Rotating shaft flight load testing device

Abstract

A rotating shaft flight load testing device, comprising a fuselage provided with a rotating shaft and a force sensor, the fuselage is fixed with the force sensor with a testing surface facing downward; the rotating shaft is connected with a rotor assembly at one end and is fixed with a mounting base which rises and falls synchronously with the rotating shaft at the other end; a power assembly is further installed on the rotating shaft to drive the rotating shaft to rotate independently relative to the mounting base; the mounting base is reserved with a working surface for closely contacting the testing surface; the rotating shaft is perpendicular to the working surface, the testing surface and the working surface are parallel to each other, and the rotating shaft, the testing surface and the working surface are coaxially arranged. The mounting base is arranged at the bottom end of the rotating shaft, the force of the bottom end of the rotating shaft on the fuselage is transferred to the working surface, the flight load data at the position near the center of gravity of the fuselage of the rotating shaft is indirectly obtained through testing the load of the working surface; the force sensor is arranged on the lengthened section of the lower part of the rotating shaft, the number of modifications of the accessories of the fuselage is effectively reduced, the spare space of the lower part of the conventional aircraft is adapted, and the testing device has a wide application range.

Description

Technical Field

[0001] This utility model patent relates to the technical field of remote-controlled helicopters, and in particular to a rotating shaft flight load testing device. Background Technology

[0002] Remote-controlled helicopters utilize motors and other power components to drive the rotor assembly via a rotating shaft, providing upward lift to the fuselage. General-purpose models often employ an assembly method where the rotor assembly is mounted at one end of the rotating shaft, and the other end is fixed to the main mounting plate of the fuselage. The rotating shaft can rotate independently relative to the main mounting plate. Flight load data from remote-controlled helicopters provides data support for optimizing the performance of various components and for aircraft teaching and research.

[0003] Existing rotation axis flight load data mostly focus on the connection between the rotation axis and the rotor assembly, which deviates significantly from the fuselage center of gravity. To address this, we provide a rotation axis flight load testing device that is closer to the fuselage center of gravity. Utility Model Content

[0004] The purpose of this invention is to solve existing technical problems by proposing a rotating shaft flight load testing device.

[0005] To achieve the above objectives, this utility model adopts the following technical solution: a rotating shaft flight load testing device, comprising a fuselage equipped with a rotating shaft and a force sensor.

[0006] A force sensor with its test surface facing downwards is fixed on the machine body;

[0007] One end of the rotating shaft is connected to a rotor assembly, and the other end is fixed to a mounting base that rises and falls synchronously with the rotating shaft; a power assembly is also installed on the rotating shaft to drive the rotating shaft to rotate independently relative to the mounting base; the mounting base has a reserved working surface for close contact with the test surface;

[0008] The rotating axis is perpendicular to the working surface, and the test surface is parallel to the working surface. The rotating axis, test surface, and working surface are set coaxially to realize the function of real-time testing of the rotating axis flight load.

[0009] Preferably, the rotating shaft extends downward to form an extended section, and the lower part of the extended section is fitted with an upper limit member and a lower limit member for limiting the lifting and lowering of the mounting base relative to the rotating shaft, with the mounting base located between the upper limit member and the lower limit member.

[0010] Preferably, the machine body is also provided with a main mounting plate connected to the side plate. The main mounting plate is parallel to the working surface, and the force sensor is clamped between the main mounting plate and the mounting base.

[0011] Preferably, the mounting base is connected to the force sensor via the first connector; several positioning through holes are opened on the working surface, and several positioning holes are reserved on the test surface. The positioning holes and positioning through holes correspond one-to-one, and the first connector passes through the positioning through holes and is fixed in the positioning holes.

[0012] Preferably, the force sensor is a through-shaft force sensor or a spoke-type force sensor.

[0013] Preferably, the housing also includes a secondary mounting plate arranged parallel to the main mounting plate. The secondary mounting plate is connected to the main mounting plate via a second connector to form a mounting cavity for clamping the force sensor. The secondary mounting plate has a second through hole for exposing the test surface, and the inner diameter of the second through hole is larger than the outer diameter of the mounting base.

[0014] Preferably, a data transmission radio is also installed on the fuselage, and the force sensor is electrically connected to the fuselage circuit and the data transmission radio respectively, so as to realize the communication connection between the force sensor and the fuselage flight control system.

[0015] The beneficial effects of this utility model are: by setting a mounting base at the bottom of the rotating shaft, the force exerted by the bottom of the rotating shaft on the fuselage is transferred to the working surface, and the flight load data near the center of gravity of the rotating shaft is indirectly obtained by testing the load on the working surface; by setting a force sensor in the extended section at the bottom of the rotating shaft, the number of fuselage parts to be modified is effectively reduced, it can be adapted to the spare space at the bottom of conventional aircraft models, and the testing device has a wide range of applications. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of this utility model;

[0017] Figure 2 This is a cross-sectional view of the present invention;

[0018] Figure 3 This is a schematic diagram of the force sensor of this utility model;

[0019] Figure 4 This is a schematic diagram of the mounting base of this utility model. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0021] In conjunction with the embodiments and appendices Figure 1-4 A rotating shaft flight load testing device includes a fuselage equipped with a rotating shaft 1 and a force sensor 3, with the force sensor 3 having a test surface 30 facing downwards fixed on the fuselage;

[0022] One end of the rotating shaft 1 is connected to a rotor assembly, and the other end is fixed with a mounting base 4 that rises and falls synchronously with the rotating shaft 1; a power assembly 5 is also installed on the rotating shaft 1 to drive the rotating shaft 1 to rotate independently relative to the mounting base 4; the mounting base 4 has a reserved working surface 40 for closely adhering to the test surface 30.

[0023] The rotating shaft 1 is perpendicular to the working surface 40, and the test surface 30 is parallel to the working surface 40. The rotating shaft 1, the test surface 30 and the working surface 40 are set coaxially to realize the function of real-time testing of the flying load of the rotating shaft.

[0024] The fuselage is also equipped with a data transmission radio. The force sensor 3 is electrically connected to the fuselage circuit and the data transmission radio, respectively, to realize the communication connection between the force sensor 3 and the fuselage flight control system, which facilitates the transmission and reception of real-time data.

[0025] The rotating shaft 1 extends downward to form an extended section. The lower part of the extended section is fitted with an upper limit member 71 and a lower limit member 72 for limiting the lifting and lowering of the mounting base 4 relative to the rotating shaft 1. The mounting base 4 is located between the upper limit member 71 and the lower limit member 72. The upper limit member and the lower limit member can be a spindle fixing ring or a bushing.

[0026] The machine body is also provided with a main mounting plate 21 connected to the side plate. The main mounting plate 21 is parallel to the working surface 40. The force sensor 3 is clamped between the main mounting plate 21 and the mounting base 4. The extended section penetrates vertically through the main mounting plate 21. The power assembly 5 is located above the main mounting plate.

[0027] The mounting base 4 is connected to the force sensor 3 via the first connector 61; the working surface 40 has several positioning through holes 41, and the test surface 30 has several positioning holes 31 reserved. The positioning holes 31 and the positioning through holes 41 correspond one-to-one. The first connector 61 passes through the positioning through holes 41 and is fixed in the positioning holes 31.

[0028] Force sensor 3 is a through-shaft force sensor or a spoke-type force sensor, and the force sensor can be a three- to six-dimensional force sensor.

[0029] The body also includes a secondary mounting plate 22 arranged parallel to the main mounting plate 21. The secondary mounting plate 22 is connected to the main mounting plate 21 through the second connector 62 to form a mounting cavity 20 for clamping the force sensor 3. The secondary mounting plate 22 and the main mounting plate 21 are parallel to each other. The secondary mounting plate 22 has a second through hole for exposing the test surface 30. The inner diameter of the second through hole is larger than the outer diameter of the mounting base. The secondary mounting plate 22 does not contact the test surface 30, so as to avoid the secondary mounting plate from squeezing the test surface.

[0030] Furthermore, the upper surface of the force sensor 3 is provided with several fixing holes 32, and the main mounting plate 21 is provided with a fixing through hole. The third connector 63 passes through the fixing through hole and is fixed in the fixing hole 32. The fixing holes 32 and the positioning holes 31 are circumferentially spaced, and a vertical gap is left between the upper surface of the inner ring of the force sensor 3 and the main mounting plate 21 to ensure the stable installation of the force sensor.

[0031] The first connector 61, the second connector 62, and the third connector 63 can be fixedly connected to the positioning hole 31, the main mounting plate 21 and / or the auxiliary mounting plate 22, and the fixing hole 32 by plugging, riveting, or screwing. The first connector 61, the second connector 62, and the third connector 63 can be a connecting rod, a screw, or a nut assembly.

[0032] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A rotating shaft flight load testing device, comprising a fuselage equipped with a rotating shaft and a force sensor, characterized in that: A force sensor with its test surface facing downwards is fixed on the machine body; One end of the rotating shaft is connected to a rotor assembly, and the other end is fixed to a mounting base that rises and falls synchronously with the rotating shaft; a power assembly is also installed on the rotating shaft to drive the rotating shaft to rotate independently relative to the mounting base; the mounting base has a reserved working surface for close contact with the test surface; The rotating axis is perpendicular to the working surface, and the test surface is parallel to the working surface. The rotating axis, test surface, and working surface are set coaxially to realize the function of real-time testing of the rotating axis flight load.

2. The rotating shaft flight load testing device according to claim 1, characterized in that: The rotating shaft extends downward to form an extended section. The lower part of the extended section is fitted with an upper limit member and a lower limit member to limit the lifting and lowering of the mounting base relative to the rotating shaft. The mounting base is located between the upper limit member and the lower limit member.

3. The rotating shaft flight load testing device according to claim 1, characterized in that: The machine body is also equipped with a main mounting plate connected to the side plate. The main mounting plate is parallel to the working surface, and the force sensor is clamped between the main mounting plate and the mounting base.

4. The rotating shaft flight load testing device according to claim 3, characterized in that: The mounting base is connected to the force sensor via the first connector; several positioning through holes are opened on the working surface, and several positioning holes are reserved on the test surface. The positioning holes and positioning through holes correspond one-to-one, and the first connector passes through the positioning through holes and is fixed in the positioning holes.

5. The rotating shaft flight load testing device according to claim 1, characterized in that: The force sensor is either a through-shaft force sensor or a spoke-type force sensor.

6. The rotating shaft flight load testing device according to claim 3, characterized in that: The body also includes a secondary mounting plate arranged parallel to the main mounting plate. The secondary mounting plate is connected to the main mounting plate through a second connector to form a mounting cavity for clamping the force sensor. The secondary mounting plate has a second through hole for exposing the test surface. The inner diameter of the second through hole is larger than the outer diameter of the mounting base.

7. The rotating shaft flight load testing device according to claim 1, characterized in that: The fuselage is also equipped with a data transmission radio, and the force sensor is electrically connected to the fuselage circuit and the data transmission radio respectively, realizing the communication connection between the force sensor and the fuselage flight control system.

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