Ground simulation experiment device for installation air inlet environment of high-speed aircraft power system

Abstract

The invention relates to the technical field of simulation experiment equipment, and particularly discloses a ground simulation experiment device for an installation air inlet environment of a high-speed aircraft power system, which is used for solving the problem that the ground of the installation air inlet environment of the aircraft power system is difficult to simulate in the prior art. Comprising a base, an experiment outer cylinder is vertically arranged at the upper end of the base, a top cover is arranged at the opening position of the top of the experiment outer cylinder in a matched mode, a plurality of reinforcing ribs are arranged between the base and the bottom of the experiment outer cylinder, and the structural strength of the bottom of the experiment outer cylinder is provided through the reinforcing ribs. In the testing process, the rotating speed and the height can be adjusted according to needs, so that the power system can obtain different airflow velocities, upper and lower airflows generate convection by setting different air temperatures of the upper and lower layers, the turbulence degree of the airflows is increased, and thus the complex airflow state is simulated; the power system can be tested in different air flow states, the air inlet environment of the power system under the limit working condition can also be tested, and the actual test requirement is met.

Description

Technical Field

[0001] The invention relates to the technical field of simulation experiment equipment, in particular to a ground simulation experiment device for the installed air intake environment of a high-speed aircraft power system. Background Art

[0002] The rotor system of the engine is the core component of the engine, and is also the main body of the engine vibration and the main source of excitation. When the aircraft is in extreme conditions, such as turning, pitching, somersaults, and being subjected to adverse conditions such as cold and hot air currents, the engine is prone to over-limit and even cause mid-air parking accidents. In response to this, the existing patent announcement number CN112710459B discloses an aircraft engine rotor flight state experimental platform, in which the experimental platform detection data includes the rotor speed, rotation angle, rotor vibration information, etc., and different parameters can be used to comprehensively characterize the motion state of the rotor in the flight state of the aircraft from multiple aspects. Specifically, the detection circuit may include one or more of a water cooling circuit, an oil supply / return circuit, an optical fiber cable, and an air supply circuit. The detection circuit can be connected to different detection components through a rotary joint to realize the collection of different parameters in the experimental platform through the water cooling system, lubrication system, optical fiber system, and air path system;

[0003] However, the experimental platform that can be provided in the prior art can only simulate the rotation state of the rotor system, and cannot simulate the complex intake environment of the power system under the installed state, making it impossible for the power system to obtain the intake environment under different airflow speeds and airflow stabilities, resulting in the acquisition of experimental data that is not realistic enough.

[0004] Based on this, a ground simulation experimental device for the installed air intake environment of a high-speed aircraft power system is now provided, which can eliminate the drawbacks of the existing devices. Summary of the invention

[0005] The purpose of the present invention is to provide a high-speed aircraft power system installed air intake environment ground simulation experimental device, which solves the problem that the aircraft power system installed air intake environment is difficult to simulate on the ground in the prior art.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A ground simulation experiment device for the installed air intake environment of a high-speed aircraft power system comprises a base, an experimental outer cylinder is vertically arranged on the upper end of the base, a top cover is matched with the top opening position of the experimental outer cylinder, a plurality of reinforcing ribs are arranged between the base and the bottom of the experimental outer cylinder, the reinforcing ribs are used to provide structural strength to the bottom of the experimental outer cylinder, an insulating layer for heat insulation is arranged on the outer side of the experimental outer cylinder, so that the experimental outer cylinder can be kept warm, a movable door is arranged on the outer side of the bottom of the base, and the power system to be tested can be sent into the experimental outer cylinder through the movable door, a temperature regulating component for adjusting the internal temperature of the experimental outer cylinder is arranged on the outer side of the experimental outer cylinder, and a displacement mechanism for driving the power system to move at high speed is also arranged inside the experimental outer cylinder.

[0008] On the basis of the above technical solution, the present invention also provides the following optional technical solution:

[0009] In an optional scheme: the displacement mechanism includes a mounting seat arranged at the bottom of the experimental outer cylinder, a second rotating ring is rotatably provided at the middle position of the mounting seat, a first rotating ring is rotatably provided at the top of the experimental outer cylinder, two groups of connecting columns are symmetrically provided between the first rotating ring and the second rotating ring, each group of connecting columns is provided with a positioning tool for fixing the power system, the second rotating ring is connected to a rotating driving member for driving its rotation, and the positioning tool is connected to a lifting member for driving its up and down movement.

[0010] In an optional scheme: the positioning tooling includes a lifting block that slides with two connecting columns, a tooling seat is rotatably provided between two adjacent lifting blocks, a positioning cavity matching the power system is provided on the upper end of the tooling seat, two tooling splints are symmetrically provided inside the positioning cavity, the bottom of the tooling splint is slidably set at the bottom of the positioning cavity, one end of the two tooling splints is slidably set on the guide rod, and the other side of the two tooling splints is threadedly connected to the working screw, the rotation directions of the threaded areas on both sides of the working screw are opposite, the working screw is connected to a clamping motor for driving it to rotate, the cross-section of the tooling splint is an L-shaped structure, and the working screw and the tooling splint are driven to rotate relative to each other by the clamping motor, a rotating motor for driving the tooling seat to rotate is provided on the lifting block, and an installation notch is provided on the lifting block for facilitating the installation of the rotating motor.

[0011] In an optional solution: the lifting member includes a lifting screw connected to the positioning fixture threadedly, the upper end of the lifting screw is rotatably connected to the lower end of the first rotating ring, and the lower end of the first rotating ring is connected to a lifting motor for driving the lifting screw to rotate.

[0012] In an optional solution: the rotary drive member includes a driven gear ring arranged outside the second rotating ring, the outer side of the driven gear ring is meshed with a driving gear, and the driving gear is arranged at the output end of the driving motor.

[0013] In an optional scheme: the temperature control component includes a plurality of air guide ring boxes arranged on the outside of the experimental outer cylinder, the inner cavity of the air guide ring box is connected with the experimental outer cylinder through a connecting port, two partitions are provided in the inner cavity of the air guide ring box, the two partitions divide the inner cavity of the air guide ring box into an air intake area and an exhaust area, the air intake area is connected with the air supply box through a connecting pipe, and the exhaust area is connected with the air exhaust box through a connecting pipe.

[0014] In an optional solution: a thermometer for detecting temperature is provided on the inner wall of the experimental outer cylinder where the air guide ring box is located.

[0015] In an optional solution: the air guide ring box is provided with two respectively located at the upper end and the bottom position of the experimental outer cylinder.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present invention is designed according to existing needs, and can simulate the air intake environment of the power system under the installed state on the ground, and here at least two sets of experimental data can be obtained at one time to ensure the authenticity of the data acquisition. In addition, the air intake environment under extreme working conditions can be constructed. When testing, the rotation speed and height can be adjusted as needed, so that the system can obtain different air flow speeds. By setting different air temperatures in the upper and lower layers, convection is generated in the upper and lower air flows, making the air flow more turbulent. In this way, the power system can be tested under different air flow states, and the air intake environment of the power system under extreme working conditions can also be tested, meeting the actual test needs;

[0018] 2. When fixing the power system, the present invention drives the working screw and the tooling clamp to rotate relative to each other through the clamping motor. Under the action of the thread, the two tooling clamps will slide relative to or away from each other, thereby completing the clamping of the power system, facilitating the rapid tooling positioning of the power system, and the installation height can be lowered during the installation process to simulate the intake environment at different heights. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the structure of the present invention.

[0020] Figure 2 It is a schematic diagram of the internal structure of the present invention.

[0021] Figure 3 It is a schematic diagram of the structure of the first rotating ring and the second rotating ring of the present invention.

[0022] Figure 4 It is a schematic diagram of the positioning tool structure of the present invention.

[0023] Reference numerals: base 100, test outer cylinder 101, movable door 102, reinforcing rib 103, heat insulation layer 104, top cover 105, communication port 106, mounting seat 107;

[0024] Air supply box 200, air extraction box 201, air guide ring box 202, connecting pipe 203;

[0025] The first rotating ring 301, the connecting column 302, the second rotating ring 303, the positioning tool 304, the driving gear 305, the driving motor 306, the driven gear ring 307, the lifting motor 308, the lifting screw 309, the lifting block 311, the installation notch 312, the rotating motor 313, the tool seat 314, the working screw 315, the tool clamping plate 316, and the positioning cavity 317. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0027] Example 1

[0028] like Figure 1-4 As shown, the embodiment of the present invention provides a ground simulation experiment device for the air intake environment of a high-speed aircraft power system, including a base 100, a test outer cylinder 101 is vertically arranged on the upper end of the base 100, a top cover 105 is arranged at the top opening position of the test outer cylinder 101, a plurality of reinforcing ribs 103 are arranged between the base 100 and the bottom of the test outer cylinder 101, and the structural strength of the bottom of the test outer cylinder 101 is provided by the reinforcing ribs 103, and a heat insulation layer 104 for heat insulation is arranged on the outside of the test outer cylinder 101, so that The experimental outer cylinder 101 is insulated. A movable door 102 is provided on the outer side of the bottom of the base 100. The power system to be tested can be sent into the experimental outer cylinder 101 through the movable door 102. A temperature adjustment component for adjusting the internal temperature of the experimental outer cylinder 101 is provided on the outer side of the experimental outer cylinder 101. The temperature adjustment component can be used to build a corresponding extremely hot or extremely cold test environment inside the experimental outer cylinder 101. A displacement mechanism for driving the power system to move at high speed is also provided inside the experimental outer cylinder 101. The displacement mechanism drives the power system to simulate the actual flight state of the aircraft;

[0029] The power system is provided with an air intake sensor and a flow meter for detecting the amount of input oil, so that the air flow and oil flow of the power system under extreme flight can be detected;

[0030] The displacement mechanism includes a mounting seat 107 arranged at the bottom of the experimental outer cylinder 101, a second rotating ring 303 is rotatably arranged in the middle position of the mounting seat 107, a first rotating ring 301 is rotatably arranged at the top of the experimental outer cylinder 101, two groups of connecting columns 302 are symmetrically arranged between the first rotating ring 301 and the second rotating ring 303, each group of connecting columns 302 is provided with a positioning fixture 304 for fixing the power system, the second rotating ring 303 is connected to a rotating driving member for driving its rotation, the positioning fixture 304 is connected to a lifting member for driving its up and down movement, under the lifting action, the positioning fixture 304 will drive the power system to move up and down, so as to adjust the flight altitude, and the second rotating ring 303 is driven to rotate by the rotating driving member, thereby driving the positioning fixture 304 to rotate rapidly, so that the power system can fly at high speed;

[0031] The positioning fixture 304 includes a lifting block 311 that is slidably matched with the two connecting columns 302, and a fixture seat 314 is rotatably arranged between the two adjacent lifting blocks 311. A positioning cavity 317 matching the power system is arranged on the upper end of the fixture seat 314, and two fixture clamps 316 are symmetrically arranged inside the positioning cavity 317. The bottom of the fixture clamp 316 is slidably arranged at the bottom of the positioning cavity 317, and one end of the two fixture clamps 316 is slidably arranged on the guide rod, and the other side of the two fixture clamps 316 is threadedly connected to the working screw 315. The rotation directions of the threaded areas on both sides of the working screw 315 are opposite, and the working screw 315 is connected to drive The clamping motor rotates, and the cross section of the tooling clamping plate 316 is an L-shaped structure. The clamping motor drives the working screw 315 and the tooling clamping plate 316 to rotate relative to each other. Under the action of the thread, the two tooling clamping plates 316 will slide relative to or away from each other, thereby completing the clamping of the power system. The lifting block 311 is provided with a rotating motor 313 for driving the tooling seat 314 to rotate. The lifting block 311 is provided with an installation notch 312 for facilitating the installation of the rotating motor 313, so that the tooling seat 314 can be driven to rotate by the rotating motor 313, so that the clamped power system can be driven to rotate at high speed, thereby simulating the extreme action of high-speed rotation of the aircraft;

[0032] The lifting member includes a lifting screw 309 threadedly connected to the positioning fixture 304, the upper end of the lifting screw 309 is rotatably connected to the lower end of the first rotating ring 301, and the lower end of the first rotating ring 301 is connected to a lifting motor 308 for driving the first rotating ring 301 to rotate. Under the action of the lifting motor 308, the lifting screw 309 and the positioning fixture 304 rotate relative to each other. Under the action of the thread, the positioning fixture 304 slides along the lifting screw 309, thereby driving the power system to adjust its height;

[0033] The rotary drive member includes a driven gear ring 307 disposed on the outer side of the second rotating ring 303, the outer side of the driven gear ring 307 is meshed with the driving gear 305, and the driving gear 305 is disposed at the output end of the driving motor 306. Under the action of the driving motor 306, the driving gear 305 matches the driven gear ring 307 to drive the second rotating ring 303 to rotate, thereby providing power for high-speed flight;

[0034] The temperature control component includes a plurality of air guide ring boxes 202 arranged outside the experimental outer cylinder 101, the inner cavity of the air guide ring box 202 is connected with the experimental outer cylinder 101 through a connecting port 106, and two partitions are arranged in the inner cavity of the air guide ring box 202, and the two partitions divide the inner cavity of the air guide ring box 202 into an air intake area and an exhaust area, the air intake area is connected with the air supply box 200 through a connecting pipe 203, and the exhaust area is connected with the air extraction box 201 through a connecting pipe. Under the action of the air supply box 200, hot air or cooling will enter the air intake area of ​​the air guide ring box 202, and then enter the interior of the experimental outer cylinder 101 through the connecting port 106, and a low temperature or high temperature environment is constructed inside the experimental outer cylinder 101, so that the power system can be tested under the corresponding extreme environment;

[0035] The inner wall of the experimental outer cylinder 101 where the air guide ring box 202 is located is provided with a thermometer for detecting the temperature, so that the test environment temperature can be detected:

[0036] The air guide ring box 202 is provided with two positions at the upper end and the bottom of the test outer cylinder 101, so that an extremely cold area and an extremely hot area can be constructed at the bottom and the top of the test outer cylinder 101, respectively, so as to test the operation of the power system under extreme environment switching;

[0037] Working principle / working process, in actual use, by fixing the power system on the positioning fixture 304, and then driving the driving motor 306 to drive the driving gear 305 to rotate, the driving gear 305 matches the driven gear ring 307 to drive the second rotating ring 303 to rotate, thereby driving the power system to revolve, simulating the high-speed flight of the aircraft, and during the flight, the positioning fixture 304 can be driven to adjust by the lifting member, thereby simulating the extreme actions of the aircraft diving and lifting, and the power system can also be driven to rotate quickly, thereby simulating actions such as the aircraft rotating. During the flight test, the temperature inside the base 100 can also be adjusted by the temperature adjustment component to meet the working conditions of different extreme temperatures. In addition, by setting the air guide ring box 202 into two, and respectively placing them at the upper end and bottom position of the experimental outer cylinder 101, an extremely cold area and an extremely hot area can be constructed at the bottom and top of the experimental outer cylinder 101, respectively, so as to test the power system working under extreme environment switching; and the present application uses two power systems for each test, and the two power systems are symmetrically arranged, which can make the rotation more balanced, and can also obtain more data, thereby improving the authenticity of the data.

[0038] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A ground simulation experimental device for an installed air intake environment of a high-speed aircraft power system, comprising a base (100), an experimental outer cylinder (101) vertically disposed at the upper end of the base (100), a top cover (105) cooperating with the top opening of the experimental outer cylinder (101), characterized in that: A plurality of reinforcing ribs (103) are arranged between the base (100) and the bottom of the experimental outer cylinder (101), and the structural strength of the bottom of the experimental outer cylinder (101) is provided by the reinforcing ribs (103). A movable door (102) is arranged on the outer side of the bottom of the base (100). A temperature regulating component for regulating the internal temperature of the experimental outer cylinder (101) is arranged on the outer side of the experimental outer cylinder (101). A displacement mechanism for driving a power system to move at high speed is also arranged inside the experimental outer cylinder (101).

2. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 1 is characterized in that: The displacement mechanism comprises a mounting seat (107) arranged at the bottom of the experimental outer cylinder (101); a second rotating ring (303) is rotatably arranged in the middle position of the mounting seat (107); a first rotating ring (301) is rotatably arranged at the top of the experimental outer cylinder (101); two groups of connecting columns (302) are symmetrically arranged between the first rotating ring (301) and the second rotating ring (303); each group of connecting columns (302) is provided with a positioning fixture (304) for fixing the power system; the second rotating ring (303) is connected to a rotating driving member for driving the second rotating ring to rotate; and the positioning fixture (304) is connected to a lifting member for driving the second rotating ring to move up and down.

3. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 1 is characterized in that: The positioning tool (304) comprises a lifting block (311) slidably matched with the two connecting columns (302); a tool seat (314) is rotatably arranged between two adjacent lifting blocks (311); a positioning cavity (317) matching the power system is arranged at the upper end of the tool seat (314); two tool clamps (316) are symmetrically arranged inside the positioning cavity (317); the bottom of the tool clamps (316) is slidably arranged at the bottom of the positioning cavity (317); one end of the two tool clamps (316) is slidably arranged on the guide rod; the other end of the two tool clamps (316) is slidably arranged on the guide rod; One side is threadedly connected to the working screw (315), and the threaded areas on both sides of the working screw (315) have opposite rotation directions. The working screw (315) is connected to a clamping motor for driving it to rotate. The cross-section of the tooling clamping plate (316) is an L-shaped structure. The clamping motor drives the working screw (315) and the tooling clamping plate (316) to rotate relative to each other. The lifting block (311) is provided with a rotating motor (313) for driving the tooling seat (314) to rotate. The lifting block (311) is provided with an installation notch (312) for facilitating the installation of the rotating motor (313).

4. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 3 is characterized in that: The lifting member comprises a lifting screw (309) threadedly connected to the positioning fixture (304); the upper end of the lifting screw (309) is rotatably connected to the lower end of the first rotating ring (301); and the lower end of the first rotating ring (301) is connected to a lifting motor (308) for driving the first rotating ring (301) to rotate.

5. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 3 is characterized in that: The rotary drive member comprises a driven gear ring (307) arranged outside the second rotating ring (303), the outer side of the driven gear ring (307) meshing with a driving gear (305), and the driving gear (305) is arranged at the output end of the driving motor (306).

6. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 1 is characterized in that: The temperature control component comprises a plurality of air guide ring boxes (202) arranged outside the experimental outer cylinder (101); the inner cavity of the air guide ring box (202) is connected to the experimental outer cylinder (101) through a connecting port (106); two partitions are arranged in the inner cavity of the air guide ring box (202); the two partitions divide the inner cavity of the air guide ring box (202) into an air intake area and an exhaust area; the air intake area is connected to the air supply box (200) through a connecting pipe (203); and the exhaust area is connected to the air exhaust box (201) through a connecting pipe.

7. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 6 is characterized in that: The inner wall of the experimental outer cylinder (101) where the air guide ring box (202) is located is provided with a thermometer for detecting temperature.

8. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 6 is characterized in that: The air guide ring box (202) is provided with two respectively located at the upper end and the bottom of the experimental outer cylinder (101).

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