Testing device for total pressure pipe assembly of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle total pressure pipe assembly testing device, which comprises an upper clamp and a lower clamp with symmetrical clamping parts, one ends of the upper clamp and the lower clamp are connected through a connecting rotating shaft, and the other ends of the upper clamp and the lower clamp are fixed through a fixing piece; the clamping part of the upper clamp and the clamping part of the lower clamp are respectively provided with a test groove, and the temperature sensors are fixed in the test grooves. The temperature sensor is fixed in the middle test groove, and the temperature sensor of the total pressure tube assembly test device is connected with the temperature sensor input interface of the detector; 28V voltage is output to the total voltage tube assembly, and temperature information collected by a temperature sensor is read through an RS232 interface; and reading the temperature of the total pressure pipe assembly, and judging whether the temperature of the total pressure pipe assembly is in a normal state or not. The temperature sensors are arranged in the middle and are symmetrically arranged, so that system errors are effectively avoided, and the measurement and calibration of the unmanned aerial vehicle total pressure pipe assembly can be assisted.

Description

Technical Field

[0001] This utility model belongs to the field of unmanned aerial vehicle (UAV) testing technology and relates to a UAV main pressure pipe assembly testing device. Background Technology

[0002] Total pressure (TP) of a drone refers to the total pressure at the air intake inlet during flight. TTP is a parameter that measures the total energy of the airflow and is crucial for drone performance and flight control. Accurate TTP measurement ensures the engine operates at its optimal state, thereby improving drone efficiency and performance. In the drone's flight control system, TTP is used to calculate key parameters such as flight speed, altitude, and attitude. Accurate TTP measurement ensures stable and precise control of the drone under various flight conditions.

[0003] Measuring the total pressure (i.e., the sum of dynamic and static pressure) of a UAV is one of the core technologies of its flight control system and atmospheric data system, involving various sensor technologies and data processing methods. Traditional methods measure total pressure using a pitot tube and static pressure using a pressure orifice, combining both to calculate dynamic pressure (total pressure minus static pressure). Methods for measuring the total pressure of a UAV may include using different types of pressure sensors, combining them with dynamic or pitot tube structures, and using MEMS or fiber optic sensors to improve accuracy. However, regardless of the detection method, regular testing and calibration of the sensors are necessary. Summary of the Invention

[0004] The technical problem solved by this utility model is to provide a test device for the main voltage tube assembly of a drone, which can be used to assist in the DC voltage detection and working status detection of the main voltage tube assembly of a drone.

[0005] This utility model is achieved through the following technical solution:

[0006] A test device for a drone total pressure pipe assembly includes an upper clamp and a lower clamp with symmetrical clamping parts. One end of the two clamps is connected by a connecting shaft, and the other end is fixed by a fastener. Test grooves are provided on the clamping parts of the upper clamp and the lower clamp, and a temperature sensor is fixed in the test groove.

[0007] The clamping parts of the upper and lower clamps are both hemispherical; one end of the clamping part extends into a pivot end, and the pivot ends of the two are connected by a connecting pivot; the other end of the clamping part extends into a free end, and the free ends of the two are connected by a fastener.

[0008] The fixing component is a fixing bolt. The upper and lower clamps have corresponding bolt holes, and the fixing bolt passes through the bolt holes to connect the upper and lower clamps.

[0009] The test grooves of the upper and lower clamps are opened along the central axis of symmetry, and the test grooves of the two are symmetrical.

[0010] During testing, the temperature sensor is connected to the temperature sensor input interface of the detector.

[0011] Compared with the prior art, the present invention has the following beneficial technical effects:

[0012] This utility model provides a test device for a UAV total pressure tube assembly. The free end of the assembly can be separated, allowing it to be clamped between an upper and lower clamp. A temperature sensor is fixed in the central test groove. The temperature sensor of the test device is connected to the temperature sensor input interface of a detector. By outputting a 28V voltage to the total pressure tube assembly, the temperature information collected by the temperature sensor is read via an RS232 interface. The temperature of the total pressure tube assembly is then read to determine if it is within the normal range. Because the temperature sensor is positioned centrally and symmetrically, systematic errors are effectively avoided, thus assisting in the measurement and calibration of the UAV total pressure tube assembly. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of this utility model;

[0014] Among them, 1 is the upper clamp, 2 is the lower clamp, and 3 is the temperature sensor. Detailed Implementation

[0015] The present invention will now be described in further detail with reference to the accompanying drawings. These descriptions are intended to explain the present invention and not to limit it.

[0016] The main pressure tube assembly testing device, acting as a fixture, can be used to accurately and quickly measure the data of the main pressure tube assembly, thereby calibrating the main pressure tube assembly. During calibration, it is necessary to accurately measure the main pressure tube assembly's supply voltage, supply current, and temperature, and then determine whether the main pressure tube is in a normal state based on the temperature change table.

[0017] When calibrating the main voltage tube assembly, it is necessary to accurately measure the supply voltage and current of the main voltage tube assembly. The main voltage tube assembly is clamped using the UAV main voltage tube assembly testing device provided in this invention, and a +28V power supply is provided to the main voltage tube assembly through a calibration tester.

[0018] like Figure 1 As shown, the total pressure pipe assembly testing device includes an upper clamp 1 and a lower clamp 2 with symmetrical clamping parts. One end of the two clamps is connected by a connecting shaft, and the other end is fixed by a fastener (fixing bolt). The middle part of the upper clamp 1 and the lower clamp 2 are provided with a test groove, and the temperature sensor 3 is fixed in the test groove.

[0019] Specifically, a test device for a drone total pressure pipe assembly includes an upper clamp and a lower clamp with symmetrical clamping parts. One end of the two clamps is connected by a connecting shaft, and the other end is fixed by a fastener. Test grooves are provided on the clamping parts of the upper clamp and the lower clamp, and a temperature sensor is fixed in the test groove.

[0020] Furthermore, the clamping portions of the upper and lower clamps are both hemispherical; one end of the clamping portion extends into a pivot end, and the pivot ends of the two are connected by a connecting pivot; the other end of the clamping portion extends into a free end, and the free ends of the two are connected by a fastener.

[0021] Specifically, the fixing component is a fixing bolt, and the upper and lower clamps have corresponding bolt holes. The fixing bolt passes through the bolt holes to connect the upper and lower clamps.

[0022] The test grooves of the upper and lower clamps are opened along the central axis of symmetry, and the test grooves of the two are symmetrical.

[0023] During testing, the temperature sensor is connected to the temperature sensor input interface of the detector.

[0024] When in use, open one end of the fixing piece, separate the free ends of the upper clamp 1 and the lower clamp 2, and fix the two temperature sensors in the upper and lower grooves of the test device; then install the test device on the total pressure tube assembly, and connect the temperature sensor of the test device to the temperature sensor input interface of the detector.

[0025] The detector outputs 28V to the main pressure tube assembly and reads the temperature information collected by the temperature sensor via the RS232 interface. Then, it reads the temperature of the main pressure tube assembly to determine whether the temperature of the main pressure tube assembly is within the normal range. When the predetermined temperature threshold is reached, the detector cuts off the power supply.

[0026] The power supply current of the main voltage tube assembly is directly acquired by the power module built into the detector, and then the current value is read through the RS485 serial port.

[0027] Specific implementation examples are given below.

[0028] Design parameters

[0029] Power supply voltage: +28V;

[0030] Output power: 150W;

[0031] Temperature range: 0℃~40℃;

[0032] The temperature sensor selected is the DL12-M232-D1 serial temperature sensor, which adopts the standard Modbus RTU protocol, supports RS232 serial port, has a baud rate of 1200bps~115200bps, a temperature measurement range of -40~125℃, and a power supply voltage of 3.3~5V.

[0033] The embodiments given above are preferred examples of implementing this utility model, and this utility model is not limited to the above embodiments. Any non-essential additions or substitutions made by those skilled in the art based on the technical features of the technical solution of this utility model shall fall within the protection scope of this utility model.

Claims

1. An unmanned aerial vehicle total pressure pipe assembly testing device, characterized by, The upper clamp and the lower clamp are connected by a connecting shaft at one end and fixed by a fixing member at the other end.

2. The UAV total pressure pipe assembly test device of claim 1, wherein, The clamping portions of the upper clamp and the lower clamp are both semispherical, and the clamping portions of the upper clamp and the lower clamp extend into a shaft end at one end and extend into a free end at the other end.

3. The UAV total pressure pipe assembly testing device of claim 1 or 2, wherein, The fixing member is a fixing bolt, and the upper clamp and the lower clamp are connected by the fixing bolt.

4. The UAV total pressure pipe assembly test device of claim 2, wherein, The test grooves of the upper clamp and the lower clamp are symmetrically arranged along the middle symmetry axis.

5. The UAV total pressure pipe assembly test device of claim 1, wherein, The temperature sensor is connected with the temperature sensor input interface of the detector.

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