A detection device for testing an aircraft

Abstract

This application relates to a testing device for testing aircraft, including a machine base, a wind tunnel shell, a motor located at one end of the wind tunnel shell, and fan blades disposed on the motor shaft. The wind tunnel shell includes an inner shell with several through holes on its radial inner wall. The machine base is provided with a placement platform for placing the aircraft, which is located inside the inner shell. The fan blades can be driven by the motor to generate airflow inside the inner shell. One axial end of the inner shell is the air inlet, and the other axial end is the air outlet. The through holes are distributed between the air inlet and the air outlet. The fan blades are located at the air outlet, and the placement platform is located between the air inlet and the air outlet. Air outside the inner shell can enter the inner shell from the air inlet and the through holes due to the action of the fan blades. The airflow direction at the air inlet is different from the airflow direction at the through holes. This application has the function of testing the flight capability of an aircraft under the influence of airflow with different directions.

Description

Technical Field

[0001] This application relates to the field of aircraft testing technology, and in particular to a testing device for testing aircraft. Background Technology

[0002] In daily life, with the advancement of technology, various small aircraft, such as drones, are widely used in various industries and fields. In order to enable aircraft to better cope with various possible flight conditions, environmental simulation tests are conducted on the flight capabilities of aircraft during the production process.

[0003] A small wind tunnel testing device is mainly used to test the wind resistance of drones during flight. It includes a test bench with a wind tunnel shell and a platform for placing the drone inside the wind tunnel shell. A motor is arranged at one end of the wind tunnel shell, and a fan blade is fixed on the motor shaft. During the test, the drone is placed on the platform, then the drone is started and suspended in the air. The motor is then started to make the fan blade rotate and generate airflow. The flight parameters of the drone under airflow disturbance are then observed.

[0004] Regarding the above solution, the inventors believe that the airflow generated by the fan blades is relatively uniform, making it difficult to test the flight performance of the aircraft under different airflow directions. Summary of the Invention

[0005] To test the flight performance of aircraft under different wind conditions, this application provides a testing device for testing aircraft.

[0006] The testing device for testing aircraft provided in this application adopts the following technical solution.

[0007] A testing device for testing aircraft includes a platform, a wind tunnel shell, a motor located at one end of the wind tunnel shell, and fan blades disposed on the motor shaft. The wind tunnel shell includes an inner shell with several through holes on its radial inner wall. The platform is provided with a placement platform for placing the aircraft, and the placement platform is located inside the inner shell. The fan blades can be driven by the motor to generate airflow inside the inner shell. One axial end of the inner shell is an air inlet, and the other axial end is an air outlet. The through holes are distributed between the air inlet and the air outlet. The fan blades are located at the air outlet, and the placement platform is located between the air inlet and the air outlet. Air from outside the inner shell can enter the inner shell from the air inlet and the through holes under the action of the fan blades. The airflow direction at the air inlet is different from the airflow direction at the through holes.

[0008] Optionally, the placement platform includes a placement plate for placing the aircraft, the placement plate being located within the through-hole area.

[0009] Optionally, the machine base further includes a support plate, a slide rod, and a movable sleeve. The support plate is fixed to the machine base. One end of the slide rod is slidably connected to the support plate, and a baffle is fixed to the other end of the slide rod. The movable sleeve is movably sleeved on the slide rod. A retaining ring is fixed to the end of the movable sleeve facing the machine base. The inner diameter of the retaining ring is smaller than the diameter of the baffle. There is a gap between the inner wall of the retaining ring and the side wall of the slide rod. A baffle is fixed to the end of the movable sleeve away from the machine base. There is a gap between the inner wall of the movable sleeve and the side wall of the slide rod. The baffle is located between the retaining ring and the baffle. The placement plate is fixedly disposed at the end of the baffle away from the machine base, and the placement plate is fixed to the aircraft.

[0010] Optionally, the slide bar can slide away from the support plate.

[0011] Optionally, the outer wall of the inner shell is fitted with an outer shell, the outer shell is slidably connected to the machine base, and the outer shell can move along the axial direction of the inner shell to block or disengage from the through hole.

[0012] Optionally, the bearing plate has a first sliding groove, the sliding rod is slidably disposed in the first sliding groove, the side wall of the first sliding groove has an opening, a first wedge plate is radially disposed in the opening along the inner shell, the sliding rod can abut or disengage from the inclined surface of the first wedge plate, the machine base has a second sliding groove, a first connecting rod is disposed between the second sliding groove and the first wedge plate, one end of the first connecting rod is fixedly connected to the first wedge plate, the other end of the first connecting rod is slidably disposed in the second sliding groove, the machine base is movably disposed with a second wedge plate, a second connecting rod is disposed between the second wedge plate and the first connecting rod, the second connecting rod is radially disposed in the second sliding groove along the inner shell, one end of the second connecting rod is fixed to the first connecting rod, the other end of the second connecting rod is fixed to the second wedge plate, and the outer shell can abut against the inclined surface of the second wedge plate.

[0013] Optionally, the machine base is provided with a first return spring, one end of which is fixed to the outer shell and the other end of which is fixed to the machine base. The first return spring can drive the outer shell to move and cover the through hole. A second return spring is provided on the inner wall of the second slide groove, one end of which is fixed to the inner wall of the second slide groove and the other end of which is fixed to the second connecting rod. The second return spring can drive the second connecting rod to move radially along the inner shell and approach the bearing plate.

[0014] Optionally, the machine tool has a limiting groove, a limiting rod is provided in the limiting groove, and a driving spring is provided between the limiting rod and the bottom of the limiting groove. The driving spring can drive the limiting rod to move and extend out of the limiting groove. The limiting groove is located on the moving path of the housing, and the housing can open or close the opening of the limiting groove.

[0015] Optionally, the through hole is funnel-shaped, and the diameter of the through hole at the end near the machine base is smaller than the diameter of the through hole at the end away from the machine base.

[0016] Optionally, an indicator light is provided on the outer wall of the movable sleeve, and a spring button switch is fixed at the end of the baffle facing the retaining ring. The spring button switch is electrically connected to the indicator light. The spring button switch can be opened under the squeezing action of the baffle and the retaining ring. When the spring button switch is opened, the indicator light is lit.

[0017] In summary, this application includes at least one of the following beneficial effects:

[0018] When the fan blades rotate, they generate suction on the inner shell. Airflow enters the inner shell from the air inlet and the through hole respectively. The airflow from the air inlet acts on the aircraft along the axial direction of the inner shell, while the airflow from the through hole acts on the aircraft along the radial direction of the inner shell. This makes it easy to test the flight status of the aircraft under airflow interference in different directions.

[0019] When only one wind direction flight condition needs to be tested, the outer shell covers the inner shell, thus blocking the through-holes. At this time, the aircraft is only affected by the airflow entering from the air inlet. When multiple wind directions need to be tested, the kinetic energy output of the aircraft is reduced, causing the aircraft to move under the influence of airflow. At this time, the aircraft moves the slide rod through the placement plate, causing the slide rod to press the first wedge plate along the inclined surface of the first wedge plate. The first wedge plate drives the second connecting rod to move radially away from the support plate along the inner shell through the first connecting rod. The second connecting rod drives the second wedge plate to move radially away from the outer shell along the inner shell. At this time, the outer shell is not restricted by the second wedge plate and moves under the action of the first return spring, thereby gradually opening the various through-holes of the inner shell, causing the aircraft to be affected by the airflow from the through-holes, thus providing multiple options for the testing process.

[0020] When testing the aircraft's load-bearing flight capability, the aircraft's power output is reduced, causing airflow to propel the aircraft and move the sliding rod away from the support plate. Under the influence of gravity, the sliding rod slides down, causing the baffle to move towards the retaining ring. This compresses the spring button switch, activating the indicator light. The on / off status of the indicator light indicates whether the aircraft can fly normally under load. When the indicator light is on, it proves that the aircraft can hover normally. When the indicator light is off, it proves that the aircraft has descended, causing the sliding rod to contact the platform or the ground, thus moving the baffle away from the retaining ring and deactivating the spring button switch. This allows for easier observation by the test personnel during further testing of the aircraft's load-bearing flight capability. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application;

[0022] Figure 2 This is a schematic diagram of the placement platform structure in this embodiment;

[0023] Figure 3 This is a schematic diagram of the entire embodiment from other angles.

[0024] Explanation of reference numerals in the attached drawings: 1. Machine base; 2. Air duct shell; 201. Inner shell; 202. Outer shell; 3. Fan blade; 4. Motor; 5. Air inlet; 6. Air outlet; 7. Through hole; 8. Placement platform; 801. Placement plate; 802. Support plate; 803. Slide rod; 804. Movable sleeve; 9. Retaining ring; 10. Baffle plate; 11. Baffle; 12. First wedge plate; 13. Second wedge plate; 14. First connecting rod; 15. Second connecting rod; 16. First return spring; 17. Limiting rod; 18. Indicator light; 19. Spring button switch; 20. Through port. Detailed Implementation

[0025] The following is in conjunction with the appendix Figure 1-3 The present application will be further described with reference to specific embodiments:

[0026] First, it should be noted that in the description of this application, the use of directional terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" indicates the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are used solely for descriptive purposes and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the use of numerical quantifiers such as "first," "second," and "third" is for descriptive purposes only and should not be construed as indicating or implying relative importance. Additionally, in this application, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, interference fits, transition fits, or integral connections; they can refer to direct connections or indirect connections through an intermediate medium. Therefore, those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0027] This application discloses a testing device for testing aircraft.

[0028] A testing device for testing aircraft, as shown in the reference. Figure 1 The system includes a base 1, a wind tunnel housing 2, a motor 4 located at one end of the wind tunnel housing 2, and fan blades 3 mounted on the shaft of the motor 4. The wind tunnel housing 2 includes an inner shell 201, with several through holes 7 on its radial inner wall. The base 1 is equipped with a placement platform 8 for placing the aircraft. The placement platform 8 is located inside the inner shell 201. The fan blades 3 are driven by the motor 4 to generate airflow inside the inner shell 201. One axial end of the inner shell 201 is the air inlet 5, and the other axial end is the air outlet 6. The through holes 7 are distributed between the air inlet 5 and the air outlet 6. The fan blades 3 are located at the air outlet 6, and the placement platform 8 is located between the air inlet 5 and the air outlet 6. Between the air inlet 6 and the air outlet 6, the air outside the inner shell 201 can enter the inner shell 201 from the air inlet 5 and the through hole 7 under the action of the fan blade 3. The airflow direction at the air inlet 5 is different from that at the through hole 7. When the fan blade 3 rotates, the fan blade 3 generates suction force on the inner shell 201. The airflow enters the inner shell 201 from the air inlet 5 and the through hole 7 respectively. The airflow entering from the air inlet 5 acts on the aircraft along the axial direction of the inner shell 201, and the airflow entering the inner shell 201 from the through hole 7 acts on the aircraft along the radial direction of the inner shell 201. This makes it convenient to test the flight status of the aircraft under the interference of airflow in different directions.

[0029] Reference Figures 1-3 The placement platform 8 includes a placement plate 801 for placing the aircraft. The placement plate 801 is located within the through hole 7 area, which reduces the probability of placing the aircraft outside the area where the airflow cannot reach when placing the aircraft.

[0030] Reference Figures 1-3 The machine base 1 also includes a support plate 802, a slide rod 803, and a movable sleeve 804. The support plate 802 is fixed to the machine base 1. One end of the slide rod 803 is slidably connected to the support plate 802, and a baffle 10 is fixed to the other end of the slide rod 803. The movable sleeve 804 is movably sleeved on the slide rod 803. A retaining ring 9 is fixedly provided at the end of the movable sleeve 804 facing the machine base 1. The inner diameter of the retaining ring 9 is smaller than the diameter of the baffle 10. There is a gap between the inner wall of the retaining ring 9 and the side wall of the slide rod 803. A baffle 11 is fixedly provided at the end of the movable sleeve 804 away from the machine base 1. The inner wall of the movable sleeve 804 is close to the side wall of the slide rod 803. There is a gap between the three side walls. The baffle 10 is located between the baffle ring 9 and the baffle plate 11. The placement plate 801 is fixedly set on the baffle plate 11 at the end away from the machine base 1. The placement plate 801 is fixed to the aircraft. During the test, the aircraft is fixed to the placement plate 801. Then the motor 4 is started to make the fan blade 3 rotate to generate airflow and the aircraft rises. At this time, the placement plate 801 drives the movable sleeve 804 to move until the baffle 10 and the baffle ring 9 abut, which limits the aircraft from continuing to rise and reduces the probability that the aircraft will hit the outer wall of the inner shell 201 due to excessive initial kinetic energy.

[0031] Reference Figures 1-3 The slide bar 803 can slide away from the support plate 802. When it is necessary to test the aircraft's load-bearing flight capability under airflow interference, the tester actively reduces the aircraft's output kinetic energy so that the thrust generated by the airflow is greater than the aircraft's power. At this time, the aircraft moves along the axial direction of the inner shell 201 under the action of the airflow, thereby driving the slide bar 803 to move away from the support plate 802. At this time, the placement plate 801, the movable sleeve 804, and the slide bar 803 become the load of the aircraft, which facilitates the testing of the aircraft's load-bearing capability.

[0032] Reference Figures 1-3 The outer wall of the inner shell 201 is fitted with an outer shell 202, which is slidably connected to the machine tool 1. The outer shell 202 can move along the axial direction of the inner shell 201 to block or disengage from the through hole 7. When it is necessary to measure the flight capability of the aircraft under different airflow interference, the outer shell 202 is driven to move, thereby opening the through hole 7. When it is only necessary to measure airflow interference in one direction, the outer shell 202 closes the through hole 7, which facilitates providing staff with a variety of test scenarios.

[0033] Reference Figures 1-3The bearing plate 802 has a first sliding groove, and the sliding rod 803 is slidably disposed in the first sliding groove. The side wall of the first sliding groove has an opening 20, and a first wedge plate 12 is radially movable within the opening 20 along the inner shell 201. The sliding rod 803 can abut or disengage from the inclined surface of the first wedge plate 12. The machine base 1 has a second sliding groove, and a first connecting rod 14 is disposed between the second sliding groove and the first wedge plate 12. One end of the first connecting rod 14 is fixedly connected to the first wedge plate 12, and the other end of the first connecting rod 14 is slidably disposed in the second sliding groove. The machine base 1 is movably disposed with a second wedge plate 13, and a second connecting rod 15 is disposed between the second wedge plate 13 and the first connecting rod 14. The second connecting rod 15 is radially movable along the inner shell 201 and disposed in the second sliding groove. One end of the second connecting rod 15 is fixed to the first connecting rod 14, and the other end of the second connecting rod 15 is fixed to the second wedge plate 13. The outer shell 20... 2. It can abut against the inclined surface of the second wedge plate 13. When only one wind direction flight condition needs to be tested, the outer shell 202 covers the inner shell 201, thereby blocking the through hole 7. At this time, the aircraft is only affected by the airflow entering from the air inlet 5. When multiple wind directions flight conditions need to be tested, the kinetic energy output of the aircraft is reduced, so that the aircraft is affected by the airflow and moves. At this time, the aircraft drives the slide bar 803 to move through the placement plate 801, so that the slide bar 803 presses the first wedge plate 12 along the inclined surface of the first wedge plate 12 and moves the first wedge plate 12. The first wedge plate 12 drives the second connecting rod 15 to move radially along the inner shell 201 away from the bearing plate 802 through the first connecting rod 14. The second connecting rod 15 drives the second wedge plate 13 to move radially along the inner shell 201 away from the outer shell 202. At this time, the outer shell 202 is not restricted by the second wedge plate 13. Then, the outer shell 202 is moved to open the through hole 7, which is convenient and quick.

[0034] Reference Figures 1-3The machine base 1 is equipped with a first return spring 16. One end of the first return spring 16 is fixed to the outer shell 202, and the other end is fixed to the machine base 1. The first return spring 16 can drive the outer shell 202 to move and block the through hole 7. A second return spring is provided on the inner wall of the second slide groove. One end of the second return spring is fixed to the inner wall of the second slide groove, and the other end is fixed to the second connecting rod 15. The second return spring can drive the second connecting rod 15 to move radially along the inner shell 201 and approach the support plate 802. The elastic force of the first return spring 16 is less than the elastic force of the second return spring, and the elastic force of the second return spring is less than the wind force of the fan blade 3. When it is necessary to test flight under different wind directions... When the aircraft is in flight, the aircraft drives the slide bar 803 to press the first wedge plate 12. The first wedge plate 12 compresses the second return spring, thereby pushing the second wedge plate 13 to move radially away from the support plate 802 along the outer shell 202. At this time, the outer shell 202 is not restricted by the inclined surface of the second wedge plate 13. Then the first return spring 16 pulls the outer shell 202 to move axially, thereby opening the through hole 7. After the test is completed, the slide bar 803 slides away from the inclined surface of the first wedge plate 12. The second return spring pulls the second connecting rod 15 to slide the outer shell 202 radially closer to the support plate 802. The second wedge plate 13 moves by pressing the outer shell 202 through the inclined surface to cover the through hole 7 again, which is convenient and quick.

[0035] Reference Figures 1-3 The machine tool 1 has a limiting groove, and a limiting rod 17 is installed in the limiting groove. A driving spring is installed between the limiting rod 17 and the bottom of the limiting groove. The driving spring can drive the limiting rod 17 to move and extend out of the limiting groove. The limiting groove is located on the moving path of the outer shell 202. The outer shell 202 can open or close the opening of the limiting groove. When the outer shell 202 moves to open the through hole 7, the opening of the limiting groove is not covered by the outer shell 202. Then the limiting rod 17 extends out under the action of the driving spring and abuts against the end of the outer shell 202 that is axially away from the first return spring 16. This restricts and prevents the outer shell 202 from closing the through hole 7 again when the slide rod 803 is disengaged from the support plate 802. This facilitates the testing of the aircraft under different wind directions when the aircraft is under load.

[0036] Reference Figures 1-3 The through hole 7 is funnel-shaped. The diameter of the through hole 7 at the end near the machine base 1 is smaller than the diameter at the end away from the machine base 1, which facilitates the acceleration of airflow from the through hole 7 into the inner shell 201, and can generate a greater force.

[0037] Reference Figures 1-3An indicator light 18 is provided on the outer wall of the movable sleeve 804. A spring-loaded push-button switch 19 is fixed to the end of the baffle 10 facing the retaining ring 9. The spring-loaded push-button switch 19 is electrically connected to the indicator light 18. The spring-loaded push-button switch 19 can be opened under the pressure of the baffle 10 and the retaining ring 9. When the spring-loaded push-button switch 19 is opened, the indicator light 18 is lit. When it is necessary to test the load-bearing flight capability of the aircraft, the power output of the aircraft is reduced, causing the airflow to blow the aircraft and move it, thereby driving the slide bar 803 to move away from the support plate 802. At this time, under the influence of gravity, the slide bar 803... As the aircraft descends, the baffle 10 moves toward the retaining ring 9, thereby squeezing the spring button switch 19 and turning on the indicator light 18. The presence or absence of the indicator light 18 indicates whether the aircraft can hover normally under load. When the indicator light 18 is on, it proves that the aircraft can hover normally. When the indicator light 18 is off, it proves that the aircraft descends, causing the slide bar 803 to contact the platform 1 or the ground, thereby moving the baffle 10 away from the retaining ring 9 and turning off the spring button switch. This allows for further testing of the aircraft's load-bearing flight capability and facilitates observation by the test personnel.

[0038] It should be noted that the above embodiments are only used to illustrate this application and are not intended to limit the technical solutions described in this application. Although this specification has described this application in detail with reference to the above embodiments, those skilled in the art should understand that they can still make modifications or equivalent substitutions to this application. All technical solutions and improvements that do not depart from the spirit and scope of this application should be covered within the scope of the claims of this application.

Claims

1. A testing device for testing aircraft, comprising a base (1), a wind tunnel housing (2), a motor (4) located at one end of the wind tunnel housing (2), and fan blades (3) disposed on the shaft of the motor (4), characterized in that: The duct shell (2) includes an inner shell (201), the inner shell (201) having several through holes (7) on its radial inner wall. The machine base (1) is provided with a placement platform (8) for placing the aircraft. The placement platform (8) is located inside the inner shell (201). The fan blade (3) can be driven by the motor (4) to generate airflow inside the inner shell (201). One axial end of the inner shell (201) is the air inlet (5), and the other axial end of the inner shell (201) is the air outlet (6). The through holes (7) are distributed between the air inlet (5) and the air outlet (6). The fan blade (3) is located at the air outlet (6). The placement platform (8) is located between the air inlet (5) and the air outlet (6). External air can enter the inner shell (201) from the air inlet (5) and the through hole (7) by the action of the fan blade (3). The airflow direction at the air inlet (5) is different from the airflow direction at the through hole (7). The outer wall of the inner shell (201) is fitted with an outer shell (202). The outer shell (202) is slidably connected to the machine base (1). The outer shell (202) can move along the axial direction of the inner shell (201) to block or detach from the through hole (7). The machine base (1) also includes a support plate. (802) A sliding rod (803) is provided on the bearing plate (802). The sliding rod (803) is slidably disposed in the first sliding groove. The side wall of the first sliding groove is provided with an opening (20). A first wedge plate (12) is provided in the opening (20) and moves radially along the inner shell (201). The sliding rod (803) can abut or disengage from the inclined surface of the first wedge plate (12). The machine base (1) is provided with a second sliding groove. A first connecting rod (14) is provided between the second sliding groove and the first wedge plate (12). One end of the first connecting rod (14) is connected to the first wedge plate (12). The first connecting rod (14) is fixedly connected, and the other end of the first connecting rod (14) is slidably disposed in the second sliding groove. The machine base (1) is movably disposed with a second wedge plate (13). A second connecting rod (15) is disposed between the second wedge plate (13) and the first connecting rod (14). The second connecting rod (15) is radially moved along the inner shell (201) and disposed in the second sliding groove. One end of the second connecting rod (15) is fixed to the first connecting rod (14), and the other end of the second connecting rod (15) is fixed to the second wedge plate (13). The outer shell (202) can abut against the inclined surface of the second wedge plate (13).

2. The testing device for testing aircraft according to claim 1, characterized in that: The placement platform (8) includes a placement plate (801) for placing the aircraft, and the placement plate (801) is located in the area of ​​the through hole (7).

3. The testing device for testing aircraft according to claim 2, characterized in that: The machine base (1) further includes a support plate (802), a slide rod (803), and a movable sleeve (804). The support plate (802) is fixed to the machine base (1). One end of the slide rod (803) is slidably connected to the support plate (802), and a baffle plate (10) is fixed to the other end of the slide rod (803). The movable sleeve (804) is movably sleeved on the slide rod (803). A retaining ring (9) is fixed to one end of the movable sleeve (804) facing the machine base (1). The inner diameter of the retaining ring (9) is smaller than that of the baffle plate (804). 10) Diameter, there is a gap between the inner wall of the retaining ring (9) and the side wall of the slide rod (803), a baffle (11) is fixedly provided at one end of the movable sleeve (804) away from the machine base (1), there is a gap between the inner wall of the movable sleeve (804) and the side wall of the slide rod (803), the baffle (10) is located between the retaining ring (9) and the baffle (11), the placement plate (801) is fixedly set at one end of the baffle (11) away from the machine base (1), and the placement plate (801) is fixed to the aircraft.

4. The testing device for testing aircraft according to claim 3, characterized in that: The slide bar (803) can slide away from the support plate (802).

5. A testing device for testing aircraft according to claim 4, characterized in that: The machine base (1) is provided with a first return spring (16), one end of the first return spring (16) is fixed to the outer shell (202), and the other end of the first return spring (16) is fixed to the machine base (1). The first return spring (16) can drive the outer shell (202) to move and cover the through hole (7). The inner wall of the second slide groove is provided with a second return spring, one end of the second return spring is fixed to the inner wall of the second slide groove, and the other end of the second return spring is fixed to the second connecting rod (15). The second return spring can drive the second connecting rod (15) to move radially along the inner shell (201) and approach the support plate (802).

6. A testing device for testing aircraft according to claim 5, characterized in that: The machine base (1) has a limiting groove, and a limiting rod (17) is provided in the limiting groove. A driving spring is provided between the limiting rod (17) and the bottom of the limiting groove. The driving spring can drive the limiting rod (17) to move and extend out of the limiting groove. The limiting groove is located on the moving path of the housing (202). The housing (202) can open or close the opening of the limiting groove. The limiting rod (17) can abut against the end of the housing (202) that is axially away from the fan blade (3).

7. The testing device for testing aircraft according to claim 1, characterized in that: The through hole (7) is funnel-shaped, and the diameter of the through hole (7) at the end near the machine base (1) is smaller than the diameter of the through hole (7) at the end away from the machine base (1).

8. A testing device for testing aircraft according to claim 3, characterized in that: An indicator light (18) is provided on the outer wall of the movable sleeve (804). A spring button switch (19) is fixed on one end of the baffle (10) facing the retaining ring (9). The spring button switch (19) is electrically connected to the indicator light (18). The spring button switch (19) can be opened under the squeezing action of the baffle (10) and the retaining ring (9). When the spring button switch (19) is opened, the indicator light (18) lights up.

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