Flight controller based on edge calculation

Abstract

The utility model relates to the field of flight controller equipment, in particular to a flight controller based on edge calculation. The flight controller based on edge computing comprises a flight controller body and a structure fixing plate, the flight controller body is arranged above the structure fixing plate, the lower end of the flight controller body is installed on the upper portion of the structure fixing plate through a damping structure, and an expansion interface is arranged on the front side of the flight controller body. The flight controller has the advantages that the structural design is simple and reasonable, the flight controller can be connected with various types of flight equipment through configuration of the expansion interface, the edge computing flight controller body can be damped and protected through the design of the damping structure, interference of external vibration on the flight controller is avoided, and in addition, the structural fixing plate and the flight controller are designed in a split mode, so that the flight controller is more stable. And the structural compatibility of the flight controller on different flight equipment is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to flight controller equipment field, especially in kind based on edge calculation's flight controller. BACKGROUND

[0002] The edge computing aircraft has efficient real-time data processing capacity, can process flight data, flight attitude and positioning controller coordinates in real time, and can send the processing result to the cloud or other equipment. Such equipment usually has high-speed processor, GPS high-precision positioning, small size, low power consumption, the existing flight controller processing capacity is low, size is big, cannot satisfy the application scene of high -speed flight and multi -pose switching flight, and the damping system is not sensitive enough, and the attitude switching will influence the stability of work.

[0003] Therefore, it is necessary to develop a flight controller based on edge computing to overcome the above technical problems. UTILITY MODEL CONTENT

[0004] The utility model solves the technical problem that provide a kind of flight controller based on edge calculation, effectively overcome the defects of prior art.

[0005] The technical scheme that the utility model solves above technical problem is as follows:

[0006] A kind of flight controller based on edge calculation, including flight controller body and structure fixed plate, the flight controller body is set in the structure fixed plate upper, its lower end is equipped on the structure fixed plate upper portion by damping structure, the front side of the flight controller body is equipped with expansion interface.

[0007] On the basis of the above technical scheme, the utility model can also be improved as follows.

[0008] Further, the front side of the flight controller body is equipped with GPS interface.

[0009] Further, the left and right side of the flight controller body is equipped with SD card interface.

[0010] Further, the damping structure includes multiple groups of damping components, and the lower part of the opposite two side walls of the flight controller body is respectively provided with at least two groups of damping components.

[0011] Further, the lower part of the opposite two side walls of the flight controller body is provided with ear plate at intervals, and the damping component is arranged between the ear plate and the structure fixed plate.

[0012] Further, the damping assembly comprises a cylindrical damping air bag and fixing members fixed to upper and lower ends of the damping air bag respectively, the fixing member at the upper end is assembled with the ear plate, and the fixing member at the lower end is assembled with the structural fixing plate.

[0013] Further, the fixing member comprises a circular rubber block, the rubber block is connected and fixed to the middle of the corresponding end of the damping air bag through a short column coaxial with the rubber block and integrally formed, the upper surface of the ear plate is provided with a clamping groove matched with the rubber block, a first through hole is arranged at the center of the bottom of the clamping groove, the rubber block at the upper end is embedded in the clamping groove, and the short column at the upper end penetrates through the first through hole, the structural fixing plate is provided with a second through hole matched with the short column at the lower end, the rubber block at the lower end is attached to the lower surface of the structural fixing plate, and the short column at the lower end penetrates through the second through hole.

[0014] Further, the flight controller body has a detachable top plate, and the electrical elements in the flight controller body are arranged on the inner side of the top plate.

[0015] Further, the inner side of the top plate is attached with a heat dissipation pad, and the electrical elements in the flight controller body are distributed on the inner side of the heat dissipation pad.

[0016] Further, a plurality of assembly holes are arranged at the left and right side edges of the structural fixing plate in the front-rear direction.

[0017] The flight controller based on edge computing has the advantages that the structure is simple and reasonable, multiple types of flight equipment can be connected through the configuration of the expansion interface, the damping protection effect of the edge computing flight controller body can be achieved through the design of the damping structure, the interference of external vibration on the flight controller is avoided, and in addition, the structural compatibility of the flight controller on different flight equipment is increased due to the split design of the structural fixing plate and the flight controller. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 It is a structure perspective view of the flight controller based on edge computing of the utility model;

[0019] Figure 2 It is a structure side view of the flight controller based on edge computing of the utility model;

[0020] Figure 3 It is a structure top view of the flight controller based on edge computing of the utility model;

[0021] Figure 4 It is a structure schematic view of the damping assembly in the flight controller based on edge computing of the utility model.

[0022] In the drawings, the component list represented by each reference numeral is as follows: In the drawings, the component list represented by each reference numeral is as follows:

[0023] 1, flight controller body; 2, structure fixing plate; 3, damping assembly; 11, expansion interface; 12, GPS interface; 13, SD card interface; 14, ear plate; 15, top plate; 21, assembly hole; 31, damping air bag; 32, fixing piece; 321, rubber block. DETAILED DESCRIPTION

[0024] The principles and characteristics of the present application are described below in conjunction with the accompanying drawings, and the examples are only used to explain the present application and are not intended to limit the scope of the present application.

[0025] EMBODIMENT

[0026] As shown in FIGS. Figure 1 , 2 , the flight controller based on edge computing of the present embodiment includes a flight controller body 1 and a structure fixing plate 2. The flight controller body 1 is arranged above the structure fixing plate 2, and the lower end is arranged on the upper part of the structure fixing plate 2 through a damping structure. An expansion interface 11 is arranged on the front side of the flight controller body 1.

[0027] In the flight controller based on edge computing of the present embodiment, the flight controller body 1 is a product of the prior art. In the present embodiment, only the shape and structure of the outer shell are partially adjusted, and an expansion interface 11 (which is a product of the prior art on other instruments) is added. Through the design of the expansion interface 11, the flight controller based on edge computing has a wider range of applications. The design of the damping structure improves the performance of the flight controller, attenuates the vibration introduced by the aircraft, enhances the stability of the edge computing flight controller, and avoids the influence of external vibration on internal sensor data acquisition.

[0028] In the present embodiment, a GPS interface 12 is arranged on the front side of the flight controller body 1, which can be connected to a GPS antenna. The GPS interface 12 is a product of the prior art and is configured on many instruments, so no further description is given here.

[0029] In the present embodiment, an SD card interface 13 is arranged on any one side of the flight controller body 1. The SD card interface 13 is used to connect an SD storage card to expand the internal storage space. The SD card interface 13 is a product of the prior art and is applied to some other smart devices, so no further description is given here.

[0030] As a preferred embodiment, the damping structure includes a plurality of damping assemblies 3, and at least two groups of the damping assemblies 3 are arranged on the lower part of the opposite side walls of the flight controller body 1, respectively.

[0031] In the above embodiment, the vibration introduced by the flight controller body 1 during use is attenuated in various directions by multiple sets of damping assemblies 3, greatly enhancing the stability of the edge computing flight controller.

[0032] In the present embodiment, the lower part of the opposite side walls of the flight controller body 1 is provided with an ear plate 14, and the damping assembly 3 is arranged between the ear plate 14 and the structural fixing plate 2. The design of the ear plate 14 facilitates the assembly of the damping assembly 3.

[0033] In the present embodiment, as shown in Figure 4 The damping assembly 3 includes a cylindrical damping air bag 31 and a fixing member 32 fixed to the upper and lower ends of the damping air bag 31, respectively. The fixing member 32 at the upper end is assembled with the ear plate 14, and the fixing member 32 at the lower end is assembled with the structural fixing plate 2. In the above embodiment, the upper and lower end fixing members 32 facilitate the assembly of the damping air bag 31 and other components.

[0034] More specifically, the fixing member 32 includes a circular rubber block 321, which is connected and fixed to the middle part of the corresponding end of the damping air bag 31 through a short column coaxial and integrally formed with the rubber block 321. The upper surface of the ear plate 14 is provided with a clamping groove adapted to the rubber block 321, and the bottom center of the clamping groove is provided with a first through hole. The rubber block 321 at the upper end is embedded in the clamping groove, and the short column at the upper end passes through the first through hole. The structural fixing plate 2 is provided with a second through hole adapted to the short column at the lower end, and the rubber block 321 at the lower end is attached to the lower surface of the structural fixing plate 2, and the short column at the lower end passes through the second through hole. During assembly, the rubber block 321 at the upper end is extruded and deformed to pass through the first through hole on the ear plate 14, and then released in the clamping groove. The rubber block 321 at the lower end passes through the second through hole on the structural fixing plate 2, and then releases on the lower surface of the structural fixing plate 2. After the release of the two rubber blocks 321, the damping air bag 31 is stably connected between the ear plate 14 and the structural fixing plate 2, and the flight controller body 1 has good shock absorption performance in the vertical, horizontal and oblique directions relative to the structural fixing plate 2, effectively attenuating the vibration.

[0035] In the present embodiment, the flight controller body 1 has a detachable top plate 15, and the electrical components inside the flight controller body 1 are arranged inside the top plate 15. The top plate 15 is generally assembled by screwing a plurality of bolts spaced apart at the edges thereof with screw holes adapted on the inside of the lower half of the flight controller body 1. After the top plate 15 is opened, the internal electrical components are exposed, facilitating maintenance and repair.

[0036] In the embodiment, the heat dissipation pad is attached to the inner side of the top plate 15, and the electrical components in the flight controller body 1 are distributed in the heat dissipation pad.

[0037] In the embodiment, the structure fixing plate 2 is provided with a plurality of assembly holes 21 at the left and right side edges in the front-rear direction. The assembly holes 21 are penetrated by bolts to assemble other carriers or components.

[0038] In the description of the utility model, it is understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the utility model.

[0039] In addition, the terms "first" and "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" can explicitly or implicitly include at least one of the features. In the description of the utility model, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0040] In the utility model, unless otherwise specifically defined and limited, the terms "mounting", "connection", "connection", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication or interaction relationship between two elements, unless otherwise specifically limited. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0041] In the present application, unless otherwise explicitly specified and limited, the first feature is "on" or "under" the second feature, which can be direct contact between the first and second features, or indirect contact through an intermediate medium. Moreover, the first feature "above", "over" and "on" the second feature can be directly above or obliquely above the first feature, or only indicate that the first feature is higher than the second feature in horizontal height. The first feature "below", "under" and "under" the second feature can be directly below or obliquely below the first feature, or only indicate that the first feature is lower than the second feature in horizontal height.

[0042] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, the skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0043] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limiting the present application, and those skilled in the art can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A flight controller based on edge computing, characterized in that: The system includes a flight controller body (1) and a structural fixing plate (2). The flight controller body (1) is located above the structural fixing plate (2), and its lower end is mounted on the upper part of the structural fixing plate (2) through a shock-absorbing structure. An expansion interface (11) is provided on the front side of the flight controller body (1).

2. The flight controller based on edge computing according to claim 1, characterized in that: The flight controller body (1) is equipped with a GPS interface (12) on the front side.

3. The flight controller based on edge computing according to claim 1, characterized in that: An SD card interface (13) is provided on either the left or right side of the flight controller body (1).

4. The flight controller based on edge computing according to claim 1, characterized in that: The shock absorption structure includes multiple sets of shock absorption components (3), and at least two sets of the shock absorption components (3) are respectively provided at intervals on the lower part of the opposite side walls of the flight controller body (1).

5. A flight controller based on edge computing according to claim 4, characterized in that: The flight controller body (1) has ear plates (14) spaced apart on the lower part of the opposite side walls, and the shock absorption assembly (3) is provided between the ear plates (14) and the structural fixing plate (2).

6. A flight controller based on edge computing according to claim 5, characterized in that: The shock absorption assembly (3) includes a cylindrical shock absorption airbag (31) and fasteners (32) fixed to the upper and lower ends of the shock absorption airbag (31), respectively. The fastener (32) at the upper end is assembled with the ear plate (14), and the fastener (32) at the lower end is assembled with the structural fixing plate (2).

7. A flight controller based on edge computing according to claim 6, characterized in that: The fastener (32) includes a circular rubber block (321). The rubber block (321) is connected and fixed to the middle of the corresponding end of the shock-absorbing airbag (31) by a short column that is coaxial with and integrally formed thereon. The upper surface of the ear plate (14) is provided with a slot that is adapted to the rubber block (321). A first through hole is provided at the center of the bottom of the slot. The upper rubber block (321) is fitted into the slot and the upper short column passes through the first through hole. The structural fixing plate (2) is provided with a second through hole that is adapted to the lower short column. The lower rubber block (321) is attached to the lower surface of the structural fixing plate (2) and the lower short column passes through the second through hole.

8. A flight controller based on edge computing according to claim 1, characterized in that: The flight controller body (1) has a detachable top plate (15), and the electrical components inside the flight controller body (1) are installed inside the top plate (15).

9. A flight controller based on edge computing according to claim 8, characterized in that: A heat dissipation pad is attached to the inner side of the top plate (15), and the electrical components inside the flight controller body (1) are distributed on the inner side of the heat dissipation pad.

10. A flight controller based on edge computing according to any one of claims 1 to 9, characterized in that: The structural fixing plate (2) has multiple assembly holes (21) spaced apart along the front-back direction on both sides of its left and right edges.

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