A simulation device for aircraft ground traction operation training
By designing a simulation device for aircraft ground towing operations, which simulates the external dimensions and operational functions of the aircraft, the high cost and complex operation problems of aircraft ground towing operation training have been solved, achieving effective skills training and safety assurance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- SHIJIAZHUANG HAISHAN IND DEV CORP
- Filing Date
- 2025-08-13
- Publication Date
- 2026-08-04
AI Technical Summary
In the existing technology, aircraft ground towing operation training requires practice with real aircraft, which results in high costs and difficulty in simulating complex operational requirements, especially for aircraft ground towing operation training without a towing rod.
Design a simulation device including an airframe simulation unit, a front wheel support unit, a rear wheel support unit, and a control system to simulate the aircraft's external dimensions, front landing gear steering, and main landing gear braking function. It achieves matching with the aircraft through a segmented structure and visual radar, providing repeated practice and early warning functions.
This approach achieves the goal of reducing training costs while meeting trainees' needs for repeated practice in ground traction operations, ensuring the effectiveness of skills training, and avoiding collisions with surrounding facilities.
Smart Images
Figure CN224595176U_ABST
Abstract
Description
Technical Field
[0001] This invention provides an aircraft simulation device, and more particularly a simulation device for training aircraft ground towing operations. Background Technology
[0002] Against the backdrop of the booming development of the modern air transport industry, aircraft ground towing operations are a crucial link in ensuring the normal operation of airports, and their importance is becoming increasingly prominent. Currently, there are two types of aircraft ground towing methods: pole-mounted towing and poleless towing. The poleless towing method uses a unique clamping and lifting device on the towing vehicle to lift and secure the aircraft's nose landing gear to the towing vehicle, completing the aircraft ground towing operation without the need for a towing rod connection.
[0003] According to relevant aircraft ground towing operation procedures, operators must undergo aircraft towing skills training before being allowed to work. The practical training component for poleless towing includes training exercises such as forward towing, 180° turns, and backward fixed-point pushing. Due to the high cost and complex structure of aircraft, strict control of towing speed and angle is required during the towing process to prevent collisions with surrounding facilities. Therefore, trainees are required to practice repeatedly under different working conditions. Since real aircraft cannot be used as training tools for these exercises, a simulation device matching the external dimensions of an aircraft must be designed to replace the real aircraft and meet the training requirements. Utility Model Content
[0004] This utility model provides a simulation device for training aircraft ground towing operations. It aims to simulate the aircraft's external dimensions, nose landing gear steering, and main landing gear braking function through the cooperation of an airframe simulation unit, a front wheel support unit, a rear wheel support unit, and a control system. This is to meet the needs of trainees for repeated practice of ground towing operations, thereby ensuring the effectiveness of practical skills training and reducing training costs.
[0005] To achieve the above objectives, the present invention adopts the following technical solution: A simulation device for training aircraft ground towing operations includes an airframe simulation unit, a front wheel support unit, a rear wheel support unit, and a control system. The aircraft body simulation unit includes a longitudinal rod, a transverse rod, and a connecting seat. The longitudinal rod and the transverse rod are fixedly connected by the connecting seat. The length of the longitudinal rod is consistent with the length dimension of the aircraft body, and the length of the transverse rod is consistent with the width dimension of the aircraft body. The front wheel support unit includes a front wheel and a support axle. Two sets of front wheels are symmetrically arranged on the left and right sides. The two sets of front wheels are connected by a front wheel axle. The middle part of the front wheel axle is fixedly connected to the lower end of the support axle. The upper end of the support axle is pivotally assembled with a bearing assembly to a bearing seat arranged at the front end of the longitudinal rod. The rear wheel support unit includes a support frame, rear wheels and brake components. The support frame is provided with a bottom crossbeam and several sets of columns. The lower end of the columns is fixedly assembled with the bottom crossbeam. The upper end of the middle set of columns is fixedly connected with the connecting seat. The upper ends of the remaining columns are fixedly connected with the crossbar in the body simulation unit. The left and right ends of the bottom crossbeam are equipped with rear wheels. The left and right sets of rear wheels are respectively equipped with brake components. The control system includes an electric control box and a visual radar. The electric control box is installed above the front wheel support unit. A wide-angle visual radar is installed on the bottom surface of the electric control box. Combined visual radars are installed at the rear end of the longitudinal bar and the left and right ends of the crossbar, respectively. The processor arranged in the electric control box is communicatively connected to the control elements of the wide-angle visual radar, the combined visual radar, and the brake assembly.
[0006] The aforementioned simulation device for aircraft ground towing operation training has segmented hollow rods in the airframe simulation unit, and the processor arranged in the electrical control box is connected to the visual radar and brake assembly control elements by wires, which pass through the hollow of the longitudinal and transverse rods.
[0007] The aforementioned simulation device for training aircraft ground towing operations has a longitudinal rod segment that is a square tube structure. At each end of each segment, a sleeve-type external threaded plug and an internal threaded insertion hole are respectively provided. Adjacent longitudinal rod segments are fastened together by the sleeve-type external threaded plug and the internal threaded insertion hole.
[0008] The aforementioned simulation device for training aircraft ground towing operations has a crossbar segment that is a circular tube structure. At each end of each crossbar segment, a sleeve-type external threaded plug and an internal threaded insertion hole are respectively provided. Adjacent crossbar segments are fastened together by the sleeve-type external threaded plug and the internal threaded insertion hole.
[0009] The aforementioned simulation device for aircraft ground towing operation training includes a connecting seat comprising a longitudinal rod sleeve, a transverse rod sleeve, and a vertical sleeve. The longitudinal rod sleeve is a square tube structure that can slide back and forth along the longitudinal rod axis. A threaded hole is provided on the upper end face of the longitudinal rod sleeve, and the connecting seat is fixedly connected to the longitudinal rod by a clamping bolt fitted in the threaded hole. The transverse rod sleeve is a horizontal sleeve arranged on the left and right sides of the longitudinal rod sleeve, and the inner wall of the horizontal sleeve is provided with an internal thread that mates with the external threaded plug of the sleeve-type transverse rod. The vertical sleeve is arranged on the bottom surface of the longitudinal rod sleeve and is inserted and assembled with the upper end of the middle set of columns of the support frame.
[0010] The aforementioned simulation device for training aircraft ground traction operations has a bushing installed outside the front wheel axle and support axle of the front wheel support unit.
[0011] The aforementioned simulation device for aircraft ground towing operation training has a combined visual radar with three sets of cameras installed at the rear end of the longitudinal bar and the left and right ends of the transverse bar, with adjacent sets of cameras installed at a 90-degree angle.
[0012] The aforementioned simulation device for training aircraft ground traction operations has a disc brake structure in the rear wheel support unit.
[0013] The aforementioned simulation device for training aircraft ground towing operations includes cables installed between the longitudinal bar, the transverse bar, and the support frame.
[0014] The aforementioned simulation device for training aircraft ground towing operations has metal hubs for the front and rear wheels and rubber tires.
[0015] This invention provides a simulation device for aircraft ground towing operation training. It uses segmented longitudinal bars in the fuselage simulation unit to simulate the length of the aircraft fuselage, segmented transverse bars to simulate the width, and the longitudinal positioning of the aircraft wings through the assembly position of the connecting seats with the longitudinal bars. This not only achieves consistency with the aircraft fuselage dimensions but also provides universal performance adaptable to different aircraft models. The invention uses a front wheel support unit to simulate the guiding function of the aircraft's nose landing gear and a rear wheel support unit to simulate the differential turning function of the aircraft's main landing gear. Furthermore, the invention uses visual radar to observe the surrounding complex environment and the towing process, issuing audible warnings when obstacles approach or the towing action is not performed correctly. In summary, this invention, through the cooperation of the fuselage simulation unit, front wheel support unit, rear wheel support unit, and control system, simulates the aircraft fuselage dimensions, the nose landing gear and its steering, and the main landing gear and its braking function, thereby meeting the needs of trainees for repeated practice of ground towing operations, ensuring the effectiveness of practical skills training, and reducing training costs. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model; Figure 2 This is a schematic diagram of the longitudinal rod assembly structure of a segmental structure; Figure 3 This is a schematic diagram of the segmental crossbar assembly structure; Figure 4 This is a schematic diagram of the connector structure; Figure 5 This is a schematic diagram of the electrical control box and the front wheel support unit. Figure 6 This is a schematic diagram of the cross-sectional structure of the front wheel support unit; Figure 7 This is a schematic diagram of the rear wheel and brake assembly structure in the rear wheel support unit (taking the right rear wheel as an example). Figure 8 This is a schematic diagram of installing visual radar on vertical and horizontal bars (taking the installation of visual radar on the left end of the horizontal bar as an example).
[0017] Explanation of each label in the diagram: 1 is the longitudinal rod, 1-1 is the sleeve-type longitudinal rod external thread plug, and 1-2 is the longitudinal rod internal thread insertion hole; 2 is the crossbar, 2-1 is the sleeve-type crossbar external thread plug, and 2-2 is the crossbar internal thread insertion hole; 3 is the connecting seat, 3-1 is the longitudinal rod sleeve, 3-1-1 is the threaded hole, 3-2 is the cross rod sleeve, 3-2-1 is the internal thread that mates with the external threaded plug of the sleeve-type cross rod, and 3-3 is the vertical sleeve. 4 is the support frame, 4-1 is the bottom crossbeam, and 4-2 is the column; 5 represents a combined visual radar, and 5-1 represents a camera; 6 represents the rear wheel, and 6-1 represents the brake assembly; 7 represents the cable; 8 represents the electrical control box; 9 represents the bushing; 10 represents the front wheels; 11 is a wide-angle visual radar; 12 is the front axle; 13 is a bearing assembly; 14 is the bearing seat; 15 is the support axis. Detailed Implementation
[0018] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.
[0019] See Figure 1. Figure 5 , Figure 6 , Figure 7 , Figure 8 This utility model provides a simulation device for training aircraft ground towing operations. It includes an airframe simulation unit, a front wheel support unit, a rear wheel support unit, and a control system, wherein: The aircraft simulation unit includes a longitudinal rod 1, a horizontal rod 2, and a connecting seat 3. The longitudinal rod 1 and the horizontal rod 2 are fixedly connected by the connecting seat 3. The length of the longitudinal rod 1 is the same as the length of the aircraft body, and the length of the horizontal rod 2 is the same as the width of the aircraft body. The front wheel support unit includes a front wheel 10 and a support shaft 15. Two sets of front wheels 10 are symmetrically arranged on the left and right sides. The two sets of front wheels 10 are connected by a front wheel axle 12. The middle part of the front wheel axle 12 is fixedly connected to the lower end of the support shaft 15. The upper end of the support shaft 15 is pivotally assembled with a bearing assembly 13 to a bearing seat 14 arranged at the front end of the longitudinal rod 1. A bushing 9 is provided outside the front wheel axle 12 and the support shaft 15. The front wheel support unit is used to simulate the front landing gear of an aircraft and its guiding function. The rear wheel support unit includes a support frame 4 and a rear wheel 6. The support frame 4 is provided with a bottom crossbeam 4-1 and at least three sets of columns 4-2. The lower end of the column 4-2 is fixedly assembled with the bottom crossbeam 4-1. The upper end of the middle set of columns is fixedly connected with the connecting seat 3. The upper ends of the remaining columns are fixedly connected with the crossbar 2. The left and right ends of the bottom crossbeam are equipped with rear wheels 6. The left and right sets of rear wheels 6 are respectively equipped with brake assemblies 6-1. The brake assemblies 6-1 adopt a disc brake structure. The rear wheel support unit is used to simulate the main landing gear of an aircraft and its differential turning function. The control system includes an electric control box 8 and a visual radar. The electric control box 8 is installed above the front wheel support unit. Two sets of wide-angle visual radars 11 are installed on the bottom surface of the electric control box. Combined visual radars 5 are installed at the rear end of the longitudinal bar 1 and the left and right ends of the crossbar 2. The combined visual radar 5 is equipped with three sets of cameras 5-1. The two adjacent sets of cameras are installed at a 90-degree angle. The processor arranged in the electric control box 8 is communicatively connected to the control elements of the wide-angle visual radar 11, the combined visual radar 5, and the brake assembly 6-1. In a specific embodiment of this utility model, a cable 7 is provided between the longitudinal bar 1, the transverse bar 2 and the support frame 4, the hubs of the front wheel 10 and the rear wheel 6 are made of metal, and the tires are rubber tires.
[0020] See Figure 1 , Figure 2 The simulation device for aircraft ground traction operation training described in this utility model has a segmented hollow rod 1 in its airframe simulation unit. The processor arranged in the electrical control box 8 is connected to the visual radar and brake assembly control elements through wires. The wires pass through the hollow of the longitudinal rod 1. Each segment of the longitudinal rod 1 is a square tube structure. At both ends of each segment of the longitudinal rod, a sleeve-type external threaded plug 1-1 and a longitudinal rod internal threaded insertion hole 1-2 are respectively provided. Adjacent longitudinal rod segments 1 are fastened by inserting the sleeve-type external threaded plug 1-1 of one segment into the longitudinal rod internal threaded insertion hole 1-2 of the other segment.
[0021] See Figure 1 , Figure 3 The simulation device for aircraft ground traction operation training described in this utility model has a crossbar 2 in its body simulation unit, which is a segmented hollow rod. The wires in the control system can pass through the hollow crossbar 2. Each segment of the crossbar 2 is a circular tube structure. At both ends of each segment of the crossbar, there are sleeve-type crossbar external thread plugs 2-1 and crossbar internal thread insertion holes 2-2. Adjacent crossbar segments are fastened by inserting the sleeve-type crossbar external thread plug 2-1 of one crossbar into the internal thread insertion hole 2-2 of the other crossbar.
[0022] See Figure 1 , Figure 2 , Figure 3, Figure 4 The simulation device for aircraft ground towing operation training described in this utility model includes a connecting seat 3 in the aircraft simulation unit comprising a longitudinal rod sleeve 3-1, a transverse rod sleeve 3-2, and a vertical sleeve 3-3. The longitudinal rod sleeve 3-1 is a square tube structure that can slide back and forth along the axial direction of the longitudinal rod 1. A threaded hole 3-1-1 is provided on the upper end face of the longitudinal rod sleeve 3-1. The connecting seat 3 is fixedly connected to the longitudinal rod 1 by a clamping bolt fitted in the threaded hole 3-1-1. The transverse rod sleeve 3-2 is a horizontal sleeve arranged on the left and right sides of the longitudinal rod sleeve 3-1. The inner wall of the horizontal sleeve is provided with an internal thread 3-2-1 that mates with the external threaded plug of the sleeve-type transverse rod. The vertical sleeve 3-3 is arranged on the bottom surface of the longitudinal rod sleeve 3-1 and is inserted and assembled with the upper end of the middle set of columns of the support frame 4.
[0023] See Figures 1 to 8 The simulation device for aircraft ground traction operation training described in this utility model uses a segmented longitudinal rod 1 in the fuselage simulation unit to simulate the length of the aircraft fuselage and a segmented transverse rod 2 to simulate the width of the aircraft fuselage. The connecting seat 3 of this utility model can slide along the axial direction of the longitudinal rod 1. By adjusting the assembly position of the connecting seat 3 and the longitudinal rod 1, the longitudinal installation position of the wings of different aircraft models can be simulated. This not only achieves consistency with the overall dimensions of the aircraft fuselage but also has universal performance adaptable to different aircraft models. This utility model uses a front wheel support unit to simulate the aircraft's nose landing gear and its guiding function, and a rear wheel support unit to simulate the aircraft's main landing gear and its differential turning function. For example, when practicing turning left, under the drive of the traction vehicle's wheel-holding device, the front wheel 10 deflects to the left, and at the same time, the left... When the brake assembly 6-1 of the rear wheel 6 is activated, the right rear wheel remains free-rolling, and the present invention deflects to the left by the difference in friction. The present invention also observes the complex surrounding environment and the traction process through visual radar. It can issue an audible warning when an obstacle approaches or the traction action is not standardized. For example, during practical training on the wheel clamping process of the traction vehicle, if the clamping and lifting device is activated before the traction vehicle has reached the correct position, the wide-angle visual radar 11 on the bottom of the electrical control box 8 will transmit the relevant information collected to the processor, which will then command a warning signal to indicate an operational error. When the present invention approaches an obstacle, the combined visual radar 5 installed at the rear end of the longitudinal bar 1 and / or the left and right ends of the crossbar 2 will transmit the relevant information collected to the processor, which will then command a warning signal to prompt the operator to adjust the traction route.
Claims
1. A simulation device for aircraft ground traction operation training, characterized in that: It is equipped with a body simulation unit, a front wheel support unit, a rear wheel support unit, and a control system; The aircraft body simulation unit includes a longitudinal rod (1), a transverse rod (2) and a connecting seat (3). The longitudinal rod (1) and the transverse rod (2) are fixedly connected by the connecting seat (3). The length of the longitudinal rod (1) is consistent with the length of the aircraft body, and the length of the transverse rod (2) is consistent with the width of the aircraft body. The front wheel support unit includes a front wheel (10) and a support shaft (15). Two sets of front wheels (10) are symmetrically arranged on the left and right sides. The two sets of front wheels (10) are connected by a front wheel axle (12). The middle part of the front wheel axle (12) is fixedly connected to the lower end of the support shaft (15). The upper end of the support shaft (15) is pivotally assembled with a bearing assembly (13) and a bearing seat (14) arranged at the front end of the longitudinal rod (1). The rear wheel support unit includes a support frame (4) and a rear wheel (6). The support frame (4) is provided with a bottom crossbeam (4-1) and several sets of columns (4-2). The lower end of the column (4-2) is fixedly assembled with the bottom crossbeam (4-1). The upper end of the middle set of columns is fixedly connected with the connecting seat (3). The upper ends of the remaining columns are fixedly connected with the crossbar (2). The left and right ends of the bottom crossbeam are equipped with rear wheels (6). The left and right sets of rear wheels (6) are respectively equipped with brake components (6-1). The control system includes an electric control box (8) and a visual radar. The electric control box (8) is installed above the front wheel support unit. A wide-angle visual radar (11) is installed on the bottom surface of the electric control box. Combined visual radars (5) are installed at the rear end of the longitudinal bar (1) and the left and right ends of the crossbar (2). The processor arranged in the electric control box (8) is connected to the control elements of the wide-angle visual radar (11), the combined visual radar (5), and the brake assembly (6-1).
2. The simulation device for training in aircraft ground traction operations according to claim 1, characterized in that: In the body simulation unit, the longitudinal rod (1) and the transverse rod (2) are both segmented hollow rods. The processor arranged in the electrical control box (8) is connected to the visual radar and brake assembly control elements by wires, which pass through the hollow longitudinal rod (1) and the transverse rod (2).
3. The simulation device for aircraft ground traction operation training according to claim 2, characterized in that: Each segment of the longitudinal rod (1) is a square tube structure. At each end of each segment of the longitudinal rod, a sleeve-type external threaded plug (1-1) and a longitudinal rod internal threaded insertion hole (1-2) are respectively provided. Adjacent longitudinal rods (1) are fastened together by the sleeve-type external threaded plug (1-1) and the longitudinal rod internal threaded insertion hole (1-2).
4. The simulation device for training in aircraft ground traction operations as claimed in claim 3, characterized in that: Each segment of the crossbar (2) is a circular tube structure. At each end of each segment of the crossbar, a sleeve-type crossbar external thread plug (2-1) and a crossbar internal thread insertion hole (2-2) are respectively provided. Adjacent crossbar segments are fastened together by the sleeve-type crossbar external thread plug (2-1) and the crossbar internal thread insertion hole (2-2).
5. The simulation device for training in aircraft ground traction operations as claimed in claim 4, characterized in that: The connecting seat (3) includes a longitudinal rod sleeve (3-1), a transverse rod sleeve (3-2), and a vertical sleeve (3-3). The longitudinal rod sleeve (3-1) is a square tube structure that can slide back and forth along the longitudinal rod (1) axis. A threaded hole (3-1-1) is provided on the upper end face of the longitudinal rod sleeve (3-1). The connecting seat (3) is fixedly connected to the longitudinal rod (1) by tightening bolts fitted in the threaded hole (3-1-1). The transverse rod sleeve (3-2) is a horizontal sleeve arranged on the left and right sides of the longitudinal rod sleeve (3-1). The inner wall of the horizontal sleeve is provided with an internal thread (3-2-1) that mates with the external threaded plug of the sleeve-type transverse rod. The vertical sleeve (3-3) is arranged on the bottom surface of the longitudinal rod sleeve (3-1) and is inserted and assembled with the upper end of the middle set of columns of the support frame (4).
6. The simulation device for training in aircraft ground traction operations according to any one of claims 1 to 5, characterized in that: A bushing (9) is provided outside the front wheel axle (12) and support shaft (15) of the front wheel support unit.
7. The simulation device for training in aircraft ground traction operations according to any one of claims 1 to 5, characterized in that: The combined visual radar (5) installed at the rear end of the longitudinal bar (1) and the left and right ends of the horizontal bar (2) is equipped with three sets of cameras (5-1), with adjacent sets of cameras installed at a 90-degree angle.
8. The simulation device for training in aircraft ground traction operations according to any one of claims 1 to 5, characterized in that: The brake assembly (6-1) in the rear wheel support unit is a disc brake structure.
9. The simulation device for training in aircraft ground traction operations according to any one of claims 1 to 5, characterized in that: A cable (7) is installed between the longitudinal bar (1), the transverse bar (2) and the support frame (4).
10. The simulation device for training in aircraft ground traction operations according to any one of claims 1 to 5, characterized in that: The hubs of the front wheel (10) and the rear wheel (6) are made of metal, and the tires are rubber tires.