Novel unmanned aerial vehicle fixed test system

Abstract

The utility model discloses a novel unmanned aerial vehicle fixed test system, which comprises an unmanned aerial vehicle, a tilt angle sensor, a connecting plate, a joint bearing, a central shaft, a bearing seat, a screw rod, a balancing weight and a supporting base. The two ends of the knuckle bearing are connected with the unmanned aerial vehicle and the balancing weight respectively, the gravity center of the movable part is adjusted to the center of the knuckle bearing, the stress condition of the unmanned aerial vehicle flying in the air is truly reflected, the pitching or yawing posture is adjusted through the remote controller, and tilt data on all coordinate axes are transmitted and recorded through the tilt angle sensor. Checking whether the comprehensive performance of the unmanned aerial vehicle meets flight requirements or not. The utility model can effectively solve the problems that the existing unmanned aerial vehicle is high in test flight explosion rate and the data cannot be reproduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane application technical field, especially a novel unmanned plane fixed type test system. BACKGROUND

[0002] With the development of low altitude economy, the unmanned plane application is also more and more extensive. But for the beginner or new machine just assembly, the performance of unmanned plane is not very clear, and the test flight process often occurs the situation of blowing machine, which causes economic loss, and is not conducive to the promotion of skills. The unmanned plane detection device on the market at present is mostly aimed at single part, such as motor, propeller, electric governor etc., and can not reflect the performance parameter of whole machine. In view of the above problems, a novel unmanned plane fixed type test system is urgently needed. UTILITY MODEL CONTENT

[0003] The utility model is directed at the lack of unmanned plane whole machine test device on the market at present, and the situation of blowing machine often occurs in the test flight process, and a novel unmanned plane fixed type test system is proposed.

[0004] The technical solution for realizing the utility model is as follows: a novel unmanned plane fixed type test system, including unmanned plane, inclination sensor, connecting plate, joint bearing, center shaft, bearing seat, screw rod, counterweight, supporting base, the inclination sensor is stuck in the center position of unmanned plane, the unmanned plane is fixed on the connecting plate through screw, the center shaft is matched with the inner ring of joint bearing, the joint bearing is fixed in the center position of bearing seat, the bearing seat is fixed on the supporting base, the screw rod passes through the inner hole of connecting plate and center shaft, and is locked at both ends with nut, the counterweight is matched with the screw thread of screw rod.

[0005] Further, the unmanned plane can be adjusted in three attitudes of pitching, yawing and rolling through remote controller.

[0006] Further, the inclination sensor supports wireless transmission data, and can measure three-axis angle and angular acceleration.

[0007] Further, the inner ring of joint bearing can rotate and incline freely relative to the outer ring, and the friction coefficient is small.

[0008] Further, the center shaft is matched with the inner ring of joint bearing in interference, can realize synchronous rotation, and the center screw hole can be connected with screw rod.

[0009] Further, the counterweight is connected with the screw thread of screw rod, can adjust the position of counterweight according to the weight of unmanned plane, so that the center of movable part is in the center of joint bearing.

[0010] Further, the supporting base is heavy, and can prevent the whole system from overturning when the attitude of unmanned plane is changed.

[0011] Compared with the prior art, the utility model has the following remarkable advantages:

[0012] 1) the unmanned aerial vehicle is connected through the joint bearing, so that the unmanned aerial vehicle can complete attitude actions such as pitching, yawing and rolling without real take-off, and the occurrence of the airplane explosion accident is avoided.

[0013] 2) the distance between the counterweight and the joint bearing is adjusted, so that the moment balance of the unmanned aerial vehicle and the counterweight is achieved, the gravity center of the movable part is located at the center position of the joint bearing, when the remote controller controls the unmanned aerial vehicle to pitch, yaw and roll, the whole test system can be not affected by the counterweight, fast response instruction is achieved, and the reality of the test is improved.

[0014] 3) the three-axis attitude data of the unmanned aerial vehicle are transmitted to the storage device in real time through the inclination sensor, data can be sorted and analyzed, the whole machine performance of the unmanned aerial vehicle is judged, targeted adjustment is carried out, and the skill improvement of beginners can also be used.

[0015] The utility model will be further described in detail below with reference to the drawings. DRAWINGS

[0016] Fig. 1 It is a structure diagram of the novel unmanned aerial vehicle fixed type test system provided in an embodiment.

[0017] Fig. 2 It is a partial sectional view of the novel unmanned aerial vehicle fixed type test system provided in an embodiment.

[0018] The drawings are as follows: unmanned aerial vehicle 1, inclination sensor 2, connecting plate 3, joint bearing 4, center shaft 5, bearing seat 6, lead screw 7, counterweight 8, supporting base 9. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the application more clear and understandable, the application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the application, and are not used to limit the application.

[0020] It should be noted that if the embodiment of the utility model has directionality indication (such as up, down, left, right, front, back, etc.), the directionality indication is only used to explain the relative position relationship, movement condition and the like between the components in a certain specific posture (such as shown in the drawings), if the specific posture changes, the directionality indication also changes accordingly.

[0021] In addition, if the description of "first", "second" and the like is involved in the embodiments of the utility model, the description of "first", "second" and the like is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features with "first" and "second" can be explicitly or implicitly included at least one feature. In addition, the technical solutions of various embodiments can be combined with each other, but it must be based on the realization of ordinary technical personnel, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope required by the utility model.

[0022] In combination Figs. 1-2 In one embodiment, a new unmanned aerial vehicle fixed test system is provided, comprising an unmanned aerial vehicle 1, an inclination sensor 2, a connecting plate 3, a joint bearing 4, a center shaft 5, a bearing seat 6, a lead screw 7, a counterweight 8 and a supporting base 9. The inclination sensor 2 is adhered to the center position of the unmanned aerial vehicle 1. The unmanned aerial vehicle 1 is fixed on the connecting plate 3 through screws. The center shaft 5 is matched with the inner ring of the joint bearing 4. The joint bearing 4 is fixed at the center position of the bearing seat 6. The bearing seat 6 is fixed on the supporting base 9. The lead screw 7 passes through the inner hole of the connecting plate 3 and the center shaft 5, and is locked at both ends by nuts. The counterweight 8 is matched with the lead screw 7 in screw threads.

[0023] The working principle of the unmanned aerial vehicle fixed test system is as follows: the unmanned aerial vehicle 1 is fixed on the joint bearing 4 through the connecting plate 3 and the center shaft 5, and can freely move with the inner ring of the bearing. The adjustable counterweight 8 is used to transfer the center of gravity of the movable part to the center of the joint bearing 4, so that the unmanned aerial vehicle 1 can more sensitively respond to the instructions of the external remote controller, and the flight performance of the unmanned aerial vehicle 1 can be tested in a fixed condition. At the same time, the inclination sensor 2 is used to measure the three-axis attitude of the unmanned aerial vehicle 1 in real time, and data acquisition is carried out, so that the flight process can be recorded and analyzed.

[0024] Further, in one of the embodiments, the unmanned aerial vehicle can be adjusted in pitch, yaw and roll attitudes through a remote controller.

[0025] Further, in one of the embodiments, the inclination sensor supports wireless data transmission, and can measure three-axis angles and angular acceleration.

[0026] Further, in one of the embodiments, the inner ring of the joint bearing can freely rotate and tilt relative to the outer ring, and the friction coefficient is small.

[0027] Further, in one of the embodiments, the center shaft is interference-fitted with the inner ring of the joint bearing, synchronous rotation can be realized, and the center screw hole can be connected with the lead screw.

[0028] Further, in one of the embodiments, the counterweight is threadedly connected with the lead screw, and the position of the counterweight can be adjusted according to the weight of the unmanned aerial vehicle, so that the center of the movable part is located at the center of the joint bearing.

[0029] Further, in one of the embodiments, the support base has a large weight, and can prevent the whole system from overturning when the posture of the unmanned aerial vehicle is changed.

[0030] In conclusion, the utility model connects the unmanned aerial vehicle with the joint bearing, so that the unmanned aerial vehicle can complete posture actions such as pitching, yawing and rolling without actually taking off, and the explosion of the unmanned aerial vehicle is avoided; the distance between the counterweight and the joint bearing is adjusted, so that the moment of the unmanned aerial vehicle and the counterweight is balanced, and the center of gravity of the movable part is located at the center of the joint bearing; when the remote controller controls the unmanned aerial vehicle to pitch, yaw and roll, the whole test system can quickly respond to the instruction without being affected by the counterweight, and the test authenticity is improved; the three-axis posture data of the unmanned aerial vehicle are transmitted to the storage device in real time through the inclination sensor, the data can be sorted and analyzed, the performance of the whole unmanned aerial vehicle can be judged, and targeted adjustment can be made; in addition, the utility model can also be used for improving the skills of beginners.

[0031] The above is only the preferred embodiment of the utility model, and does not limit the utility model. Any person skilled in the art can make any form of equivalent replacement, modification or change to the technical scheme and technical content disclosed by the utility model without departing from the technical scheme of the utility model, and the change still belongs to the protection scope of the utility model.

Claims

1. A novel fixed-type testing system for unmanned aerial vehicles (UAVs), characterized in that, The system includes a drone (1), a tilt sensor (2), a connecting plate (3), a joint bearing (4), a central shaft (5), a bearing seat (6), a lead screw (7), a counterweight (8), and a support base (9). The tilt sensor (2) is attached to the center of the drone (1). The drone (1) is fixed to the connecting plate (3) with screws. The central shaft (5) is engaged with the inner ring of the joint bearing (4). The joint bearing (4) is fixed to the center of the bearing seat (6). The bearing seat (6) is fixed to the support base (9). The lead screw (7) passes through the inner holes of the connecting plate (3) and the central shaft (5), and is locked at both ends with nuts. The counterweight (8) is threadedly engaged with the lead screw (7).

2. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The UAV (1) can be adjusted in three attitudes: pitch, yaw, and roll via remote control.

3. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The tilt sensor (2) supports wireless data transmission and can measure triaxial angles and angular acceleration.

4. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The inner ring of the spherical bearing (4) can rotate and tilt freely relative to the outer ring, and has a small coefficient of friction.

5. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The central shaft (5) is interference-fitted with the inner ring of the spherical bearing (4) to achieve synchronous rotation, and the central screw hole can be connected to the lead screw (7).

6. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The counterweight (8) is threadedly connected to the lead screw (7). The position of the counterweight (8) can be adjusted according to the weight of the UAV (1) so that the center of the moving part is at the center of the joint bearing (4).

7. The novel fixed-type testing system for unmanned aerial vehicles according to claim 1, characterized in that, The support base (9) is heavy and can prevent the entire system from tipping over when the UAV (1) changes attitude.

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