RU213093U1 - Stand for determining the kinematic and power characteristics of the propeller of the aircraft power plant - Google Patents

Abstract

The utility model relates to the field of aviation, in particular to devices for determining the kinematic and power characteristics of an aircraft power plant propeller, and can be used as research equipment in the form of stands demonstrating the dependence of the thrust force on the propeller rotation speed and the angle of rotation of the blades. The technical result consists in creating a bench, simple in design, for determining the kinematic and power parameters of the propeller of the aircraft power plant as equipment for studying the dependence of thrust on the propeller rotation speed and the angle of rotation of the ridges by introducing a movable carriage moving along rails and containing an electric motor, a power module, a controller , a shaft that transmits torque from an electric motor, with a VISH installed on it through a bearing, and an elastic element of the load cell in the form of a spring is attached to the carriage. The technical result is achieved by the fact that a movable carriage moving along the rail and containing an electric motor, a shaft that transmits torque from the VISH electric motor, which is installed through a bearing, and the carriage is connected to a fixed rack through the elastic element of the strain gauge - a spring, and the fixed rack of the stand contains a strain gauge of the strain gauge , a microcomputer, a multi-channel visualization module and a control panel containing a control lever and keys for adjusting the angle of inclination of the propeller crests, a display showing the set angle of rotation of the crests of the propeller, a display showing the thrust force, a display showing the speed of rotation of the VIS. 3 ill.

Description

The utility model relates to the field of aviation, in particular to devices for determining the kinematic and power characteristics of an aircraft power plant propeller, and can be used as research equipment in the form of stands demonstrating the dependence of the thrust force on the propeller rotation speed and the angle of rotation of the blades.

Known "Stand for aerodynamic and acoustic studies of fans of bypass turbojet engines (TEF)" (US Pat. RU2337342, IPC G01M 15/14, publ. with air intake filters installed in them, a birotational fan, a gearbox, a drive, for example, a turbine or an electric motor, an exhauster system, a measurement system, and the birotational fan is installed in the acoustic chamber at a distance of at least ten diameters of the fan impeller from the front, rear and one of side walls of the chamber, contains a front impeller and a rear impeller, which are located at the front ends of the shaft lines installed coaxially, the rear end of each shaft line, respectively, of the front impeller and rear impeller is connected to their drives through gearing, and pairs of bevel gears of the birotational reducer kinematically disconnected ana among themselves, which ensures their independent rotation according to the frequency and power of the impellers of the birotational fan, the shaft lines of the front and rear impellers are enclosed in a housing supported on conical shells, an external conical air intake is installed outside the conical shells, the cavity between the housing and the conical shells is connected to the flow meter air, the housing and conical shells are connected to the supporting housing, the supporting housing is connected to the supporting frame, the outer conical air intake is connected to the air collector supported on the foundation, the exhauster system is connected to the cavity formed by the conical shells and the housing, as well as to the air collector, while the drives of the workers birotational fan wheels, birotational gearbox, exhauster system are placed outside the acoustic chamber.

The disadvantage of the technical solution is the complexity of the design, which consists in the presence of several shaft lines installed coaxially, and the rear end of each shaft line, respectively, of the front impeller and the rear impeller is connected to their drives through gearing, as well as the large dimensions of the structure associated with the distance between the fan and the walls chamber equal to at least ten diameters of the fan impeller, which reduces the visibility of the stand.

Known "Stand for measuring the traction force of the engine" (US Pat. RU72544, IPC G01L 5/13, publ. 20.04.2008, bull. No. 11), the device of which contains a dynamo platform for mounting the engine, hinged to the frame, a force-transmitting assembly and a force meter , characterized in that the dynamo platform is mounted on two supports made in the form of cantilever beams made of elastic plates, rigidly fixed on the frame on one side and having two protruding elements on the opposite side, on which low-resistance hinges are installed, located between the dynamo platform and rigidly connected to it side bars with two openings for the protruding elements of the supports, and the role of the force meter is played by supports in the form of cantilever beams made of elastic plates with strain gauges glued on them, and the low-resistance hinge is a structure of two coaxial truncated cones fixed on the dynamo platform and the side bar and contacting with both edges of the hole, made in the protruding element of the support, and there is no contact between the truncated cones, or a structure of two balls sandwiched between the recesses of the dynamo platform and the side rail and in contact with both edges of the hole made in the protruding element of the support, and there is no contact between the balls, or a structure of two prisms fixed on the dynamo platform and the side bar and squeezing the protruding support element on both sides, and the working edges of all hinge prisms lie in the same plane parallel to the frame, and stops are installed on the frame, limiting the movement of the dynamo platform in the direction of the measured force, and the force-transmitting assembly and stops , limiting the course of the dynamo platform, are made adjustable.

The disadvantage of the technical solution is the structural complexity, which consists in the use of two cantilever beams made of elastic plates, with strain gauges glued to them, and the cantilever beams are connected to the dynamo platform using low-resistance hinges, which can have different designs.

The closest in technical essence to the claimed technical solution is the "Unmanned aerial vehicle propeller lifting thrust test stand" (US Pat. RU 186022 U1, IPC G01L 5/13, B64C 11/00, publ. 26.12.2018, bull. No. 36) containing a protective frame, a two-arm lever in the form of a rectangular beam, an electric motor mounted on one end of the two-arm lever, a lever rotation axis support located on a base consisting of longitudinal, transverse and vertical beams of square section, rigidly interconnected by diagonals, and a strain gauge is introduced , which is installed on the other end of the two-arm lever, the battery and the controller, which are fixed on the two-arm lever, and the battery is connected to the electric motor through the controller, moreover, the controller and the load cell attached to the two-arm lever are connected to the personal computer via the USB port by means of a communication wire.

The disadvantage of the known technical solution is the effect of the gravity of the fan and the power plant on the readings of the load cell, since the motor is fixed at one end of the two-arm lever, and the load cell is installed at the other end of this lever.

The technical problem is the creation of a stand with a simple design for determining the kinematic and power parameters of the aircraft power plant propeller as equipment for studying the dependence of thrust on the propeller rotation speed and the angle of rotation of the ridges.

The technical result consists in creating a bench, simple in design, for determining the kinematic and power parameters of the propeller of the aircraft power plant as equipment for studying the dependence of thrust on the propeller rotation speed and the angle of rotation of the ridges by introducing a movable carriage moving along rails and containing an electric motor, a power module, a controller , a shaft that transmits torque from an electric motor, with a VISH installed on it through a bearing, and an elastic element of the load cell in the form of a spring is attached to the carriage.

The technical result is achieved by the fact that a movable carriage moving along the rail and containing an electric motor, a shaft that transmits torque from the VISH electric motor, which is installed through a bearing, and the carriage is connected to a fixed rack through the elastic element of the strain gauge - a spring, and the fixed rack of the stand contains a strain gauge of the strain gauge , a microcomputer, a multi-channel visualization module and a control panel containing a control lever and keys for adjusting the angle of inclination of the propeller crests, a display showing the set angle of rotation of the crests of the propeller, a display showing the thrust force, a display showing the speed of rotation of the VIS, and connected to the screen through the microcomputer, displaying the flight of an aircraft at a certain speed, depending on the angle of rotation of the propeller crests, using a 3D model of an aircraft in the sky.

To clarify the technical essence of the proposed solution, consider the graphic images:

In FIG. 1 - general view of the stand for determining the kinematic and power characteristics of the propeller of the aircraft power plant, where:

1. Fixed stand;

2. Rails;

3. Control panel;

4. control lever;

5. Keys for adjusting the angle of inclination of the crests of the screw;

6. The display showing the set angle of rotation of the crests of the propeller;

7. Display showing traction force;

8. Display showing the speed of rotation of the VISH;

9. Screen displaying the flight of an aircraft at a certain speed, depending on the angle of rotation of the propeller crests, using a 3D model of the aircraft in the sky;

10. Movable carriage;

11. Shaft transmitting torque from the electric motor to VISH;

12. Bearing;

13. Adjustable pitch screw (VISh);

14. The elastic element of the load cell is a spring.

Figure 2 is a schematic diagram of the stand, where:

1. Fixed stand;

2. Rails;

3. Control panel;

4. control lever;

5. Keys for adjusting the angle of inclination of the crests of the screw;

6. The display showing the set angle of rotation of the crests of the propeller;

7. Display showing traction force;

8. Display showing the speed of rotation of the VISH;

9. Screen displaying the flight of an aircraft at a certain speed, depending on the angle of rotation of the propeller crests, using a 3D model of the aircraft in the sky;

10. Movable carriage;

11. Shaft transmitting torque from the electric motor to VISH;

12. Bearing;

13. Adjustable pitch screw (VISh);

14. Elastic element of the load cell - spring;

15. Microcomputer;

16. Module of multi-channel visualization;

17. Load cell strain gauge;

18. Power module;

19. Controller;

20. Electric motor.

Figure 3 is a schematic diagram of the output of information, where:

1. The display showing the set angle of rotation of the crests of the propeller;

2. Display showing traction force;

3. Display showing the speed of rotation of the VISH;

4. A screen displaying the flight of an aircraft at a certain speed, depending on the angle of rotation of the propeller crests, using a 3D model of the aircraft in the sky;

5. Movable carriage;

13. Adjustable pitch screw (VISh);

14. Elastic element of the load cell - spring;

15. Microcomputer;

16. Module of multi-channel visualization;

17. Load cell strain gauge.

The proposed technical solution makes it possible to create a stand, simple in design, for determining the kinematic and power characteristics of an aircraft power plant propeller as equipment for studying the dependence of thrust on the propeller rotation speed and the angle of rotation of the crests by introducing a movable carriage moving along the rail and containing an electric motor, a shaft that transmits torque from the VISH electric motor, which is installed through a bearing, and the carriage is connected to a fixed rack through the elastic element of the load cell - a spring, also due to the introduction of a screen that displays the flight of an aircraft at a certain speed, depending on the angle of rotation of the propeller ridges, using a 3D model of an aircraft in the sky connected by means of a multi-channel visualization module to a microcomputer, and by introducing a control lever on the control panel, a key for adjusting the angle of inclination of the screw ridges, a display showing the set angle of rotation of the ridges of the screw, a display showing the traction force, and a display showing the rotation speed of the VISH.

The design of the stand for determining the kinematic and power characteristics of the propeller of the aircraft power plant is a fixed rack 1 with a screen 9 that displays the flight of the aircraft at a certain speed, depending on the angle of rotation of the propeller crests, using a 3D model of the aircraft in the sky, and an elastic element of the load cell - a spring 14, consisting of a load cell strain gauge 17, a rail 2, a microcomputer 15, a multi-channel visualization module 16, a control panel 3 containing a control lever 4, keys for adjusting the angle of inclination of the screw ridges 5, a display 6 showing the set angle of rotation of the ridges of the screw, a display 7 showing traction force, and a display 8 showing the rotation speed of the VISH, also a movable carriage 10 containing an electric motor 20, a power module 18, a controller 19, a shaft 11 with a bearing 12 that transmits torque from the electric motor 20 VISH 13, and an adjustable pitch screw (HISP) 13.

The stand for determining the kinematic and power characteristics of the propeller of the aircraft power plant operates as follows:

The control lever 4 includes an electric motor 20 connected to the power module 18 through the controller 19. The electric motor 20 transmits torque through the shaft 11 to the variable pitch screw 13, and the shaft is fixed to the body of the movable carriage 10 using a bearing 12. The control panel 3 is located on the fixed rack 1 , containing the control lever 4, the keys for adjusting the angle of inclination of the crests of the screw 5, the display 6 showing the set angle of rotation of the crests of the screw, the display 7 showing the traction force, and the display 8 showing the rotation speed of the VIS. The keys for adjusting the angle of inclination of the crests of the screw 5 set the desired angle. VISH 13 creates a force that stretches the elastic element of the strain gauge - the spring 14, which, in turn, transmits a signal to the strain gauge of the strain gauge 17, from which the signal enters the microcomputer 15, and through the multi-channel visualization module 16 is displayed on the screen 9, which displays the aircraft flight with a certain speed depending on the angle of rotation of the propeller crests, using a 3D model of the aircraft in the sky, as well as on display 6 showing the set angle of rotation of the crests of the propeller, display 7 showing the thrust force, and on display 8 showing the rotation speed of the VIS.

In terms of its technical and economic advantages, in comparison with known analogues, the proposed technical solution makes it possible to obtain a useful model of a simple design stand for determining the kinematic and power characteristics of an aircraft power plant propeller by introducing a movable carriage moving along rails and containing an electric motor, a power module, controller, a shaft that transmits torque from an electric motor, with a VISH installed on it through a bearing, and an elastic element of the load cell in the form of a spring is attached to the carriage, as well as introducing a control lever and a key for adjusting the angle of inclination of the screw ridges, a display showing the set angle rotation of the screw crests, a display showing the thrust force, and a display showing the speed of rotation of the VIS, which generally increases the visibility of the stand.

Claims (1)

Stand for determining the kinematic and power characteristics of the propeller of the aircraft power plant, including a fixed stand of the stand, containing a strain gauge strain gauge, a microcomputer and a control panel, an adjustable pitch propeller (VSP), an electric motor, a shaft that transmits torque from the VSP electric motor, a power supply module connected to with an electric motor through a controller, characterized in that a movable carriage is introduced that moves along the rail and contains an electric motor, a shaft that transmits torque from the VISH electric motor, which is installed through a bearing, and the carriage is connected to a fixed rack through an elastic element of the load cell - a spring, on the control panel a control lever, keys for adjusting the angle of inclination of the propeller crests, a display showing the set angle of rotation of the crests of the propeller, a display showing the thrust force, and a display showing the speed of rotation of the VISh are introduced.

Images