A ground simulation experimental device for the installed air intake environment of a high-speed aircraft power system

Abstract

The present invention relates to the technical field of simulation experimental equipment, and specifically discloses a ground simulation experimental device for the installed air intake environment of a high-speed aircraft power system, which solves the problem in the prior art that the installed air intake environment of an aircraft power system is difficult to simulate on the ground; it comprises a base, an experimental outer cylinder is vertically provided on the upper end of the base, a top cover is provided at the top opening of the experimental outer cylinder, and a plurality of reinforcing ribs are provided between the base and the bottom of the experimental outer cylinder, and the structural strength of the bottom of the experimental outer cylinder is provided by the reinforcing ribs. During the test process, the present invention can adjust the rotation speed and height as needed, so that the power system can obtain different air flow speeds, and by setting different air temperatures in the upper and lower layers, the upper and lower air flows generate convection, which aggravates the turbulence of the air flow, thereby simulating a complex air flow state, allowing the power system to be tested under different air flow states, and can also test the air intake environment of the power system under extreme working conditions, meeting actual test needs.

Description

Technical Field

[0001] The present 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 severe conditions such as cold and hot air currents, the engine is prone to over-limit, and even causes an accident of parking in the air. 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 the motion state of the rotor in the aircraft flight state can be comprehensively characterized from multiple aspects through different parameters. Specifically, the detection circuit may include one or more of a water cooling circuit, an oil supply / return circuit, an optical 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 by the existing technology 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 disadvantages 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 to solve the problem in the prior art that the aircraft power system installed air intake environment is difficult to simulate on the ground.

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

[0007] A ground simulation experimental device for the installed air intake environment of a high-speed aircraft power system includes a base, an experimental outer cylinder is vertically provided on the upper end of the base, a top cover is provided at the top opening position of the experimental outer cylinder, a plurality of reinforcing ribs are provided between the base and the bottom of the experimental outer cylinder, and the structural strength of the bottom of the experimental outer cylinder is provided by the reinforcing ribs, an insulating layer for heat insulation is provided on the outside of the experimental outer cylinder, so that the experimental outer cylinder can be kept warm, a movable door is provided on the outside 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 control component is provided on the outside of the experimental outer cylinder for adjusting the internal temperature of the experimental outer cylinder, and a displacement mechanism for driving the power system to move at high speed is also provided inside the experimental outer cylinder.

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

[0009] In an optional solution: the displacement mechanism includes a mounting seat arranged at the bottom of the experimental outer cylinder, a second rotating ring is rotatably provided in the middle position of the mounting seat, a first rotating ring is rotatably provided at the top inner portion 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 drive 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 tool includes a lifting block that slides with two connecting columns, a tool seat is rotatably provided between two adjacent lifting blocks, and a positioning cavity matching the power system is provided on the upper end of the tool seat, and two tool clamps are symmetrically provided inside the positioning cavity, and the bottom of the tool clamp is slidably set at the bottom of the positioning cavity, and one end of the two tool clamps is slidably set on the guide rod, and the other side of the two tool clamps is threadedly connected to the working screw, and the rotation directions of the threaded areas on both sides of the working screw are opposite, and the working screw is connected to a clamping motor for driving it to rotate, and the cross-section of the tool clamp is an L-shaped structure, and the working screw and the tool clamp are driven to rotate relative to each other by the clamping motor, and a rotating motor for driving the tool 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 tool thread, 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 first rotating ring 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 solution: 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 to the experimental outer cylinder through a connecting port, and two partitions are provided in the inner cavity of the air guide ring box, which 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 to the air supply box through a connecting pipe, and the exhaust area is connected to 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 at the upper end and the bottom position of the experimental outer cylinder respectively.

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

[0017] The present invention is designed to meet existing needs and can perform ground simulation of the intake environment of a power system in an installed state. At least two sets of experimental data can be acquired at one time to ensure the authenticity of the data acquired. In addition, an intake environment under extreme working conditions can be constructed. During testing, the rotation speed and altitude can be adjusted as needed, so that the system can obtain different airflow speeds. By setting different air temperatures in the upper and lower layers, convection is generated in the upper and lower airflows, making the airflow more turbulent. In this way, the power system can be tested under different airflow conditions. The intake environment of the power system under extreme working conditions can also be tested, meeting actual testing needs.

[0018] When fixing the power system, the present invention drives the working screw and the tooling plate to rotate relative to each other through the clamping motor. Under the action of the thread, the two tooling plates 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 air intake environment at different heights. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a structural schematic diagram 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 structural diagram 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 , experimental outer cylinder 101 , movable door 102 , reinforcing rib 103 , thermal insulation layer 104 , top cover 105 , communication port 106 , mounting base 107 ;

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

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

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

[0027] like Figure 1-4 As shown, the embodiment of the present invention provides a ground simulation experimental device for the air intake environment of a high-speed aircraft power system, including a base 100, a test outer cylinder 101 is vertically provided on the upper end of the base 100, a top cover 105 is provided at the top opening position of the test outer cylinder 101, a plurality of reinforcing ribs 103 are provided between the base 100 and the bottom of the test outer cylinder 101, and the reinforcing ribs 103 provide structural strength to the bottom of the test outer cylinder 101, and a heat insulation layer 104 for heat insulation is provided on the outside of the test outer cylinder 101, so that The test 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 placed into the test outer cylinder 101 through the movable door 102. A temperature control component is provided on the outside of the test outer cylinder 101 for regulating the internal temperature of the test outer cylinder 101. The temperature control component can be used to create a corresponding extremely hot or extremely cold test environment inside the test outer cylinder 101. A displacement mechanism is also provided inside the test outer cylinder 101 to drive the power system to move at high speed. The displacement mechanism drives the power system to simulate the actual flight state of an aircraft.

[0028] 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 can be detected under extreme flight conditions;

[0029] The displacement mechanism includes a mounting base 107 arranged at the bottom of the experimental outer cylinder 101, a second rotating ring 303 is rotatably provided in the middle position of the mounting base 107, a first rotating ring 301 is rotatably provided at the top of the experimental outer cylinder 101, two groups of connecting columns 302 are symmetrically provided 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 drive member for driving its rotation, and 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 to adjust the flight altitude, and the second rotating ring 303 is driven to rotate by the rotating drive member, thereby driving the positioning fixture 304 to rotate rapidly, so that the power system can fly at high speed;

[0030] The positioning tool 304 includes a lifting block 311 that slides with the two connecting columns 302, and a tool seat 314 is rotatably provided between the two adjacent lifting blocks 311. A positioning cavity 317 that matches the power system is provided on the upper end of the tool seat 314. Two tool clamps 316 are symmetrically provided inside the positioning cavity 317. The bottom of the tool clamp 316 is slidably set at the bottom of the positioning cavity 317. One end of the two tool clamps 316 is slidably set on the guide rod, and the other side of the two tool 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. The working screw 315 is connected to drive the The rotating clamping motor, 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 a mounting notch 312 for facilitating the installation of the rotating motor 313. In this way, 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 an aircraft;

[0031] 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. 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 height of the power system to adjust;

[0032] The rotary drive member includes a driven gear ring 307 disposed on the outside of the second rotating ring 303. The outside of the driven gear ring 307 is meshed with a driving gear 305. The driving gear 305 is disposed at the output end of a driving motor 306. Under the action of the driving motor 306, the driving gear 305 and the driven gear ring 307 match and drive the second rotating ring 303 to rotate, thereby providing power for high-speed flight.

[0033] The temperature control component includes a plurality of air guide ring boxes 202 arranged on the outside of 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 provided 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 extraction box 201 through a connecting pipe. Under the action of the air supply box 200, hot air or cooling air 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, thereby constructing a low-temperature or high-temperature environment inside the experimental outer cylinder 101, so that the power system can be tested under the corresponding extreme environment;

[0034] 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:

[0035] The air guide ring box 202 is provided with two 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;

[0036] Working principle / working process: In actual use, the power system is fixed to the positioning fixture 304, and then the driving motor 306 drives the driving gear 305 to rotate. The driving gear 305 matches the driven gear ring 307 and drives the second rotating ring 303 to rotate, thereby driving the power system to revolve, simulating the high-speed flight of the aircraft. During flight, the positioning fixture 304 can be driven by the lifting member for adjustment, thereby simulating the extreme movements of the aircraft such as diving and lifting. In addition, the power system can be driven to rotate rapidly, thereby simulating movements such as aircraft rotation. During the flight test, the temperature inside the base 100 can be adjusted by the temperature control component to meet the working conditions of different extreme temperatures. In addition, by providing two air guide ring boxes 202, and placing them at the upper and bottom positions of the experimental outer cylinder 101 respectively, extremely cold and extremely hot areas can be constructed at the bottom and top of the experimental outer cylinder 101, respectively, to test the operation of the power system under extreme environmental switching conditions; and in this application, two power systems are used in each test. The symmetrical arrangement of the two power systems can make the rotation more balanced, obtain more data, and improve the authenticity of the data.

[0037] 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 principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A ground simulation experimental device for the air intake environment of a high-speed aircraft power system, comprising a base (100), an experimental outer cylinder (101) vertically provided at the upper end of the base (100), and a top cover (105) provided at the top opening of the experimental outer cylinder (101), characterized in that: A plurality of reinforcing ribs (103) are provided 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 provided on the outside of the bottom of the base (100). A temperature regulating component for regulating the internal temperature of the experimental outer cylinder (101) is provided on the outside of 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 includes a mounting seat (107) arranged at the bottom of the experimental outer cylinder (101), a second rotating ring (303) is rotatably provided at the middle position of the mounting seat (107), a first rotating ring (301) is rotatably provided at the top of the inner portion of the experimental outer cylinder (101), two groups of connecting columns (302) are symmetrically provided 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; The positioning tool (304) includes a lifting block (311) that is slidably matched with the two connecting columns (302), and a tool seat (314) is rotatably provided between the two adjacent lifting blocks (311). The upper end of the tool seat (314) is provided with a positioning cavity (317) that matches the power system, and two tool clamps (316) are symmetrically provided inside the positioning cavity (317). The bottom of the tool clamp (316) is slidably set at the bottom of the positioning cavity (317), and one end of the two tool clamps (316) is slidably set on the guide rod, and the other end of the two tool clamps (316) is symmetrically provided with a positioning cavity (317) that matches the power system. 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 the working screw (315) 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). 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. 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) being meshed with a driving gear (305), and the driving gear (305) being arranged at the output end of the driving motor (306); The temperature control assembly 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 to the experimental outer cylinder (101) through a connecting port (106), and two partitions are provided 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 to the air supply box (200) through a connecting pipe (203), and the exhaust area is connected to the air extraction box (201) through a connecting pipe.

2. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 1 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.

3. The high-speed aircraft power system installed air intake environment ground simulation experimental device according to claim 1 is characterized in that: The air guide ring box (202) is provided with two portions located at the upper end and the bottom of the experimental outer cylinder (101).

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