CN211969778U - Angle adjusting device and test unmanned aerial vehicle - Google Patents
Angle adjusting device and test unmanned aerial vehicle Download PDFInfo
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- CN211969778U CN211969778U CN202020199024.5U CN202020199024U CN211969778U CN 211969778 U CN211969778 U CN 211969778U CN 202020199024 U CN202020199024 U CN 202020199024U CN 211969778 U CN211969778 U CN 211969778U
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Abstract
The application discloses an angle adjusting device and a test unmanned aerial vehicle, wherein the angle adjusting device comprises a base unit, a first adjusting unit and a second adjusting unit; the first end of the first adjusting unit is directly and movably connected with the base unit, the second end of the first adjusting unit is movably connected with the base unit through the first lifting module, similarly, the first end of the second adjusting unit is directly and movably connected with the first adjusting unit, the second end of the second adjusting unit is movably connected with the first adjusting unit through the second lifting module, the first end and the second end of the first adjusting unit are arranged along a first direction, and the first end and the second end of the second adjusting unit are arranged along a second direction perpendicular to the first direction; like this, through adjusting first lifting module and second lifting module simultaneously, can be so that the rotor motor shaft of locating the second adjustment unit has the inclination of two directions simultaneously to the technical problem of measuring rotor motor shaft roll angle and inclination simultaneously and influencing flight performance has been solved.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to an angular adjustment device and test unmanned aerial vehicle of many rotor unmanned aerial vehicle motor shaft.
Background
To many rotor unmanned aerial vehicle, among the prior art, in order to improve unmanned aerial vehicle's flight performance, can set up roll angle and inclination in the motor shaft of rotor usually, the angle value combination of suitable roll angle and inclination in can improve unmanned aerial vehicle's mobility and stability simultaneously, consequently, in unmanned aerial vehicle's design test, it has the significance to improve unmanned aerial vehicle performance to seek suitable roll angle and inclination in combination.
However, there is no prior art angle adjustment device that can measure both roll and camber of a rotor motor shaft simultaneously to provide a reference for aircraft design.
SUMMERY OF THE UTILITY MODEL
The embodiment of the application provides an angle adjusting device and a test unmanned aerial vehicle, wherein the angle adjusting device comprises a base unit, a first adjusting unit arranged on the base unit and a second adjusting unit arranged on the first adjusting unit; the first end of the first adjusting unit is directly and movably connected with the base unit, the second end of the first adjusting unit is movably connected with the base unit through the first lifting module, similarly, the first end of the second adjusting unit is directly and movably connected with the first adjusting unit, the second end of the second adjusting unit is movably connected with the first adjusting unit through the second lifting module, the first end and the second end of the first adjusting unit are arranged along a first direction, and the first end and the second end of the second adjusting unit are arranged along a second direction perpendicular to the first direction; like this, through adjusting first lifting module and second lifting module simultaneously, can be so that the rotor motor shaft of locating the second adjustment unit has the inclination of two directions simultaneously to solved the technical problem of measuring rotor motor shaft roll angle and inclination simultaneously and to flight performance's influence, realized can measuring rotor motor shaft roll simultaneously and inclination to flight performance's influence through an angle adjusting device, in order to provide the technological effect of reference to the aircraft design.
The embodiment of the application provides an angle adjusting device, includes:
the base unit is provided with a first lifting module;
the first end of the first adjusting unit is movably connected with the base unit, the second end of the first adjusting unit is movably connected with the first lifting module, and the second end of the first adjusting unit is lifted along with the first lifting module, so that the second end of the first adjusting unit is lifted relative to the first end of the first adjusting unit; the first adjusting unit is provided with a second lifting module;
a first end of the second adjusting unit is movably connected with the first adjusting unit, a second end of the second adjusting unit is movably connected with the second lifting module, and the second end of the second adjusting unit is lifted along with the second lifting module, so that the second end of the second adjusting unit is lifted relative to the first end of the second adjusting unit;
the second adjusting unit is used for installing a rotor wing assembly of the unmanned aerial vehicle;
the first and second ends of the first adjusting unit are arranged in a first direction, the first and second ends of the second adjusting unit are arranged in a second direction, and the first direction is perpendicular to the second direction.
In the embodiment of the present disclosure, the first adjusting unit includes a mounting seat and a base, and the mounting seat is detachably connected below the base; the base unit and the mounting seat form a first angle adjusting module, and the base and the second adjusting unit form a second angle adjusting module.
In an embodiment of the present disclosure, the first lifting module includes a first screw, a first nut is sleeved outside the first screw, the first nut moves along the first screw along with the rotation of the first screw, and the first nut is movably connected to the second end of the first adjusting unit through a first connecting rod, so that the second end of the first adjusting unit is lifted along with the movement of the first nut; and/or the presence of a gas in the gas,
the second lifting module comprises a second screw rod, a second nut is sleeved outside the second screw rod and moves along the second screw rod along with the rotation of the second screw rod, and the second nut is movably connected with the second end of the second adjusting unit through a second connecting rod so that the second end of the second adjusting unit is lifted along with the movement of the second nut.
In the embodiment of the present disclosure, the first screw is mounted on the base unit through a first screw support;
wherein the first screw is perpendicular to the base unit; alternatively, the first screw is arranged in parallel to the base unit and in the first direction.
In the embodiment of the present disclosure, the first screw support is provided with angle scale marks.
In the embodiment of the present disclosure, the second screw is mounted on the first adjusting unit through a second screw support;
wherein the second screw is perpendicular to the first adjusting unit; alternatively, the second screw is parallel to the first adjustment unit and arranged in the second direction.
In the embodiment of the present disclosure, the second screw support is provided with angle scale marks.
In the embodiment of the present disclosure, a first end of the first adjusting unit is hinged to the base unit, and a first end of the second adjusting unit is hinged to the first adjusting unit; and the first nut is hinged with the second end of the first adjusting unit through the first connecting rod, and the second nut is hinged with the second end of the second adjusting unit through the second connecting rod.
In an embodiment of the present disclosure, the rotor assembly includes a rotor motor, and a motor shaft of the rotor motor is perpendicular to the second adjusting unit.
The embodiment of the application still provides a test unmanned aerial vehicle, test unmanned aerial vehicle is many rotor unmanned aerial vehicle, many rotor unmanned aerial vehicle's rotor motor through two-way angle adjusting device with many rotor unmanned aerial vehicle's fuselage is connected, wherein, two-way angle adjusting device is foretell angle adjusting device.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
in an embodiment of the present application, the angle adjusting apparatus includes a base unit, and a first adjusting unit is disposed on the base unit, wherein a first end of the first adjusting unit is movably connected to the base unit, and a second end of the first adjusting unit is movably connected to the base unit through a first lifting module, so that the second end of the first adjusting unit can be lifted relative to the first end by adjusting the first lifting module, that is, the first adjusting unit can tilt along a first direction relative to the base unit; similarly, a second adjusting unit is arranged on the first adjusting unit, wherein a first end of the second adjusting unit is movably connected with the first adjusting unit, and a second end of the second adjusting unit is movably connected with the first adjusting unit through a second lifting module, so that the second end of the second adjusting unit can be lifted relative to the first end by adjusting the second lifting module, that is, the second adjusting unit can be inclined relative to the first adjusting unit along a second direction, and the first direction is perpendicular to the second direction; can understand, through locating rotor motor second adjustment unit top, like this, through adjusting first lifting module and second lifting module simultaneously, can be so that rotor motor's motor shaft has the inclination of two directions simultaneously, the inclination of first direction and the inclination stack of second direction promptly, like this, just can measure the influence of the inclination of two directions of motor shaft to flight performance simultaneously to provide the reference to many rotor unmanned aerial vehicle's design, improved design efficiency.
Drawings
Fig. 1 is a schematic structural view of a rotor assembly provided with the angle adjusting apparatus according to the embodiment of the present application.
Fig. 2 is a schematic structural diagram of the angle adjusting apparatus in the embodiment of the present application.
Fig. 3 is a schematic view of another perspective of the rotor assembly mounted on the angle adjustment apparatus according to the embodiment of the present application.
Fig. 4 is a schematic structural diagram of the first lifting module and the second lifting module in the embodiment of the present application.
Fig. 5 is a schematic structural diagram of the test drone in the embodiment of the present application.
Fig. 6 is a schematic structural diagram of the angle adjusting device for adjusting a roll angle in the embodiment of the present application.
Fig. 7 is a schematic structural diagram of the angle adjusting device for adjusting the inclination angle in the embodiment of the present application.
Wherein, the reference numbers:
10-first adjustment Unit
11-second mounting projection
12-second lifting module
121-second screw
122-second nut
123-second connecting rod
124-second screw support
13-base
14-mounting seat
20-second adjustment unit
21-strip shaped hole
30-base unit
31-first mounting projection
32-first lifting module
321-first screw
322-first nut
323-first link
324-first screw support
40-rotor assembly
51-fuselage
52-undercarriage
53-machine arm
54-bidirectional angle adjusting device
A-side inclination angle
B-inner inclination angle
C-first direction
D-second direction
Detailed Description
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
SUMMARY
For a multi-rotor unmanned aerial vehicle, in the existing design, a rotor wing is usually set with a roll angle and an inner inclination angle at the same time, where, referring to fig. 6, the roll angle a is an angle that a horn of the rotor wing axially rotates, and referring to fig. 7, the inner inclination angle B is an angle that the horn of the rotor wing tilts towards a fuselage direction; the unmanned aerial vehicle can be understood that the flying stability of the unmanned aerial vehicle can be improved by arranging the rotor wing with the inner inclination angle, and then the problem of poor yawing maneuverability caused by larger wheel base of the rotor wing can be solved by arranging the rotor wing with the side inclination angle; therefore, the influence of the roll angle and the inner inclination angle of the rotor wing on the flight performance is tested, so that a proper combination of the roll angle and the inner inclination angle is selected, and the method has important significance for aircraft design.
However, in the existing test device for the unmanned aerial vehicle, there is no bidirectional angle adjusting device for simultaneously adjusting the roll angle and the inner inclination angle of the shaft of the rotor motor.
Based on the above-mentioned current situation, the technical scheme that this application discloses relates to an angle adjustment device, and this angle adjustment device is through with base unit, first adjustment unit and second adjustment unit stack to, the adjustment of angle is realized through the lift module of locating one end respectively between base unit and first adjustment unit, first adjustment unit and the second adjustment unit, thereby can realize the regulation to rotor motor shaft side inclination and interior inclination simultaneously.
An embodiment of the present application discloses an angle adjusting apparatus, which, as shown in fig. 1 and 2, includes a base unit 30, a first adjusting unit 10 disposed on the base unit 30, and a second adjusting unit 20 disposed on the first adjusting unit 10;
wherein, the base unit 30 is provided with a first lifting module 32; then, the first end of the first adjusting unit 10 is movably connected to the base unit 30, and the second end of the first adjusting unit 10 is movably connected to the first lifting module 32, so that the second end of the first adjusting unit 10 can lift along with the first lifting module 32, and thus the second end of the first adjusting unit 10 can lift relative to the first end of the first adjusting unit 10; at this time, it can be understood that, under the effect of the first lifting module 32 lifting, one end of the first adjusting unit 10 can be tilted with respect to the base unit 30, that is, the first adjusting unit 10 has an inclination angle with respect to the base unit 30; similarly, a second lifting module 12 is disposed on the first adjusting unit 10, a first end of the second adjusting unit 20 is movably connected to the first adjusting unit 10, and a second end of the second adjusting unit 20 is movably connected to the second lifting module 12, so that the second end of the second adjusting unit 20 can lift with the second lifting module 12, and thus the second end of the second adjusting unit 20 can lift relative to the first end of the second adjusting unit 20; at this time, under the effect of the second lifting module 12 lifting, one end of the second adjusting unit 20 can tilt relative to the first adjusting unit 10, that is, the second adjusting unit 20 also has an inclination angle relative to the first adjusting unit 10; it can be understood that, at this time, the two inclination angles are superposed;
with reference to fig. 1, the second adjusting unit 20 is used to mount a rotor assembly 40 of an unmanned aerial vehicle, and then, with reference to fig. 2, the first end and the second end of the first adjusting unit 10 are arranged along a first direction C, and the first end and the second end of the second adjusting unit 20 are arranged along a second direction D, and the first direction C is perpendicular to the second direction D, that is, the directions of the two tilt angles are perpendicular, so that the motor shaft of the rotor assembly 40 has an adjustable tilt angle in both the first direction C and the second direction D, thereby being capable of simultaneously adjusting the roll angle a and the roll angle B of the motor shaft of the rotor; for example, the angle adjustment device may be arranged with reference to fig. 6 and 7 such that the C-direction of the angle adjustment device is perpendicular to the axis of the horn 53 and the second lift module 12 is mounted away from the fuselage such that the first lift module 32 is used to adjust the roll angle a of the rotor assembly 40 and the second lift module 12 is used to adjust the camber angle B of the rotor assembly 40.
In an embodiment of the present application, the angle adjusting apparatus includes a base unit, and a first adjusting unit is disposed on the base unit, wherein a first end of the first adjusting unit is movably connected to the base unit, and a second end of the first adjusting unit is movably connected to the base unit through a first lifting module, so that the second end of the first adjusting unit can be lifted relative to the first end by adjusting the first lifting module, that is, the first adjusting unit can have an inclination angle along a first direction relative to the base unit; similarly, a second adjusting unit is arranged on the first adjusting unit, wherein a first end of the second adjusting unit is movably connected with the first adjusting unit, and a second end of the second adjusting unit is movably connected with the first adjusting unit through a second lifting module, so that the second end of the second adjusting unit can be lifted relative to the first end by adjusting the second lifting module, that is, the second adjusting unit can have an inclination angle along a second direction relative to the first adjusting unit, and the first direction is perpendicular to the second direction; can understand, through locating rotor motor second adjustment unit top, like this, through adjusting first lifting module and second lifting module simultaneously, can be so that rotor motor's motor shaft has the inclination of two directions simultaneously, the inclination of first direction and the inclination stack of second direction promptly, like this, just can change the inclination of two directions of motor shaft simultaneously and measure its influence to flight performance to provide the reference to many rotor unmanned aerial vehicle's design, improved design efficiency.
In the above embodiment, it can be understood that the first end of the first adjusting unit 10 is movably connected to the base unit 30, i.e. the first end of the first adjusting unit 10 is fixed in position relative to the base unit 30, and similarly, the first end of the second adjusting unit 20 is movably connected to the first adjusting unit 10, i.e. the first end of the second adjusting unit 20 is fixed in position relative to the first adjusting unit 10.
Specifically, referring to fig. 2, for example, the base unit 30, the first adjusting unit 10 and the second adjusting unit 20 are each in a plate shape, wherein one end of the base unit 30 is bent upward to form a first mounting protrusion 31, and the other end is provided with a first lifting module 32, so that a first end of the first adjusting unit 10 is hinged to the first mounting protrusion 31, and a second end of the first adjusting unit 10 is hinged to the first lifting module 32; then, similarly, one end of the first adjusting unit 10 is bent upwards to form a second mounting protrusion 11, and the other end is provided with a second lifting module 12, so that the first end of the second adjusting unit 20 is hinged to the second mounting protrusion 11, and the second end of the second adjusting unit 20 is hinged to the second lifting module 12, thereby realizing the above-mentioned bidirectional angle adjustment; it can be understood that, in other embodiments, the first adjusting unit may further have a first mounting protrusion bent downward, and the second adjusting unit may further have a second mounting protrusion bent downward, which is not limited in this application.
In the above embodiments, it can be understood that the first lifting module can be lifted and lowered relative to the base unit so as to lift and lower the second end of the first adjusting unit, wherein it can be understood that, in terms of power, the first lifting module can be, for example, a power-driven lifting or a manual lifting; secondly, in terms of construction, the first lifting module may comprise, for example, a gear drive or a screw drive or the like; the second lifting module is similar to the first lifting module and is not described in detail.
In a possible embodiment, the first adjusting unit 10 comprises a mounting seat 14 and a base 13, the mounting seat 14 being detachably connected below the base 13; wherein the base unit 30 and the mounting seat 14 form a first angle adjusting module, and the base 13 and the second adjusting unit 20 form a second angle adjusting module.
As shown in fig. 2, the angle adjusting apparatus is formed by stacking a first angle adjusting module and a second angle adjusting module, wherein the first angle adjusting module and the second angle adjusting module have similar structures, and the two angle adjusting modules are vertically stacked; specifically, the first end of the mounting seat is hinged to the base unit, the second end of the mounting seat is hinged to the first lifting module arranged on the base unit, similarly, the first end of the second adjusting unit is hinged to the base, and the second end of the second adjusting unit is hinged to the second lifting module arranged on the base.
That is, in this embodiment, the angle adjusting device is formed by vertically stacking two modularized angle adjusting modules having similar structures, one of which realizes roll angle adjustment of a rotor motor shaft, and the other realizes camber angle adjustment; in addition, the installation, the disassembly and the replacement are convenient, and the production efficiency and the use efficiency of the angle adjusting device are improved; in addition, it can be understood that the two angle adjusting modules can adjust the stacking angle, and the application is expanded.
In one possible embodiment, the first lifting module 32 includes a first screw rod 321, a first nut 322 is sleeved on the first screw rod 321, then the first nut 322 can move along the first screw rod 321 along with the rotation of the first screw rod 321, and the first nut 322 is movably connected to the second end of the first adjusting unit 10 through a first connecting rod 323, so that the second end of the first adjusting unit 10 is lifted and lowered along with the movement of the first nut 322; and/or, the second lifting module 12 includes a second screw rod 121, a second nut 122 is sleeved outside the second screw rod 121, then the second nut 122 moves along the second screw rod 121 along with the rotation of the second screw rod 121, and the second nut 122 is movably connected to the second end of the second adjusting unit 20 through a second connecting rod 123, so that the second end of the second adjusting unit 20 is lifted and lowered along with the movement of the second nut 122.
Specifically, as shown in fig. 2 and 3, the first lifting module 32 may include, for example, a first screw 321, the first screw 321 has an external thread, and then a first nut 322 having an internal thread is sleeved on the first screw 321, and the first nut 322 is adapted to the first screw 321, such that the first nut 322 moves along the first screw 321 with the rotation of the first screw 321, and then the first nut 322 is, for example, a special-shaped nut, and the first nut 322 is movably connected to the second end of the first adjusting unit 10 through a first connecting rod 323, for example, one end of the first connecting rod 323 is hinged to the second end of the first adjusting unit 10, and the other end of the first connecting rod 323 is hinged to the first nut 322.
When the first screw rod is driven by external force to rotate, the first nut can move along the first screw rod, and meanwhile, the first nut is hinged with the second end of the first adjusting unit through a first connecting rod with a fixed length, so that the movement of the first nut is transmitted to the second end of the first adjusting unit, and the second end of the first adjusting unit is caused to lift; it can be understood that the first adjusting unit and the first lifting module are similar to a crank block structure, and the inclination angle of the first adjusting unit is adjusted through the reciprocating movement of the first nut; the second lifting module structure may be similar to the first lifting module structure, and is not described in detail.
In the above embodiment, the adjustment of the inclination angles of the first adjusting unit and the second adjusting unit is realized by a simple crank-slider-like structure; moreover, the continuous stepless adjustment of the inclination angle can be realized through the combination of the screw and the nut; meanwhile, the screw and the nut can have a self-locking effect.
In one possible embodiment, the first screw 321 is mounted to the base unit 30 by a first screw support 324, wherein the first screw 321 is perpendicular to the base unit 30; alternatively, the first screw 321 is arranged in parallel to the base unit 30 and in the first direction C.
For example, referring to fig. 2, an embodiment is shown in which the first screw is mounted on the base unit through a first screw support, wherein the lower end of the first screw support 324 is fixedly connected to the base unit 30 through a screw, then the first screw 321 is arranged perpendicular to the base unit 30, and two ends of the first screw 321 are respectively hinged to the first screw support 324 and the base unit 30, so that the first screw 321 is limited to rotate only under the driving of an external force, and further, the first nut 322 is driven to move up and down along the first screw 321;
alternatively, for example, referring to fig. 4, another embodiment is shown in which the first screw is mounted on the base unit through a first screw support, wherein the first screw support 324 is hinged to two ends of the first screw 321 and is fixedly connected to the base unit 30, at this time, the first screw 321 is horizontally disposed on the base unit 30, so that the first screw 321 can be limited to rotate only under the driving of an external force, and at this time, the first nut 322 horizontally moves along the first screw 321, and the second end of the first adjusting unit 10 can be adjusted to lift up and down.
In this embodiment, through the articulated mode of simple screw rod, nut and connecting rod, realized similar slider-crank's structure, rotate through the screw rod and drive nut reciprocating motion, and then realize the lift of first adjustment unit second end, realize the adjustment of angle promptly, simple structure, convenient to use.
In one possible embodiment, the first screw support 324 is provided with angular graduations. An operator can conveniently read the inclination angle of the first adjusting unit according to the angle scale mark.
In one possible embodiment, the second screw 121 is mounted on the first adjusting unit 10 through a second screw support 124, wherein the second screw 121 is perpendicular to the first adjusting unit 10; alternatively, the second screw 121 is parallel to the first adjusting unit 10 and arranged along the second direction D; the second screw support 124 is provided with angular graduation marks.
That is, in this embodiment, the second lifting module may adopt the same structure as the first lifting module, and is not described in detail.
In a possible embodiment, the rotor assembly 40 comprises a rotor motor, the motor axis of which is perpendicular to the second adjustment unit 20.
Specifically, for example, 4 strip-shaped holes 21 arranged in the circumferential direction may be provided on the second adjustment unit 20, and the rotor motor is fixed to the second adjustment unit 20 through the strip-shaped holes 21.
The embodiment of this application has still disclosed a test unmanned aerial vehicle, combines fig. 5 to show, and this test unmanned aerial vehicle is many rotor unmanned aerial vehicle, including fuselage 51, is equipped with undercarriage 52 below the fuselage 51, and fuselage 51 extends has a plurality of horn 53, then, and rotor motor passes through two-way angle adjustment device 54 to be connected with fuselage 51's horn 53, and wherein, this two-way angle adjustment device 54 is foretell angle adjustment device.
In this embodiment, the rotor motor is connected to the body through the angle adjusting device, so that, on one hand, for one rotor, the combination of the roll angle and the inner inclination angle of the rotor can be optimized by adjusting the first screw and the second screw; on the other hand, each rotor in the rotors can adjust the roll angle and the inner inclination angle independently so as to select a proper angle value and provide reference for airplane design.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An angle adjusting apparatus, comprising:
the base unit is provided with a first lifting module;
the first end of the first adjusting unit is movably connected with the base unit, the second end of the first adjusting unit is movably connected with the first lifting module, and the second end of the first adjusting unit is lifted along with the first lifting module, so that the second end of the first adjusting unit is lifted relative to the first end of the first adjusting unit; the first adjusting unit is provided with a second lifting module;
a first end of the second adjusting unit is movably connected with the first adjusting unit, a second end of the second adjusting unit is movably connected with the second lifting module, and the second end of the second adjusting unit is lifted along with the second lifting module, so that the second end of the second adjusting unit is lifted relative to the first end of the second adjusting unit;
the second adjusting unit is used for installing a rotor wing assembly of the unmanned aerial vehicle;
the first and second ends of the first adjusting unit are arranged in a first direction, the first and second ends of the second adjusting unit are arranged in a second direction, and the first direction is perpendicular to the second direction.
2. The angle adjusting apparatus according to claim 1, wherein the first adjusting unit includes a mount and a base, the mount being detachably attached below the base; the base unit and the mounting seat form a first angle adjusting module, and the base and the second adjusting unit form a second angle adjusting module.
3. Angle adjustment device according to one of claims 1 or 2,
the first lifting module comprises a first screw rod, a first nut is sleeved outside the first screw rod, the first nut moves along the first screw rod along with the rotation of the first screw rod, and the first nut is movably connected with the second end of the first adjusting unit through a first connecting rod so that the second end of the first adjusting unit is lifted along with the movement of the first nut; and/or the presence of a gas in the gas,
the second lifting module comprises a second screw rod, a second nut is sleeved outside the second screw rod and moves along the second screw rod along with the rotation of the second screw rod, and the second nut is movably connected with the second end of the second adjusting unit through a second connecting rod so that the second end of the second adjusting unit is lifted along with the movement of the second nut.
4. The angular adjustment apparatus of claim 3, wherein the first screw is mounted to the base unit via a first screw mount;
wherein the first screw is perpendicular to the base unit; alternatively, the first screw is arranged in parallel to the base unit and in the first direction.
5. The angular adjustment apparatus of claim 4, wherein the first screw mount is provided with angular graduation marks.
6. The angle adjusting apparatus according to claim 3, wherein the second screw is mounted to the first adjusting unit through a second screw mount;
wherein the second screw is perpendicular to the first adjusting unit; alternatively, the second screw is parallel to the first adjustment unit and arranged in the second direction.
7. The angular adjustment apparatus of claim 6, wherein the second screw support is provided with angular graduation marks.
8. The angular adjustment apparatus of claim 3, wherein a first end of the first adjustment unit is hinged to the base unit and a first end of the second adjustment unit is hinged to the first adjustment unit; and the first nut is hinged with the second end of the first adjusting unit through the first connecting rod, and the second nut is hinged with the second end of the second adjusting unit through the second connecting rod.
9. The angular adjustment apparatus of claim 1, wherein the rotor assembly comprises a rotor motor having a motor shaft perpendicular to the second adjustment unit.
10. The utility model provides a test unmanned aerial vehicle, its characterized in that, test unmanned aerial vehicle is many rotor unmanned aerial vehicle, many rotor unmanned aerial vehicle's rotor motor through two-way angle adjustment device with many rotor unmanned aerial vehicle's fuselage is connected, wherein, two-way angle adjustment device is the angle adjustment device of any one of claim 1 ~ 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020199024.5U CN211969778U (en) | 2020-02-24 | 2020-02-24 | Angle adjusting device and test unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020199024.5U CN211969778U (en) | 2020-02-24 | 2020-02-24 | Angle adjusting device and test unmanned aerial vehicle |
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| Publication Number | Publication Date |
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| CN211969778U true CN211969778U (en) | 2020-11-20 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275188A (en) * | 2021-12-29 | 2022-04-05 | 北京理工大学 | Pitching mechanism with adjustable amplitude and aircraft aerodynamic force measurement experiment platform thereof |
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2020
- 2020-02-24 CN CN202020199024.5U patent/CN211969778U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275188A (en) * | 2021-12-29 | 2022-04-05 | 北京理工大学 | Pitching mechanism with adjustable amplitude and aircraft aerodynamic force measurement experiment platform thereof |
| CN114275188B (en) * | 2021-12-29 | 2023-10-17 | 北京理工大学 | Pitch mechanism with adjustable amplitude and aircraft aerodynamic force measurement experiment platform thereof |
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