Icing wind tunnel rotor test device and anti-icing test method

Abstract

An icing wind tunnel rotor test device and an anti-icing test method belong to the field of ice wind tunnel tests. It includes blades, a hub, an electric slip ring, a rotor main shaft, a slip ring bracket, a bearing seat, a six-component balance, a fixed support, a rotor motor, a tilt motor, a tilt sensor, a speed encoder, a tilt driven shaft, a tilt base and a tilt driving shaft. The two ends of the tilt base are respectively rotatably mounted on the fixed support through the tilt driving shaft and the tilt driven shaft. The fixed support is equipped with a tilt motor, and the output end of the tilt motor is fixedly connected to the tilt driving shaft. The tilt base is equipped with a rotor motor, and the top of the tilt base is equipped with a six-component balance. The top of the six-component balance is equipped with a bearing seat, and the top of the bearing seat is equipped with an electric slip ring through a slip ring bracket. The tilt base is equipped with a tilt sensor. Solving the problem of being able to obtain blade anti-icing test effects of different rotor tilt angles and icing conditions is conducive to standardizing the subsequent anti-icing test process of rotor test devices and improving test efficiency.

Description

Technical Field

[0001] The invention relates to an icing wind tunnel rotor test device and an anti-icing test method, belonging to the field of ice wind tunnel tests. Background Art

[0002] As a widely used method in aerodynamic research, wind tunnel testing provides necessary guarantees for the development of aviation, aerospace, rail transportation and other fields. The rotor is the main component used to provide lift for the helicopter. The icing of the rotor blades can cause blade vibration, increased torque, etc., which have a great impact on the safe flight of the helicopter. Compared with the flight test of the helicopter under real icing meteorological conditions, the study of the icing characteristics of the rotor through icing wind tunnel tests can greatly reduce the research cost and testing risk. For example, the invention patent with application number CN202010486809.5 is named a helicopter rotor model icing wind tunnel test method, which discloses a helicopter rotor model icing wind tunnel test method. The invention patent establishes a control method, data collection and analysis method for a helicopter rotor model under icing conditions, and standardizes the icing test process of the rotor model, but does not mention the structural scheme and anti-icing test method of the rotor test device.

[0003] Therefore, it is urgent to propose an icing wind tunnel rotor test device and an anti-icing test method to solve the above technical problems. Summary of the invention

[0004] The purpose of the present invention is to solve the problem of obtaining the anti-icing test effect of blades under different rotor pitch angles and icing conditions. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0005] The technical solution of the present invention:

[0006] An icing wind tunnel rotor test device comprises a blade, a hub, an electric slip ring, a rotor main shaft, a slip ring bracket, a bearing seat, a six-component balance, a fixed support, a rotor motor, a tilt motor, a tilt sensor, a speed encoder, a tilt driven shaft, a tilt base and a tilt driving shaft, the left and right ends of the tilt base are rotatably mounted on the fixed support through the tilt driving shaft and the tilt driven shaft respectively, the fixed support is fixedly mounted with the tilt motor, the output end of the tilt motor is fixedly connected with the tilt driving shaft, the rotor motor is fixedly mounted on the tilt base, the six-component balance is fixedly mounted on the top of the tilt base, the bearing seat is mounted on the top of the six-component balance, the electric slip ring is mounted on the top of the bearing seat through the slip ring bracket, and the tilt sensor is mounted on the tilt base;

[0007] A plurality of blades are mounted on the hub, one end of the rotor main shaft is fixedly connected to the hub, and the other end of the rotor main shaft passes through the electric slip ring, the bearing seat and the six-component balance once, and then enters the interior of the tilt base and is fixedly connected to the output end of the rotor motor. At the same time, the rotor main shaft rotates with the electric slip ring and the bearing seat respectively, and a speed encoder is mounted on the rotor main shaft.

[0008] Preferably, a commutator is fixedly installed inside the tilt base, the output end of the rotor motor is inserted into the tilt base and fixedly connected to the commutator shaft on one side of the commutator, and the commutator shaft on the other side of the commutator is fixedly connected to the rotor main shaft through a coupling.

[0009] Preferably, one end of the tilt driving shaft and the tilt driven shaft are fixedly connected to the left and right ends of the tilt base respectively, and the other ends of the tilt driving shaft and the tilt driven shaft are slidably connected to the fixed support through the tilt bearings respectively.

[0010] Preferably, the rotor main shaft is rotationally connected to the bearing seat via a main shaft bearing.

[0011] Preferably: a heating film and a thermocouple are attached to each of the blades, and a power line of the heating film and a signal line of the thermocouple are connected to a ground measuring device via an electric slip ring.

[0012] Solution 2: An icing wind tunnel rotor anti-icing test method is based on an icing wind tunnel rotor test device described in Solution 1, and includes the following steps:

[0013] Step 1, set the test inclination angle and speed, start the inclination motor, drive the tilting base to rotate to the specified test inclination angle, and start the rotor motor to the specified speed;

[0014] Step 2, open the wind tunnel to the agreed wind speed and total temperature conditions;

[0015] Step 3, energizing and heating the heating film installed on the blade, and collecting the temperature of the blade surface through a thermocouple;

[0016] Step 4: Turn on the wind tunnel spray system to conduct an anti-icing test. Visually observe the surface conditions of the blade anti-icing area through the camera set up in the test section and monitor the temperature measurement points to determine the anti-icing effect.

[0017] Step 5: If the anti-icing effect cannot be achieved, control the voltage of the heating film to increase the heating amount of the heating film until the surface of the blade anti-icing area is visually free of ice;

[0018] Step 6: After the anti-icing effect is achieved, wait for the temperature to stabilize and record 3 minutes of steady-state data to complete data collection and turn off the heating film heating;

[0019] Step 7: After the anti-icing test is completed, the spray system is turned off, the wind tunnel speed is reduced, and the total temperature is restored to normal temperature;

[0020] Step 8, reduce the speed of the rotor motor to 0, start the tilt motor, and drive the tilt angle of the tilt base to return to 0°.

[0021] The present invention has the following beneficial effects:

[0022] 1. The invention can adjust the inclination angle, and its maximum inclination angle can be adjusted to 90° from the horizontal, which is more flexible to use;

[0023] 2. The rotor main shaft of the present invention is provided with a speed encoder, which can accurately control the rotor speed. At the same time, the tilt base is provided with an inclination sensor, which can obtain the accurate rotor inclination angle in real time, making the test result more accurate;

[0024] 3. The six-component balance of the present invention can obtain mechanical properties of different inclination angles and speed conditions, and can simulate the influence of rotor icing on mechanical properties of helicopters in different flight states at small inclination angles, and can simulate the influence of blade icing on mechanical properties of propellers at a horizontal angle of 90°, so it has a wider range of applications;

[0025] 4. The electric slip ring of the present invention can allow the test device to carry out icing test and anti-icing test;

[0026] 5. The icing wind tunnel rotor anti-icing test method of the present invention is conducive to standardizing the subsequent rotor test device anti-icing test process and improving test efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a front view of an icing wind tunnel rotor test device;

[0028] Figure 2 It is a top view of an icing wind tunnel rotor test device;

[0029] Figure 3 yes Figure 1 AA section view;

[0030] Figure 4 It is a diagram of the use status of an icing wind tunnel rotor test device;

[0031] Figure 5 It is a flow chart of a rotor anti-icing test method in an icing wind tunnel;

[0032] In the figure, 1-blade, 2-hub, 3-electric slip ring, 4-rotor main shaft, 5-slip ring bracket, 6-bearing seat, 7-six-component balance, 8-fixed support, 10-rotor motor, 11-reducer, 12-tilt motor, 13-tilt sensor, 14-spindle bearing pressure cover, 15-spindle bearing, 16-spindle locking nut, 17-speed encoder, 18-tilt bearing, 19-tilt driven shaft, 20-coupling, 21-commutator, 22-tilt base, 23-tilt active shaft, 24-tilt shaft active side pressure cover. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0034] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection is a non-detachable connection including but not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: a fixed connection is selected as a welding connection, and a detachable connection is selected as a hinge connection.

[0035] Specific implementation method 1: Combination Figure 1-Figure 5 The present embodiment is described. An icing wind tunnel rotor test device of the present embodiment includes a blade 1, a hub 2, an electric slip ring 3, a rotor main shaft 4, a slip ring bracket 5, a bearing seat 6, a six-component balance 7, a fixed support 8, a rotor motor 10, a tilt motor 12, a tilt sensor 13, a speed encoder 17, a tilt driven shaft 19, a tilt base 22 and a tilt driving shaft 23;

[0036] The left and right ends of the tilt base 22 are rotatably mounted on the fixed support 8 through the tilt driving shaft 23 and the tilt driven shaft 19 respectively. The tilt driven shaft 19 and the tilt driving shaft 23 are connected to the tilt base through a key, and there is no relative rotation between the shaft and the tilt base; the fixed support 8 is fixedly mounted with a tilt motor 12, and the output end of the tilt motor 12 is fixedly connected to the tilt driving shaft 23 through a reducer 11, that is, the reducer 11 is fixed on the fixed support 8, and its output shaft is connected to the tilt driving shaft 23, and the tilt motor 1 2 is connected to the input shaft of the reducer 11, a rotor motor 10 is fixedly mounted on the tilt base 22, a six-component balance 7 is fixedly mounted on the top of the tilt base 22 by screws, a bearing seat 6 is mounted on the top of the six-component balance 7 by screws, an electric slip ring 3 is mounted on the top of the bearing seat 6 by a slip ring bracket 5, the inner ring of the electric slip ring 3 is sleeved on the rotor main shaft 4 and rotates with the rotor main shaft 4, the outer ring of the electric slip ring 3 is fixed, and an inclination sensor 13 is mounted on the tilt base 22 for monitoring the inclination angle of the rotor device;

[0037] A plurality of blades 1 are mounted on the hub 2, one end of the rotor main shaft 4 is fixedly connected to the hub 2 by bolts, the other end of the rotor main shaft 4 passes through the electric slip ring 3, the bearing seat 6 and the six-component balance 7 once, and then enters the interior of the tilt base 22 and is fixedly connected to the output end of the rotor motor 10. At the same time, the rotor main shaft 4 rotates with the electric slip ring 3 and the bearing seat 6 respectively, and a speed encoder 17 is mounted on the rotor main shaft 4, the fixed ring of the speed encoder 17 is connected to the tilt base 22, and the rotating ring of the speed encoder 17 is connected to the rotor main shaft 4, for real-time measurement of the speed of the rotor main shaft 4.

[0038] The commutator 21 is fixedly installed inside the tilt base 22 by screws. The output end of the rotor motor 10 is inserted into the tilt base 22 and fixedly connected to the commutator shaft on one side of the commutator 21. The commutator shaft on the other side of the commutator 21 is fixedly connected to the rotor main shaft 4 through the coupling 20.

[0039] One end of the tilt driving shaft 23 and the tilt driven shaft 19 are respectively fixedly connected to the left and right ends of the tilt base 22, and the other ends of the tilt driving shaft 23 and the tilt driven shaft 19 are respectively connected to the fixed support 8 through the tilt bearing 18. Both sides of the tilt base 22 are connected to the fixed support 8 through the tilt bearing 18, the tilt driven shaft 19, the tilt driven side pressure cover 9, the tilt driving shaft 23, and the tilt shaft active side pressure cover 24.

[0040] The rotor main shaft 4 is connected to the bearing seat 6 through the main shaft bearing 15, and the rotor main shaft 4 passes through the bearing seat 6, and is positioned radially and axially through the main shaft bearing 15. The main shaft bearing gland 14 is connected to the bearing seat 6, and the main shaft locking nut 16 is tightened onto the rotor main shaft 4. The main shaft bearing gland 14 and the main shaft locking nut 16 jointly limit the main shaft bearing 15. The loads such as the lift generated by the rotation of the blade 1, the hub 2, and the rotor main shaft 4 are transmitted to the bearing seat 6 and the six-component balance 7 through the main shaft bearing 15.

[0041] This embodiment can be used for icing tests or anti-icing tests. During the icing test, the six-component balance 7 can obtain mechanical data such as the lift of the rotor test device, record the mechanical data before and after the blades are frozen at different rotor inclination angles and speed conditions, and obtain the effect of the icing of the blades 1 on the lift of the rotor test device. During the icing test, attention should be paid to the vibration value of the test device within the allowable range. When conducting an anti-icing test, a heating film and a thermocouple are pasted on each of the blades 1, and the power line of the heating film and the signal line of the thermocouple are connected to the ground measurement equipment through the electric slip ring 3.

[0042] Specific implementation method 2: Combination Figure 1-Figure 5 The present embodiment is described. The present embodiment is an icing wind tunnel rotor anti-icing test method, which is based on an icing wind tunnel rotor test device described in the first embodiment, and includes the following steps: Step 1, setting the test inclination angle and rotation speed, starting the inclination motor 12, driving the tilting base 22 to rotate to the specified test inclination angle, and starting the rotor motor 10 to the specified rotation speed;

[0043] Step 2, open the wind tunnel to the agreed wind speed and total temperature conditions;

[0044] Step 3, energizing and heating the heating film installed on the blade 1, and collecting the surface temperature of the blade 1 through a thermocouple;

[0045] Step 4, start the wind tunnel spray system to conduct an anti-icing test, and visually observe the surface condition of the anti-icing area of ​​blade 1 through the camera set in the test section and monitor the temperature measurement points to determine the anti-icing effect;

[0046] Step 5: If the anti-icing effect cannot be achieved, control the voltage of the heating film to increase the heating amount of the heating film until the surface of the anti-icing area of ​​the blade 1 is visually free of ice;

[0047] Step 6: After the anti-icing effect is achieved, wait for the temperature to stabilize and record 3 minutes of steady-state data to complete data collection and turn off the heating film heating;

[0048] Step 7: After the anti-icing test is completed, the spray system is turned off, the wind tunnel speed is reduced, and the total temperature is restored to normal temperature;

[0049] Step 8, reducing the rotation speed of the rotor motor 10 to 0, starting the tilt motor 12, and driving the tilt base 22 to restore the tilt angle to 0°.

[0050] When the rotor motor 10 is started to a specified speed, the power of the rotor motor 10 is estimated as follows:

[0051] ;

[0052] Where: A: safety factor; : airflow density; : blade tip loss coefficient; R: rotor radius; : The average induced velocity of the rotor disc plane when the rotor is hovering; : Induced power correction factor; : Type resistance power correction coefficient; : airfoil drag coefficient; K: number of rotor blades; : Blade chord length; : Rotor speed.

[0053] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities based on the mathematical knowledge of arrangement and combination. Therefore, the present invention will no longer describe the technical solutions after arrangement and combination one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present invention.

[0054] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An icing wind tunnel rotor test device, characterized in that: The invention comprises a blade (1), a propeller hub (2), an electric slip ring (3), a rotor main shaft (4), a slip ring bracket (5), a bearing seat (6), a six-component balance (7), a fixed support (8), a rotor motor (10), a tilt motor (12), a tilt sensor (13), a speed encoder (17), a tilt driven shaft (19), a tilt base (22) and a tilt driving shaft (23), wherein the left and right ends of the tilt base (22) are rotatably mounted on a fixed shaft through the tilt driving shaft (23) and the tilt driven shaft (19) respectively. On the support (8), a tilt motor (12) is fixedly mounted on the fixed support (8), an output end of the tilt motor (12) is fixedly connected to a tilt driving shaft (23), a rotor motor (10) is fixedly mounted on the tilt base (22), a six-component balance (7) is fixedly mounted on the top of the tilt base (22), a bearing seat (6) is mounted on the top of the six-component balance (7), an electric slip ring (3) is mounted on the top of the bearing seat (6) through a slip ring bracket (5), and a tilt sensor (13) is mounted on the tilt base (22); A plurality of blades (1) are mounted on the hub (2); one end of a rotor main shaft (4) is fixedly connected to the hub (2); the other end of the rotor main shaft (4) passes through an electric slip ring (3), a bearing seat (6) and a six-component balance (7) at one time, and then enters the interior of a tilting base (22) and is fixedly connected to the output end of a rotor motor (10); at the same time, the rotor main shaft (4) is respectively rotationally matched with the electric slip ring (3) and the bearing seat (6); a speed encoder (17) is mounted on the rotor main shaft (4); A commutator (21) is fixedly installed inside the tilting base (22); the output end of the rotor motor (10) is inserted into the tilting base (22) and fixedly connected to a commutation shaft on one side of the commutator (21); and the commutation shaft on the other side of the commutator (21) is fixedly connected to a rotor main shaft (4) via a coupling (20); One end of the tilt driving shaft (23) and the tilt driven shaft (19) are respectively fixedly connected to the left and right ends of the tilt base (22), and the other ends of the tilt driving shaft (23) and the tilt driven shaft (19) are respectively slidably connected to the fixed support (8) through the tilt bearing (18); The rotor main shaft (4) is connected to the bearing seat (6) in rotation via the main shaft bearing (15). During the icing test, the six-component balance (7) obtains mechanical data of the rotor test device, records mechanical data of blades before and after icing at different rotor inclination angles and speed conditions, and obtains the lift effect of blade (1) icing on the rotor test device. The maximum inclination angle can be adjusted to 90° horizontally. Also included is an icing wind tunnel rotor anti-icing test method, which is implemented based on the icing wind tunnel rotor test device, and includes the following steps: Step 1, setting the test inclination angle and rotation speed, starting the inclination motor (12), driving the tilting base (22) to rotate to the specified test inclination angle, and starting the rotor motor (10) to the specified rotation speed; Step 2, open the wind tunnel to the agreed wind speed and total temperature conditions; Step 3, energizing and heating the heating film installed on the blade (1), and collecting the temperature of the surface of the blade (1) through a thermocouple; Step 4, start the wind tunnel spray system to conduct an anti-icing test, visually observe the surface condition of the anti-icing area of ​​the blade (1) through a camera set in the test section, and monitor the temperature measurement point to determine the anti-icing effect; Step 5: If the anti-icing effect cannot be achieved, control the voltage of the heating film to increase the heating amount of the heating film until the surface of the anti-icing area of ​​the blade (1) is visually free of ice; Step 6: After the anti-icing effect is achieved, wait for the temperature to stabilize and record 3 minutes of steady-state data to complete data collection and turn off the heating film heating; Step 7: After the anti-icing test is completed, the spray system is turned off, the wind tunnel speed is reduced, and the total temperature is restored to normal temperature; Step 8, reducing the rotation speed of the rotor motor (10) to 0, starting the tilt motor (12), and driving the tilt base (22) to restore the tilt angle to 0°; When the rotor motor (10) is started to a specified speed, the power of the rotor motor (10) is estimated as follows: Where: A: safety factor; ρ: airflow density; a: blade tip loss coefficient; R: rotor radius; v0: average induced speed of the rotor disc plane when the rotor is hovering; J0: induced power correction coefficient; k p0 : Type resistance power correction coefficient; C x : airfoil drag coefficient; K: number of rotor blades; b: blade chord length; Ω: rotor speed.

2. The icing wind tunnel rotor test device according to claim 1, characterized in that: A heating film and a thermocouple are attached to each blade (1), and a power line of the heating film and a signal line of the thermocouple are connected to a ground measurement device via an electric slip ring (3).

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