General airplane sensor system model teaching aid

Abstract

The invention belongs to the technical field of aerospace education, and discloses a general aircraft sensor system model teaching aid, which comprises a model aircraft main body, an attitude sensing model aircraft, a wing sensor control box, a self-adjusting lighting system mounting box and a simulated oil supply liquid level detection system box body, the model airplane main body comprises a first nose, a first fuselage, a first wing and a first tail; the invention has the following beneficial effects; through a multi-sensor system set, multi-element coupling among an aircraft sensor system, a platform and a load is reproduced, a plurality of novel sensors such as temperature and humidity, keys, multi-axis attitude, illuminance and ultrasonic waves are integrated in a general aircraft sensor system model teaching carrier, and integrated layout design of aircraft sensor system development is supported. Learning skills are provided for students from the four aspects of flight ability, detection ability, perception ability and cooperative ability, and reference is provided for subsequent novel ISR aircrafts.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace education, and particularly relates to a general aircraft sensor system model teaching aid. Background Art

[0002] In the current practice teaching process, in order to better implement the teaching pertinence, strengthen the adaptability of vocational education practice teaching, and serve the practice teaching of sensor courses for related majors such as aircraft electronics and Internet of Things, a general aircraft sensor system model teaching carrier is designed. Adopting the technical concept of platform-load integration, it has the dual characteristics of an aircraft and a sensor. There are multi-element couplings between the platform and the load. A variety of new sensors such as temperature and humidity sensors, button sensors, multi-axis attitude sensors, illuminance sensors, and ultrasonic sensors are integrated into the general aircraft sensor system model teaching carrier to support the integrated layout design of the development of the aircraft sensor system, and provide references for subsequent new ISR (Intelligence, Surveillance and Reconnaissance) aircraft in terms of flight ability, detection ability, perception ability, and coordination ability.

[0003] Since it is not convenient to train students' skills before practice teaching, problems such as damaged sensors caused by students' irregular operations and low service life of practice teaching equipment are caused. Summary of the Invention

[0004] In view of the problems in the prior art that it is not convenient to train students' skills before practice teaching, resulting in damaged sensors caused by students' irregular operations and low service life of practice teaching equipment, the present invention proposes the following technical solutions;

[0005] A general aircraft sensor system model teaching aid, comprising: a model aircraft main body, an attitude perception model aircraft, a wing sensor control box, a self-adjusting lighting system installation box, and a simulated fuel supply liquid level detection system box body;

[0006] The model aircraft main body includes: a first nose, a first fuselage, a first wing, and a first tail;

[0007] The first tail is connected to the first nose through the first fuselage, and the first wing is connected to the first nose through the first fuselage;

[0008] The attitude perception model aircraft includes: a second nose, a second fuselage, a second wing, and a second tail;

[0009] The second tail is connected to the second nose through the second fuselage, and the second wing is connected to the second nose through the second fuselage;

[0010] The wing sensor control box includes a top cover plate, an installation panel, and a bottom floor;

[0011] The top cover plate and the bottom base plate are combined into a box body to wrap the installation panel;

[0012] The self - adjusting lighting system installation box includes: a top shell, a bottom shell, and a lighting system control board;

[0013] The top shell and the bottom shell are combined into a box body to wrap the lighting system control board;

[0014] The simulation fuel supply liquid level detection system box body includes: a placement box and a top fixing cover;

[0015] The top fixing cover is snap - connected to the top end of the placement box.

[0016] As a preference of the above - mentioned technical solution, a nose landing gear is installed at the bottom end of the first nose. The first wheel is connected to the first nose through the nose landing gear. A landing light mounting bracket is connected to the bottom end of the first nose at a position on one side of the nose landing gear. The white LED light is fixedly connected to the first nose through the landing light mounting bracket. A first servo mounting seat is connected to the first nose at a position at one end of the landing light mounting bracket. One end of the first servo mounting seat is connected to a fixing bracket. The ultrasonic ranging module is fixedly connected to the first nose through the fixing bracket and the first servo mounting seat. The outside of the first nose is penetrated and connected with an angle - of - attack sensor wing surface. A fine - tuning potentiometer rotation angle sensor is connected to the inside of the first nose at a position at one end of the angle - of - attack sensor wing surface.

[0017] As a preference of the above - mentioned technical solution, a sensor control box is installed inside the first fuselage. An access cover is installed at the bottom of the first fuselage at a position at the bottom of the sensor control box by screws. A fan is installed inside the sensor control box at a position close to the first nose. A relay is installed inside the sensor control box at a position on one side of the fan. A positioning frame is installed inside the sensor control box at a position at one end of the relay. A first six - axis sensor is installed inside the sensor control box at a position on one side of the positioning frame. A voice development board is installed inside the sensor control box at a position above the first six - axis sensor. A first ten - axis sensor is installed inside the sensor control box at a position on one side of the voice development board. A first temperature and humidity sensor is installed inside the sensor control box at a position below the first six - axis sensor.

[0018] As a preference of the above technical solution, ailerons are movably connected to the edge of one end of the first wing. Flaps are movably connected to the position on one side of the ailerons at one end of the first wing. An engine bracket is installed at one end of the first wing. A turbofan engine is fixedly connected to the first wing through the engine bracket. A main landing gear is installed on one side at the bottom end of the first wing. The second wheel is connected to the first wing through the main landing gear. Second servo mounts are symmetrically installed inside the first wing. A positioning servo is connected to the first wing through the second servo mounts.

[0019] As a preference of the above technical solution, horizontal stabilizers are symmetrically installed on both sides of the first tail. A vertical stabilizer is installed at the top end of the first tail. Elevators are movably connected inside both the horizontal stabilizers and the vertical stabilizer. Servo mounts are installed inside both the horizontal stabilizers and the vertical stabilizer. A second servo is connected to the horizontal stabilizer through the servo mounts.

[0020] As a preference of the above technical solution, the second fuselage is composed of two cylinders. An installation platform is installed inside one end of one cylinder and inside the other cylinder. Rectangular installation slots are symmetrically provided at the top end of the installation platform. A twentieth-axis sensor is connected to the installation platform through the rectangular installation slots. An axis attitude sensor is connected to the installation platform through the rectangular installation slots.

[0021] As a preference of the above technical solution, a resistive film pressure sensor is inserted into the installation panel. A PS dual-axis button joystick is inserted into the installation panel and is located below the resistive film pressure sensor. A first development board is inserted into the middle of the installation panel and is located on one side of the PS dual-axis button joystick. A second development board is inserted into the middle of the installation panel and is located on one side of the first development board. A single-chip microcomputer development board is inserted into the middle of the installation panel and is located on one side of the second development board. An OLED display screen is connected to the top end of the installation panel and is located below the single-chip microcomputer development board. A second temperature and humidity sensor is inserted into the installation panel and is located at the bottom end of the OLED display screen. A chip capacitive 16-way touch switch is inserted at the bottom end of the OLED display screen and is located below the second temperature and humidity sensor.

[0022] As a preference of the above technical solution, a plurality of fuel supply and ventilation holes are provided on one side at the top end of the top fixed cover. A fuel supply pipe penetrates and is connected to the other side at the top end of the top fixed cover. A small laser range finder is inserted into the top fixed cover and is located on one side of the fuel supply pipe. An ultrasonic range finder is inserted into the top fixed cover and is located below the top fixed cover. A transceiver integrated open ultrasonic range finder is inserted into the top fixed cover and is located at one end of the ultrasonic range finder.

[0023] Preferably, as the above technical solution, the number of the fuel supply pipes is set to two, and the outer sides of the two fuel supply pipes are sleeved with the same connecting plate.

[0024] The beneficial effects of the present invention are as follows:

[0025] (1) Through the integration of multi-sensor systems, the aircraft sensor system is reproduced, and the multi-factor coupling between the platform and the payload is realized. A variety of new sensors such as temperature and humidity, buttons, multi-axis attitude, illuminance, and ultrasonic are integrated into the teaching carrier of the general aircraft sensor system model, supporting the integrated layout design for the development of the aircraft sensor system, providing students with learning skills in four aspects: flight ability, detection ability, perception ability, and coordination ability, and providing reference for subsequent new ISR aircraft;

[0026] (2) Through model teaching, the safety risk is low. Compared with the high-voltage electricity and complex circuit systems on the aircraft, the aircraft sensor system model teaching is for low-voltage electricity teaching, reducing the safety threat;

[0027] (4) The product is composed of 52 parts, all of which can be spliced and fastened with screws, avoiding the use of dangerous items such as glue, and ensuring the assembly safety to the greatest extent. Description of the Drawings

[0028] Figure 1 Fig. shows the structural schematic diagram of a general aircraft sensor system model teaching aid in Embodiment 1;

[0029] Figure 2 Fig. shows the structural schematic diagram of the model aircraft body in Embodiment 1;

[0030] Figure 3 Fig. shows the structural schematic diagram of the first nose in Embodiment 1;

[0031] Figure 4 Fig. shows the structural schematic diagram of the first fuselage in Embodiment 1;

[0032] Figure 5 Fig. shows the structural schematic diagram of the first temperature and humidity sensor in Embodiment 1;

[0033] Figure 6 Fig. shows the structural schematic diagram of the sensor control box in Embodiment 1;

[0034] Figure 7 Fig. shows the structural schematic diagram of the first wing in Embodiment 1; [[ID=4...]]

[0035] Figure 8 Fig. shows the front view of the first wing in Embodiment 1;

[0036] Figure 9 Fig. shows the structural schematic diagram of the first tail in Embodiment 1;

[0037] Figure 10 Shown is a schematic structural diagram of the attitude perception model aircraft in Embodiment 1;

[0038] Figure 11 Shown is an explosion view of the attitude perception model aircraft in Embodiment 1;

[0039] Figure 12 Shown is a schematic structural diagram of the installation of the 6-axis attitude sensor in Embodiment 1;

[0040] Figure 13 Shown is a schematic structural diagram of the wing sensor control box in Embodiment 1;

[0041] Figure 14 Shown is an explosion view of the wing sensor control box in Embodiment 1;

[0042] Figure 15 Shown is a schematic installation structure diagram of the chip capacitive 16-way touch switch in Embodiment 1;

[0043] Figure 16 Shown is a schematic structural diagram of the second temperature and humidity sensor in Embodiment 1;

[0044] Figure 17 Shown is a schematic installation structure diagram of the installation panel in Embodiment 1;

[0045] Figure 18 Shown is a schematic structural diagram of the installation box of the self-adjusting lighting system in Embodiment 1

[0046] Figure 19 Shown is an explosion view of the installation box of the self-adjusting lighting system in Embodiment 1;

[0047] Figure 20 Shown is a schematic structural diagram of the box body of the analog fuel supply liquid level detection system in Embodiment 1;

[0048] Figure 21 Shown is an explosion view of the box body of the analog fuel supply liquid level detection system in Embodiment 1.

[0049] In the figure; 1. Model aircraft main body; 11. First nose; 111. Front landing gear; 112. First wheel; 113. Aircraft landing light mounting bracket; 114. White LED light; 115. First servo mounting base; 116. Fixed bracket; 117. Ultrasonic ranging module; 118. Angle-of-attack sensor wing surface; 119. Fine-tuning potentiometer rotation angle sensor;

[0050] 12. First fuselage; 121. Sensor control box; 1211. First ten-axis sensor; 1212. First six-axis sensor; 1213. First temperature and humidity sensor; 1214. Voice development board; 1215. Relay; 1216. Fan; 1217. Mounting bracket; 122. Access cover

[0051] 13. First wing; 131. Aileron; 132. Flap; 133. Engine mount; 134. Turbular engine; 135. Nose landing gear; 136. Second wheel; 137. Second servo mount; 138. Positioning servo

[0052] 14. First tail; 141. Horizontal stabilizer; 142. Elevator; 143. Servo mount; 144. Second servo; 145. Vertical stabilizer

[0053] 2. Attitude perception model aircraft; 21. Second nose; 22. Second fuselage; 221. Mounting platform; 222. Rectangular mounting groove; 223. Second ten-axis sensor; 224. 6-axis attitude sensor; 23. Second wing; 24. Second tail

[0054] 3. Wing sensor control box; 31. Top cover plate; 32. Mounting panel; 33. Bottom floor; 34. Resistive film pressure sensor; 35. PS2 dual-axis button rocker; 36. First development board; 37. Second development board; 38. Microcontroller development board; 39. OLED display screen; 311. Second temperature and humidity sensor; 312. Chip capacitive 16-way touch switch

[0055] 4. Self-adjusting lighting system installation box; 41. Top housing; 42. Bottom housing; 43. Lighting system control board

[0056] 5. Simulation fuel supply liquid level detection system box; 51. Placing box; 52. Top fixing cover; 53. Fuel supply vent hole; 54. Fuel supply pipe; 55. Small laser range finder sensor; 56. Transceiver integrated open range finder sensor; 57. Ultrasonic range finder sensor Detailed implementation manners

[0057] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments

[0058] Embodiment 1

[0059] The present invention provides a general aircraft sensor system model teaching aid, such as Figures 1 to 21As shown in the figure, it includes: a model aircraft body 1, an attitude-sensing model aircraft 2, a wing sensor control box 3, a self-adjusting lighting system installation box 4, and a simulated fuel supply level detection system box body 5; the model aircraft body 1 includes: a first nose 11, a first fuselage 12, a first wing 13, and a first tail 14; the first tail 14 is connected to the first nose 11 through the first fuselage 12, and the first wing 13 is connected to the first nose 11 through the first fuselage 12; the attitude-sensing model aircraft 2 includes: a second nose 21, a second fuselage 22, a second wing 23, and a second tail 24; the second tail 24 is connected to the second nose 21 through the second fuselage 22, and the second wing 23 is connected to the second nose 21 through the second fuselage 22; the wing sensor control box 3 includes: a top cover plate 31, an installation panel 32, and a bottom base plate 33; the top cover plate 31 and the bottom base plate 33 are combined into a box body to cover the installation panel 32; the self-adjusting lighting system installation box 4 includes: a top shell 41, a bottom shell 42, and a lighting system control board 43; the top shell 41 and the bottom shell 42 are combined into a box body to cover the lighting system control board 43; the simulated fuel supply level detection system box body 5 includes: a placement box 51 and a top fixing cover 52; the top fixing cover 52 is snap-connected to the top end of the placement box 51.

[0060] Before practical teaching, it is not convenient to train students' skills before training, resulting in problems such as damaged sensors caused by students' irregular operations, and low service life of practical teaching equipment. Therefore, the concept of platform-load integration technology is adopted, which has the dual characteristics of an aircraft and a sensor. There are multi-factor couplings between the platform and the load. A variety of new sensors such as temperature and humidity, buttons, multi-axis attitude, illuminance, and ultrasonic waves are integrated into the general aircraft sensor system model teaching carrier, supporting the integrated layout design for the development of the aircraft sensor system, providing reference for the subsequent new ISR aircraft from four aspects: flight ability, detection ability, perception ability, and collaboration ability, so as to achieve the purpose of training students' skills before practical teaching.

[0061] Specifically, assemble the first nose 11, the first fuselage 12, the first wing 13, and the first tail 14 to form the model aircraft body 1, assemble the second nose 21, the second fuselage 22, the second wing 23, and the second tail 24 to form the attitude-sensing model aircraft 2, assemble the top cover plate 31, the installation panel 32, and the bottom base plate 33 to form the wing sensor control box 3, assemble the top shell 41, the bottom shell 42, and the lighting system control board 43 to form the self-adjusting lighting system installation box 4, and then snap-connect the top fixing cover 52 between the placement boxes 51 to assemble the simulated fuel supply level detection system box body 5.

[0062] Specifically, the first nose 11 is overall in an elliptical conical shape, with a length of 150 mm, a diameter of 100 mm, and a thickness of 1 mm. At the connection of the first nose 11, there is an extended connection section with a length of 10 mm, a diameter of 49 mm, and a thickness of 1 mm. At 6 mm of the connection section, there are 12 round holes with a radius of 1.5 mm, which are tightly connected to the first fuselage 12. The first fuselage 12 is in a cylindrical shape, with a length of 800 mm, a diameter of 100 mm, and a thickness of 1 mm. On the outer wall, 62 holes with a length of 15 mm, a height of 20 mm, and chamfered corners of 5 mm at the four corners are opened 20 mm upward along the axial centerline of the first fuselage 12. The hole pitch is 10.25 mm, with 31 on each side. At the bottom of the middle section of the first fuselage 12 along the axial direction, there is an access hatch hole with a length of 300 mm, a width of 70 mm, and chamfered corners of 20 mm at the four corners. Along the axial direction of the first fuselage on both sides of the access hatch hole at 2.5 mm, there are 3 round holes with a diameter of 1.5 mm each, and the hole pitch is 10 mm. On the outer wall along the center point of the middle section of the first fuselage, 90 mm in front of the center point, and 60 mm behind the center point, there are 3 round holes with a radius of 5 mm for installing and fixing the first wings 13 on both sides. The single wingspan of the first wing 13 is 520 mm, the maximum chord length is 247 mm, the minimum chord length is 50 mm, the leading edge sweep angle is 60°, the trailing edge sweep angle is 74°, and the thickness transitions from 18 mm to 4 mm along the wingspan direction. At the wing tip of the first wing 13, the wing tip is upturned with a wingspan of 47.2 mm, the maximum chord length is 50 mm, the minimum chord length is 30 mm, the thickness transitions from 4 mm to 2 mm along the wingspan direction of the first wing 13, and the upturn angle is 108.2°. The first tail 14 is overall in an elliptical conical shape, with a length of 141 mm, a diameter of 100 mm, and a thickness of 1 mm. At the connection of the first tail 14, there is an extended connection section with a length of 10 mm, a diameter of 49 mm, and a thickness of 1 mm. At 6 mm of the connection section, there are 12 round holes with a radius of 1.5 mm, which are tightly connected to the first fuselage 12;

[0063] The second nose 21 is overall in an elliptical conical shape, with a length of 60 mm, a diameter of 32 mm, and a thickness of 1 mm. At the connection of the second nose 21, there is an extended connection section with a length of 5 mm, a diameter of 30 mm, and a thickness of 1 mm. At 2.5 mm of the connection section, there are 3 round holes with a radius of 1.5 mm, which are connected and fastened to the second fuselage 22. The main body of the second fuselage 22 is divided into two sections and is overall in a cylindrical shape, with a length of 200 mm, a diameter of 32 mm, and a thickness of 1 mm. The front section of the second fuselage 22 has a length of 100 mm, a diameter of 32 mm, and a thickness of 1 mm. At 2.5 mm from the edges at both ends, there are 3 round holes of 1.5 mm each, which are used for the second nose 21 and the rear section of the second fuselage 22. The single wingspan of the second wing 23 is 160 mm, the maximum chord length is 100 mm, the minimum chord length is 30 mm, the leading edge sweep angle is 59.86°, the trailing edge sweep angle is 82.65°, and the thickness transitions from 8 mm to 4.6 mm along the wingspan direction. The second tail 24 is overall in an elliptical conical shape, with a length of 52 mm, a diameter of 32 mm, and a thickness of 1 mm. At the connection of the second tail 24, there is an extended connection section with a length of 5 mm, a diameter of 15 mm, and a thickness of 1 mm. At 2.5 mm of the connection section, there are 3 round holes with a radius of 1.5 mm, which are connected and fastened to the second fuselage 22;

[0064] An installation panel 32 is snap - installed inside the bottom base plate 33, and a top cover plate 31 is snap - installed outside the bottom base plate 33. At this time, the top cover plate 31, the installation panel 32, and the bottom base plate 33 are assembled to form the wing sensor control box 3. The wing sensor control box 3 is overall 250 mm long, 150 mm wide, 16 mm high, and has chamfers of 10 mm at the four corners;

[0065] The top shell 41 and the bottom shell 42 are snap - installed to form the self - adjusting lighting system installation box 4. The lighting system control board 43 is snap - installed inside the self - adjusting lighting system installation box 4. The lighting system control board 43 is overall 100 mm long, 50 mm wide, and 1.2 mm thick;

[0066] The top fixed cover 52 is snap - installed at the top of the placement box 51, and the two are assembled to form the analog fuel supply liquid level detection system box 5. The placement box 51 is overall 120 mm long, 80 mm wide, 120 mm high, has chamfers of 20 mm at the four corners, and a shell thickness of 1 mm. The top fixed cover 52 is overall 120 mm long, 80 mm wide, 9 mm high, has chamfers of 20 mm at the four corners, and a shell thickness of 1 mm.

[0067] Such as Figures 1 to 3As shown in the figure, the front landing gear 111 is installed at the bottom of the first nose 11. The first wheel 112 is connected to the first nose 11 through the front landing gear 111. A landing light mounting bracket 113 is connected to the bottom of the first nose 11 at a position on one side of the front landing gear 111. The white LED light 114 is fixedly connected to the first nose 11 through the landing light mounting bracket 113. (The LED in the white LED light 114 belongs to a light-emitting diode) A first servo mounting seat 115 is connected to the first nose 11 at a position at one end of the landing light mounting bracket 113. One end of the first servo mounting seat 115 is connected to a fixed bracket 116. The ultrasonic ranging module 117 is fixedly connected to the first nose 11 through the fixed bracket 116 and the first servo mounting seat 115. The angle of attack sensor wing surface 118 is connected through the outside of the first nose 11. A fine-tuning potentiometer rotation angle sensor 119 is connected to the inside of the first nose 11 at a position at one end of the angle of attack sensor wing surface 118.

[0068] During use, the white LED light 114 on the landing light mounting bracket 113 illuminates the road surface, and the angle of the angle of attack sensor wing surface 118 is adjusted through the fine-tuning potentiometer rotation angle sensor 119. At the same time, when the first nose 11 lands, the first wheel 112 at the bottom of the front landing gear 111 contacts the ground, so that the first wheel 112 slides along the ground, and then the model aircraft body 1 slides along the ground, thus completing the phenomenon of the aircraft's simulated landing.

[0069] Specifically, the front landing gear 111 and two first wheels 112 are installed 15 mm in front of the center point below the first nose 11. The front landing gear 111 is fixed through a designed fixing hole with a radius of 1.5 mm. A landing light mounting bracket 113 is designed in front of the front landing gear 111. The white LED light 114 is installed inside the landing light mounting bracket 113 to form an imitation landing light system. A first servo mounting seat 115 is designed in front of the front landing gear 111 at 47 mm in front of the center point of the installation surface of the first nose 11. A fixed bracket 116 is designed below the first servo mounting seat 115. The ultrasonic ranging module 117 is installed inside the fixed bracket 116. The bracket cylinder mechanism is connected to the 2.5 mm servo mounting shaft to realize the detection of the aircraft's simulated radar detection system. The angle of attack sensor wing surface 118 is rotatably connected to the right side of the first nose 11. A connecting bracket for the fine-tuning potentiometer rotation angle sensor 119 is installed inside the first nose 11 at a position at one end of the angle of attack sensor wing surface 118. The fine-tuning potentiometer rotation angle sensor 119 is installed inside the connecting bracket through two 1.5 mm screws.

[0070] In this application, the model of the first servo mounting seat 115 is SG90, the model of the fine-tuning potentiometer rotation angle sensor 119 is SV01A103AEA01R00, and the model of the ultrasonic ranging module 117 is HC-SR04.

[0071] As Figures 4 to 6 shown, a sensor control box 121 is installed inside the first fuselage 12. An access cover 122 is installed at the bottom end of the first fuselage 12 at the bottom position of the sensor control box 121 by screws. A fan 1216 is installed inside the sensor control box 121 near the first nose 11. A relay 1215 is installed inside the sensor control box 121 on one side of the fan 1216. A positioning bracket 1217 is installed inside the sensor control box 121 at one end of the relay 1215. A first six-axis sensor 1212 is installed inside the sensor control box 121 on one side of the positioning bracket 1217. A voice development board 1214 is installed inside the sensor control box 121 above the first six-axis sensor 1212. A first ten-axis sensor 1211 is installed inside the sensor control box 121 on one side of the voice development board 1214. A first temperature and humidity sensor 1213 is installed inside the sensor control box 121 below the first six-axis sensor 1212.

[0072] During use, connect the structure to an external power supply. The current is distributed to each module through the relay 1215. The relay 1215 is default in a closed state to ensure that the sensor control box 121 is powered on. At this time, the voice development board 1214 plays a startup prompt sound (such as "System starting up"), and at the same time, the first ten-axis sensor 1211 performs zero-bias calibration. The first six-axis sensor 1212 confirms that the three-axis acceleration and angular velocity measurement functions are normal. The first temperature and humidity sensor 1213 reads the initial environmental value and judges whether it exceeds the working range (such as humidity > 85%RH triggering an alarm). If the first temperature and humidity sensor 1213 detects that the temperature > 35°C, or when the system load is high, the fan 1216 automatically starts, forming a flow from the side of the first nose 11 towards the relay 1215 to reduce the temperature of the components. The first ten-axis sensor 1211 continuously collects three-dimensional acceleration, angular velocity, and magnetic field data for calculating the device attitude (pitch, roll, yaw angles). The first six-axis sensor 1212 serves as a redundant backup. When the first ten-axis sensor 1211 fails, it continues to provide basic attitude data. The first temperature and humidity sensor 1213 continuously monitors the environment inside the sensor control box 121, and the data is transmitted to the voice development board 1214. When the temperature > 50°C, it triggers the relay 1215 to cut off the power supply of non-essential modules to protect the core components.

[0073] Inside the first fuselage 12, a sensor control box 121 is installed by screws. The sensor control box 121 is 315 mm long, 70 mm wide, with 20 mm chamfers at the four corners. It is stretched to the inner wall of the first fuselage 12, and the shell thickness after shelling is 1 mm. The top surface of the sensor control box 121 inside the first fuselage 12 is 300 mm long, 70 mm wide, with 20 mm chamfers at the four corners and a thickness of 1 mm. At an axial distance of 28.65 mm from the center of the left outer wall on the top surface, there are two U-shaped mounting grooves approximately in the shape of a rectangle with a length of 17 mm, a width of 17 mm, and a height of 4 mm. The thickness of the U-shaped mounting grooves is 1 mm. Inside the mounting grooves, the first ten-axis sensor 1211 is snap-fitted and installed, which can detect information such as model acceleration, gyroscope, angle, and magnetic field. At an axial distance of 28.65 mm from the center of the left outer wall on the top surface and 20 mm below, there is a round hole with a radius of 1.5 mm for installing the first six-axis sensor 1212, which can detect information such as model acceleration and angle. At 5 mm and 95 mm at an axial distance of 45 mm from the center of the right outer wall on the top surface, there are two round holes with a radius of 1.5 mm each. The positioning frame 1217 is installed on the top surface of the sensor control box 121 through the round holes. The positioning frame 1217 is used for the installation of the self-adjusting lighting system installation box 4. At the center point of the top surface of the internal sensor control box 121, 90 mm in front of the center point, and 20 mm below 60 mm behind the center point, there are 3 U-shaped holes with a length of 10 mm, a height of 20 mm, and a 5 mm lower chamfer for the 10 mm fixing rods of the two first wings 13 on both sides to penetrate and fix. At a distance of 30 mm from the center point and a height of 23 mm on the side of the internal sensor control box 121, there is a ring with an outer diameter of 3 mm, an inner diameter of 1.5 mm, and a height of 4 mm. Inside the ring of the internal sensor control box 121, the first temperature and humidity sensor 1213 is installed. At the top end 20 mm of the left inner wall on the top surface of the sensor control box 121, there is an installation bracket with a length of 27 mm, a width of 27 mm, a height of 4 mm, and a thickness of 1 mm. Inside the installation bracket, a fan 1216 is fixedly installed. The size of the fan 1216 is 25*25 mm, thus imitating the aircraft air conditioning system. At a distance of 30 mm from the center point of the top surface of the internal sensor control box 121, there is a ring with an outer diameter of 3 mm and an inner diameter of 1.5 mm. Inside the ring, a voice development board 1214 is installed. At the left 40.97 mm and right 12.68 mm of the center point on the bottom surface of the sensor control box 121, at the four corners of a rectangle with a length of 65 mm and a width of 45 mm, there are four rings with an outer diameter of 3 mm and an inner diameter of 1.5 mm. Two relays 1215 are installed on the rings. The relays 1215 can control the on-board lighting system, air conditioning system, power system, etc.

[0074] In this application, the model of the first ten-axis sensor 1211 is Weite Intelligent JY901 B, the model of the first six-axis sensor 1212 is MPU6050, the model of the first temperature and humidity sensor 1213 is DHT11, and the model of the voice development board 1214 is the ASR-PRO voice recognition module AI offline voice development board.

[0075] As Figure 7 and Figure 8 shown, at one end edge of the first wing 13, an aileron 131 is movably connected. At a position on one side of the aileron 131 at one end of the first wing 13, a flap 132 is movably connected. At one end of the first wing 13, an engine bracket 133 is installed. A turbofan engine 134 is fixedly connected to the first wing 13 through the engine bracket 133. At one side of the bottom end of the first wing 13, a main landing gear 135 is installed. A second wheel 136 is connected to the first wing 13 through the main landing gear 135. Inside the first wing 13, two second servo mounts 137 are symmetrically installed. A positioning servo 138 is connected to the first wing 13 through the second servo mounts 137.

[0076] Specifically, the number of the first wings 13 is set to two. Ailerons 131 and flaps 132 are installed at the trailing edges of the left and right first wings 13. The leading edge of the aileron 131 is 148.3 mm long, the trailing edge is 148.3 mm long, the maximum chord length is 29.3 mm, the minimum chord length is 29 mm, and the thickness is 2 mm. The leading edge of the flap 132 is 256 mm long, the trailing edge is 254 mm long, the maximum chord length is 29 mm, the minimum chord length is 18 mm, and the thickness is 2 mm. An engine bracket 133 is installed below the first wing 13, at a position 200 mm from the center point, 60 mm below, and designed according to the leading edge of the first wing 13. The engine bracket 133 is in an elliptical conical shape, with a front radius of 42 mm, a rear radius of 20 mm, a length of 131.5 mm, and a shell thickness of 1 mm. A turbofan engine 134 is designed on the inner central axis. The turbofan engine 134 has a total of 12 blades with a thickness of 1 mm. The blades of the turbofan engine 134 are connected to the tail fairing through a round rod with a diameter of 1.5 mm. The operation of the turbofan engine 134 can be simulated and controlled through a 4-channel 5V relay 1215. A main landing gear 135 is installed below the first wing 13, at a position 200 mm from the center point, 60 mm below, and 158 mm from the leading edge of the first wing 13. The radius of the strut of the main landing gear 135 is 5 mm and the height is 100 mm. A fixing bracket is designed at the connection between the main landing gear 135 and the lower surface of the first wing 13. Two second wheels 136 with a diameter of 60 mm are installed at the bottom end of the main landing gear 135. On the upper surface of each wing of the first wing 13, two second servo mounts 137 are designed. The two second servo mounts 137 are divided into an aileron servo and a wing servo. The position of the aileron servo is 117.5 mm from the center, and the position of the wing servo is 314.4 mm from the center. A positioning servo 138 is installed inside the second servo mount 137, and the corresponding aileron 131 and flap 132 are controlled through a servo shaft and a connecting rod.

[0077] In this application, the model of the positioning servo 138 is SG90.

[0078] As Figure 9As shown in the figure, horizontal stabilizers 141 are symmetrically installed on both sides of the first tail 14. A vertical stabilizer 145 is installed at the top of the first tail 14. Elevators 142 are movably connected inside both the horizontal stabilizers 141 and the vertical stabilizer 145. Servo mounts 143 are installed inside both the horizontal stabilizers 141 and the vertical stabilizer 145. A second servo 144 is connected to the horizontal stabilizer 141 through the servo mount 143.

[0079] During the actual assembly process, first, the horizontal stabilizers 141 and the vertical stabilizer 145 are accurately installed on the first tail 14 to build the basic framework of the tail wing. Subsequently, the elevators 142 are inserted into the horizontal stabilizers 141 and the vertical stabilizer 145 and the movable connections are completed. After installation, the second servo 144 is started, which can adjust the deflection angle of the elevators 142. In this way, the flight attitudes such as pitching and yawing of the main body 1 of the model aircraft are controlled to ensure the stability and safety of the flight process.

[0080] Specifically, two horizontal stabilizers 141 and a vertical stabilizer 145 are installed on the left and right sides and the upper side of the first tail 14. The single-side wingspan of the horizontal stabilizer 141 is 121.9 mm, the maximum chord length is 71.7 mm, the minimum chord length is 32 mm, the leading-edge sweep angle is 63.3°, the trailing-edge sweep angle is 84°, and the thickness transitions from 8 mm to 3 mm along the wingspan direction. An elevator 142 is designed behind the horizontal stabilizer 141. The projection plane of the elevator 142 is a parallelogram with a length of 100.5 mm, a chord length of 9.1 mm, and the thickness transitions from 2 mm to 0 backward. A servo mount 143 is designed at a distance of 71.5 mm from the central axis of each horizontal stabilizer 141. A second servo 144 is installed inside the servo mount 143 to control the elevator surface of the horizontal stabilizer 141. The wingspan of the vertical stabilizer 145 is 103.3 mm, the maximum chord length is 104 mm, the minimum chord length is 19.4 mm, the leading-edge sweep angle is 41.3°, the trailing-edge sweep angle is 74.3°, and the thickness transitions from 8 mm to 3 mm along the wingspan direction. A rudder surface is designed behind the vertical stabilizer 145. The projection plane of the rudder surface is a parallelogram with a length of 90.3 mm, a chord length of 8 mm, and the thickness transitions from 2 mm to 0 backward. A servo mount 143 is designed at a distance of 63.5 mm from the central axis of each vertical stabilizer 145. A second servo 144 is installed inside the servo mount 143 to control the rudder surface of the vertical stabilizer 145.

[0081] In this application, the model of the second servo 144 is SG90.

[0082] As Figures 10 to 12 shown in the figure, the second fuselage 22 is composed of two cylinders. One end of one cylinder is installed inside the other cylinder with an installation platform 221. Rectangular installation grooves 222 are symmetrically provided at the top of the installation platform 221. A 20-axis sensor 223 is connected to the installation platform 221 through the rectangular installation groove 222. A 6-axis attitude sensor 224 is connected to the installation platform 221 through the rectangular installation groove 222.

[0083] During use, when the device is started, the twentieth-axis sensor 223 and the 6-axis attitude sensor 224 installed in the rectangular installation groove 222 of the installation platform 221 start to work together. The twentieth-axis sensor 223 real-time monitors the multi-dimensional motion data of the device in a complex space, including information such as linear acceleration, angular velocity, and magnetic field strength; the 6-axis attitude sensor 224 focuses on capturing the attitude changes of the device and feedbacks the pitch, roll, and yaw angle data.

[0084] Specifically, the second cylinder inside the second fuselage 22 extends forward 40 mm to the device installation platform 221 inside the first cylinder. The installation platform 221 is designed with a rectangular installation groove 222 that is approximately 17 mm long, 17 mm wide, and 2 mm high at a distance of 25 mm from the center of the connection section of the first cylinder. The thickness of the rectangular installation groove 222 is 1 mm. The twentieth-axis sensor 223 is installed through the rectangular installation groove 222 and the second fuselage 22, and can detect information such as model acceleration, gyroscope, angle, and magnetic field. At a position 5 mm axially from the center of the left outer wall on the top surface of the installation platform 221, there is a rectangular installation groove 222 that is 17 mm long, 15 mm wide, and 2 mm high. The thickness of the rectangular installation groove 222 is 1 mm. The 6-axis attitude sensor 224 is installed inside the rectangular installation groove 222 and can detect information such as model acceleration and angle. Both the 6-axis attitude sensor 224 and the twentieth-axis sensor 223 are fixed on the installation platform 221 through a U-shaped fixing bracket.

[0085] In this application, the model of the twentieth-axis sensor 223 is Weite Intelligent JY901B, and the model of the 6-axis attitude sensor 224 is MPU6050.

[0086] As Figures 13 to 17 shown, the resistive film pressure sensor 34 is inserted into the installation panel 32. The PS2 dual-axis button rocker 35 is inserted into the installation panel 32 and is located below the resistive film pressure sensor 34. The first development board 36 is inserted into the middle of the installation panel 32 and is located on one side of the PS2 dual-axis button rocker 35. The second development board 37 is inserted into the middle of the installation panel 32 and is located on one side of the first development board 36. The single-chip microcomputer development board 38 is inserted into the middle of the installation panel 32 and is located on one side of the second development board 37. The OLED display screen 39 is connected to the top of the installation panel 32 and is located below the single-chip microcomputer development board 38. (The OLED display screen 39 is specifically an organic light-emitting diode display screen) The second temperature and humidity sensor 311 is inserted into the installation panel 32 and is located at the bottom of the OLED display screen 39. The chip capacitive 16-way touch switch 312 is inserted at the bottom of the OLED display screen 39 and below the second temperature and humidity sensor 311.

[0087] During use, the resistive thin-film pressure sensor 34 senses external pressure changes and converts the pressure signal into an electrical signal; the PS2 dual-axis button joystick 35 captures the user's direction operations and button commands, and both transmit the collected data to the first development board 36 for preliminary processing;

[0088] After integrating the sensor data, the first development board 36 transmits it to the adjacent second development board 37 for further analysis. The second development board 37 then conveys the processing result to the single-chip microcomputer development board 38. As the core control unit, the single-chip microcomputer development board 38 deeply analyzes and makes logical judgments on the data according to the preset program to generate control instructions;

[0089] The OLED display screen 39 displays the device status, operation feedback, and data collected by the sensors in real time, facilitating the user to intuitively obtain information; the chip capacitive 16-way touch switch 312 provides a convenient touch interaction interface for the user. The user can send instructions through touch operations, and after being processed by the single-chip microcomputer development board 38, the functions of the device are controlled;

[0090] The second temperature and humidity sensor 311 continuously monitors the environmental temperature and humidity data around the installation panel 32 and transmits the information to the single-chip microcomputer development board 38, and the single-chip microcomputer development board 38 transmits the temperature data.

[0091] Specifically, at a position 19.75 mm from the center of the left edge of the installation panel 32, there is an installation bracket for the single-chip microcomputer development board 38; the single-chip microcomputer development board 38 is installed between the installation bracket and the installation panel 32. At a position 64.45 mm from the center of the left edge of the installation panel 32, there is an installation bracket for the second development board 37, and the second development board 37 is connected to the installation panel 32 through the installation bracket; the first development board 36 is snap-mounted at a position 104 mm from the center of the left edge of the installation panel 32. Below the single-chip microcomputer development board 38, there is an installation seat for the PS2 dual-axis button joystick 35, and the PS2 dual-axis button joystick 35 is installed on the PS2 dual-axis button joystick 35. At the upper end of the installation panel 32, there is a 0.96-inch OLED display screen 39. At a position below the OLED display screen 39 on the installation panel 32, there is a hole with a diameter of 3 mm. At the bottom end of the installation panel 32, the second temperature and humidity sensor 311 is installed through the hole. At the top end of the installation panel 32, on the right side of the OLED display screen 39, there is a 3-mm installation hole for the resistive thin-film pressure sensor 34, and the resistive thin-film pressure sensor 34 is installed on the installation panel 32 through the hole. At the bottom end of the installation panel 32, below the second temperature and humidity sensor 311, there is an installation bracket, and the chip capacitive 16-way touch switch 312 is installed on the installation bracket.

[0092] Specifically, the model of the single-chip microcomputer development board 38 is STM32F103C8T6, the model of the second development board 37 is ESP32-S3, the model of the first development board 36 is Arduino UNO R3, the model of the second temperature and humidity sensor 311 is DHT11, the model of the resistive film pressure sensor 34 is FSR402 strain gauge RFP602 resistive film pressure sensor, and the model of the chip capacitive 16-way touch switch 312 is TTP229 chip capacitive 16-way touch switch.

[0093] As Figure 20 and Figure 21 As shown, on one side of the top of the top fixing cover 52, there are multiple fuel supply and ventilation holes 53. On the other side of the top of the top fixing cover 52, there is a fuel supply pipe 54 penetratingly connected. The small laser range finder 55 is inserted into the top fixing cover 52 and is located on one side of the fuel supply pipe 54. The ultrasonic range finder 57 is inserted into the top fixing cover 52 and is located below the top fixing cover 52. The transceiver integrated open ultrasonic range finder 56 is inserted into the top fixing cover 52 and is located at one end of the ultrasonic range finder 57. The number of fuel supply pipes 54 is set to two in total, and the outer sides of the two fuel supply pipes 54 are sleeved with the same connecting plate.

[0094] During use, the two fuel supply pipes 54 are responsible for transporting media such as fuel or lubricating oil into the device. The connecting plate sleeved on the outside enhances the connection stability of the two fuel supply pipes 54 and ensures the continuity of media transportation. The fuel supply and ventilation holes 53 on one side of the top of the top fixing cover 52 balance the internal air pressure during fuel supply, prevent poor fuel supply caused by pressure difference, and at the same time avoid safety hazards caused by the accumulation of fuel vapor. The small laser range finder 55 is used to measure the liquid level height inside the placement box 51. The transceiver integrated open range finder 56 is installed below the top fixing cover 52. Its open design enables it to detect the space inside the placement box 51 in all directions. The ultrasonic range finder 57, in cooperation with other sensors, constructs a three-dimensional ranging network around the device.

[0095] Specifically, on the upper end of the top fixed cover 52, there is a mounting bracket for a small laser rangefinder 55 with dimensions of 30mm * 16mm * 4mm. Inside the mounting bracket, there is a small laser rangefinder 55. On the upper end of the top fixed cover 52, there is also a mounting bracket for a transceiver integrated open-type rangefinder 56 with dimensions of 20mm * 20mm * 4mm. Inside the mounting bracket, there is a transceiver integrated open-type rangefinder 56. On the lower end of the top fixed cover 52, there is a mounting bracket for an ultrasonic rangefinder 57 with dimensions of 46mm * 20.5mm * 1.2mm. Inside the mounting bracket, there is an ultrasonic rangefinder 57. On the left side of the lower end of the top fixed cover 52, there are two mounting holes 54 for the oil supply pipes with a diameter of 8mm. On the right side of the lower end of the top fixed cover 52, there are three oil supply vent holes 53 with a size of 1.5mm. There are two top oil supply pipes 54 in total, and the dimensions of the oil supply pipe 54 are a diameter of 8mm, an inner diameter of 6mm, a spacing of 10mm, and a length of 25mm.

[0096] The model of the small laser rangefinder 55 is MVR2TB, the model of the transceiver integrated open-type rangefinder 56 is RCWL-1605 transceiver integrated open-type rangefinder, and the model of the ultrasonic rangefinder 57 is HC-SR04.

[0097] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it.

Claims

1. A teaching aid for a general aircraft sensor system model, characterized in that Including: Model aircraft body (1), attitude sensing model aircraft (2), wing sensor control box (3), self - adjusting lighting system installation box (4) and simulated fuel supply liquid level detection system box body (5); The model aircraft body (1) includes: a first nose (11), a first fuselage (12), a first wing (13) and a first tail (14); The first tail (14) is connected to the first nose (11) through the first fuselage (12), and the first wing (13) is connected to the first nose (11) through the first fuselage (12); The attitude sensing model aircraft (2) includes: a second nose (21), a second fuselage (22), a second wing (23) and a second tail (24); The second tail (24) is connected to the second nose (21) through the second fuselage (22), and the second wing (23) is connected to the second nose (21) through the second fuselage (22); The wing sensor control box (3) includes a top cover plate (31), a mounting panel (32) and a bottom base plate (33); The top cover plate (31) and the bottom base plate (33) are combined into a box body to cover the mounting panel (32); The self - adjusting lighting system installation box (4) includes: a top shell (41), a bottom shell (42) and a lighting system control board (43); The top shell (41) and the bottom shell (42) are combined into a box body to cover the lighting system control board (43); The simulated fuel supply liquid level detection system box body (5) includes: a placement box (51) and a top fixing cover (52); The top fixing cover (52) is snap - connected to the top end of the placement box (51).

2. The general aircraft sensor system model teaching aid according to claim 1, wherein A front landing gear (111) is installed at the bottom end of the first nose (11). A first wheel (112) is connected to the first nose (11) through the front landing gear (111). An aircraft landing light mounting bracket (113) is connected to the bottom end of the first nose (11) at a position on one side of the front landing gear (111). A white LED light (114) is fixedly connected to the first nose (11) through the aircraft landing light mounting bracket (113). A first servo mounting seat (115) is connected to the first nose (11) at a position at one end of the aircraft landing light mounting bracket (113). One end of the first servo mounting seat (115) is connected to a fixing bracket (116). An ultrasonic ranging module (117) is fixedly connected to the first nose (11) through the fixing bracket (116) and the first servo mounting seat (115). An angle - of - attack sensor wing surface (118) penetrates and is connected to the outside of the first nose (11). A trimming potentiometer rotation angle sensor (119) is connected to the inside of the first nose (11) at a position at one end of the angle - of - attack sensor wing surface (118).

3. The general aircraft sensor system model teaching aid according to claim 2, characterized in that, Inside the first fuselage (12), a sensor control box (121) is installed. At the bottom of the first fuselage (12) and at the bottom position of the sensor control box (121), a cover (122) is installed by screws. Inside the sensor control box (121), near the side of the first nose (11), a fan (1216) is installed. Inside the sensor control box (121) and on one side of the fan (1216), a relay (1215) is installed. Inside the sensor control box (121) and at one end position of the relay (1215), a positioning bracket (1217) is installed. Inside the sensor control box (121) and on one side of the positioning bracket (1217), a first six-axis sensor (1212) is installed. Inside the sensor control box (121) and above the first six-axis sensor (1212), a voice development board (1214) is installed. Inside the sensor control box (121) and on one side of the voice development board (1214), a first ten-axis sensor (1211) is installed. Inside the sensor control box (121) and below the first six-axis sensor (1212), a first temperature and humidity sensor (1213) is installed.

4. A general aircraft sensor system model teaching aid according to claim 3, characterized in that, One end edge of the first wing (13) is movably connected to an aileron (131). One end of the first wing (13) and on one side of the aileron (131) is movably connected to a flap (132). One end of the first wing (13) is provided with an engine mount (133). A turbofan engine (134) is fixedly connected to the first wing (13) through the engine mount (133). On one side at the bottom of the first wing (13), a main landing gear (135) is installed. A second wheel (136) is connected to the first wing (13) through the main landing gear (135). Inside the first wing (13), second servo mounts (137) are symmetrically installed. A positioning servo (138) is connected to the first wing (13) through the second servo mounts (137).

5. The general aircraft sensor system model teaching aid according to claim 4, characterized in that, On both sides of the first tail (14), horizontal stabilizers (141) are symmetrically installed. At the top of the first tail (14), a vertical stabilizer (145) is installed. Inside both the horizontal stabilizers (141) and the vertical stabilizer (145), elevators (142) are movably connected. Inside both the horizontal stabilizers (141) and the vertical stabilizer (145), servo mounts (143) are installed. A second servo (144) is connected to the horizontal stabilizer (141) through the servo mounts (143).

6. A general aircraft sensor system model teaching aid according to claim 1, characterized in that, The second fuselage (22) is composed of two cylinders. One end of one cylinder is located inside the other cylinder, and an installation platform (221) is installed. Rectangular installation grooves (222) are symmetrically arranged at the top of the installation platform (221). The twentieth-axis sensor (223) is connected to the installation platform (221) through the rectangular installation groove (222), and the 6-axis attitude sensor (224) is connected to the installation platform (221) through the rectangular installation groove (222).

7. A general aircraft sensor system model teaching aid according to claim 1, characterized in that, The resistive film pressure sensor (34) is inserted into the installation panel (32). The PS2 two-axis button rocker (35) is inserted into the installation panel (32) and is located below the resistive film pressure sensor (34). The first development board (36) is inserted into the middle of the installation panel (32) and is located on one side of the PS2 two-axis button rocker (35). The second development board (37) is inserted into the middle of the installation panel (32) and is located on one side of the first development board (36). The single-chip microcomputer development board (38) is inserted into the middle of the installation panel (32) and is located on one side of the second development board (37). The OLED display screen (39) is connected to the top of the installation panel (32) and is located below the single-chip microcomputer development board (38). The second temperature and humidity sensor (311) is inserted into the installation panel (32) and is located at the bottom of the OLED display screen (39). The chip capacitive 16-way touch switch (312) is inserted at the bottom of the OLED display screen (39) and is located below the second temperature and humidity sensor (311).

8. The general aircraft sensor system model teaching aid according to claim 1, characterized in that, A plurality of oil supply and ventilation holes (53) are arranged on one side of the top of the top fixed cover (52). The other side of the top of the top fixed cover (52) is connected through a fuel supply pipe (54). The small laser distance sensor (55) is inserted into the top fixed cover (52) and is located on one side of the fuel supply pipe (54). The ultrasonic distance sensor (57) is inserted into the top fixed cover (52) and is located below the top fixed cover (52). The transceiver integrated open ultrasonic distance sensor (56) is inserted into the top fixed cover (52) and is located at one end of the ultrasonic distance sensor (57).

9. The general aircraft sensor system model teaching aid according to claim 8, characterized in that, The number of the fuel supply pipes (54) is set to two in total, and the same connecting plate is sleeved outside between the two fuel supply pipes (54).

Images