CN209905100U - Rotor craft attitude control test platform - Google Patents
Rotor craft attitude control test platform Download PDFInfo
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- CN209905100U CN209905100U CN201920561239.4U CN201920561239U CN209905100U CN 209905100 U CN209905100 U CN 209905100U CN 201920561239 U CN201920561239 U CN 201920561239U CN 209905100 U CN209905100 U CN 209905100U
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- eccentric rod
- attitude control
- base
- control test
- root
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Abstract
The utility model discloses a rotor craft attitude control test platform, including base, eccentric rod, mount pad. Wherein, the eccentric rod is the rocking handle structure, and its root is articulated with the base, and the eccentric rod is whole can be around root articulated axis in the horizontal plane rotation. The top end of the eccentric rod is provided with a spherical hinge, and the mounting seat is hinged with the eccentric rod through the spherical hinge. During operation, fix the base on ground or basis, can carry out the attitude control test with aircraft fixed mounting on the mount pad. The utility model discloses technical scheme provides a rotor craft attitude control test platform simple structure has a plurality of degrees of freedom, can conveniently carry out the attitude control test to the rotor craft.
Description
Technical Field
The utility model relates to an aircraft test field, in particular to rotor craft attitude control test platform.
Background
Compared with a fixed-wing aircraft, the rotary-wing aircraft has unique hovering and vertical take-off and landing capabilities and has wide military and civil applications. In particular, in recent years, the development of multi-rotor unmanned aerial vehicles is extremely rapid, and the multi-rotor unmanned aerial vehicles become aerial sharp devices which are seen everywhere.
In the design and manufacture process of the rotor craft, scientific attitude control test needs to be carried out. In the prior art, the test platform of the rotor craft has fewer reports, and the existing test platform of the rotor craft is complex in structure, high in cost and not beneficial to popularization and application.
Disclosure of Invention
The utility model aims at overcoming above-mentioned problem, provide a rotor craft attitude control test platform.
In order to achieve the purpose, the utility model discloses a method is: a rotor craft attitude control test platform comprises a base, an eccentric rod and a mounting seat, wherein the eccentric rod is of a rocking handle structure, the root of the eccentric rod is hinged with the base, and the whole eccentric rod can rotate in a horizontal plane around a root hinged axis; the top end of the eccentric rod is provided with a spherical hinge, the mounting seat is hinged with the eccentric rod through the spherical hinge, the base is used for being fixed on the ground or a foundation, and the mounting seat is used for fixing an aircraft for performing attitude control testing.
As the utility model discloses an prefer, base center open and to have the through-hole. The root of the eccentric rod is a cylinder, and the end face of the root is provided with a threaded hole. Wherein, a pair of bearings is arranged in the through hole of the base, the outer ring of the bearing is matched with the through hole of the base, and the inner ring is matched with the root of the eccentric rod. A bolt is arranged in a threaded hole in the end face of the root part of the eccentric rod, the diameter of the bolt head is larger than that of the bearing inner ring, the eccentric rod is limited, and the eccentric rod is prevented from being pulled out of the base due to overlarge stress.
Has the advantages that:
the utility model discloses technical scheme provides a rotor craft attitude control test platform simple structure has a plurality of degrees of freedom, can conveniently carry out the attitude control test to the rotor craft.
Drawings
FIG. 1 is a schematic structural view of a rotorcraft attitude control test platform;
FIG. 2 is a schematic view of a rotorcraft attitude control test platform with an aircraft;
FIG. 3 is a schematic view of the connection between the eccentric rod and the mounting seat;
FIG. 4 is a schematic view of the connection between the eccentric rod and the base.
Shown in fig. 1 to 4 are 1, a base, 2, an eccentric rod, 3, a mounting seat, 4, a spherical hinge, 5, a bearing, 6, a bolt, 1a, a through hole, 2a and a threaded hole.
Detailed Description
The present invention will be further clarified by the following embodiments with reference to the attached drawings, which are implemented on the premise of the technical solution of the present invention, and it should be understood that these embodiments are only used for illustrating the present invention and are not used for limiting the scope of the present invention.
Example 1:
a rotorcraft attitude control test platform as shown in fig. 1 to 3 includes a base 1, an eccentric rod 2, and a mounting base 3. The eccentric rod 2 is of a rocking handle structure, the root of the eccentric rod is hinged with the base 1, and the whole eccentric rod 2 can rotate in the horizontal plane around the root hinged axis. The top end of the eccentric rod 2 is provided with a spherical hinge 4, and the mounting seat 3 is hinged with the eccentric rod 2 through the spherical hinge 4. During operation, fix base 1 on ground or basis, can carry out the attitude control test with aircraft fixed mounting on mount pad 3.
Fig. 4 is a schematic view showing the connection between the eccentric rod and the base of the attitude control test platform of the rotorcraft according to the embodiment. The center of the base 1 is provided with a through hole 1 a. The root of the eccentric rod 2 is a cylinder, and the end face of the root is provided with a threaded hole 2 a. Wherein, be provided with a pair of bearing 5 in base 1 through-hole 1a, the bearing 5 outer lane cooperates with base 1 through-hole 1a, and the inner circle cooperates with 2 roots of eccentric rod. A bolt 6 is arranged in a threaded hole 2a at the end face of the root of the eccentric rod 2, the diameter of the head of the bolt 6 is larger than that of the inner ring of the bearing 5, the eccentric rod 2 is limited, and the eccentric rod is prevented from being pulled out of the base 1 due to overlarge stress.
The utility model discloses technical scheme provides a rotor craft attitude control test platform simple structure has a plurality of degrees of freedom, can conveniently carry out the attitude control test to the rotor craft.
The technical means disclosed by the scheme of the utility model is not limited to the technical means disclosed by the technical means, but also comprises the technical scheme formed by the arbitrary combination of the technical characteristics. The foregoing is a detailed description 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 are also considered as the protection scope of the present invention.
Claims (2)
1. The utility model provides a rotor craft attitude control test platform which characterized in that: the eccentric rod is of a rocking handle structure, the root part of the eccentric rod is hinged with the base, and the whole eccentric rod can rotate around a root part hinge axis in a horizontal plane; the top end of the eccentric rod is provided with a spherical hinge, the mounting seat is hinged with the eccentric rod through the spherical hinge, the base is used for being fixed on the ground or a foundation, and the mounting seat is used for fixing an aircraft for performing attitude control testing.
2. A rotorcraft attitude control test platform according to claim 1, wherein: the center of the base is provided with a through hole, the root of the eccentric rod is a cylinder, the end face of the root is provided with a threaded hole, a pair of bearings are arranged in the through hole of the base, the outer ring of each bearing is matched with the through hole of the base, the inner ring is matched with the root of the eccentric rod, a bolt is arranged in the threaded hole of the end face of the root of the eccentric rod, the diameter of the head of the bolt is larger than that of the inner ring of the bearing, the eccentric rod is limited.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920561239.4U CN209905100U (en) | 2019-04-24 | 2019-04-24 | Rotor craft attitude control test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920561239.4U CN209905100U (en) | 2019-04-24 | 2019-04-24 | Rotor craft attitude control test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209905100U true CN209905100U (en) | 2020-01-07 |
Family
ID=69045150
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920561239.4U Active CN209905100U (en) | 2019-04-24 | 2019-04-24 | Rotor craft attitude control test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209905100U (en) |
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2019
- 2019-04-24 CN CN201920561239.4U patent/CN209905100U/en active Active
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