second axis.

Optionally, the connecting arm assembly further includes a first connecting arm, the first connecting arm is mounted to the second connecting arm through the first rotary driving member, and the launching assembly is mounted to the first connecting arm.

Optionally, the launching assembly includes a plurality of launching tubes connected in parallel, the connecting arm assembly further includes a switching rotation driving member, and each launching tube is mounted on the first connecting arm through the switching rotation driving member, so that the switching rotation driving member can drive each launching tube to rotate relative to the first connecting arm, and further each launching tube can sequentially and alternately become the main launching tube.

The technical scheme has the beneficial effects that: under some circumstances, a plurality of launching tubes are needed to alternately launch ammunition, at the moment, the launching tube in the ammunition launching state becomes a main launching tube, the launching axis of the main launching tube is intersected with the first axis, or the launching axis, the first axis and the second axis are intersected at one point, so that the force arm of recoil force is zero or very small when the ammunition is launched each time, the stability when the ammunition is launched is further improved, and the accuracy of striking is improved.

Optionally, the launch assembly comprises three of the launch tubes.

Optionally, the first connecting arm and the second connecting arm are both L-shaped rods, the launching assembly is located on the inner side of the first connecting arm, and the launching assembly and the first connecting arm are both located on the inner side of the second connecting arm.

The technical scheme has the beneficial effects that: thus, when the first rotary driving part, the second rotary driving part and the launching assembly are installed, the first axis and the launching axis can be conveniently intersected vertically, or the first axis, the second axis and the launching axis can be conveniently intersected vertically.

Another aspect of the present application provides a drone, including an airborne launcher provided by the present application.

The technical scheme provided by the application can achieve the following beneficial effects:

the airborne launching pad and unmanned aerial vehicle that this application embodiment provided, because the axis of the output shaft of first rotation driving piece with the axis of main launching tube is crossing, when main launching tube launches the ammunition, the direction of recoil is crossing with the axis of the output shaft of first rotation driving piece, makes the arm of force size of recoil be zero or almost zero, and then reduces the moment that the recoil produced, the amplitude of fluctuation of main launching tube when reducing main launching tube and launching the ammunition improves the accuracy of hitting.

Additional features of the present application and advantages thereof will be set forth in the description which follows, or may be learned by practice of the present application.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings used in the description of the embodiments will be briefly described below. It should be apparent that the drawings in the following description are embodiments of the present application and that other drawings may be derived from those drawings by a person of ordinary skill in the art without inventive step.

Fig. 1 is a schematic perspective view of an embodiment of an airborne launcher provided in an embodiment of the present application;

fig. 2 is a schematic perspective view of another embodiment of an airborne transmitting station provided in the embodiments of the present application;

fig. 3 is a schematic perspective view of a third implementation of an airborne launcher provided in the examples of the present application;

fig. 4 is a schematic bottom view of fig. 3.

Reference numerals:

100-a mounting seat;

200-a first rotary drive;

300-a first connecting arm;

400-a transmitting assembly;

410-a main transmitting tube;

420-a launch tube;

500-a second rotary drive;

600-a second connecting arm;

700-switching the rotary drive.

Detailed Description

The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

As shown in fig. 1 to 4, one aspect of the present application provides an airborne launch pad comprising a mounting base 100, a connecting arm assembly and a launch assembly 400 connected in sequence; the connecting arm assembly comprises a first rotating driving part 200 for driving the launching assembly 400 to rotate relative to the mounting base 100, the axis of the output shaft of the first rotating driving part 200 is a first axis, the launching assembly 400 comprises a main launching tube 410, the axis of the main launching tube 410 is a launching axis, and the first axis is intersected with the launching axis. In the embodiment of the present application, the rotary drive member may be an electric motor, preferably a permanent magnet brushless motor.

The axis of the drive shaft of the rotary driving piece and the axis of the main launching tube 410 generally do not keep an intersection state, so that the distance between the axis of the drive shaft and the axis of the main launching tube 410 forms a moment arm of recoil, when the recoil of the launched ammunition is applied to the main launching tube 410, a large moment is formed, the launching tube relatively rotates the driving piece under the action of the moment, and further, relatively large swinging is generated on the unmanned aerial vehicle body, so that great deviation occurs in the accuracy of striking.

The airborne launching pad provided in the embodiment of the application, because the axis of the output shaft of the first rotary driving member 200 intersects with the axis of the main launching tube 410, when the main launching tube 410 launches ammunition, the direction of recoil intersects with the axis of the output shaft of the first rotary driving member 200, so that the force arm of recoil is zero or almost zero, the moment generated by recoil is further reduced, the swing amplitude of the main launching tube 410 when the main launching tube 410 launches ammunition is reduced, and the accuracy of striking is improved.

As shown in fig. 1, the connecting arm assembly further optionally includes a first connecting arm 300, the firing assembly 400 is mounted to the first connecting arm 300, and the first connecting arm 300 is mounted to the mounting base 100 through the first rotary driving member 200. The main shooting pipe 410 is directly mounted to the mounting base 100 through the first connecting arm 300, so that the structure is relatively simple, and the stability of the main shooting pipe 410 when ammunition is shot is improved.

Optionally, the first connecting arm 300 is an L-shaped rod, and the launching assembly 400 is mounted on the inner side of the L-shaped rod. This design, in which the first axis intersects the emission axis, is easier to achieve. Of course, the first connecting arm 300 may be a straight rod, and the firing assembly 400 and the first rotary driving member 200 may be mounted on both end surfaces of the straight rod, respectively.

As shown in fig. 2 to 4, optionally, the connecting arm assembly further includes a second rotary driving member 500 for driving the launching assembly 400 to rotate relative to the mounting base 100, an axis of an output shaft of the second rotary driving member 500 is a second axis, and the second axis, the first axis and the launching axis intersect at a point. When the ammunition firing device comprises the first rotary driving piece 200 and the second rotary driving piece 500, the firing axis of the main firing tube 410 is intersected with the first axis and the second axis, the recoil force and the force arm between the first axis and the second axis are zero or almost zero when ammunition is fired, the swing amplitude of the main firing tube 410 relative to the first rotary driving piece 200 and the second rotary driving piece 500 when ammunition is fired is reduced, and the accuracy of striking is improved. Of course, it is also possible to have a connecting arm assembly with more than two rotary drives and to have the axis of the output shaft of each rotary drive intersecting the firing axis of the main firing tube 410.

Optionally, at least two of the first axis, second axis and the emission axis intersect perpendicularly with each other. This positional relationship facilitates the installation of the first rotary driving member 200, the second rotary driving member 500 and the main launch tube 410, and the related components are relatively easy to process, thereby improving the production efficiency of the airborne launcher.

Optionally, the connecting arm assembly further includes a second connecting arm 600 and a second rotary driving member 500, the second connecting arm 600 is mounted on the mounting base 100 through the second rotary driving member 500, and the launching assembly 400 is mounted on the second connecting arm 600 through the first rotary driving member 200. At this time, the emission axis may intersect only the first axis, or may intersect both the first axis and the second axis. At this time, the emission axis may intersect only the first axis, or may intersect both the first axis and the second axis.

Optionally, the connecting arm assembly further comprises a first connecting arm 300, the first connecting arm 300 is mounted to the second connecting arm 600 through the first rotary driving member 200, and the firing assembly 400 is mounted to the first connecting arm 300.

Optionally, the launching assembly 400 includes a plurality of launching tubes 420 connected in parallel, the connecting arm assembly further includes a switching rotary driving member 700, and each launching tube 420 is mounted on the first connecting arm 300 through the switching rotary driving member 700, so that the switching rotary driving member 700 can drive each launching tube 420 to rotate relative to the first connecting arm 300, and further each launching tube 420 can sequentially and alternately become the main launching tube 410. In some cases, it is necessary to alternately fire ammunition by a plurality of firing tubes 420, at this time, the firing tube 420 in the ammunition firing state becomes the main firing tube 410, the firing axis of the main firing tube 410 intersects with the first axis, or the firing axis, the first axis and the second axis intersect at a point, so that the moment arm of recoil force is zero or small when ammunition is fired each time, thereby improving the stability when ammunition is fired and the accuracy of striking.

Optionally, the launch assembly 400 includes three of the launch tubes 420. The number of the transmitting tubes 420 can be specifically set according to the requirement, and can also be 2, 4, 5, 6 and the like. In the embodiment of the application, the launching assembly can be various ammunition launching devices at home and abroad, such as firearms (including various types of rifles and pistols) and rocket launchers, and can also be laser launching devices and liquid or gas spraying devices.

Optionally, the first connecting arm 300 and the second connecting arm 600 are both L-shaped rods, the firing assembly 400 is located inside the first connecting arm 300, and the firing assembly 400 and the first connecting arm 300 are both located inside the second connecting arm 600. In this way, it is convenient to have the first axis and the firing axis intersect perpendicularly, or to have the first axis, the second axis and the firing axis intersect perpendicularly, when the first rotary drive member 200, the second rotary drive member 500 and the firing assembly 400 are installed.

Another aspect of the present application provides an unmanned aerial vehicle, including the airborne transmitting station that the embodiment of the present application provided.

The unmanned aerial vehicle that this application embodiment provided has adopted the airborne firing platform that this application embodiment provided, because the axis of the output shaft of first rotation driving piece 200 with the axis of main launching tube 410 is crossing, when main launching tube 410 launches the ammunition, the direction of recoil is crossing with the axis of the output shaft of first rotation driving piece 200, makes the arm of force size of recoil zero or nearly zero, and then reduces the moment that the recoil produced, the swing range of main launching tube 410 when reducing main launching tube 410 and launching the ammunition improves the accuracy of hitting.

Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.

Claims

1. The airborne transmitting station is characterized by comprising a mounting seat, a connecting arm assembly and a transmitting assembly which are sequentially connected; the connecting arm subassembly is including being used for driving the transmission subassembly is relative mount pad pivoted first rotation driving piece, the axis of the output shaft of first rotation driving piece is first axis, the transmission subassembly includes main transmitting tube, the axis of main transmitting tube is the transmission axis, first axis with the transmission axis is crossing.

2. The airborne launcher according to claim 1, wherein said linking arm assembly further comprises a first linking arm, said launcher assembly being mounted to said first linking arm, said first linking arm being mounted to said mounting base by said first rotational drive.

3. The airborne launcher according to claim 2, wherein said first connecting arm is an L-shaped bar, said launcher assembly being mounted inside said L-shaped bar.

4. The airborne launcher according to claim 1, wherein the link arm assembly further comprises a second rotational drive member for rotating the launcher assembly relative to the mounting base, wherein an axis of an output shaft of the second rotational drive member is a second axis, and the second axis, the first axis, and the launch axis intersect at a point.

5. The airborne launcher according to claim 4, wherein at least two of said first axis, second axis, and said launch axis intersect perpendicularly with one another.

6. The airborne launcher according to any one of claims 1-5, wherein said linking arm assembly further comprises a second linking arm and a second rotational drive, said second linking arm being mounted to said mounting base by said second rotational drive, said launcher assembly being mounted to said second linking arm by said first rotational drive.

7. The airborne launcher according to claim 6, wherein said linking arm assembly further comprises a first linking arm mounted to said second linking arm by said first rotational drive, said launcher assembly being mounted to said first linking arm.

8. The airborne launcher according to claim 7, wherein the launcher assembly comprises a plurality of launcher tubes connected in parallel with one another, and the connecting arm assembly further comprises a switching rotary drive member, each of the launcher tubes being mounted to the first connecting arm by the switching rotary drive member, such that the switching rotary drive member can drive each of the launcher tubes to rotate relative to the first connecting arm, thereby enabling each of the launcher tubes to become the main launcher tube in turn.

9. The airborne launcher according to claim 7, wherein said first connecting arm and said second connecting arm are both L-shaped bars, said launcher assembly is located inside said first connecting arm, and said launcher assembly and said first connecting arm are both located inside said second connecting arm.

10. Unmanned aerial vehicle, comprising an airborne launch pad according to any of claims 1-9.