CN210503245U - Rotor flapping response lag phase angle test frame - Google Patents
Rotor flapping response lag phase angle test frame Download PDFInfo
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- CN210503245U CN210503245U CN201921199832.5U CN201921199832U CN210503245U CN 210503245 U CN210503245 U CN 210503245U CN 201921199832 U CN201921199832 U CN 201921199832U CN 210503245 U CN210503245 U CN 210503245U
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Abstract
The utility model discloses a rotor waves response lag phase angle test jig, including base, bottom sprag frame, dowel steel, rotor system support frame, rotor system, dowel steel, transition pole and force sensor. Wherein the bottom support frame is fixedly arranged on the base. The force transmission frame is hinged with the top end of the bottom support frame through a spherical hinge. The rotor system support frame is fixedly arranged above the force transmission frame. The rotor system is fixedly arranged above the rotor system support frame. The dowel bars are provided with two, each dowel bar is fixedly connected with the dowel frame and is parallel to the plane of the base, and the two dowel bars are orthogonal to each other. The tail end of the dowel bar is hinged with the transition bar. The other end of the transition rod is fixedly connected with one end of the tension sensor. The other end of the tension sensor is fixedly connected with the base. The utility model discloses technical scheme provides a rotor waves response lag phase angle test jig simple structure, and low in manufacturing cost is honest and clean, can effectively test the rotor and wave response lag phase angle.
Description
Technical Field
The utility model relates to a rotor characteristic test field, in particular to rotor waves response lag phase angle test jig.
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. Especially, in recent years, the development of the rotor unmanned aerial vehicle is extremely rapid, and the rotor unmanned aerial vehicle is widely applied to the fields of aerial photography, search and rescue, monitoring and the like.
Rotors are sources of aerodynamic forces for rotorcraft, and their characteristics are directly related to the performance of the aircraft. In practical engineering, the flapping response of the rotor has a lagging phase angle, for example, when the rotor disk swings forwards, the direction of the control force of the actual rotor disk to the fuselage lags a certain angle around the rotation direction of the rotor, which has an influence on the control of the rotorcraft. If the flapping response hysteresis characteristic of the rotor cannot be accurately obtained, the real-time accurate control on the rotor aircraft cannot be realized, the flight efficiency is slightly influenced, and the flight accident is seriously caused. The flap response hysteresis characteristic may be obtained by calculation or experimental means. In the prior art, no relevant report of a rotor flap response lag phase angle testing device exists, and experimental study on the rotor flap response lag phase angle is lacked.
Disclosure of Invention
The utility model aims at overcoming above-mentioned problem, provide a rotor wave response lag phase angle test jig.
In order to achieve the purpose, the utility model discloses a method is: a rotor flapping response lag phase angle test frame comprises a base, a bottom support frame, a force transmission frame, a rotor system support frame, a rotor system, a force transmission rod, a transition rod and a tension sensor. The bottom support frame is fixedly arranged on the base. The force transmission frame is hinged with the top end of the bottom support frame through a spherical hinge. The rotor system support frame is fixedly arranged above the force transmission frame. The rotor system is fixedly arranged above the rotor system support frame. The dowel bars are provided with two, each dowel bar is fixedly connected with the dowel frame and is parallel to the plane of the base, and the two dowel bars are orthogonal to each other. The tail end of the dowel bar is hinged with the transition bar. The other end of the transition rod is fixedly connected with one end of the tension sensor. The other end of the tension sensor is fixedly connected with the base.
As the utility model discloses a preferred, rotor system support frame include three vertical poles, the rib is connected through the rib in the middle part of three vertical poles and is consolidated.
Has the advantages that:
the utility model discloses technical scheme provides a rotor waves response lag phase angle test jig simple structure, and low in manufacturing cost is honest and clean, can effectively test the rotor and wave response lag phase angle.
Drawings
FIG. 1 is a schematic structural diagram of a rotor flap response lag phase angle test rig;
figure 2 is a schematic representation of the rotor flap response lag phase angle.
Shown in fig. 1 and 2, 1, a base, 2, a bottom support frame, 3, a force transmission frame, 4, a rotor system support frame, 5, a rotor system, 6, a force transmission rod, 7, a transition rod, 8, a tension sensor, 4a, a longitudinal rod, 4b and a rib.
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:
fig. 1 is a schematic structural diagram of a rotor flapping response delay phase angle test rig according to the present embodiment. The rotor flapping response lag phase angle test frame disclosed by the embodiment comprises a base 1, a bottom support frame 2, a force transmission frame 3, a rotor system support frame 4, a rotor system 5, a force transmission rod 6, a transition rod 7 and a tension sensor 8.
The bottom support frame 2 is fixedly arranged on the base 1. The force transmission frame 3 is hinged with the top end of the bottom support frame 2 through a spherical hinge. Rotor system support frame 4 is fixed the setting in the top of dowel frame 3. Rotor system 5 is fixed the setting in rotor system support frame 4 top. The number of the dowel bars 6 is two, each dowel bar 6 is fixedly connected with the dowel frame 3 and is parallel to the plane of the base 1, and the two dowel bars 6 are orthogonal to each other. The tail end of the dowel bar 6 is hinged with a transition bar 7. The other end of the transition rod 7 is fixedly connected with one end of a tension sensor 8. The other end of the tension sensor 8 is fixedly connected with the base 1.
Rotor system support frame 4 includes three vertical poles 4a, and three vertical poles 4a middle part is connected through muscle 4b and is strengthened.
Fig. 2 is a schematic diagram illustrating a lag phase angle of a rotor flapping response according to the present disclosure. In the figure, the angle theta is the rotor flap response lag phase angle.
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 flap response lag phase angle test jig which characterized in that: the aircraft comprises a base (1), a bottom support frame (2), a force transmission frame (3), a rotor system support frame (4), a rotor system (5), a force transmission rod (6), a transition rod (7) and a tension sensor (8); the bottom support frame (2) is fixedly arranged on the base (1), and the force transmission frame (3) is hinged with the top end of the bottom support frame (2) through a spherical hinge; the rotor wing system support frame (4) is fixedly arranged above the force transmission frame (3), and the rotor wing system (5) is fixedly arranged above the rotor wing system support frame (4); the two dowel bars (6) are arranged, each dowel bar (6) is fixedly connected with the dowel frame (3), the dowel bars (6) are parallel to the plane of the base, and the two dowel bars (6) are orthogonal to each other; the tail end of the dowel bar (6) is hinged with the transition bar (7), the other end of the transition bar (7) is fixedly connected with one end of the tension sensor (8), and the other end of the tension sensor (8) is fixedly connected with the base (1).
2. A rotor flap response lag phase angle test rig according to claim 1, wherein: rotor system support frame (4) include three vertical poles (4 a), three vertical poles (4 a) middle part is connected through rib (4 b) and is strengthened.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921199832.5U CN210503245U (en) | 2019-07-29 | 2019-07-29 | Rotor flapping response lag phase angle test frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921199832.5U CN210503245U (en) | 2019-07-29 | 2019-07-29 | Rotor flapping response lag phase angle test frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210503245U true CN210503245U (en) | 2020-05-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921199832.5U Active CN210503245U (en) | 2019-07-29 | 2019-07-29 | Rotor flapping response lag phase angle test frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210503245U (en) |
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2019
- 2019-07-29 CN CN201921199832.5U patent/CN210503245U/en active Active
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