CN206031805U - Core plate during multiaxis aircraft is general - Google Patents

Abstract

The utility model discloses a general center plate of a multi-axis aircraft, which comprises a body, and a center hole is arranged in the center of the body; with the center hole as the center of a circle, at least four first assembling holes are arranged in a circular array from near to far. , at least six second assembly holes, and at least six third assembly holes, the second assembly holes are long arc through holes, and the arc of the second assembly holes is 15°-60°. The center plate of the utility model distributes assembly holes in an alternate array, which meets the relevant requirements of symmetrical installation structure and equal distances of the frame on the center plate; the number of optional holes for assembly and the installation direction realize the conversion from four axes to six axes; There are many types of mounting holes, and the fixed port can be selected according to the shape stability of the rack during use; it can effectively save installation time, and the fixing can be more convenient and stable, and the deformation of the rack by external force can also be effectively alleviated; by designing the center hole in the center , the function of the center hole is to reduce the weight of the center plate without affecting the performance of the center plate.

Description

A kind of universal center plate of multicopter

technical field

The utility model relates to a fixing device for mounting and fixing a multi-axis aircraft, in particular to a general center plate of a multi-axis aircraft.

Background technique

At present, the center plate of general-purpose multi-axis aircraft still has a long installation time, and the installation is not firm and stable enough, and the angle of the rack cannot be freely changed according to the ideal position of the rack on the center plate. When the flight control is out of control, the body will easily deform the frame when it falls from a high altitude, which may cause unnecessary property loss. In order to overcome the problems of long installation time and insufficient stability and firmness of the existing center panel of the aircraft, the utility model provides a The universal center plate of the multi-axis aircraft can not only make the installation more firm and stable, but also can freely change the angle or position of the aircraft frame according to the different aircraft structures. The center plate has a simple structure and light weight; it has versatility, and the frame is not easily deformed after the fixed point is fixed.

Utility model content

The purpose of the utility model is to provide a universal center plate of a multi-axis aircraft, which is more firm and stable in installation, simple in structure, light in weight, good in practicability, and not easily deformed.

The utility model is realized through the following technical solutions: a general center plate of a multi-axis aircraft, including a body, and a center hole is arranged in the center of the body; with the center hole as the center of a circle, at least four There are three first assembly holes, at least six second assembly holes, and at least six third assembly holes, the second assembly holes are long arc through holes, and the arc of the second assembly holes is 15°-60°.

The working principle of this technical solution is: according to the situation of different frames, select the first assembly hole, the second assembly hole and the third assembly hole located on the body, and install them in different positions to realize the multi-axis aircraft frame. The way of installation, the multi-axis aircraft frame can be adjusted freely according to different installation positions; the second assembly hole is a long arc through hole, which can make parts with different tolerances fit together during installation, which improves the adaptability of the parts themselves. The tolerance of the corresponding parts is also large, which is beneficial to reduce the processing difficulty and production cost of the parts; at the same time, the fixed positions during installation are the corresponding first assembly hole, the second assembly hole and the second assembly hole are long arcs There are four fixing points at both ends of the through hole, and the fixing method can make the frame of the multicopter be firmly installed on the center plate.

In order to better realize the utility model, further, the number of the third assembly holes is twelve, and they are evenly distributed on the outer edge of the body.

In order to better realize the utility model, further, the body is in the shape of a regular twelve prism, the central hole is a circle or a regular polygon, and the ratio of the radius of the circumscribed circle of the body to the radius of the circumscribed circle of the central hole is 3: 8. The main body is designed in a twelve-prism shape, which is convenient for better combining the frame of the multi-axis aircraft with the center plate. The size of the center hole can satisfy the weight of the center plate without affecting the performance of the center plate.

In order to better realize the utility model, further, cylindrical bosses coaxial with the central hole are provided on both sides of the body, and both the central hole and the first assembly hole pass through the bosses. The addition of bosses further improves the strength of the body, prevents the body from being deformed or broken when receiving an external force, and effectively enhances the strength of the center plate.

In order to better realize the utility model, further, there are fourth assembly holes distributed in a circular array between the first assembly hole and the fourth assembly hole, and the number of second assembly holes is eight, and the shape is Oval, the fourth assembly hole runs through the boss.

In order to better realize the utility model, further, the body and the boss form an integral structure, and are made of aluminum alloy. Aluminum alloy is stronger and lower in cost. It is preferred as the material of the body and the boss. The body and the boss are in an integrated structure, which is more convenient to install on the multi-axis aircraft.

Compared with the prior art, the utility model has the following advantages and beneficial effects:

(1) The center plate of the utility model distributes the assembly holes in an alternate array, which meets the relevant requirements of the rack on the center plate with a symmetrical structure and equal distances;

(2) The number of optional holes and the installation direction of the utility model can realize the conversion from four axes to six axes;

(3) The utility model has many kinds of assembly holes, and the fixed port can be selected according to the shape of the frame and the stability of the clamping during use; this can effectively save installation time, and the fixing can be more convenient and stable, and the frame is deformed by external force. can be effectively relieved.

(4) The utility model designs a center hole in the center, and the function of the center hole is to reduce the weight of the center plate without affecting the performance of the center plate.

Description of drawings

Other features, objects and advantages of the present invention will become more apparent by reading the detailed description of non-limiting embodiments with reference to the following drawings:

Fig. 1 is the structural representation of the utility model;

Fig. 2 is a side view of the utility model.

Among them: 1—first assembly hole, 2—second assembly hole, 3—third assembly hole, 4—fourth assembly hole, 5—body, 6—central hole, 7—boss.

detailed description

Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present utility model, but should not be construed as limiting the present utility model.

In describing the present utility model, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention. Novel and simplified descriptions do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the utility model. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be interpreted as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features. Therefore, the definition of "first" and "second" is for descriptive purposes only, and should not be understood as indicating or implying relative importance or implicitly including one or more of these features. In the description of the present utility model, unless otherwise specified, "plurality" means two or more.

In the description of the present utility model, it should be noted that, unless otherwise clearly stipulated and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a flexible connection. Detachable connection, or integral connection; it can be mechanical connection or electrical connection; it can also be direct connection or indirect connection through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

Example 1:

The main structure of the present embodiment, as shown in Figure 1, is a general-purpose center plate for a multi-axis aircraft, comprising a body 5, the center of which is provided with a center hole 6; with the center hole 6 as the center of a circle, it forms a ring from near to far. At least four first assembly holes 1, at least six second assembly holes 2, and at least six third assembly holes 3 are arranged in a shape array, the second assembly holes 2 are long arc through holes, and the second assembly holes The radian of 2 is 15 °-60 °.

The specific implementation method is to select the first assembly hole 1, the second assembly hole 2 and the third assembly hole 3 on the body 5 according to the situation of different racks, and install them in different positions to realize various installation methods of the rack ; The frame can be adjusted freely according to different installation positions. The fourth assembly hole 5 is a strip-shaped hole. During installation, parts with different tolerances can be installed together, which improves the adaptability of the parts themselves. The tolerance is also large, which is beneficial to reduce the processing difficulty and production cost of the parts; the fixed positions during installation are the two ends of the corresponding first assembly hole 1, the second assembly hole 2 and the third assembly hole 3, and the fixed There are four points, and the fixing method can make the rack firmly installed on the center board; the function of the center hole 6 is to reduce the weight of the center board without affecting the performance of the center board, and at the same time it has the function of wiring.

Example 2:

In this embodiment, on the basis of the above embodiments, the number of third assembly holes 3 is further limited. As shown in FIG. at the edge. The third assembly holes 3 are mainly for better fixing the periphery of the main body 5 on the multi-axis aircraft. Twelve are provided for uniform force and avoiding deformation of the main body 5 of the center plate. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Example 3:

On the basis of the above embodiments, this embodiment further defines the shape and size of the body 5 and the central hole. As shown in Figure 1, the body 5 is in the shape of a regular twelve prism, and the central hole 6 is circular Or it is a regular polygon, the ratio of the radius of the circumscribed circle of the body 6 to the radius of the circumscribed circle of the central hole 6 is 3:8. The body 5 is designed in a twelve-prism shape, which is convenient for better combining the frame of the multi-axis aircraft with the center plate. The size of the center hole 6 can meet the weight reduction of the center plate without affecting the performance of the center plate. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Example 4:

In this embodiment, on the basis of the above-mentioned embodiments, the structure of the boss 7 is further added, as shown in Figure 1 and Figure 2, the two sides of the body 5 are also provided with cylindrical bosses coaxial with the central hole 6 7. Both the central hole 6 and the first assembly hole 2 pass through the boss 7 . Adding the boss 7 further improves the strength of the main body 5, prevents the main body 5 from being deformed or broken when receiving an external force, and effectively enhances the strength of the center plate. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Example 5:

In this embodiment, on the basis of the above-mentioned embodiments, a fourth assembly hole 4 is further added. As shown in FIG. The fourth assembly hole 4 and the second assembly hole 3 are eight in number and oval in shape, and the fourth assembly hole 4 runs through the boss 7 . Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

Embodiment 6:

In this embodiment, on the basis of the above embodiments, it is further defined that the body 5 and the boss 7 are of an integral structure, and are made of aluminum alloy. Aluminum alloy is stronger and lower in cost, and is preferably used as the material of the body 5 and the boss 7. The body 5 and the boss 7 have an integrated structure, which is more convenient to install on a multi-axis aircraft. Other parts of this embodiment are the same as those of the foregoing embodiment, and will not be repeated here.

The above is only a preferred embodiment of the utility model, and does not limit the utility model in any form. Any simple modification or equivalent change made to the above embodiments according to the technical essence of the utility model falls within the scope of the present utility model. Protection scope of the present utility model.

Claims (6)

1. a kind of Multi-axis aircraft Universal centre plate, it is characterised in that including body（5）, body（5）Center be provided with centre bore （6）；With centre bore（6）For the center of circle, from the close-by examples to those far off array arrangement annular in shape has at least four first pilot holes successively（1）, at least Six the second pilot holes（2）, and at least six the 3rd pilot holes（3）, second pilot hole（2）For long arc through hole, second Pilot hole（2）Radian be 15 ° 60 °.

2. a kind of Multi-axis aircraft Universal centre plate according to claim 1, it is characterised in that：3rd pilot hole （3）Quantity be 12, and be evenly distributed on body（5）Outer edge.

3. a kind of Multi-axis aircraft Universal centre plate according to claim 1 and 2, it is characterised in that：The body（5）For Positive 12 is prismatic, the centre bore（6）For circular or regular polygon, body（5）Circumradius and centre bore（6） Circumradius ratio be 3：8.

4. a kind of Multi-axis aircraft Universal centre plate according to claim 3, it is characterised in that：The body（5）Both sides It is additionally provided with and centre bore（6）Concentric cylindrical boss（7）, the centre bore（6）With the first pilot hole（2）Run through boss （7）.

5. a kind of Multi-axis aircraft Universal centre plate according to claim 4, it is characterised in that：First pilot hole （1）With the 4th pilot hole（4）Between be additionally provided with the 4th pilot hole of array distribution annular in shape（4）, the second pilot hole（3）Quantity is Eight, it is shaped as ellipse, the 4th pilot hole（4）Through boss（7）.

6. a kind of Multi-axis aircraft Universal centre plate according to claim 5, it is characterised in that the body（5）With it is convex Platform（7）In integrative-structure, material is aluminium alloy.