CN211108073U - Rotor unmanned vehicles capability test and trainer - Google Patents
Rotor unmanned vehicles capability test and trainer Download PDFInfo
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- CN211108073U CN211108073U CN201921570100.2U CN201921570100U CN211108073U CN 211108073 U CN211108073 U CN 211108073U CN 201921570100 U CN201921570100 U CN 201921570100U CN 211108073 U CN211108073 U CN 211108073U
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Abstract
The utility model discloses a rotor unmanned vehicles capability test and trainer, include: the device comprises an aircraft positioning disc, a Z-axis testing unit, an X-axis testing unit, a Y-axis testing unit, an XY-axis connecting unit, an equipment frame and a lifting support. The aircraft positioning disc is used for fixing the aircraft on the test platform; the Z-axis test unit is used for acquiring Z-direction rotation data and supporting the structure; the X-axis test unit is used for collecting X-direction rotation data and supporting the structure; the Y-axis test unit is used for collecting Y-direction rotation data and supporting the structure; the XY axis connecting unit is used for connecting the X axis testing unit and the Y axis testing unit; the equipment frame and the lifting bracket are used for driving the aircraft to move in the vertical direction; the utility model discloses can gather data information such as measurement aircraft lift, aerial gesture, pulling force, for rotor unmanned vehicles's performance and control personnel and control the training and provide the real equipment of instructing of experiment.
Description
Technical Field
The utility model relates to a test equipment technical field especially relates to a rotor unmanned vehicles capability test and trainer.
Background
At present, the technology of the rotor unmanned aerial vehicle is continuously and rapidly developed, and the rotor unmanned aerial vehicle is gradually popularized to the civil commercial field from military use. The wide application and popularization of the rotor unmanned aerial vehicle promote the rotor unmanned aerial vehicle to need a large amount of technical skills in the manufacturing and application industry. But the capability test of rotor unmanned aerial vehicle complete machine is less with operation training professional equipment, and especially control personnel in the earlier stage of learning operation, very easily cause rotor unmanned aerial vehicle to damage because of misoperation. Therefore, the rotor unmanned aerial vehicle performance testing and training device has great significance for rotor unmanned aerial vehicle research and education training.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to overcome the not enough of above-mentioned technique, and provide a rotor unmanned vehicles capability test and trainer.
The utility model discloses a realize above-mentioned purpose, adopt following technical scheme: the utility model provides a rotor unmanned vehicles capability test and trainer which characterized in that: the device comprises an aircraft positioning disc, a Z-axis testing unit, an X-axis testing unit, a Y-axis testing unit, an XY-axis connecting unit and a vertical moving unit; the aircraft positioning disc is mounted on the Z-axis testing unit and used for fixing an aircraft; the Z-axis testing unit is fixed on the X-axis testing unit; the X-axis testing unit is arranged on the XY axis connecting unit; the XY shaft connecting unit is arranged on the Y shaft testing unit; the vertical motion unit is divided into an equipment frame and a lifting support, the Y-axis test unit is fixed on the lifting support, and the lifting support is in up-and-down sliding fit with the frame.
Preferably, the aircraft positioning disc is provided with a T-shaped groove, the rotor unmanned aircraft is fixed on the positioning disc through a T-shaped screw,
preferably, the Z-axis testing unit comprises a bearing sleeve, a bearing set, a stepped mandrel and a gasket, wherein the bearing sleeve is used for installing the bearing set, the upper part of the stepped mandrel is fixedly connected with the bottom of the aircraft positioning disc, the stepped mandrel is matched with an inner ring of the bearing set, and the gasket is used for compressing the bearing set in the bearing sleeve.
Preferably, the X-axis test unit comprises a U-shaped bracket, a bearing baffle, an X-axis counterweight, an X-direction bearing sleeve and an X-direction supporting shaft; the upper portion of the U-shaped support is connected with the bottom of the bearing sleeve, X-direction bearing sleeves are mounted on two sides of the U-shaped support, one end of each X-direction supporting shaft is mounted inside the X-direction bearing sleeve, the other end of each X-direction supporting shaft is hinged to the XY shaft connecting unit, and the X-axis balance weight is fixed below the U-shaped support.
Preferably, the XY axis connecting unit comprises a rectangular bracket, an XY axis shaft sleeve and a Y axis counterweight; circular hole grooves are uniformly distributed on four sides of the rectangular support, XY shaft sleeves and the hole grooves are concentrically arranged on the rectangular support, the XY shaft sleeves are respectively hinged with the X-direction support shaft and the Y-axis testing unit, and the Y-axis balance weight is fixed below the rectangular support.
Preferably, the Y-axis test unit comprises a bottom plate, a Y-axis shaft sleeve and an L-type bracket, wherein the L-type bracket is fixed on the bottom plate, the two L-type brackets are symmetrically arranged and are concentric with the hole groove, and the Y-axis shaft sleeve is fixed on the L-type bracket and is concentric with the hole groove.
Preferably, the vertical motion unit comprises an equipment frame, a lifting support, a guide rail, a linear bearing, a bottom plate, a connecting plate, a pulley block, a large balancing weight and a steel cable, wherein the guide rail is fixed on the frame, the linear bearing is fixed on the connecting plate, the connecting plate is also fixed on the lifting support, the linear bearing slides along the guide rail, the bottom plate is fixed at the upper end of the lifting support, an L-shaped support is fixed on the bottom plate, the pulley block is fixed on the equipment frame, and the large balancing weight and the lifting support are connected through the steel cable.
Compared with the prior art, the utility model, this device can gather data information such as measurement aircraft lift, aerial gesture, pulling force, provides the real equipment of instructing of experiment for the performance of aircraft and control personnel operation training.
Drawings
Fig. 1 is a schematic structural diagram of the present invention;
FIG. 2 is a schematic view of the aircraft puck of the present invention;
FIG. 3 is a structural view of the Z-axis test unit of the present invention;
FIG. 4 is a schematic diagram of the X-axis test unit of the present invention;
FIG. 5 is a structural view of the XY spindle connecting unit of the present invention;
FIG. 6 is a structural diagram of the Y-axis test unit of the present invention;
FIG. 7 is a view of the structure of the vertical movement unit of the present invention;
in the figure, an aircraft positioning disc 1, a Z-axis testing unit 2, a bearing sleeve 21, a bearing group 22, a stepped mandrel 23 and a gasket 24, an X-axis testing unit 3, a U-shaped support 31, a bearing baffle 32, an X-axis counterweight 33, an X-axis bearing sleeve 34 and an X-axis supporting shaft 35, an XY-axis connecting unit 4, a rectangular support 41, a shaft sleeve 42 and a Y-axis counterweight 43, a Y-axis testing unit 5, a bottom plate 51, a shaft sleeve 52 and an L-shaped support 53, and a vertical moving unit comprises a lifting support 6, an equipment frame 7, a steel cable 71, a large balancing weight 72, a connecting plate 73, a linear bearing 74, a guide rail 75 and a pulley block 76.
Detailed Description
The following detailed description of the preferred embodiments of the present invention is provided in connection with the accompanying drawings. The utility model provides a rotor unmanned vehicles capability test and trainer, includes aircraft positioning disk 1, Z axle test unit 2, X axle test unit 3, XY hub connection unit 4, Y axle test unit 5, lifting support 6 and equipment frame 7.
A T-shaped groove is formed in the aircraft positioning disc 1, the aircraft is fixed on the positioning disc through T-shaped screws, and arc-shaped structures are arranged on two sides of the aircraft positioning disc 1 to increase the rigidity of the positioning disc.
The Z-axis testing unit 2 comprises a bearing sleeve 21, a bearing set 22, a stepped mandrel 23 and a gasket 24. The bearing sleeve 21 is used for mounting the bearing set 22, the stepped mandrel 23 is matched with an inner ring of the bearing set 33, and the washer 24 is used for pressing the bearing set 22 in the bearing sleeve 21. The Z-axis test unit 2 is used for collecting Z-direction rotation data and supporting the structure;
the X-axis test unit 3 comprises a U-shaped bracket 31, a bearing baffle 32, an X-axis counterweight 33, an X-direction bearing sleeve 34 and an X-direction supporting shaft 35; an X-direction bearing sleeve 34 is arranged on two sides of the U-shaped support 31, one end of an X-direction support shaft 35 is arranged in the X-direction bearing sleeve 34, the other end of the X-direction support shaft is hinged with the XY shaft connecting unit 4, an X-axis counterweight 33 is fixed below the U-shaped support 31, and the moment is in a balanced state in the X-axis direction. The X-axis test unit 3 is used for collecting X-direction rotation data and supporting the structure;
the XY axle connecting unit 4 comprises a rectangular bracket 41, a shaft sleeve 42 and a Y axle counterweight 43; circular hole grooves are uniformly distributed on four sides of the rectangular support 41, the shaft sleeve 42 and the hole grooves are concentrically arranged on the rectangular support 41, the shaft sleeve 42 is hinged with the X-axis testing unit 3 and the Y-axis testing unit 5 respectively, and the Y-axis counterweight 43 is fixed below the rectangular support 41 to enable the moment to be in a balanced state.
The Y-axis test unit 5 comprises a bottom plate 51, shaft sleeves 52 and L type supports 53, a L type support 53 is fixed on the bottom plate 51, the two L type supports 53 are symmetrically arranged and are concentric with each other, the shaft sleeve 52 is fixed on the L type support 53 and is concentric with the hole, and the Y-axis test unit 4 is used for collecting Y-direction rotation data and supporting the structures.
The vertical motion unit comprises a lifting bracket 6, an equipment frame 7, a steel cable 71, a large balancing weight 72, a connecting plate 73, a linear bearing 74, a guide rail 75 and a pulley block 76. The equipment frame 7 is fixed with a guide rail 75, the linear bearing 74 is fixed on the connecting plate 73, meanwhile, the connecting plate 73 is also fixed on the lifting support 6, the linear bearing 74 slides along the guide rail 75, the pulley block 76 is fixed on the equipment frame 7, the large counterweight 72 is connected with the lifting support 6 through a steel cable 71 which bypasses the pulley block 76, and the tension of the two ends of the pulley block 76 is kept equal.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (7)
1. The utility model provides a rotor unmanned vehicles capability test and trainer which characterized in that: the device comprises an aircraft positioning disc, a Z-axis testing unit, an X-axis testing unit, a Y-axis testing unit, an XY-axis connecting unit and a vertical moving unit; the aircraft positioning disc is mounted on the Z-axis testing unit and used for fixing an aircraft; the Z-axis testing unit is fixed on the X-axis testing unit; the X-axis testing unit is arranged on the XY axis connecting unit; the XY shaft connecting unit is arranged on the Y shaft testing unit; the vertical motion unit is divided into an equipment frame and a lifting support, the Y-axis test unit is fixed on the lifting support, and the lifting support is in up-and-down sliding fit with the frame.
2. The rotorcraft performance testing and training device of claim 1, wherein: a T-shaped groove is formed in the aircraft positioning disc, and the rotor unmanned aircraft is fixed on the positioning disc through T-shaped screws.
3. The rotorcraft performance testing and training device of claim 2, wherein: the Z-axis testing unit comprises a bearing sleeve, a bearing group, a stepped mandrel and a gasket, wherein the bearing sleeve is used for installing the bearing group, the upper part of the stepped mandrel is fixedly connected with the bottom of the aircraft positioning disc, the stepped mandrel is matched with the inner ring of the bearing group, and the gasket is used for compressing the bearing group in the bearing sleeve.
4. The rotorcraft performance testing and training device of claim 3, wherein: the X-axis testing unit comprises a U-shaped bracket, a bearing baffle, an X-axis counterweight, an X-direction bearing sleeve and an X-direction supporting shaft; the upper portion of the U-shaped support is connected with the bottom of the bearing sleeve, X-direction bearing sleeves are mounted on two sides of the U-shaped support, one end of each X-direction supporting shaft is mounted inside the X-direction bearing sleeve, the other end of each X-direction supporting shaft is hinged to the XY shaft connecting unit, and the X-axis balance weight is fixed below the U-shaped support.
5. The rotorcraft performance testing and training device of claim 4, wherein: the XY shaft connecting unit comprises a rectangular bracket, an XY shaft sleeve and a Y shaft counterweight; circular hole grooves are uniformly distributed on four sides of the rectangular support, XY shaft sleeves and the hole grooves are concentrically arranged on the rectangular support, the XY shaft sleeves are respectively hinged with the X-direction support shaft and the Y-axis testing unit, and the Y-axis balance weight is fixed below the rectangular support.
6. The rotary-wing unmanned aerial vehicle performance testing and training device of claim 5, wherein the Y-axis testing unit comprises a bottom plate, a Y-axis sleeve and a L-type bracket, wherein the L-type bracket is fixed on the bottom plate, the two L-type brackets are symmetrically arranged and are concentric with the hole groove, and the Y-axis sleeve is fixed on the L-type bracket and is concentric with the hole groove.
7. The rotor unmanned aerial vehicle performance testing and training device of claim 6, wherein the vertical motion unit comprises a device frame, a lifting bracket, a guide rail, a linear bearing, a bottom plate, a connecting plate, a pulley block, a large counterweight block and a steel cable, the guide rail is fixed on the frame, the linear bearing is fixed on the connecting plate, the connecting plate is also fixed on the lifting bracket, the linear bearing slides along the guide rail, the bottom plate is fixed at the upper end of the lifting bracket, an L-shaped bracket is fixed on the bottom plate, the pulley block is fixed on the device frame, and the large counterweight block is connected with the lifting bracket through the steel cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921570100.2U CN211108073U (en) | 2019-09-20 | 2019-09-20 | Rotor unmanned vehicles capability test and trainer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921570100.2U CN211108073U (en) | 2019-09-20 | 2019-09-20 | Rotor unmanned vehicles capability test and trainer |
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| Publication Number | Publication Date |
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| CN211108073U true CN211108073U (en) | 2020-07-28 |
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| CN201921570100.2U Active CN211108073U (en) | 2019-09-20 | 2019-09-20 | Rotor unmanned vehicles capability test and trainer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4129833A1 (en) * | 2021-08-06 | 2023-02-08 | Shanghai Autoflight Co., Ltd. | An unmanned aerial vehicle (uav) test bench |
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2019
- 2019-09-20 CN CN201921570100.2U patent/CN211108073U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4129833A1 (en) * | 2021-08-06 | 2023-02-08 | Shanghai Autoflight Co., Ltd. | An unmanned aerial vehicle (uav) test bench |
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