CN103175679A - Comprehensive test system for characteristics of rotors of four-rotor aircrafts - Google Patents

Abstract

The invention discloses a comprehensive testing system for rotor characteristics of a four-rotor aircraft, which includes a testing device and an electrical control device. The testing device includes a complete machine base, a press base is placed in the complete machine base, and a torque shaft is installed on the upper end of the press base. , the outer wall of the torque shaft is pasted with a resistance strain gauge, the top of the torque shaft is connected with the DC motor of the rotor to be tested through the chassis of the motor holder, the Hall sensor is installed on the chassis of the motor holder, and the blade of the rotor to be tested is The magnetic body that cooperates with Hall sensor is provided with; Electric control device comprises: computer, and the data acquisition and counting card that are connected with computer respectively; The rotor to be tested of the present invention and DC motor all can be replaced, therefore, can reach The purpose of testing various quadrotor aircraft rotor reaction torque and rotor speed parameters, and the invention has the characteristics of simple structure, high test accuracy, low test cost, and high degree of automation of system operation.

Description

Integrated Test System for Rotor Characteristics of Quadrotor Aircraft

technical field

The invention relates to the field of aerospace power machinery, in particular to a comprehensive test system for rotor characteristics of a four-rotor aircraft.

Background technique

With the continuous expansion of the application field of quadrotor aircraft, the requirements for testing the rotor characteristic parameters of quadrotor aircraft are getting higher and higher. The acquisition of traditional quadrotor rotor characteristic parameters mostly depends on empirical estimation or wind tunnel tests.

The reliability of the aircraft rotor characteristic parameters estimated by experience is low, and the estimated results are closely related to the experience of the estimator. Therefore, many problems are prone to occur in the process of using the estimated parameters. The use of rotorcraft rotor characteristic parameters in the acquisition process is greatly limited; wind tunnel tests can theoretically obtain more accurate and reliable rotor characteristic parameters, but the cost is too high, which is not suitable for low-cost quadrotor aircraft. At the same time, The operation of wind tunnel test is complicated and requires high professionalism of operators, so its use in the test of rotor characteristic parameters of quadrotor aircraft is also greatly limited.

Contents of the invention

In view of the above defects or deficiencies, the present invention provides a comprehensive test system for rotor characteristics of quadrotor aircraft with simple structure, convenient operation and high test accuracy.

The present invention is realized through the following technical solutions:

including the test apparatus, and the electrical control apparatus, wherein,

The test device includes a complete machine base with a cavity structure inside, a press base is placed in the cavity of the complete machine base, a torque shaft is installed on the upper end of the press base, and a number of resistance strain gauges are pasted on the outer wall of the torque shaft. The top of the torque shaft is connected with the DC motor through the chassis of the motor holder, and the rotor to be tested is installed on the rotating shaft of the DC motor, wherein a Hall sensor is installed on the chassis of the motor holder, and the blade of the rotor to be tested is provided with a Magnetic body matched with Hall sensor;

The electrical control device includes: a computer, and data acquisition and counting cards respectively connected to the computer, wherein the data acquisition card is connected to the output signal of the resistance strain gauge, and the counting card is connected to the pulse signal of the Hall sensor.

A pressure sensor is installed at the lower end of the press base, and the data acquisition card is connected with the output signal of the pressure sensor.

Four resistance strain gauges are pasted on the outer wall of the torque shaft, and the four resistance strain gauges form a bridge measuring circuit.

The base of the whole machine is a concave platform structure, the pressure base is a convex platform structure, and the convex platform of the pressure base matches the concave platform of the whole machine base.

The chassis of the motor holder is connected to the DC motor through the first set of fastening screws. The chassis of the motor holder is connected to the torque shaft through the second set of fastening screws, and the torque shaft is connected to the pressure base through the third set of fastening screws.

The invention provides a comprehensive test system for the rotor characteristics of a four-rotor aircraft. By installing the DC motor carrying the rotor to be tested on the torque shaft attached with the resistance strain gauge, since the rotor to be tested rotates, the torque shaft will The torsional deformation is generated under the counter torque of the rotor. This torsional deformation causes the resistance strain gauge pasted on the torque shaft to output a deformation signal. The deformation signal is collected by the data acquisition card and sent back to the computer for corresponding calculations. Therefore, the accuracy is achieved. The purpose of testing the counter torque of the rotor; on the other hand, since the Hall sensor is installed on the chassis of the motor holder, and the magnetic body matched with the Hall sensor is arranged under the blade of the rotor to be tested, when the rotor to be tested rotates When passing through the Hall sensor, a group of pulse signals will be output, which will be sent back to the computer by the counting card to achieve the purpose of accurately testing the rotor speed. Compared with the prior art, the rotor to be tested and the DC motor of the present invention can be replaced, therefore, the purpose of testing various quadrotor aircraft rotor counter torque and rotor speed parameters can be achieved, and the present invention has a simple structure and is easy to test. High precision, low test cost, and high degree of automation in system operation.

Further, since a pressure sensor is installed at the lower end of the press base, when the rotor to be tested is rotating, the torque axis exerts an upward force on the pressure base, and the pressure sensor arranged below the pressure base outputs The pressure signal changes, the pressure signal is collected by the data acquisition card and sent back to the computer to achieve the purpose of testing the rotor lift.

Description of drawings

Fig. 1 is a schematic structural view of the testing device of the present invention;

Fig. 2 is a schematic structural view of the torque shaft part in the testing device of the present invention;

Fig. 3 is a schematic structural view of the pressure base part in the testing device of the present invention;

Fig. 4 is a schematic structural view of the base part of the whole machine in the testing device of the present invention;

Fig. 5 is a structural block diagram of the electrical control part of the present invention.

In the figure, 1-rotor to be tested; 2-DC motor; 3-first set of fastening screws; 4-motor fixed chassis; 5-second set of fastening screws; 6-resistance strain gauge; 7-torque axis ; 8-pressure sensor; 9-complete machine base; 10-pressure base; 11-third set of fastening screws; 12-Hall sensor; 13-magnetic body; 14-computer; - Counting cards.

Detailed ways

The present invention will be described in detail below in conjunction with the accompanying drawings.

Referring to shown in Fig. 1, the present invention provides a kind of comprehensive test system of rotor characteristic of quadrotor aircraft, comprises test device, and electric control device, and wherein, described test device comprises the complete machine base 9 that the interior is cavity structure, complete machine A press base 10 is placed in the cavity of the base 9, a pressure sensor 8 is installed at the lower end of the press base 10, and the upper end of the press base 10 is connected with the torque shaft 7 through a third set of fastening screws 11, as shown in Fig. 2 , the outer wall of the torque shaft 7 is pasted with several resistance strain gauges 6, the top of the torque shaft 7 is connected with the DC motor 2 through the motor holder chassis 4, wherein the torque shaft 7 is connected to the motor holder through the second set of fastening screws 5 The chassis 4 is connected, and the chassis 4 of the motor fixing seat is connected to the DC motor 2 through the first set of fastening screws 3. Therefore, the rotor 1 to be tested and the DC motor 2 can be replaced, thereby achieving the goal of testing the rotor characteristic parameters of various quadrotor aircraft. Purpose, it should be noted that the DC motors used in the present invention are all brushless DC motors. In addition, the rotor 1 to be tested is installed on the rotating shaft of the DC motor 2, wherein a Hall sensor 12 is installed on the chassis 4 of the motor holder, and the blade of the rotor 1 to be tested is provided with a sensor that matches the Hall sensor 12. Magnetic body 13;

Described electrical control device comprises: computer 14, and the data acquisition 15 that is connected with computer 14 and counting card 16 respectively, wherein, data acquisition card 15 is connected with the output signal of resistance strain gauge 6 and pressure transducer 8, counting card 16 Connect with the pulse signal of Hall sensor.

In order to increase the accuracy of counter torque measurement, four resistance strain gauges are pasted on the torque shaft to form a bridge measurement circuit to reduce the torque measurement error caused by temperature changes and improve the measurement accuracy.

Referring to Figures 3 and 4, the complete machine base 9 is a concave platform structure, the pressure base 10 is a convex platform structure, and the convex platform of the pressure base 10 matches the concave platform of the complete machine base 9 to prevent the pressure base from Seat 10 twists under the action of rotor torque.

Working process of the present invention is:

Referring to Figure 5, when the brushless DC motor 2 is energized and running, it will drive the tested rotor 1 to rotate, and the tested rotor 1 will generate lift, thereby generating an upward force on the pressure base 10 through the motor fixed chassis 4 and the torque shaft 7. Active force, the pressure signal that the pressure sensor 8 that is arranged below the pressure base 10 outputs changes, and this pressure signal is collected by the data acquisition card through the terminal block and sent back to the computer through the PCI bus to achieve the purpose of testing the lift of the rotor; at the same time , the rotor 1 to be tested will generate an anti-torque during the rotation process, and the anti-torque will act on the torque shaft 7 through the motor fixed chassis 4. Since the lower end of the torque shaft 7 is fixedly connected with the pressure base 10, the pressure base 10 is connected to the pressure base 10 through the square hole. The base of the whole machine cooperates and cannot rotate. Therefore, the torque shaft will produce torsional deformation under the action of the counter-torque of the rotor to be tested. This torsional deformation will cause the output signal of the resistance strain gauge 6 pasted on the torque shaft 7 to change. The deformation signal Through the terminal block, the data collected by the data acquisition card is sent back to the computer via the PCI bus, and the computer performs corresponding calculations to achieve the purpose of testing the counter torque of the rotor; in addition, when the rotor 1 to be tested rotates, the magnetic body attached to the torque shaft 13 periodically passes above the Hall sensor 12, and whenever the rotor 1 to be tested passes above the Hall sensor 12 once, the Hall sensor 12 will output a group of pulse signals, and this group of pulse signals will be returned by the counting card through the PCI bus through the terminal block. Pass it to the computer to achieve the purpose of testing the rotor speed. After the corresponding software is installed in the computer, the data acquisition card and the counting card execute the data acquisition command of the corresponding software, collect the test information of the sensor in the mechanical part, and calculate the test information, so as to obtain the corresponding value of the tested rotor at the current speed. Pull force, reactive torque, and rotational speed.

Claims (5)

1. A four-rotor aircraft rotor characteristic comprehensive testing system, is characterized in that: comprise testing device and electric control device, wherein, The test device includes a complete machine base (9) with a cavity structure inside, a press base (10) is placed in the cavity of the complete machine base (9), and a torque shaft ( 7), the outer wall of the torque shaft (7) is pasted with a number of resistance strain gauges (6), the top of the torque shaft (7) is connected with the DC motor (2) through the motor holder chassis (4), and the DC motor (2) The rotor to be tested (1) is installed on the rotating shaft, wherein, a Hall sensor (12) is installed on the chassis (4) of the motor holder, and a Hall sensor (12) is installed under the blade of the rotor to be tested (1). 12) matching magnetic body (13); The electrical control device includes: a computer (14), and a data acquisition card (15) and a counting card (16) respectively connected to the computer (14), wherein the data acquisition card (15) and the resistance strain gauge (6 ) is connected to the output signal, and the counting card (16) is connected to the pulse signal of the Hall sensor. 2. The comprehensive test system for rotor characteristics of quadrotor aircraft according to claim 1, characterized in that: a pressure sensor (8) is installed at the lower end of the press base (10), and the data acquisition card (15) and the pressure sensor (8) Output signal connection. 3. The comprehensive test system for rotor characteristics of quadrotor aircraft according to claim 1, characterized in that: four resistance strain gauges (6) are pasted on the outer wall of the torque shaft (7), and the four resistance strain gauges (6) Form a bridge measurement circuit. 4. The comprehensive test system for rotor characteristics of quadrotor aircraft according to claim 1, characterized in that: the base of the whole machine (9) is a concave platform structure, the pressure base (10) is a convex platform structure, and the pressure base ( 10) The convex platform matches the concave platform of the complete machine base (9). 5. The comprehensive test system for rotor characteristics of quadrotor aircraft according to claim 1, characterized in that: the motor holder chassis (4) is connected to the DC motor (2) through the first set of fastening screws (3) and the motor is fixed The seat chassis (4) is connected with the torque shaft (7) through the second set of fastening screws (5), and the torque shaft (7) is connected with the pressure base (10) through the third set of fastening screws (11).

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