A new unmanned aerial vehicle multi-rotor tilt power test system
By designing a novel UAV multi-rotor tilt dynamics testing system, which utilizes a six-component sensor and a pressure-torsion sensor to simulate rotor tilt, the system solves the problem of the single structure of existing test benches. It enables efficient and stable rotor testing next to the production line in the workshop, providing accurate data under multiple environmental conditions.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- 刘德山
- Filing Date
- 2025-07-10
- Publication Date
- 2026-05-29
AI Technical Summary
Existing tilt rotor test benches have a simple structure and cannot effectively simulate the stability of the rotor during pitch or yaw control, resulting in problems such as airframe swaying and uneven stress.
A novel UAV multi-rotor tilt dynamic testing system was designed, including a base, bracket, control box, fixed frame, fixed frame tilt component and rotor tilt component. Combining a six-component sensor and a pressure-torsion sensor, it can simulate the dynamic tilt of the rotor and is equipped with an environmental module to detect temperature and humidity, supporting simultaneous testing of multiple rotors.
It enables convenient testing next to the production line in the workshop, improves the stability and efficiency of rotor testing, and can provide accurate test data under different environmental conditions to ensure the balance and stability of the rotor structure.
Smart Images
Figure CN224297441U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of rotor testing, and in particular relates to a novel multi-rotor tilting power testing system for unmanned aerial vehicles. Background Technology
[0002] Currently, with the development of aircraft, aircraft designs have undergone numerous changes. Among them, tiltrotor aircraft have become more efficient than fixed-wing aircraft in takeoff and landing. However, because tiltrotor aircraft require control of the rotor angle for tilt adjustment, their performance needs to undergo rigorous production testing to ensure overall structural stability during pitch or yaw control, preventing uneven stress and airframe swaying. However, existing test bench structures are relatively simple. Summary of the Invention
[0003] In view of this, the present invention aims to propose a novel UAV multi-rotor tilt power testing system, which is suitable for UAV multi-rotor tilt power testing, is easy to carry, can be tested on-site next to the production line in the workshop, and is convenient to use.
[0004] To achieve the above objectives, the technical solution of this utility model is implemented as follows:
[0005] A novel UAV multi-rotor tilting dynamics testing system includes a base, a support, a control box, a fixed frame, a fixed frame tilting component, and a rotor tilting component. The control box and the support are mounted on the base, the fixed frame tilting component and the fixed frame are mounted on the support, and the rotor tilting component is mounted on the fixed frame. The control box is located in the middle area of the base, and the support includes multiple inclined support rods with mounting plates on the top of the support rods, which are arranged around the control box.
[0006] The tilting component of the fixed frame includes a first tilting electric cylinder, a support, a rotating component, and a six-component sensor; the first tilting electric cylinder is mounted on the support rod, the push rod of the first tilting electric cylinder is connected to the rotating component, the rotating component is connected to the support through a rotating shaft, and the support is fixedly mounted on the mounting plate; the six-component sensor is mounted on the rotating component, and the six-component sensor is connected to the fixed frame;
[0007] The rotor tilting components consist of multiple parts, each including a profile, a second tilting electric cylinder, a tilting support, a U-shaped connecting rod, a flip cover, and a pressure-torque sensor. The profile is mounted on a fixed frame, with a tilting support on the top of the profile and a second tilting electric cylinder on the side wall of the profile. The U-shaped connecting rod is mounted on the tilting support via a rotating shaft, and the push rod of the second tilting electric cylinder and the flip cover are respectively connected to the U-shaped connecting rod. A pressure-torque sensor is mounted on the flip cover and is connected to the rotor mounting plate.
[0008] Furthermore, it also includes an environmental module, which is used to detect the temperature and humidity of the surrounding environment. The environmental module includes a PCB board and a thermal element and a humidity element set on the PCB board.
[0009] Furthermore, the environmental module includes multiple modules, which are respectively disposed on the profile and the support rod.
[0010] Furthermore, the mounting frame includes a longitudinal beam and a transverse beam. A six-component sensor is connected to the middle of the longitudinal beam via a longitudinal plate. Transverse beams are respectively installed at both ends of the longitudinal beam, and rotor tilting components are installed on the transverse beams.
[0011] Furthermore, the rotor tilting components include four, six, or eight, and the rotor tilting components are symmetrically arranged at both ends of the transverse beam.
[0012] Furthermore, the profile of the rotor tilting component is detachably connected to the transverse beam by screws.
[0013] Furthermore, the support rods include four, and the control box is generally square, with the four support rods respectively located at the four corners of the control box.
[0014] Furthermore, the four support rods form an accommodating space within which a conduit is installed. One end of the conduit is connected to the top plate of the control box, and the other end is connected to the mounting plate. Compared with the prior art, the novel UAV multi-rotor tilting power testing system of this utility model has the following advantages:
[0015] The testing system described in this invention achieves dynamic tilting simulation through a base, bracket, control box, fixed frame, fixed frame tilting component, and rotor tilting component. It forms an independent structure, making it easy to carry and enabling on-site testing next to the production line. An environmental module collects ambient temperature and humidity data, providing rotor test data under different temperature and humidity conditions. The layout is reasonable and the system is highly stable. It supports simultaneous testing of multiple rotors, improving testing efficiency and the overall structural balance. Attached Figure Description
[0016] The accompanying drawings, which form part of this utility model, are used to provide a further understanding of the utility model. The illustrative embodiments of the utility model and their descriptions are used to explain the utility model and do not constitute an undue limitation of the utility model. In the drawings:
[0017] Figure 1 This is a schematic diagram of the overall structure of the testing system described in an embodiment of the present invention;
[0018] Figure 2 This is a schematic diagram of the base and its connection structure as described in an embodiment of the present utility model;
[0019] Figure 3 This is a schematic diagram of the fixing frame and its connection structure according to an embodiment of the present utility model;
[0020] Figure 4 This is a schematic diagram of the rotor tilting component structure according to an embodiment of the present utility model.
[0021] Explanation of reference numerals in the attached figures:
[0022] 1-Base; 2-Bracket; 3-Control box; 4-Control box top plate; 5-Conduit; 6-Fixing frame; 7-Rotor tilting component; 8-Fixing frame tilting component; 12-Support rod; 13-Mounting plate; 14-Longitudinal plate; 15-Six-component sensor; 16-Rotating component; 18-First tilting electric cylinder push rod; 19-Environmental module; 20-First tilting electric cylinder; 21-Electric cylinder base; 211-Inclined support beam; 22-Support; 23-Rotating shaft; 25-Transverse beam; 26-Longitudinal beam; 31-Profile; 32-Tilting support; 33-Second tilting electric cylinder push rod; 34-U-shaped connecting rod; 35-Flip cover; 36-Pressure and torque sensor; 37-Rotor mounting plate. Detailed Implementation
[0023] It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.
[0024] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.
[0025] like Figures 1 to 4 As shown, a novel multi-rotor tilting dynamic testing system for unmanned aerial vehicles (UAVs) includes a base 1, a support 2, a control box 3, a mounting frame 6, a mounting frame tilting component 8, and a rotor tilting component 7. The control box 3 and the support 2 are mounted on the base 1, the mounting frame tilting component 8 and the mounting frame 6 are mounted on the support 2, and the rotor tilting component 7 is mounted on the mounting frame 6. The control box 3 is located in the middle area of the base 1. The support 2 includes multiple inclined support rods 12, with a mounting plate 13 on the top of each support rod 12. The support rods 12 are arranged around the control box 3.
[0026] The fixed frame tilting component 8 includes a first tilting electric cylinder 20, a support 22, a rotating component 16, and a six-component sensor 15; the first tilting electric cylinder 20 is mounted on the support rod 12, the first tilting electric cylinder push rod 18 is connected to the rotating component 16, the rotating component 16 is connected to the support 22 through a rotating shaft 23, and the support 22 is fixedly mounted on the mounting plate 13; the six-component sensor 15 is mounted on the rotating component 16, and the six-component sensor 15 is connected to the fixed frame 6;
[0027] The rotor tilting component 7 includes multiple components, each of which includes a profile 31, a second tilting electric cylinder 30, a tilting support 32, a U-shaped connecting rod 34, a flip cover 35, and a pressure-torque sensor 36. The profile 31 is mounted on the fixed frame 6, the tilting support 32 is mounted on the top of the profile 31, the second tilting electric cylinder 30 is mounted on the side wall of the profile 31, the U-shaped connecting rod 34 is mounted on the tilting support 32 via a rotating shaft, and the push rod 33 of the second tilting electric cylinder and the flip cover 35 are respectively connected to the U-shaped connecting rod 34. The pressure-torque sensor 36 is mounted on the flip cover 35 and is connected to the rotor mounting plate 37.
[0028] Among them, the compression-torsion sensor 36 is a compression-torsion composite sensor that can simultaneously measure tension, compression, and torque. The tension / compression channel and torque channel output analog signals proportional to the load. The FT2E integrated compression-torsion force sensor, commonly used in rotor testing, is employed. Its tension / compression measurement range and torque measurement range can be customized according to customer requirements to meet the needs of different force measurement applications. The six-component sensor 36 is used to measure force and torque in three orthogonal directions. Also known as a six-component balance, this embodiment uses a voltage-type six-component force / torque sensor composed of six sets of quartz rings. Flanges are installed at both ends for pre-tightening, enabling the measurement of tension, compression, and reaction torque.
[0029] Specifically, the first tilting electric cylinder 20 is arranged vertically, and the second tilting electric cylinder 30 is arranged at an angle. The first tilting electric cylinder 20 and the second tilting electric cylinder 30 are respectively mounted on the electric cylinder base 21. An inclined support beam 211 is provided at the bottom of the electric cylinder base to further improve the structural stability.
[0030] A novel multi-rotor tilting dynamic testing system for unmanned aerial vehicles (UAVs) is disclosed. The rotor is mounted on a rotor mounting plate. A tilting component of the fixed frame drives the fixed frame to tilt, and the rotor tilting component drives the flip cover to tilt, achieving dynamic tilting simulation. Specifically, when the fixed frame tilts, a first tilting electric cylinder pusher pushes a rotating component to rotate around a pivot axis via a connecting rod, thereby causing the six-component sensor mounted on the rotating component and the fixed frame to tilt. When the flip cover tilts, a second tilting electric cylinder pusher pushes a U-shaped connecting rod to rotate around a pivot axis, thereby causing the flip cover, the pressure and torque sensor mounted on the flip cover, and the rotor mounting plate to tilt. The control box can house the power supply, ADC module, and switch. The power supply provides power to the system. The switch, also known as an industrial Ethernet switch, is an Ethernet switching device used in industrial control. The ADC module is a device that converts analog signals into digital signals. The testing system described in this invention has an independent structure, is easy to carry, and can be tested on-site next to the production line in a workshop.
[0031] like Figure 1As shown, it also includes an environmental module 19, which is used to detect the temperature and humidity of the surrounding environment. The environmental module 19 includes a PCB board and a thermal element and a humidity element disposed on the PCB board. Multiple environmental modules 19 are included, and these multiple environmental modules 19 are respectively disposed on the profile 31 and the support rod 12. By collecting the ambient temperature and humidity through the environmental modules 19, rotor test data can be provided under different temperature and humidity environments.
[0032] like Figure 3 As shown, the mounting frame 6 includes a longitudinal beam 26 and a transverse beam 25. A six-component sensor 15 is connected to the middle of the longitudinal beam 26 via a longitudinal plate 14. Transverse beams 25 are respectively installed at both ends of the longitudinal beam 26, and rotor tilting components 7 are installed on the transverse beams 25. There are four rotor tilting components 7, symmetrically arranged at both ends of the transverse beams 25. The layout is reasonable and provides good stability.
[0033] like Figure 3 As shown, the profile 31 of the rotor tilting component 7 is detachably connected to the transverse beam 25 by screws. The rotor tilting component 7 and the transverse beam 25 are detachably connected, allowing for the addition or removal of the rotor tilting component 7 from the transverse beam, providing flexibility in use.
[0034] like Figure 1 and Figure 2 As shown, the support rods 12 include four, six, or eight. The control box 3 is generally square, with the four support rods 12 respectively located at the four corners of the control box 3. The structure is stable, supports simultaneous detection of multiple rotors, improves detection efficiency, and enhances the overall structural balance. The four support rods 12 form an accommodating space, within which a conduit 5 is installed. One end of the conduit 5 connects to the top plate 4 of the control box, and the other end connects to the mounting plate 13. The conduit 5 provides a wiring channel, with a reasonable layout that reduces floor space.
[0035] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.
Claims
1. A novel multi-rotor tilt dynamics testing system for unmanned aerial vehicles (UAVs), characterized in that: The system includes a base (1), a bracket (2), a control box (3), a mounting frame (6), a mounting frame tilting component (8), and a rotor tilting component (7). The control box (3) and the bracket (2) are mounted on the base (1), the mounting frame tilting component (8) and the mounting frame (6) are mounted on the bracket (2), and the rotor tilting component (7) is mounted on the mounting frame (6). The control box (3) is located in the middle area of the base (1). The bracket (2) includes multiple inclined support rods (12), and a mounting plate (13) is mounted on the top of each support rod (12). The support rods (12) are arranged around the control box (3). The fixed frame tilting component (8) includes a first tilting electric cylinder (20), a support (22), a rotating component (16), and a six-component sensor (15); the first tilting electric cylinder (20) is mounted on the support rod (12), the first tilting electric cylinder push rod (18) is connected to the rotating component (16), the rotating component (16) is connected to the support (22) through a rotating shaft (23), and the support (22) is fixedly mounted on the mounting plate (13); the six-component sensor (15) is mounted on the rotating component (16), and the six-component sensor (15) is connected to the fixed frame (6); The rotor tilting component (7) includes multiple components, each of which includes a profile (31), a second tilting electric cylinder (30), a tilting support (32), a U-shaped connecting rod (34), a flip cover (35), and a pressure and torque sensor (36). The profile (31) is mounted on a fixed frame (6), the top of the profile (31) is provided with a tilting support (32), the second tilting electric cylinder (30) is provided on the side wall of the profile (31), the U-shaped connecting rod (34) is mounted on the tilting support (32) via a rotating shaft, the second tilting electric cylinder push rod (33) and the flip cover (35) are respectively connected to the U-shaped connecting rod (34); the flip cover (35) is provided with a pressure and torque sensor (36), and the pressure and torque sensor (36) is connected to the rotor mounting plate (37).
2. The novel UAV multi-rotor tilt dynamics testing system according to claim 1, characterized in that: It also includes an environment module (19), which is used to detect the temperature and humidity of the surrounding environment. The environment module (19) includes a PCB board and a thermal element and a humidity element disposed on the PCB board.
3. The novel UAV multi-rotor tilt dynamics testing system according to claim 2, characterized in that: The environmental module (19) includes multiple modules, which are respectively disposed on the profile (31) and the support rod (12).
4. The novel UAV multi-rotor tilt dynamics testing system according to claim 1, characterized in that: The fixed frame (6) includes a longitudinal beam (26) and a transverse beam (25). The longitudinal beam (26) is connected to a six-component sensor (15) through a longitudinal plate (14) in the middle. The transverse beam (25) is provided at both ends of the longitudinal beam (26). The rotor tilting component (7) is provided on the transverse beam (25).
5. The novel UAV multi-rotor tilt dynamics testing system according to claim 4, characterized in that: The rotor tilting components (7) include four, six or eight, and the rotor tilting components (7) are symmetrically arranged at both ends of the transverse beam (25).
6. The novel UAV multi-rotor tilt dynamics testing system according to claim 4, characterized in that: The profile (31) of the rotor tilting component (7) is detachably connected to the transverse beam (25) by screws.
7. The novel UAV multi-rotor tilt dynamics testing system according to claim 1, characterized in that: The support rods (12) include four, and the control box (3) is generally square. The four support rods (12) are respectively set at the four corners of the control box (3).
8. The novel UAV multi-rotor tilt dynamics testing system according to claim 7, characterized in that: The four support rods (12) form an accommodating space, in which a conduit (5) is installed. One end of the conduit (5) is connected to the top plate (4) of the control box, and the other end is connected to the mounting plate (13).