阅读说明：本技术 一种无人机控制参数调试架 (Unmanned aerial vehicle control parameter debugging frame ) 是由 蒋佳霖 于 2020-06-18 设计创作，主要内容包括：本发明提出了一种无人机控制参数调试架,包括调试架,所述底座上设有若干个调试架,所述调试架的顶部外侧设有支撑滑台,所述调试架上设有电动推杆,所述电动推杆的推进端与所述支撑滑台的下方相连接,所述调试架的顶部中央设有连接件,所述支撑滑台顶部中央设有通孔,所述连接件的上端穿过所述通孔,所述连接件的上端设有飞机固定座,所述飞机固定座上设有无人机,所述调试架的下部设有底座。与现有技术相比,通过将飞机安装在调试架上限制其平移自由度,而不限制其旋转自由度,从而降低了调试过程中的安全隐患；提供了两种调试方式；支撑滑台可以在飞机起飞解锁前锁定飞机的姿态,起飞后再下降支撑滑台,使得飞机可以自由转动。(The invention provides an unmanned aerial vehicle control parameter debugging frame which comprises a debugging frame, wherein a plurality of debugging frames are arranged on a base, a supporting sliding table is arranged on the outer side of the top of each debugging frame, an electric push rod is arranged on each debugging frame, the pushing end of each electric push rod is connected with the lower part of each supporting sliding table, a connecting piece is arranged in the center of the top of each debugging frame, a through hole is formed in the center of the top of each supporting sliding table, the upper end of each connecting piece penetrates through the through hole, an aircraft fixing seat is arranged at the upper end of each connecting piece, an unmanned aerial vehicle is arranged on each aircraft fixing seat, and a base is arranged at the lower part of each debugging frame. Compared with the prior art, the airplane is arranged on the debugging frame to limit the translational freedom degree of the airplane, but not to limit the rotational freedom degree of the airplane, so that the potential safety hazard in the debugging process is reduced; two debugging modes are provided; the supporting sliding table can lock the attitude of the airplane before the airplane takes off and is unlocked, and the supporting sliding table descends after the airplane takes off, so that the airplane can rotate freely.)

1. The utility model provides an unmanned aerial vehicle control parameter debugging frame which characterized in that: comprises a debugging frame (1), a base (2), a supporting sliding table (3), an electric push rod (4), an airplane fixing seat (5) and a connecting piece (7), a plurality of debugging frames (1) are arranged on the base (2), a supporting sliding table (3) is arranged on the outer side of the top of each debugging frame (1), an electric push rod (4) is arranged on the debugging frame (1), the propelling end of the electric push rod (4) is connected with the lower part of the supporting sliding table (3), the center of the top of the debugging frame (1) is provided with a connecting piece (7), the center of the top of the supporting sliding table (3) is provided with a through hole (32), the upper end of the connecting piece (7) passes through the through hole (32), the upper end of the connecting piece (7) is provided with an airplane fixing seat (5), be equipped with unmanned aerial vehicle (6) on aircraft fixing base (5), the lower part of debugging frame (1) is equipped with base (2).

2. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: the connecting piece (7) is of a ball head hinge structure, a ball head seat (51) is arranged in the center of the bottom of the airplane fixing seat (5), a fixing plate (52) is arranged below the ball head seat (51), and the ball head end of the connecting piece (7) penetrates through the fixing plate (52) to be connected with the ball head seat (51).

3. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: the connecting piece (7) is of a dead axle hinge structure, a connecting seat (53) matched with the dead axle hinge is arranged at the bottom of the airplane fixing seat (5), a fixing plate (52) is arranged below the connecting seat (53), and the dead axle end of the connecting piece (7) penetrates through the fixing plate (52) to be connected with the connecting seat (53).

4. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: the bottom of the connecting piece (7) is sleeved with a quick-release piece (71), and the lower end of the quick-release piece (71) penetrates through the through hole (32) to be connected with the debugging frame (1).

5. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: the top structure of the aircraft fixing seat (5) is matched with the bottom structure of the unmanned aerial vehicle (6), and the aircraft fixing seat (5) and the unmanned aerial vehicle (6) are reinforced through an aircraft fixing binding belt (54).

6. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: be equipped with a plurality of bottom rod (21) that stabilize on base (2), a plurality of down tube (22) that stabilize between base (2) and debugging frame (1), be equipped with connecting rod (23) between debugging frame (1).

7. The unmanned aerial vehicle control parameter debugging frame of claim 1, characterized in that: and a rubber pad (31) is arranged at the top of the supporting sliding table (3).

[ technical field ] A method for producing a semiconductor device

The invention relates to the technical field of unmanned aerial vehicle debugging devices, in particular to an unmanned aerial vehicle control parameter debugging frame.

[ background of the invention ]

The unmanned aerial vehicle is an unmanned aerial vehicle operated by utilizing a radio remote control device and a self-contained program control device, has wide application, and is applied to the industries of police, city management, agriculture, geology, meteorology, electric power, emergency rescue and relief, video shooting and the like.

Unmanned aerial vehicle debugs control parameter at the design in-process to try out reasonable parameter, among the prior art, unmanned aerial vehicle's debugging adopts the form that actual space tried to fly mostly, has certain potential safety hazard like this in the debugging process.

[ summary of the invention ]

The invention aims to provide an unmanned aerial vehicle control parameter debugging frame to solve the problem that a certain potential safety hazard exists in the unmanned aerial vehicle debugging process in the prior art.

In order to achieve the purpose, the invention provides the following technical scheme:

the application discloses unmanned aerial vehicle control parameter debugging frame, including debugging frame, base, support slip table, electric putter, aircraft fixing base and connecting piece, be equipped with a plurality of debugging frame on the base, the top outside of debugging frame is equipped with supports the slip table, be equipped with electric putter on the debugging frame, electric putter's propulsion end with the below of supporting the slip table is connected, the top central authorities of debugging frame are equipped with the connecting piece, it is equipped with the through-hole to support slip table top central authorities, the upper end of connecting piece is passed the through-hole, the upper end of connecting piece is equipped with the aircraft fixing base, be equipped with unmanned aerial vehicle on the aircraft fixing base, the lower part of debugging frame is equipped with the base.

Preferably, the connecting piece is of a ball head hinge structure, a ball head seat is arranged in the center of the bottom of the aircraft fixing seat, a fixing plate is arranged below the ball head seat, and a ball head end of the connecting piece penetrates through the fixing plate to be connected with the ball head seat.

Preferably, the connecting piece is of a dead axle hinge structure, the bottom of the airplane fixing seat is provided with a connecting seat matched with the dead axle hinge, a fixing plate is arranged below the connecting seat, and the dead axle end of the connecting piece penetrates through the fixing plate to be connected with the connecting seat.

Preferably, the bottom of the connecting piece is sleeved with a quick-release piece, and the lower end of the quick-release piece penetrates through the through hole to be connected with the debugging frame.

Preferably, the top structure of the aircraft fixing seat is matched with the bottom structure of the unmanned aerial vehicle, and the aircraft fixing seat and the unmanned aerial vehicle are reinforced through an aircraft fixing bandage.

Preferably, the base is provided with a plurality of stable bottom rods, a plurality of stable inclined rods are arranged between the base and the debugging frame, and connecting rods are arranged between the debugging frames.

Preferably, a rubber pad is arranged at the top of the supporting sliding table.

The invention has the beneficial effects that: compared with the prior art, the unmanned aerial vehicle control parameter debugging frame provided by the invention has the advantages that the structure is reasonable:

(1) the aircraft is arranged on the debugging frame to limit the translational freedom degree of the aircraft, but not to limit the rotational freedom degree of the aircraft, so that the potential safety hazard in the debugging process is reduced.

(2) Two debugging modes are provided, one mode is that a connecting piece adopts a ball joint hinge to allow any axis of the airplane to rotate; the other is that the connecting piece adopts a fixed-axis hinge and only allows the airplane to rotate on one axis.

(3) The supporting sliding table is designed, the attitude of the airplane can be locked before the airplane takes off and is unlocked, and the supporting sliding table descends through the electric push rod after the airplane takes off, so that the airplane can rotate freely.

(4) The quick-release part is designed between the connecting part and the debugging frame, and the quick connection and the fixation between the quick-release part and the debugging frame are realized.

The features and advantages of the present invention will be described in detail by embodiments in conjunction with the accompanying drawings.

[ description of the drawings ]

Fig. 1 is a schematic front structural view of an unmanned aerial vehicle control parameter debugging frame of the invention;

FIG. 2 is a schematic structural diagram of an unmanned aerial vehicle control parameter debugging frame according to the present invention;

FIG. 3 is a schematic view of the attachment of the present invention using a ball joint hinge;

FIG. 4 is a schematic view of the installation of the connector of the present invention using a fixed axis hinge;

FIG. 5 is a schematic front view of the limiting mechanism of the present invention;

fig. 6 is a schematic front view of the support slide table of the present invention when releasing the limit.

In the figure: 1-debugging frame, 2-base, 21-stable low rod, 22-stable inclined rod, 23-connecting rod, 3-supporting sliding table, 31-rubber pad, 32-through hole, 4-electric push rod, 5-airplane fixing seat, 51-ball seat, 52-fixing plate, 53-connecting seat, 54-airplane fixing binding band, 6-unmanned aerial vehicle, 7-connecting piece and 71-quick-dismantling piece.

[ detailed description ] embodiments

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings and examples. It should be understood, however, that the description herein of specific embodiments is only intended to illustrate the invention and not to limit the scope of the invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.

Referring to fig. 1 to 6, the embodiment of the invention provides an unmanned aerial vehicle control parameter debugging frame, which comprises a debugging frame 1, a base 2, a supporting sliding table 3, an electric push rod 4, an airplane fixing seat 5 and a connecting piece 7, wherein the base 2 is provided with a plurality of debugging frames 1, the supporting sliding table 3 is arranged on the outer side of the top of each debugging frame 1, the debugging frame 1 is provided with the electric push rod 4, the pushing end of the electric push rod 4 is connected with the lower part of the supporting sliding table 3, the center of the top of each debugging frame 1 is provided with the connecting piece 7, the center of the top of each supporting sliding table 3 is provided with a through hole 32, the upper end of each connecting piece 7 penetrates through the through hole 32, the upper end of each connecting piece 7 is provided with the airplane fixing seat 5, the airplane fixing seat 5 is provided with the unmanned aerial vehicle 6, and the lower part of each debugging frame 1 is provided with the base 2.

The connecting piece 7 is of a ball head hinge structure, a ball head seat 51 is arranged in the center of the bottom of the aircraft fixing seat 5, a fixing plate 52 is arranged below the ball head seat 51, and the ball head end of the connecting piece 7 penetrates through the fixing plate 52 to be connected with the ball head seat 51. The connecting piece 7 is of a fixed-axis hinge structure, the bottom of the airplane fixing seat 5 is provided with a connecting seat 53 matched with the fixed-axis hinge, a fixing plate 52 is arranged below the connecting seat 53, and the fixed-axis end of the connecting piece 7 penetrates through the fixing plate 52 to be connected with the connecting seat 53. The bottom of the connecting piece 7 is sleeved with a quick-release piece 71, and the lower end of the quick-release piece 71 penetrates through the through hole 32 to be connected with the debugging frame 1.

The top structure of the aircraft fixing seat 5 is matched with the bottom structure of the unmanned aerial vehicle 6, and the aircraft fixing seat 5 and the unmanned aerial vehicle 6 are reinforced through an aircraft fixing bandage 54. The base 2 is provided with a plurality of stable bottom rods 21, a plurality of stable inclined rods 22 are arranged between the base 2 and the debugging frame 1, and a connecting rod 23 is arranged between the debugging frame 1. The top of the support sliding table 3 is provided with a rubber pad 31.

The working process of the invention is as follows:

when carrying out the unipolar pivot debugging, it is fixed with unmanned aerial vehicle 6's bottom and aircraft fixing base 5, and consolidate the back with aircraft fixing bandage 54, connect dead axle hinged joint spare 7 on the connecting seat 53 of aircraft fixing base 5 bottom, reuse fixed plate 52 is fixed the back, install connecting piece 7 at debugging frame 1 top through quick detach 71, will support slip table 3 and push away to the top through electric putter 4, make support slip table 3 and aircraft fixing base 5 contactless each other, the unblock aircraft, operation electric putter 4 will support slip table 3 and glide gradually, make the aircraft begin to carry out the unipolar debugging.

When carrying out the qxcomm technology pivot debugging, it is fixed with unmanned aerial vehicle 6's bottom and aircraft fixing base 5, and consolidate the back with aircraft fixing bandage 54, install bulb seat 51 in aircraft fixing base 5 bottom, and be connected bulb seat 51 with bulb hinged joint spare 7, reuse fixed plate 52 is fixed the back, install connecting piece 7 at debugging frame 1 top through quick detach piece 71, will support slip table 3 and push away to the top through electric putter 4, make and support slip table 3 and aircraft fixing base 5 mutual contact, the unblock aircraft, operation electric putter 4 will support slip table 3 and glide gradually, make the unmanned aerial vehicle begin to carry out the qxcomm technology pivot debugging.

In two debugging processes, unmanned aerial vehicle 6 is restricted its translation degree of freedom on debugging frame 1, and does not restrict its rotation degree of freedom to can debug unmanned aerial vehicle 6 under the circumstances of guaranteeing safety

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents or improvements made within the spirit and principle of the present invention should be included in the scope of the present invention.