Aircraft power traction and performance test stand

Abstract

The application discloses an aircraft power traction and performance test pile, which comprises a base, a supporting column, an angle sensor, a rotating speed sensor and a controller; the supporting column is fixedly installed on the base; the angle sensor is rotatably installed on the end of the supporting column far from the base through a slip ring; the input end of the angle sensor is connected with a traction line of the aircraft; the angle sensor measures the included angle between the traction line and the supporting column; the angle sensor is electrically connected with the controller; the rotating speed sensor is installed on the slip ring; the rotating speed sensor measures the rotating angular velocity of the slip ring when rotating one round around the supporting column; and the rotating speed sensor is electrically connected with the controller. The aircraft power traction and performance test pile can be used for flight test indoors without being limited by the legal regulations of outdoor aircraft flight test, and can mobilize the learning interest of students and exercise the practical ability, cooperative exploration ability and innovative practical ability of the students.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to an aircraft power traction and performance testing pile. Background Technology

[0002] Most existing aviation science popularization activities involve purchasing ready-made model aircraft kits for students to assemble and test-fly. Students cannot design and build an aircraft themselves to directly explore these issues. Even if students design and build a model aircraft and install a power system, a professional pilot is needed to remotely control it, preventing students from experiencing the joy of flight firsthand. Furthermore, with the rapid development of drones, urban airspace environments are facing increasingly complex safety hazards, and many cities have implemented long-term no-fly zones. This results in situations where students build aircraft models but have nowhere to fly them, making it impossible to test the performance of their designed aircraft.

[0003] Therefore, designing a performance test piling system that allows students to conduct flight tests on aircraft indoors after building their models and obtain feedback is one of the urgent problems to be solved in this field. Summary of the Invention

[0004] The purpose of this invention is to provide a test pile for aircraft power traction and performance, which overcomes the shortcomings of the existing technology. It can be used for test flights indoors without being restricted by laws and regulations on outdoor aircraft test flights, thereby stimulating students' learning interest and developing their hands-on skills, collaborative inquiry skills, and innovative practical abilities.

[0005] This invention provides a test pile for aircraft power traction and performance, including a base, a support column, an angle sensor, a speed sensor, and a controller;

[0006] The support column is fixedly installed on the base;

[0007] The angle sensor is rotatably mounted on the end of the support column away from the base via a slip ring. The input end of the angle sensor is connected to the traction line of the aircraft. The angle sensor measures the angle between the traction line and the support column. The angle sensor is electrically connected to the controller.

[0008] The speed sensor is mounted on the slip ring; the speed sensor measures the rotational angular velocity of the slip ring per revolution around the support column, and the speed sensor is electrically connected to the controller.

[0009] In the aircraft power traction and performance test pile described above, preferably, the slip ring includes a fixed slip ring and a movable slip ring, the fixed slip ring being fixedly connected to the support column; the angle sensor is mounted on the movable slip ring of the slip ring.

[0010] In the aircraft power traction and performance test pile described above, preferably, the rotation speed sensor is a laser rotation speed sensor, and the metal target of the laser rotation speed sensor is mounted on the support column below the moving slip ring.

[0011] In the aforementioned aircraft power traction and performance testing pile, preferably, a mounting plate is fixedly installed on the outer side wall of the moving slip ring, the mounting plate is vertically arranged, the angle sensor is fixedly installed on the mounting plate, and the input end of the angle sensor passes through the mounting plate and is connected to an adapter; the traction line is connected to the adapter.

[0012] The aircraft power traction and performance test pile described above preferably includes an upper cover, which is fixedly connected to the moving slip ring, and the angle sensor and the speed sensor are both located inside the upper cover; the upper cover has a clearance hole for the traction line to pass through.

[0013] In the aircraft power traction and performance test pile described above, preferably, a support arm is fixedly provided above the moving slip ring, and the upper cover is fixedly connected to the moving slip ring through the support arm.

[0014] In the aircraft power traction and performance test pile described above, preferably, a lower cover is fixedly installed on the support column, the lower cover is located below the moving slip ring, the opening of the lower cover is opposite to the opening of the upper cover, and the upper cover and the lower cover form a spherical structure.

[0015] As described above, in a powered traction and performance testing pile for an aircraft, preferably, the controller calculates the aircraft's flight altitude based on the angle between the traction line and the support column, using the following formula:

[0016] When α≤90°, h=h0-L cosα;

[0017] When α > 90°, h = h0 + L cos(180° - α); where h is the altitude of the aircraft, h0 is the height of the test pile, L is the length of the traction line, and α is the angle between the traction line and the support column.

[0018] The controller calculates the flight speed of the aircraft based on the rotational angular velocity of the slip ring per revolution around the support column. The calculation formula is: V = r·L·sinα, where V is the rotational velocity of the aircraft per revolution around the support column, L is the length of the traction line, r is the average angular velocity of the slip ring per revolution around the support column, and α is the angle between the traction line and the support column.

[0019] In the aircraft power traction and performance test pile described above, preferably, the controller is installed inside the base, the controller is electrically connected to a data acquisition module installed inside the base, the data acquisition module is electrically connected to the angle sensor and the rotation speed sensor respectively; the controller is electrically connected to a display.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. This invention sets up a support column, an angle sensor, a speed sensor, and a controller. The angle sensor and speed sensor are rotatably mounted on the support column via a slip ring. The input end of the angle sensor is connected to the traction line of the aircraft. When the aircraft flies around the support column, it drives the slip ring to rotate. The controller can quickly determine the flight altitude and flight speed of the aircraft based on the measurement values ​​of the angle sensor and speed sensor. This allows students to conduct test flights of the aircraft indoors after building the model and obtain teaching feedback.

[0022] 2. This invention is not subject to the laws and regulations on outdoor aircraft test flights, and test flights can be conducted indoors, which stimulates students' learning interest and helps them develop their hands-on skills, collaborative inquiry skills, and innovative practical abilities. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 This is a schematic diagram of the installation structure of the moving slip ring, angle sensor, speed sensor and support column of the present invention;

[0025] Figure 3 This is a schematic diagram illustrating the principle of calculating an aircraft's flight altitude.

[0026] Explanation of reference numerals in the attached figures:

[0027] 1-Base, 2-Support column, 3-Angle sensor, 4-Speed ​​sensor, 5-Traction line, 6-Moving slip ring, 7-Metal target, 8-Lower cover, 9-Mounting plate, 10-Adapter, 11-Upper cover, 1101-Allowing hole, 12-Support arm. Detailed Implementation

[0028] The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0029] Embodiments of the present invention: such as Figures 1-2As shown, this invention proposes a test pile for aircraft dynamic traction and performance, including a support column 2, which is vertically fixedly installed on a base 1. The cross-section of the support column 2 is shown. A slip ring is rotatably mounted on the top of the support column 2, and an angle sensor 3 and a speed sensor 4 are fixedly mounted on the slip ring. Thus, when the slip ring rotates around the support column 2, the angle sensor 3 and the speed sensor 4 also rotate with the slip ring.

[0030] The input terminal of angle sensor 3 is connected to the traction line 5 of the aircraft. Angle sensor 3 measures the angle between traction line 5 and support column 2. Angle sensor 3 is electrically connected to a controller. Angle sensor 3, speed sensor 4, and controller are all electrically connected to a power supply, which supplies power to angle sensor 3, speed sensor 4, and controller.

[0031] Angle sensor 3 transmits the collected data to the controller, which then calculates the aircraft's altitude based on the data.

[0032] The rotational speed sensor 4 measures the angular velocity of the slip ring per revolution around the support column 2. The rotational speed sensor 4 is also electrically connected to the controller, transmitting the collected values ​​to the controller, which then calculates the aircraft's flight speed. For easy observation, the controller can be electrically connected to the input of a display, allowing the calculated flight altitude and speed values ​​to be displayed on the screen.

[0033] See Figure 3 As shown, the controller calculates the aircraft's altitude based on the angle between the traction line 5 and the support column 2, using the following formula:

[0034] When α≤90°, h=h0-L cosα;

[0035] When α > 90°, h = h0 + L cos(180° - α); where h is the altitude of the aircraft, h0 is the height of the test pile, L is the length of the traction line 5, and α is the angle between the traction line 5 and the support column 2.

[0036] The controller calculates the aircraft's flight speed based on the rotational angular velocity of the slip ring per revolution around the support column 2. The calculation formula is: V = r·L·sinα, where V is the rotational velocity of the aircraft per revolution around the support column 2, L is the length of the traction line 5, r is the average angular velocity of the slip ring per revolution around the support column 2, and α is the angle between the traction line 5 and the support column 2.

[0037] To reduce errors, the aircraft is placed on the ground and connected to traction line 5. When traction line 5 hangs down parallel to support column 2, the initial value measured by the angle sensor is α0. The real-time angle measured during flight is α0. cThen the angle α between the traction line 5 and the support column 2 is α = α c -α0.

[0038] In one implementation, the controller is installed inside the base 1 and is electrically connected to the data acquisition module installed inside the base 1. The data acquisition module is electrically connected to the angle sensor 3 and the speed sensor 4, respectively. The data acquisition module is also electrically connected to a power supply, which can be a lithium battery installed inside the base 1 or an external power source. The aircraft's power supply is controlled by the remote controller via a circuit board inside the aircraft. When the remote controller button is continuously pressed, the circuit board continuously supplies power to the aircraft; when the remote controller button is released, the aircraft is powered off. The aircraft's power supply can be located separately inside the aircraft or share a power supply with the speed sensor and angle sensor 3.

[0039] After the aircraft starts, it rolls and rotates around support column 2 for takeoff and flight. Simultaneously, the slip ring rotates via traction cable 5, causing angle sensor 3 and speed sensor 4 mounted on the slip ring to rotate together. The data acquisition module collects the values ​​from angle sensor 3 and speed sensor 4 and transmits these values ​​to the controller. The controller calculates the aircraft's altitude and speed based on the obtained values ​​and transmits the calculated values ​​to the display. Data can be transmitted between the controller and the display via a wireless communication module.

[0040] In one embodiment, the slip ring includes a fixed slip ring and a moving slip ring 6. The moving slip ring 6 has a power distribution function, which can supply power and transmit signals to the angle sensor 3 and the speed sensor 4. The fixed slip ring is fixedly connected to the support column 2. The angle sensor 3 is installed on the moving slip ring 6 of the slip ring.

[0041] The speed sensor 4 is a laser speed sensor, and the metal target 7 of the laser speed sensor is mounted on the support column 2 below the moving slip ring 6. The laser speed sensor is a diffuse reflection, NPN normally open type. It will turn on when it scans the metal target 7 during the rotation of the moving slip ring 6. The average rotational angular velocity (unit: radians) of each rotation can be measured.

[0042] Preferably, a mounting plate 9 is fixedly installed on the outer side wall of the movable slip ring 6. The mounting plate 9 is vertically arranged, that is, arranged along the center line direction of the movable slip ring 6. The angle sensor 3 is fixedly installed on the mounting plate 9. The input end of the angle sensor 3 passes through the mounting plate 9 and is connected to an adapter 10. Specifically, the housing of the angle sensor 3 is fixedly installed on the mounting plate 9 by bolts. The input end of the angle sensor 3 passes through the mounting plate 9 and is rotatably connected to the mounting plate 9. The adapter 10 is fixedly installed on the input end of the angle sensor 3. The traction line 5 is connected to the adapter 10.

[0043] To reduce dust and external damage to the angle sensor 3 and speed sensor 4, a mounting cover can be used. The cover includes an upper cover 11 and a lower cover 8. Specifically, the upper cover 11 is fixedly connected to the moving slip ring 6, and both the angle sensor 3 and speed sensor 4 are located inside the upper cover 11. The upper cover 11 has a clearance hole 1101 for the traction cable 5 to pass through. Preferably, a support arm 12 is fixedly provided above the moving slip ring 6, and the upper cover 11 is fixedly connected to the moving slip ring 6 through the support arm 12. There can be multiple support arms 12, which are arranged along the circumferential direction of the moving slip ring 6.

[0044] The lower cover 8 is fixedly installed on the support column 2. The lower cover 8 is located below the moving slip ring 6. The opening of the lower cover 8 is opposite to the opening of the upper cover 11. The upper cover 11 and the lower cover 8 form a spherical structure.

[0045] Using this invention, students can unleash their creativity to design and build innovative aircraft, conduct test flights using the invention, and are not restricted by laws and regulations on outdoor aircraft test flights. Test flights can be conducted indoors, which stimulates students' learning interest and develops their hands-on skills, collaborative inquiry skills, and innovative practical abilities.

[0046] This invention allows for real-time measurement and control of various performance indicators of an aircraft, such as flight speed and altitude, to evaluate the aircraft's design level and performance.

[0047] The above description of the structure, features and effects of the present invention is based on the embodiments shown in the figures. The above are only preferred embodiments of the present invention, but the present invention is not limited to the scope of implementation shown in the figures. Any changes made in accordance with the concept of the present invention, or equivalent embodiments modified to have equivalent changes, shall be within the protection scope of the present invention as long as they do not exceed the spirit covered by the specification and figures.

Claims

1. A test pile for aircraft dynamic traction and performance, characterized in that: It includes a base (1), a support column (2), an angle sensor (3), a speed sensor (4), and a controller; The support column (2) is fixedly installed on the base (1); The angle sensor (3) is rotatably mounted on the support column (2) away from the base (1) via a slip ring. The input end of the angle sensor (3) is connected to the traction line (5) of the aircraft. The angle sensor (3) measures the angle between the traction line (5) and the support column (2). The angle sensor (3) is electrically connected to the controller. The speed sensor (4) is mounted on the slip ring; the speed sensor (4) measures the rotational angular velocity of the slip ring per revolution around the support column (2), and the speed sensor (4) is electrically connected to the controller; The controller calculates the flight altitude of the aircraft based on the angle between the traction line (5) and the support column (2), using the following formula: When α≤90° ; When α > 90° In the formula, h is the altitude of the aircraft, and h0 is the height of the test stake. L Let α be the length of the traction line (5) and α be the angle between the traction line (5) and the support column (2); The controller calculates the flight speed of the aircraft based on the rotational angular velocity of the slip ring per revolution around the support column (2), using the following formula: In the formula V Let the orbital velocity be the velocity of the aircraft as it orbits the support column (2) once. L The length of the traction line (5), r is The average angular velocity of the slip ring per revolution around the support column (2), where α is the angle between the traction line (5) and the support column (2); The slip ring includes a fixed slip ring and a moving slip ring (6). The moving slip ring (6) has a power distribution function to supply power and transmit signals to the angle sensor (3) and the speed sensor (4). The fixed slip ring is fixedly connected to the support column (2). The angle sensor (3) is installed on the moving slip ring (6) of the slip ring. The rotation speed sensor (4) is a laser rotation speed sensor, and the metal target (7) of the laser rotation speed sensor is installed on the support column (2) below the moving slip ring (6); A mounting plate (9) is fixedly installed on the outer wall of the slip ring (6). The mounting plate (9) is vertically arranged. The angle sensor (3) is fixedly installed on the mounting plate (9). The input end of the angle sensor (3) passes through the mounting plate (9) and is connected to an adapter (10). The traction line (5) is connected to the adapter (10). When the aircraft is placed on the ground and the traction line (5) is connected, and the traction line (5) hangs down parallel to the support column (2), the initial value measured by the angle sensor is α0. The real-time angle measured during the flight is α. c Then the angle α between the traction line (5) and the support column (2) is α = α c -α0.

2. The aircraft power traction and performance testing pile according to claim 1, characterized in that: It also includes an upper cover (11), which is fixedly connected to the slip ring (6). The angle sensor (3) and the speed sensor (4) are both located inside the upper cover (11). The upper cover (11) has a clearance hole (1101) for the traction line (5) to pass through.

3. The aircraft power traction and performance testing pile according to claim 2, characterized in that: A support arm (12) is fixedly provided above the movable slip ring (6), and the upper cover (11) is fixedly connected to the movable slip ring (6) through the support arm (12).

4. The aircraft power traction and performance testing pile according to claim 2, characterized in that: A lower cover (8) is fixedly installed on the support column (2). The lower cover (8) is located below the moving slip ring (6). The opening of the lower cover (8) is opposite to the opening of the upper cover (11). The upper cover (11) and the lower cover (8) form a spherical structure.

5. The aircraft power traction and performance testing pile according to claim 1, characterized in that: The controller is installed inside the base (1), and the controller is electrically connected to the data acquisition module installed inside the base (1). The data acquisition module is electrically connected to the angle sensor (3) and the rotation speed sensor (4) respectively. The controller is electrically connected to the display.

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