CN117433739B - Annular continuous magnetic levitation track simulation wind tunnel and test method thereof - Google Patents
Annular continuous magnetic levitation track simulation wind tunnel and test method thereof Download PDFInfo
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- CN117433739B CN117433739B CN202311756054.6A CN202311756054A CN117433739B CN 117433739 B CN117433739 B CN 117433739B CN 202311756054 A CN202311756054 A CN 202311756054A CN 117433739 B CN117433739 B CN 117433739B
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- 238000005339 levitation Methods 0.000 title claims abstract description 25
- 238000004088 simulation Methods 0.000 title claims abstract description 25
- 238000010998 test method Methods 0.000 title claims abstract description 10
- 238000004804 winding Methods 0.000 claims abstract description 68
- 238000000034 method Methods 0.000 claims abstract description 19
- 230000006698 induction Effects 0.000 claims abstract description 16
- 230000008569 process Effects 0.000 claims abstract description 15
- 238000007789 sealing Methods 0.000 claims description 39
- 230000005484 gravity Effects 0.000 claims description 19
- 238000006073 displacement reaction Methods 0.000 claims description 13
- 238000009423 ventilation Methods 0.000 claims description 12
- 230000001133 acceleration Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 238000002360 preparation method Methods 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 230000004044 response Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 description 11
- 230000001276 controlling effect Effects 0.000 description 4
- 238000012544 monitoring process Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
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- 238000005265 energy consumption Methods 0.000 description 1
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- 238000010278 pulse charging Methods 0.000 description 1
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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Abstract
The invention belongs to the technical field of wind tunnel tests, and discloses a ring-shaped continuous magnetic levitation track simulation wind tunnel and a test method thereof. The annular continuous magnetic levitation track simulation wind tunnel comprises an annular pipeline, wherein an annular winding coil of an independent control system and a power supply is respectively arranged on the outer wall surface of the annular pipeline in a surrounding L mode; a plurality of cylindrical coils which are uniformly distributed are arranged along the central annular line of the annular outer wall surface of the annular pipeline; upper and lower magnet blocks are symmetrically arranged above and below the annular pipeline; the model is arranged in the annular pipeline, and is connected with a model posture adjusting system, a magnet and an induction coil; the model attitude adjustment system can adjust the model attack angle in real time. The test method of the annular continuous magnetic levitation track simulation wind tunnel can truly simulate the low-altitude high-speed flight process of the aircraft, comprehensively check the pneumatic load loading process of the aircraft, has the advantages of high simulation height, large speed range, comprehensive simulation capability and long test time, and has engineering popularization value.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a ring-shaped continuous magnetic levitation track simulation wind tunnel and a test method thereof.
Background
In the aerospace field, ground tunnels are commonly used to simulate the flight environment of an aircraft. However, a test of a conventional wind tunnel device generally can only simulate a fixed flow field condition, it is difficult to adjust environmental parameters such as speed, density, temperature and the like of air flow at the same time, and multiple tests are required on a plurality of devices to simulate different parameters of a plurality of discrete orbit points on a flight history, and it is difficult to reproduce the real flight history of an aircraft for a long time along the orbit by acquiring flow characteristics under the flight condition through combined analysis.
The magnetic levitation technology can reduce friction resistance and energy consumption; the electromagnetic propulsion mode can continuously accelerate/decelerate the model and has no tail gas pollution; the annular pipeline can realize long-time circulating operation; the pipeline air flow regulating technology simulates the atmospheric environment with different heights, and the combination of the technology has the remarkable characteristics of wide airspace, wide speed range, long-time, real-time simulation and the like, and has the basic condition of developing a ring-shaped continuous magnetic levitation track simulation wind tunnel.
Disclosure of Invention
The invention aims to provide a ring-shaped continuous magnetic levitation track simulation wind tunnel, and the other technical problem to be solved by the invention is to provide a test method of the ring-shaped continuous magnetic levitation track simulation wind tunnel, which is used for overcoming the defects of the prior art.
The invention relates to a ring-shaped continuous magnetic levitation track simulation wind tunnel which is characterized by comprising a ring-shaped pipeline, wherein the radius of the ring-shaped pipeline is more than or equal to 1000m, and the material is 35CrNi3MoVR; the inner cavity of the annular pipeline is provided with a sealing cavity, a model is placed in the sealing cavity, the model adopts a real aircraft or a scaling model consistent with the real aircraft material, and the highest running speed is designed to be 3000m/s; the environment of the annular pipeline is provided with a matched component adding system, a vacuum system and a temperature system, and the model is provided with a model posture adjusting system, so that the temperature, pressure, components and flight posture of test gas in the annular pipeline can be adjusted in real time according to the flight process to be simulated;
the method comprises the steps of encircling L groups of annular winding coils along the annular outer wall surface of an annular pipeline, wherein L is more than or equal to 200, the winding directions of the groups of annular winding coils are the same, and an independent control system and an independent power supply are respectively configured; a plurality of uniformly distributed schlieren are arranged along the central annular line of the annular outer wall surface of the annular pipeline, and the frequency response is more than 20000 frames; a plurality of uniformly distributed cylindrical coils are also arranged along the central annular line of the annular outer wall surface of the annular pipeline, and the central axis of each cylindrical coil is positioned in the radial direction of the annular pipeline;
the speed measuring sensor, the displacement sensor, the temperature sensor and the pressure sensor are uniformly distributed along the central annular line of the annular inner wall surface of the annular pipeline in a staggered manner;
the upper magnet blocks are uniformly distributed in series along the central line of the annular pipeline above the annular pipeline, the lower magnet blocks which are in one-to-one correspondence with the upper magnet blocks are symmetrically distributed up and down below the annular pipeline, the S magnetic poles of the upper magnet blocks are downward, and the N magnetic poles of the lower magnet blocks are upward;
taking the advancing direction of the model as the front, and connecting a model posture adjusting system, a magnet and an induction coil at the rear of the model; the model attitude adjusting system comprises a front coil and a rear coil, wherein the front coil and the rear coil are consistent in winding direction, the first coil comprises an upper winding coil of a gravity coil I and a lower winding coil of the gravity coil I, the second coil comprises an upper winding coil of the gravity coil II and a lower winding coil of the gravity coil II, the upper winding coil and the lower winding coil of each coil are independently controlled, the current of the upper winding coil and the current of the lower winding coil of each coil are respectively controlled, the distances between the upper magnet block and the lower magnet block of each coil are adjusted, the real-time adjustment of the flight attitude of the model is realized, and the attack angle range of the model is-20 degrees; the central axes of the two groups of coils point to the upper magnet block and the lower magnet block corresponding to the positions of the two groups of coils, and the generated magnetic pole directions are opposite to the magnetic pole directions of the upper magnet block and the lower magnet block; the magnets are horizontally arranged, and the magnetic pole directions of the magnets are opposite to the magnetic pole directions generated by the cylindrical coils corresponding to the positions of the magnets; the induction coil surrounds the pipe center line of the annular pipe;
the induction coil, the annular winding coil and the annular pipeline are coaxial with the central axis.
Further, the sealed chamber is a movable chamber; when the test is prepared, the test is sealed and isolated with the rest part of the annular pipeline to form a model preparation room; when the test is carried out, the test is communicated with the rest part of the annular pipeline to form a model running channel.
The invention discloses a test method for simulating a wind tunnel by using a ring-shaped continuous magnetic levitation track, which comprises the following steps of:
s10, before a test, closing a sealing chamber, placing a model in the sealing chamber by a worker, powering on a model posture adjusting system, suspending the model in the sealing chamber, opening the sealing chamber, penetrating an annular pipeline, filling test gas into the annular pipeline according to a preset gas component, and adjusting the pressure and the temperature of the test gas to preset test conditions;
s20, in the test, grouping pulse power supply is carried out on the annular winding coil through the control system and the power supply, meanwhile, the speed measuring sensor monitors the running speed of the model and feeds back to the cylindrical coil, the vacuum system and the temperature system, and the displacement sensor monitors the distance between the model and the annular inner wall surface of the annular pipeline to prevent the model from contacting the annular inner wall surface of the annular pipeline;
in the test process, the model is subjected to acceleration, uniform speed or deceleration control by controlling and feeding back the current in the annular winding coil, the speed process on the actual flight orbit of the aircraft is simulated, the component adding system, the vacuum system and the temperature system synchronously regulate the gas medium, the pressure and the temperature, and the atmospheric parameters on the actual flight orbit of the aircraft are simulated; the model attitude adjusting system adjusts the model flight attitude in real time by adjusting the current magnitudes of an upper winding coil and a lower winding coil of the two groups of gravity coils; after the test is completed, the annular winding coil continuously decelerates the model until the model stops running; the speed measuring sensor, the displacement sensor, the temperature sensor and the schlieren on the model record data in the flight process in real time;
s30, after the test, the model posture adjustment system is continuously electrified, the model enters the sealing chamber, the sealing chamber is closed, the annular pipeline is cut off, the sealing chamber is opened for ventilation, after the ventilation is completed, staff enter the sealing chamber, the model is taken out, and meanwhile, the rest of the annular pipeline is ventilated, and after the ventilation is completed, the test is completed.
The annular continuous magnetic levitation track simulation wind tunnel has the following technical characteristics:
a. the real flight environment is simulated through the gas in the annular pipeline, and the temperature, the pressure and the components of the test gas are adjustable;
b. the annular winding coils are subjected to grouping pulse power supply, induced current is generated on the induction coils, and then propulsive force is generated on the model, and the model moves around the central line of the pipeline in the annular pipeline under the action of the propulsive force; meanwhile, the annular winding coil and the induction coil are matched to control the magnitude and the direction of the propelling force, so that acceleration and deceleration of the model are controlled;
c. in the running process of the model, the cylindrical coil is continuously powered and interacts with the magnet to generate centripetal electromagnetic force, the centripetal electromagnetic force counteracts the centrifugal force generated by running the model in the annular pipeline, the matching of the electromagnetic force and the centrifugal force is realized by adjusting the distance between the cylindrical coil and the magnetic pole of the magnet and controlling the current of the coil, and the model is ensured not to contact with the inner wall surface of the annular pipeline;
d. the magnetic field generated by the model attitude adjusting system interacts with the upper magnet block and the lower magnet block, so that the model flying attitude can be adjusted in real time, supporting lifting force is provided when the model is static, and in the running process of the model, the flying attack angle of the model is adjusted in real time and the model is ensured not to be contacted with the inner wall surface of the annular pipeline;
e. monitoring the temperature of gas in the annular pipeline through a temperature sensor, monitoring the pressure of the gas in the annular pipeline through a pressure sensor, monitoring the running speed of a model through a speed measuring sensor, and monitoring the distance between the model and the inner wall surface of the annular pipeline through a displacement sensor;
f. by continuously changing the temperature, pressure, components and running speed of the model of the gas in the annular pipeline, a plurality of measurement tasks can be completed in one test, and the test cost is reduced.
The annular continuous magnetic levitation track simulation wind tunnel adopts a magnetic levitation and electromagnetic propulsion mode, and ensures the reliability of test data by ensuring that a model is not contacted with the inner wall surface of an annular pipeline; the model attitude adjustment system is configured to adjust the flight attack angle of the model in real time; and acquiring flow field temperature, pressure and schlieren pictures at any time through measuring points arranged along the inner wall of the annular pipeline. The test method for simulating the wind tunnel by the annular continuous magnetic levitation track can truly simulate the low-altitude high-speed flight process of an aircraft, comprehensively check the pneumatic load loading process of the aircraft, has the advantages of large simulation height and speed range, comprehensive simulation capability and long test time, and has engineering popularization value.
Drawings
FIG. 1 is a schematic structural view (C-C cross-sectional view) of a ring-shaped continuous magnetic levitation track simulation wind tunnel;
FIG. 2 is a schematic structural view (front view) of a ring-shaped continuous magnetic levitation track simulation wind tunnel according to the present invention;
FIG. 3 is a timing control diagram of a toroidal winding coil in a toroidal continuous magnetic levitation track simulation wind tunnel according to the present invention.
In the figure, 1, a component adding system; 2. a control system; 3. a power supply; 4. a speed sensor; 5. a displacement sensor; 6. a temperature sensor; 7. a vacuum system; 8. a temperature system; 9. a pressure sensor; 10. sealing the chamber; 11. a model; 12. a model posture adjustment system; 13. a magnet; 14. an induction coil; 15. a top magnet block; 16. a lower magnet block; 17. a toroidal winding coil; 18. a cylindrical coil; 19. an annular pipe; 20. schlieren;
121. a winding coil is arranged on the gravity coil I; 122. a lower winding coil of the gravity coil I; 123. a winding coil is arranged on the gravity coil II; 124. and a coil is wound under the gravity coil II.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
As shown in FIG. 1 and FIG. 2, the annular continuous magnetic levitation track simulation wind tunnel of the embodiment comprises an annular pipeline 19, wherein the radius of the annular pipeline 19 is more than or equal to 1000m, and the material is 35CrNi3MoVR; the inner cavity of the annular pipeline 19 is provided with a sealing chamber 10, a model 11 is placed in the sealing chamber 10, the model 11 adopts a real aircraft or a scaling model consistent with the real aircraft, and the highest running speed is designed to be 3000m/s; the environment of the annular pipeline 19 is provided with a matched component adding system 1, a vacuum system 7 and a temperature system 8, the model 11 is provided with a model posture adjusting system 12, and the temperature, the pressure, the components and the flight posture of test gas in the annular pipeline 19 can be adjusted in real time according to the flight course which is simulated as required;
along the annular outer wall surface of the annular pipeline 19, L groups of annular winding coils 17 are encircled, L is more than or equal to 200, the winding directions of the annular winding coils 17 of each group are the same, and an independent control system 2 and an independent power supply 3 are respectively configured; a plurality of uniformly distributed schlieren films 20 are arranged along the central annular line of the annular outer wall surface of the annular pipeline 19, and the frequency response is more than 20000 frames; a plurality of uniformly distributed cylindrical coils 18 are also arranged along the central annular line of the annular outer wall surface of the annular pipeline 19, and the central axis of each cylindrical coil 18 is positioned in the radial direction of the annular pipeline 19;
the speed measuring sensor 4, the displacement sensor 5, the temperature sensor 6 and the pressure sensor 9 are uniformly distributed along the central annular line of the annular inner wall surface of the annular pipeline 19 in a staggered manner;
the upper magnet blocks 15 are uniformly distributed in series along the central line of the annular pipeline 19 above the annular pipeline 19, the lower magnet blocks 16 which are in one-to-one correspondence with the upper magnet blocks 15 are vertically and symmetrically distributed below the annular pipeline 19, the S magnetic poles of the upper magnet blocks 15 are downward, and the N magnetic poles of the lower magnet blocks 16 are upward;
the model posture adjustment system 12, the magnet 13 and the induction coil 14 are connected to the rear of the model 11 with the advancing direction of the model 11 as the front; the model attitude adjusting system 12 comprises a front coil and a rear coil, wherein the front coil and the rear coil are consistent in winding direction, the first coil comprises an upper gravity coil 121 and a lower gravity coil 122, the second coil comprises an upper gravity coil 123 and a lower gravity coil 124, the upper coil and the lower coil of each coil are independently controlled, the distances between the coils of each group and the upper magnet block 15 and the lower magnet block 16 are adjusted by controlling the current of the upper coil and the lower coil of each coil respectively, the real-time adjustment of the flight attitude of the model 11 is realized, and the attack angle range of the model 11 is-20 degrees; the central axes of the two groups of coils point to the corresponding upper magnet block 15 and lower magnet block 16, and the generated magnetic pole directions are opposite to the magnetic pole directions of the upper magnet block 15 and the lower magnet block 16; the magnet 13 is horizontally arranged, and the magnetic pole direction of the magnet 13 is opposite to the magnetic pole direction generated by the cylindrical coil 18 corresponding to the position of the magnet 13; the induction coil 14 surrounds the pipe centerline of the annular pipe 19;
the induction coil 14, the annular winding coil 17 and the annular pipe 19 are coaxial with the central axis.
Further, the sealed chamber 10 is a movable chamber; in the test preparation, the test bed is sealed and isolated from the rest of the annular pipeline 19 to form a model preparation room; the test was carried out through the remaining part of the annular pipe 19 to form a running channel for the model 11.
The test method for simulating wind tunnel by using the annular continuous magnetic levitation track in the embodiment comprises the following steps:
s10, before a test, closing a sealing chamber 10, placing a model 11 in the sealing chamber 10 by a worker, electrifying a model posture adjusting system 12, suspending the model 11 in the sealing chamber 10, opening the sealing chamber 10, penetrating an annular pipeline 19, filling test gas into the annular pipeline 19 according to a preset gas composition, and adjusting the pressure and the temperature of the test gas to preset test conditions;
s20, in the test, grouping pulse power supply is carried out on the annular winding coil 17 through the control system 2 and the power supply 3, meanwhile, the speed measuring sensor 4 monitors the running speed of the model 11 and feeds back to the cylindrical coil 18, the vacuum system 7 and the temperature system 8, the displacement sensor 5 monitors the distance between the model 11 and the annular inner wall surface of the annular pipeline 19, and the model 11 is prevented from contacting the annular inner wall surface of the annular pipeline 19;
in the test process, the model 11 is subjected to acceleration, uniform speed or deceleration control by controlling and feeding back the current in the annular winding coil 17, so as to simulate the speed course of the actual flight orbit of the aircraft, the component adding system 1, the vacuum system 7 and the temperature system 8 synchronously regulate the gas medium, the pressure and the temperature, and simulate the atmospheric parameters of the actual flight orbit of the aircraft; the model attitude adjusting system 12 adjusts the flight attitude of the model 11 in real time by adjusting the current magnitudes of the upper winding coil and the lower winding coil of the two groups of gravity coils; after the test is completed, the annular winding coil 17 continuously decelerates the model 11 until the model 11 stops running; the speed measuring sensor 4, the displacement sensor 5, the temperature sensor 6 and the schlieren 20 on the model 11 record data in the flight course in real time;
s30, after the test, the model posture adjustment system 12 is continuously electrified, the model 11 enters the sealing chamber 10, the sealing chamber 10 is closed, the annular pipeline 19 is blocked, the sealing chamber 10 is opened for ventilation, after the ventilation is completed, workers enter the sealing chamber 10, the model 11 is taken out, and meanwhile, the rest of the annular pipeline 19 is ventilated, and after the ventilation is completed, the test is completed.
Example 1:
the radius R of the annular pipe 19 in this embodiment is 1500m, the pipe diameter of the annular pipe 19 is 3m, the total weight m of the model 11, the model posture adjustment system 12, the magnet 13 and the induction coil 14 is about 200kg, and a real flight environment with an acceleration from 0km at flying height, 0m/s at flying speed to 30km at flying height, 10 mach number at flying speed, 10 ° at attack angle, and a deceleration to 10km at flying speed of 0 at attack angle of-10 ° is simulated. The air static temperature is 227K, the static pressure is 1200Pa, the relative speed of the aircraft is 3000m/s under the flight condition of 30km in height and 10 Mach number in flight speed, and the air static temperature is 223K and the static pressure is 26500Pa under the flight condition of 10km in height; the volume of the inner cavity of the annular pipeline 19 is 2.66 multiplied by 10 5 m 3 The method comprises the steps of carrying out a first treatment on the surface of the The toroidal winding coils 17 are divided into 400 groups, l=400, and the length of each group of toroidal winding coils 17 is 23.55m;
the calculation formula of the electromagnetic force F (t) is as follows:
，
in the method, in the process of the invention,W m in order for the energy to be of a type,M i0 （i=1 to L) is the mutual inductance of the induction coil 14 and the toroidal winding coil 17,I i for the current of the induction coil 14,I 0 is the current of the toroidal winding 17.
The maximum centrifugal force calculation formula is: n=mv 2 R=1200 kN, about 120 tons. Where v is the model 11 operating speed.
The specific implementation steps of this embodiment are as follows:
s10, before a test, closing a sealing chamber 10, placing a model 11 in the sealing chamber 10 by a worker, electrifying a model posture adjusting system 12, suspending the model 11 in the sealing chamber 10, opening the sealing chamber 10, penetrating an annular pipeline 19, and filling test gas with the pressure of 96000Pa and the temperature of 300K into the annular pipeline 19 according to a preset gas composition;
s20, in the test, grouping pulse power supply is carried out on the annular winding coil 17 through the control system 2 and the power supply 3, meanwhile, the speed measuring sensor 4 monitors the running speed of the model 11 and feeds back to the cylindrical coil 18, the vacuum system 7 and the temperature system 8, the displacement sensor 5 monitors the distance between the model 11 and the annular inner wall surface of the annular pipeline 19, and the model 11 is prevented from contacting the annular inner wall surface of the annular pipeline 19;
in the acceleration phase, the annular winding coil 17 continuously accelerates the model 11, and the model posture adjustment system 12 keeps the flight attack angle of the model 11 to be 10 degrees; the vacuum system 7 and the temperature system 8 adjust the temperature and the pressure in the annular pipeline 19 in real time according to the flying speed, adjust and simulate the real-time flying environment until the flying speed reaches 30km and 3000m/s, at the moment, the static air temperature is 227K, and the static pressure is 1200Pa; in the constant speed stage, the annular winding coil 17 keeps the model 11 running at a constant speed, and the model posture adjustment system 12 is adjusted to change the attack angle from 10 degrees to 0 degrees; in the deceleration stage, the annular winding coil 17 continuously decelerates the model 11, the attack angle is changed from 0 degrees to-10 degrees, and in the deceleration process, according to feedback of the speed measurement sensor 4, air is changed from static temperature 227K and static pressure 1200Pa to static temperature 223K and static pressure 26500Pa until the model 11 stops running.
The sensors on the model 11, the speed measuring sensor 4, the displacement sensor 5, the temperature sensor 6 and the schlieren 20 record data;
s30, after the test, the model posture adjustment system 12 is continuously electrified, the model 11 enters the sealing chamber 10, the sealing chamber 10 is closed, the annular pipeline 19 is blocked, the sealing chamber 10 is opened for ventilation, after the ventilation is completed, workers enter the sealing chamber 10, the model 11 is taken out, and meanwhile, the rest of the annular pipeline 19 is ventilated, and after the ventilation is completed, the test is completed.
As shown in fig. 3, in this embodiment, each four groups of toroidal winding coils 17 form a pulse period, i represents the ith toroidal winding coil 17, at time t1, the 1 st, 2 nd, 3 rd and 4 th groups of toroidal winding coils 17 are energized, at time t2, the 2 nd, 3 rd, 4 th and 5 th groups of toroidal winding coils 17 are energized, at time t3, the 3 rd, 4 th, 5 th and 6 th groups of toroidal winding coils 17 are energized, and by pulse charging, the model 11 moves in a circle around the pipe center line of the annular pipe 19 across the 3 rd, 4 th and 5 th groups of toroidal winding coils 17, and the straight section represents the circular movement in fig. 2, due to the short movement distance, the linear speed approximates the circumferential speed.
Although embodiments of the invention have been disclosed in the foregoing description and illustrated in the drawings, it will be understood by those skilled in the art that the present invention is not limited to the specific details and illustrations of features and steps set forth herein, and that all features of the invention disclosed, or steps of the method or process, except for mutually exclusive features and/or steps, may be combined in any manner without departing from the principles of the invention.
Claims (3)
1. The annular continuous magnetic levitation track simulation wind tunnel is characterized by comprising an annular pipeline (19), wherein the radius of the annular pipeline (19) is more than or equal to 1000m, and the material is 35CrNi3MoVR; the inner cavity of the annular pipeline (19) is provided with a sealing cavity (10), a model (11) is placed in the sealing cavity (10), the model (11) adopts a real aircraft or a scaling model consistent with real aircraft materials, and the highest running speed is designed to be 3000m/s; the environment of the annular pipeline (19) is provided with a matched component adding system (1), a vacuum system (7) and a temperature system (8), the model (11) is provided with a model posture adjusting system (12), and the temperature, the pressure, the components and the flight posture of test gas in the annular pipeline (19) can be adjusted in real time according to the flight history which is simulated as required;
the annular outer wall surface of the annular pipeline (19) is surrounded by L groups of annular winding coils (17), L is more than or equal to 200, the winding directions of the groups of annular winding coils (17) are the same, and an independent control system (2) and an independent power supply (3) are respectively configured; a plurality of uniformly distributed schlieren (20) are arranged along the central annular line of the annular outer wall surface of the annular pipeline (19), and the frequency response is more than 20000 frames; a plurality of uniformly distributed cylindrical coils (18) are also arranged along the central annular line of the annular outer wall surface of the annular pipeline (19), and the central axis of each cylindrical coil (18) is positioned in the radial direction of the annular pipeline (19);
the speed measuring sensors (4), the displacement sensors (5), the temperature sensors (6) and the pressure sensors (9) are uniformly distributed along the central annular line of the annular inner wall surface of the annular pipeline (19) in a staggered manner;
the upper magnet blocks (15) which are arranged in series are uniformly distributed along the central line of the annular pipeline (19) above the annular pipeline (19), the lower magnet blocks (16) which are in one-to-one correspondence with the upper magnet blocks (15) are symmetrically distributed up and down below the annular pipeline (19), the S magnetic poles of the upper magnet blocks (15) are downward, and the N magnetic poles of the lower magnet blocks (16) are upward;
the model posture adjusting system (12), the magnet (13) and the induction coil (14) are connected behind the model (11) by taking the advancing direction of the model (11) as the front; the model attitude adjusting system (12) comprises a front coil and a rear coil, wherein the front coil and the rear coil are consistent in winding direction, the first coil comprises an upper winding coil (121) of a gravity coil I and a lower winding coil (122) of the gravity coil I, the second coil comprises an upper winding coil (123) of the gravity coil II and a lower winding coil (124) of the gravity coil II, the upper winding coil and the lower winding coil of each coil are independently controlled, the current of the upper winding coil and the current of the lower winding coil of each coil are respectively controlled, the distances between the coils of each coil and an upper magnet block (15) and a lower magnet block (16) are adjusted, the real-time adjustment of the flight attitude of the model (11) is realized, and the attack angle range of the model (11) is-20 degrees; the central axes of the two groups of coils point to the upper magnet block (15) and the lower magnet block (16) corresponding to the positions of the two groups of coils, and the generated magnetic pole directions are opposite to the magnetic pole directions of the upper magnet block (15) and the lower magnet block (16); the magnets (13) are horizontally arranged, and the magnetic pole directions of the magnets (13) are opposite to the magnetic pole directions generated by the cylindrical coils (18) corresponding to the positions of the magnets (13); the induction coil (14) surrounds the pipe centerline of the annular pipe (19);
the induction coil (14), the annular winding coil (17) and the annular pipeline (19) are coaxial with the central axis.
2. The annular continuous magnetic levitation track simulation wind tunnel according to claim 1, wherein the sealed chamber (10) is a movable chamber; when in test preparation, the test device is sealed and isolated with the rest part of the annular pipeline (19) to form a model preparation room; when the test is carried out, the test runs through the rest part of the annular pipeline (19) to form a model (11) running channel.
3. The test method of the annular continuous magnetic levitation track simulation wind tunnel is used for the annular continuous magnetic levitation track simulation wind tunnel according to any one of claims 1-2, and is characterized by comprising the following steps:
s10, before a test, closing a sealing chamber (10), placing a model (11) in the sealing chamber (10) by a worker, electrifying a model posture adjustment system (12), suspending the model (11) in the sealing chamber (10), opening the sealing chamber (10), penetrating an annular pipeline (19), filling test gas into the annular pipeline (19) according to a preset gas composition, and adjusting the pressure and the temperature of the test gas to preset test conditions;
s20, in the test, grouping pulse power supply is carried out on the annular winding coil (17) through the control system (2) and the power supply (3), meanwhile, the speed measuring sensor (4) monitors the running speed of the model (11) and feeds back the running speed to the cylindrical coil (18), the vacuum system (7) and the temperature system (8), and the displacement sensor (5) monitors the distance between the model (11) and the annular inner wall surface of the annular pipeline (19) to prevent the model (11) from contacting the annular inner wall surface of the annular pipeline (19);
in the test process, the model (11) is subjected to acceleration, uniform speed or deceleration control by controlling and feeding back the current in the annular winding coil (17), the speed history of the actual flight orbit of the aircraft is simulated, the component adding system (1), the vacuum system (7) and the temperature system (8) synchronously regulate the gas medium, the pressure and the temperature, and the atmospheric parameters of the actual flight orbit of the aircraft are simulated; the model attitude adjusting system (12) adjusts the flight attitude of the model (11) in real time by adjusting the current magnitudes of an upper winding coil and a lower winding coil of the two groups of gravity coils; after the test is completed, the annular winding coil (17) continuously decelerates the model (11) until the model (11) stops running; the speed measuring sensor (4), the displacement sensor (5), the temperature sensor (6) and the schlieren (20) on the model (11) record data in the flight course in real time;
s30, after the test, the model posture adjustment system (12) is continuously electrified, the model (11) enters the sealing chamber (10), the sealing chamber (10) is closed, the annular pipeline (19) is blocked, the sealing chamber (10) is opened for ventilation, after the ventilation is completed, workers enter the sealing chamber (10), the model (11) is taken out, and meanwhile, the rest part of the annular pipeline (19) is ventilated, and after the ventilation is completed, the test is completed.
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