A type of aircraft training and production testing equipment

Abstract

This application discloses an aircraft training and production testing device, relating to the field of UAV testing technology. It includes a testing component and a tensioning component. The testing component includes a vertical plate, and the tensioning component includes a mounting ball, tension ropes, and a fracture component. The fracture component includes tension rope one, tension rope two, a sliding shell, an electromagnet, and a magnet. Multiple tension ropes are provided, with their ends respectively mounted on the vertical plate and the mounting ball. The length of the tension ropes increases sequentially from top to bottom. During testing, the tension ropes are pulled taut sequentially from top to bottom. Tension rope one is fixed at both ends to the sliding shell and the mounting ball, the electromagnet is fixed inside the sliding shell, and tension rope two has a magnet fixed at one end, with the magnet slidably positioned inside the sliding shell. This device enables phased tautness during UAV testing using multiple rubber tension ropes with progressively increasing lengths from top to bottom. It sequentially simulates the dynamic interference process of a UAV's single-sided arm, landing gear, or fuselage being progressively entangled by multiple tree branches, wires, and vines, covering complex entanglement scenarios.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) testing technology, and more particularly to an aircraft training and production testing device. Background Technology

[0002] With the rapid development of drone technology, drones have been widely used in many fields such as military reconnaissance, logistics transportation, and environmental monitoring. However, as application scenarios continue to expand and mission complexity increases, the performance requirements for drones are becoming increasingly stringent. Especially in complex and ever-changing environments, drones need to possess higher stability, anti-interference capabilities, and fault-tolerant control capabilities to ensure the smooth execution of missions and flight safety.

[0003] Performance testing is a crucial part of the design and production of drones. Traditional drone testing mainly focuses on evaluating basic parameters such as speed, altitude, and stability under normal flight conditions. While these tests can reflect the drone's performance under ideal conditions, they are insufficient to comprehensively assess the drone's real-world flight capabilities in complex and disruptive environments. For example, in actual flight, drones may encounter obstacles such as tree branches or power lines, or their flight status may be affected by heavy objects (such as rain or hail) attached to their fuselage. In some extreme cases, connecting components may even suddenly break, all of which pose significant challenges to the drone's flight control system.

[0004] Currently, testing equipment and methods for the anti-interference capabilities of drones are relatively scarce, especially the lack of comprehensive testing platforms capable of simulating various complex interference scenarios. Traditional testing methods often can only simulate single types of interference, such as wind tunnel tests which mainly simulate airflow interference, making it difficult to comprehensively cover the various complex situations that drones may encounter in actual flight. Furthermore, there is a lack of tests to simulate anti-interference capabilities, such as simulating situations where the drone comes into contact with or collides with other objects during flight, causing the fuselage to tilt, or situations where heavy objects are wrapped around the fuselage, affecting flight performance, such as weight changes, center of gravity drift, liquid sloshing, and sudden breakage of connecting components. Summary of the Invention

[0005] This application provides an aircraft training and production testing device that solves the problem that existing technologies struggle to comprehensively cover various complex situations that drones may encounter in actual flight, and lack anti-interference testing capabilities. It simulates situations where the drone comes into contact with or collides with other objects during flight, causing the fuselage to tilt, or where heavy objects become entangled in a part of the fuselage, affecting flight performance, such as weight changes, center of gravity drift, liquid sloshing, and sudden breakage of connecting components. It achieves phased stragging during drone testing using multiple rubber tension ropes of progressively increasing length from top to bottom; it sequentially simulates the dynamic interference process of a drone's single arm, landing gear, or fuselage being progressively entangled by multiple branches, wires, or vines, covering complex entanglement scenarios; the broken component uses an electromagnet to attract a magnet connecting tension rope one and tension rope two. During testing, de-energizing the electromagnet accurately simulates sudden rope breakage, verifying the flight control system's rapid response and fault tolerance to sudden interference; the binding components use separate fixing blocks and screw caps, allowing for quick disassembly and installation, adapting to different drone frame fixing requirements.

[0006] This application provides an aircraft training and production testing device, including a testing component and a tensioning component. The testing component includes a vertical plate, and the tensioning component includes a mounting ball, a tension rope, and a fracture component. The fracture component includes a tension rope one, a tension rope two, a sliding shell, an electromagnet, and a magnet.

[0007] There are multiple pull ropes, with their ends set on the upright plate and the mounting ball respectively, and the length of the pull ropes increases from top to bottom;

[0008] During the test, the taut rope is pulled from top to bottom in sequence;

[0009] One end of the pull rope is fixed to the sliding shell and the mounting ball respectively. The electromagnet is fixed inside the sliding shell. One end of the second pull rope is fixed to a magnet, which is slidably set inside the sliding shell.

[0010] In the initial state of the test, the electromagnet was energized and attracted the magnet. When testing the drone's shock resistance, the electromagnet was de-energized and the attraction to the magnet was canceled.

[0011] As an improvement, the pull rope is made of rubber.

[0012] As an improvement, the sliding shell is hollow inside and cylindrical, and the pull rope is fixed to one end of the sliding shell.

[0013] The electromagnet is fixed inside the sliding housing near one end of the pull rope.

[0014] The broken part also includes a sliding port, which is opened at the end of the sliding shell away from the electromagnet, and the second pull rope passes through the sliding port;

[0015] Multiple ventilation holes are opened on the surface of the sliding shell.

[0016] As an improvement, the test components also include a platform and a buffer pad;

[0017] The cushioning pad is fixed to the platform, and there are two uprights, which are symmetrically fixed on both sides of the cushioning pad.

[0018] It also includes drones and detectors;

[0019] The detector is detachably mounted on the drone, and during detection, the drone is placed on a cushioning pad;

[0020] The detector includes a gyroscope, accelerometer, altimeter, magnetometer, and vibration sensor.

[0021] As an improvement, there are four tension components, with two tension components symmetrically arranged on the same vertical plate;

[0022] The test components also include binding components, the number of which is the same as the number of pull components, and they correspond one-to-one;

[0023] The fasteners include a fixing ball, a binding rope, a fixing block, and a screw cap;

[0024] The fixed ball is attached to the end of the pull rope away from the magnet.

[0025] There are two binding ropes and two fixing blocks, and they correspond one to one. One end of the binding rope is fixed to the fixing ball, and the fixing block is fixed to the end of the binding rope away from the fixing ball.

[0026] The fixing block is a half-cylinder shape, and the outer ring of the fixing block is threaded;

[0027] When the two fixing blocks are in contact with each other, they form a cylindrical shape. The screw cap is threaded onto the two fixing blocks and is used to lock the two fixing blocks.

[0028] As an improvement, the test assembly also includes adjustment components, the number of which is consistent with the sum of the number of tension ropes in the multiple tension components, and there is a one-to-one correspondence between them;

[0029] The adjusting components include a fixed plate, an airbag, a limiting telescopic rod, an air pump, and an air supply pipe;

[0030] The airbag is ring-shaped, with one end fixed to the side of the upright plate away from the cushioning pad;

[0031] The fixing plate is fixed to the end of the airbag away from the upright plate, and the two ends of the limiting telescopic rod are fixed to the fixing plate and the upright plate respectively;

[0032] The end of the pull rope away from the installation ball passes through the fixed plate and is fixed to the fixed plate with the airbag;

[0033] One end of the pull rope is fixed to the mounting ball, and the pull rope is slidably connected to the upright plate;

[0034] The air pump is fixed to the upright plate, and the air supply pipe is fixed to the output end of the air pump. The end of the air supply pipe away from the air pump is connected to the air bag.

[0035] As an improvement, the tensioning assembly also includes a water pump, a delivery pipe, and a water bladder;

[0036] The number of water pumps, delivery pipes, and water bladders must match the number of pull ropes, and they must correspond one-to-one.

[0037] The water bladder is ring-shaped and fixed to the outer ring of the pull rope;

[0038] The water pump is fixed on one side of the two upright plates that are close to each other. The output end of the water pump is fixed with a delivery pipe, and the end of the delivery pipe away from the water pump is connected to the water bag.

[0039] As an improvement, the tensioning assembly also includes a regulating pipe and a second water pump;

[0040] There is one regulating pipe and one water pump, corresponding to the bottommost pull rope and the bottommost fixing plate;

[0041] The bottom pull rope is hollow inside, and the adjusting tube is fixed inside the pull rope. Both ends of the adjusting tube are fixed to the bottom fixing plate and the mounting ball.

[0042] Water pump two is fixed on the bottom fixing plate, and the output end of water pump two is connected to the regulating pipe.

[0043] As an improvement, the regulating pipe is a polyurethane hose.

[0044] As an improvement, height calculation:

[0045]

[0046] Where h(t) is the vertical displacement of the drone's binding point relative to the takeoff point, and the highest flight altitude of the drone is the length of the lowest pull rope plus the height of the lowest pull rope from the ground.

[0047] v is the uniform upward speed of the drone, and t is the time calculated from the start of takeoff;

[0048] Calculation of tension in a pulling rope:

[0049]

[0050] in, Let be the tension generated by the i-th pulling rope;

[0051] Let be the elastic coefficient of the i-th tension rope;

[0052] h(t) is the vertical displacement of the UAV's binding point relative to the takeoff point. ;

[0053] Let be the natural length of the i-th tension rope, its length when it is not under force;

[0054] Calculation of the elastic coefficient of the tension rope:

[0055]

[0056] Where E is the Young's modulus of the tension rope material;

[0057] A is the cross-sectional area of ​​the tension rope. Original length;

[0058] Sum of total tensile forces in a single tension component:

[0059]

[0060] Where n is the total number of pull ropes in a single pull assembly. The total elastic tension exerted on the drone by all the tension ropes of a single tension component;

[0061] When the drone is hovering or ascending at a constant speed, the total thrust of the rotor is balanced by the total downward force acting on it.

[0062]

[0063] Where m is the mass of the tested drone, and g is the acceleration due to gravity. The total elastic tension exerted on the drone by all the tension ropes of a single tension component;

[0064] Additional load on the water bladder:

[0065]

[0066] The total constraint force applied to the drone is the sum of the elastic tension of all the tension ropes in the single tension assembly currently being tested. Added gravity with water bladder sum;

[0067]

[0068] in, The additional gravity exerted on the drone due to the filling of the water bladder;

[0069] The mass of the water injected into the water bladder;

[0070] g is the acceleration due to gravity;

[0071] Acceleration after rope one and rope two break:

[0072]

[0073] Where 'a' represents the sudden change in the drone's acceleration at the moment of fracture;

[0074] The sum of elastic tensions that will disappear at the moment of breakage is the total elastic tension exerted on the drone by the tension rope in the single tension component that is about to break at the moment of breakage, excluding the additional gravity of the water bladder, which will become zero instantly after breakage.

[0075] m represents the mass of the drone.

[0076] One or more technical solutions provided in the embodiments of this application have at least the following technical effects or advantages:

[0077] Firstly, multiple rubber tension ropes of increasing length from top to bottom are used to achieve phased straightening during drone testing. This simulates the dynamic interference process of a drone's single arm, landing gear, or fuselage being progressively entangled by multiple branches, wires, and vines, covering complex entanglement scenarios. The broken component connects tension rope one and tension rope two via an electromagnet attracting a magnet. During testing, the electromagnet being de-energized accurately simulates the sudden breakage of the rope, verifying the flight control system's rapid response and fault tolerance to sudden interference. The binding component uses a split fixing block and screw cap, which can be quickly disassembled and installed to adapt to different drone frame fixing requirements.

[0078] Secondly, the water bladder and pump can fill or drain water into the bladder; simulating weight changes and center of gravity shifts caused by reduced water volume in the tank, and simulating increased weight or accidental load leakage during sudden heavy rain; the liquid inside the bladder flows freely during drone acceleration and turning, generating nonlinear inertial forces and torques, comprehensively testing the flight control system's resistance to liquid sloshing interference. Water bladders with different tension ropes can be independently filled with different amounts of water, enabling multi-directional asymmetric center of gravity shift testing and improving the breadth of scenario coverage.

[0079] Third, it enables seamless switching of the same equipment to simulate two distinctly different types of interference, from flexible wrapping to rigid scraping, greatly expanding the testing scope. It extends the simulation from soft wrapping to rigid interference scenarios involving scraping hard objects; the stiffness of the polyurethane hose can be reversibly adjusted after water injection, allowing for rapid switching between soft and hard interference modes. Attached Figure Description

[0080] Figure 1 This invention provides a three-dimensional training and production testing device for aircraft. Figure 1 ;

[0081] Figure 2 This invention provides a three-dimensional training and production testing device for aircraft. Figure 2 ;

[0082] Figure 3 This is a perspective view of an unmanned aerial vehicle (UAV) for an aircraft training and production testing device according to the present invention.

[0083] Figure 4 This is a structural diagram of a binding component for an aircraft training and production testing device according to the present invention;

[0084] Figure 5 This is a schematic diagram of the installation of multiple tension ropes in an aircraft training and production testing device according to the present invention;

[0085] Figure 6 This is a schematic diagram of the airbag installation of an aircraft training and production testing device according to the present invention;

[0086] Figure 7 This is a schematic diagram of the fracture structure of an aircraft training production testing device according to the present invention;

[0087] Figure 8 This is a schematic diagram of the electromagnet adsorbing a magnet in an aircraft training and production testing device according to the present invention.

[0088] Figure 9 This is a schematic diagram of the electromagnet in the de-energized state of an aircraft training and production testing device according to the present invention.

[0089] Figure 10 This is a schematic diagram of the water bladder installation of an aircraft training and production testing device according to the present invention;

[0090] Figure 11 This is a schematic diagram of the installation of the regulating pipe in an aircraft training and production testing device according to the present invention.

[0091] In the diagram: 100, Test component; 110, Platform; 120, Buffer pad; 130, Vertical plate; 140, Adjusting component; 141, Fixing plate; 142, Airbag; 143, Limiting telescopic rod; 144, Air pump; 145, Air supply pipe; 150, Binding component; 151, Fixing ball; 152, Binding rope; 153, Fixing block; 154, Screw cap; 200, Pulling component; 210, Mounting ball; 220, Pull rope; 230, Broken component; 231, Pull rope one; 232, Pull rope two; 233, Sliding shell; 234, Electromagnet; 235, Magnet; 236, Sliding port; 240, Water pump one; 250, Delivery pipe; 260, Water bag; 270, Adjusting pipe; 280, Water pump two; 300, UAV; 400, Detector. Detailed Implementation

[0092] To facilitate understanding of the present invention, a more complete description of this application will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the invention. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to enable a more thorough and complete understanding of the disclosure of the present invention.

[0093] It should be noted that the terms "vertical," "horizontal," "up," "down," "left," "right," and similar expressions used in this article are for illustrative purposes only and do not represent the only possible implementation.

[0094] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains; the terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to limit the invention; the term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0095] Example 1: As Figures 1-9 As shown, this application discloses an aircraft training and production testing device, including a testing component 100, a tensioning component 200, a drone 300, and a detector 400.

[0096] Test component 100 includes platform 110, buffer pad 120, upright plate 130, adjustment component 140 and binding component 150;

[0097] The pulling assembly 200 includes a mounting ball 210, a pulling rope 220, and a breaking component 230. The breaking component 230 includes a first pulling rope 231, a second pulling rope 232, a sliding shell 233, an electromagnet 234, a magnet 235, and a sliding opening 236.

[0098] There are multiple pull ropes 220, with their two ends respectively set on the upright plate 130 and the mounting ball 210. The length of the pull ropes 220 increases from top to bottom.

[0099] There are four tension components 200, with two tension components 200 symmetrically arranged on the same vertical plate 130;

[0100] The 220 pull rope is made of rubber.

[0101] During the test, the taut rope was pulled 220 degrees from top to bottom.

[0102] Specifically, during the test of the UAV 300, the altitude was gradually increased, and the tension ropes 220 were pulled taut from top to bottom. First, the tension rope 220 at the top was pulled taut, and then the tension ropes 220 below were pulled taut in turn, so that the tension gradually increased. This simulated the extremely complex scenario in which one side of the UAV 300's arm, landing gear, or fuselage was simultaneously entangled by multiple tree branches, wires, or vines; thus realizing a dynamic and phased interference process.

[0103] The two ends of the pull rope 231 are fixed to the sliding shell 233 and the mounting ball 210 respectively. The electromagnet 234 is fixed inside the sliding shell 233. One end of the pull rope 232 is fixed to the magnet 235, and the magnet 235 is slidably disposed inside the sliding shell 233.

[0104] In the initial state of the test, the electromagnet 234 was energized and attracted the magnet 235. When testing the drone's shock resistance, the electromagnet 234 was de-energized and the attraction to the magnet 235 was canceled.

[0105] The sliding shell 233 is hollow inside and cylindrical in shape. The pull rope 231 is fixed to one end of the sliding shell 233.

[0106] Electromagnet 234 is fixed inside sliding housing 233 near one end of pull rope 231;

[0107] A sliding opening 236 is opened at the end of the sliding shell 233 away from the electromagnet 234, and the second pull rope 232 is set through the sliding opening 236;

[0108] Specifically, during the flight of the UAV 300, the electromagnet 234 can be de-energized, causing a sudden break between the pull ropes 231 and 232. This provides a dynamically changing interference mode, enabling highly controllable and repeatable "breakage" tests. De-energizing the electromagnet 234 allows for controlled, instantaneous separation, accurately simulating such sudden and severe connection failure interference. When the UAV 300 is flying normally or facing external tension interference, suddenly "cutting off" the connection between pull ropes 231 and 232 immediately changes the stress state of the UAV 300, placing higher demands on the flight control system's rapid response capability, transient stability recovery capability, and fault-tolerant control capability, thus providing a new testing dimension.

[0109] Multiple ventilation holes are provided on the surface of the sliding shell 233.

[0110] Specifically, multiple ventilation holes are made on the surface of the sliding shell 233 to prevent the magnet 235 from being blocked by the internal gas when it slides inside the sliding shell 233, which would slow down the reaction time.

[0111] The buffer pad 120 is fixed on the platform 110, and there are two upright plates 130, which are symmetrically fixed on both sides of the buffer pad 120.

[0112] The detector 400 is detachably mounted on the drone 300. During detection, the drone 300 is placed on the buffer pad 120.

[0113] The detector 400 includes a gyroscope, accelerometer, altimeter, magnetometer, and vibration sensor.

[0114] Specifically, the buffer pad 120 is used for landing cushioning and is detected by various detection structures within the detector 400 installed on the drone 300 to obtain specific data.

[0115] The number of 150 binding components is the same as the number of 200 tension components, and they correspond one-to-one.

[0116] The fastener 150 includes a fixing ball 151, a binding rope 152, a fixing block 153, and a screw cap 154;

[0117] The fixed ball 151 is fixed to the end of the pull rope 232 away from the magnet 235;

[0118] There are two binding ropes 152 and two fixing blocks 153, and they correspond one to one. One end of the binding rope 152 is fixed to the fixing ball 151, and the fixing block 153 is fixed to the end of the binding rope 152 away from the fixing ball 151.

[0119] The fixing block 153 is a half-cylinder shape, and the outer ring of the fixing block 153 is threaded;

[0120] When the two fixing blocks 153 are in contact with each other, they form a cylindrical shape. The screw cap 154 ​​is threaded onto the two fixing blocks 153 and is used to lock the two fixing blocks 153.

[0121] Specifically, the fastener 150 is fixed to the drone 300. When fixing, the screw cap 154 ​​is manually unscrewed, and the two fixing blocks 153 are separated from each other. Then, the two binding ropes 152 are fixed to the frame of the drone 300. After that, the two fixing blocks 153 are put back together and the screw cap 154 ​​is screwed onto the two fixing blocks 153 to fix the position.

[0122] The number of adjusting components 140 is consistent with the sum of the number of pulling ropes 220 in the multiple pulling components 200, and they correspond one-to-one;

[0123] Adjustment component 140 includes a fixing plate 141, an airbag 142, a limiting telescopic rod 143, an air pump 144, and an air supply pipe 145;

[0124] The airbag 142 is ring-shaped, and one end of the airbag 142 is fixed to the side of the upright plate 130 away from the buffer pad 120.

[0125] The fixing plate 141 is fixed to the end of the airbag 142 away from the upright plate 130, and the two ends of the limiting telescopic rod 143 are respectively fixed to the fixing plate 141 and the upright plate 130.

[0126] The end of the pull rope 220 away from the mounting ball 210 passes through the fixed plate 130 and is fixed to the fixed plate 141 with the airbag 142;

[0127] One end of the pull rope 220 is fixed to the mounting ball 210, and the pull rope 220 is slidably connected to the upright plate 130;

[0128] The air pump 144 is fixed on the upright plate 130. The output end of the air pump 144 is fixed with the air supply pipe 145. The end of the air supply pipe 145 away from the air pump 144 is connected to the air bag 142.

[0129] Specifically, by inflating or deflating the airbag 142, the length of the pull rope 220 can be adjusted, thereby adjusting the stiffness and deformation capacity of the airbag 142 itself. Furthermore, when the pull rope 220 is subjected to tension, the airbag 142 can absorb the impact force and provide cushioning.

[0130] Both the UAV 300 and the detector 400 are existing technologies and will not be discussed further here.

[0131] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages:

[0132] Multiple rubber tension ropes 220, with increasing lengths from top to bottom, are used to achieve phased straightening during UAV 300 testing. This simulates the dynamic interference process of a single arm, landing gear, or fuselage of the UAV 300 being progressively entangled by multiple branches, wires, and vines, covering complex entanglement scenarios. The breakage component 230 connects tension rope 1 231 and tension rope 232 via an electromagnet 234 attracting a magnet 235. During testing, the sudden breakage of the rope can be accurately simulated when the electromagnet 234 is de-energized, verifying the flight control system's rapid response and fault tolerance to sudden interference. The binding component 150 uses a split fixing block 153 and a screw cap 154, which can be quickly disassembled and installed to adapt to the different frame fixing requirements of the UAV 300.

[0133] Example 2: In the above example, the anti-interference capability of the drone 300 is tested by stretching the deformation of the rope 220 during use. However, the simulated test scenario coverage is narrow, making it difficult to effectively simulate key real-world interference scenarios such as weight changes, center of gravity drift, and liquid sloshing. Therefore, the solution in Example 1 is improved, such as... Figure 10 As shown:

[0134] The tensioning assembly 200 also includes a water pump 240, a delivery pipe 250, and a water bladder 260;

[0135] The number of water pump 240, delivery pipe 250 and water bag 260 is the same as the number of pulling rope 220, and they correspond one-to-one;

[0136] The water bladder 260 is ring-shaped and is fixed to the outer ring of the pull rope 220;

[0137] Water pump 240 is fixed on one side of the two upright plates 130 that are close to each other. The output end of water pump 240 is fixed with delivery pipe 250. The end of delivery pipe 250 away from water pump 240 is connected to water bag 260.

[0138] The input terminal of the water pump 240 is connected to the water source.

[0139] Specifically, the water bladder 260, fixed by the tension rope 220, can be pumped or filled with water during the testing process. Different volumes of water can be injected into water bladders 260 at different locations. This simulates the weight changes and center of gravity shifts caused by the gradual reduction of pesticide in the tank when the drone 300 is performing a spraying task, the weight increase caused by rainwater adhering to the body during a sudden rainstorm, and the accidental release or leakage of the payload. It actively simulates the shift of the center of gravity and liquid sloshing interference. After filling, the water can flow freely inside the bladder. When the drone 300 performs maneuvers such as acceleration, deceleration, turning, and pitching, the sloshing of the water will generate dynamic and nonlinear inertial forces and torques. This comprehensively covers core real-world interference scenarios such as weight changes, center of gravity shifts, and liquid sloshing.

[0140] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages:

[0141] Water bladder 260 and water pump 240 can inject or pump water into water bladder 260; simulating weight changes and center of gravity drift caused by a decrease in water volume in the water tank, simulating increased weight of the aircraft or accidental load leakage during a sudden rainstorm; the liquid inside water bladder 260 flows freely during the UAV's acceleration and turns, generating nonlinear inertial forces and torques, comprehensively testing the flight control system's ability to resist liquid sloshing interference. Water bladders 260 with different tension ropes 220 can be independently filled with different amounts of water, enabling multi-directional asymmetric center of gravity shift testing and improving the breadth of scenario coverage.

[0142] Example 3: In the above examples, both the pull rope 220 and the water bladder 260 are made of deformable soft materials, which can only simulate the scenario of the drone 300 being made of soft materials, and cannot simulate the scenario of the drone 300 scraping against a hard object. Based on this, improvements are made to Example 2, such as... Figure 11 As shown:

[0143] The tensioning assembly 200 also includes an adjusting pipe 270 and a water pump 280;

[0144] There is one regulating pipe 270 and one water pump 280, which correspond to the bottommost pull rope 220 and the bottommost fixing plate 141;

[0145] The bottom pull rope 220 is hollow inside, and the adjusting tube 270 is fixed inside the pull rope 220. The two ends of the adjusting tube 270 are fixed to the bottom fixing plate 141 and the mounting ball 210.

[0146] Water pump 280 is fixed on the bottom fixing plate 141, and the output end of water pump 280 is connected to the regulating pipe 270.

[0147] The input terminal of water pump 280 is connected to the water source.

[0148] The regulating pipe 270 is a polyurethane hose.

[0149] Specifically, when testing the drone 300, water can be injected into the regulating pipe 270 using water pump 280, gradually increasing the hardness of the softest regulating pipe 270 at the bottom, thus achieving scene changes that switch between soft and hard modes.

[0150] The technical solutions described in the embodiments of this application have at least the following technical effects or advantages:

[0151] This allows for seamless switching of the same equipment to simulate two distinctly different types of interference: flexible wrapping and rigid scratching, greatly expanding the testing scope. It extends the simulation from soft wrapping to rigid interference scenarios involving scratching hard objects; the stiffness of the polyurethane hose can be reversibly adjusted after water injection, enabling rapid switching between soft and hard interference modes.

[0152] Height calculation:

[0153]

[0154] Where h(t) is the vertical displacement of the binding point of the UAV 300 relative to the takeoff point, and the maximum flight height of the UAV 300 is the length of the bottom pull rope 220 plus the height of the bottom pull rope 220 from the ground.

[0155] v is the speed at which the drone ascends at a constant speed of 300, and t is the time calculated from the start of takeoff;

[0156] Calculation of the tension force of a 220mm rope:

[0157]

[0158] in, The tension generated by the i-th tension rope 220;

[0159] Let be the elastic coefficient of the i-th tension rope 220;

[0160] h(t) is the vertical displacement of the UAV's 300 binding point relative to the takeoff point. ;

[0161] Let be the natural length of the i-th tension rope 220, the length when it is not under force;

[0162] Calculation of the elastic modulus of a 220 tension rope:

[0163]

[0164] Where E is the Young's modulus of the tension rope 220 material;

[0165] A is the cross-sectional area of ​​the 220mm tension rope. Original length;

[0166] Sum of total tensile forces in a single tensile component of 200:

[0167]

[0168] Where n is the total number of pull ropes 220 in a single pull assembly 200. The total elastic tension of all the tension ropes 220 acting on the drone 300 in a single tension component 200;

[0169] When the drone hovers at 300 degrees or ascends at a constant speed, the total rotor thrust is balanced by the total downward force:

[0170]

[0171] Where m is the mass of the tested UAV (300 kg), and g is the acceleration due to gravity. The total elastic tension of all the tension ropes 220 acting on the drone 300 in a single tension component 200;

[0172] Additional load of water bladder 260:

[0173]

[0174] The total constraint force applied to the drone 300 is the sum of the elastic tension of all the tension ropes 220 in the single tension assembly 200 currently being tested. With the addition of gravity to the water bladder 260 sum;

[0175]

[0176] in, The additional gravity exerted on the drone 300 due to the filling of the water bladder 260 with water;

[0177] The mass of water injected into water bladder 260;

[0178] g is the acceleration due to gravity;

[0179] Acceleration after rope 1 (231) and rope 2 (232) break:

[0180]

[0181] Where 'a' represents the sudden acceleration change of the UAV at the moment of fracture;

[0182] The sum of elastic tension that will disappear at the moment of breakage is the total elastic tension exerted by the tension rope 220 on the drone 300 in the single tension component 200 that is about to break at the moment of breakage, excluding the additional gravity of the water bladder 260, which will become zero instantly after breakage.

[0183] m represents the mass of the UAV 300.

[0184] Specific examples:

[0185] Test objective: To evaluate the flight control system response and stability of a UAV 300 in an extreme scenario where one of the branches suddenly breaks after the single arm is progressively entangled by multiple branches.

[0186] Test equipment and parameter settings:

[0187] The tested drone 300: mass m = 0.9 kg;

[0188] Initial hover thrust ;

[0189] The upward speed is v = 0.15 m / s (slow and stable upward movement).

[0190] Pull component 200:

[0191] The number of ropes pulled is 220, and the number of ropes pulled is n=3 (simulating three tree branches of different heights).

[0192] The original lengths of the 220mm tension rope (from top to bottom) are: L1=0.3m, L2=0.5m, L3=0.7m;

[0193] The 220 tension rope is made of natural rubber, with a Young's modulus E = 0.5 MPa = 5 × 10⁻⁶. 5 Pa, cross-sectional area A = 1 cm 2 ;

[0194] The lowest pull rope 220 is 0.3m above the ground, and the highest altitude of the drone 300 is 1 meter.

[0195] Elasticity coefficient ,

[0196]

[0197]

[0198]

[0199] Water bladder 260 water filling quality =0.15kg, water is injected only into the water bladder 260 of the bottommost pull rope 220 (i=3) to simulate the weight increase of tree branches due to rainwater or dew.

[0200] Additional gravity =0.15×9.8=1.47N.

[0201] Straightening time point:

[0202] (First pull rope 220 is taut)

[0203] (Second pull rope 220 is taut)

[0204] (The third pulling rope is taut at 220 degrees)

[0205] The water bladder 260 begins to fill with water at a time t=5.5s and breaks at a time t=7.0s.

[0206] At t=5.0s (all tension ropes 220 are taut, water bladder 260 is not filled with water):

[0207]

[0208]

[0209]

[0210]

[0211]

[0212]

[0213] This indicates the elongation of the first tension rope 220. This indicates the elongation of the second tension rope 220. This indicates the elongation of the third tension rope 220;

[0214] At t=6.0s (water bladder 260 has been filled with water):

[0215]

[0216]

[0217]

[0218]

[0219] Total elastic tensile force:

[0220] Water bladder 260 additional gravity: Only the bottom pull rope 220 plus water bladder 260;

[0221] Total constraint:

[0222] 300 thrust for drones:

[0223] At t=7.0s (the instant of fracture):

[0224] At the moment of fracture, assuming the height is the same as t=6.0s and h=0.90m.

[0225]

[0226]

[0227]

[0228] The total fracture force should be:

[0229] Assuming the breakage occurs in the lowest tension rope 220, then:

[0230]

[0231] Calculation of instantaneous acceleration after fracture:

[0232]

[0233] acceleration is approximately .

[0234] Detector 400 data records:

[0235] The gyroscope records the step changes in pitch and roll torque of the aircraft caused by the successive straightening of the 220-degree tension rope at t=2.0s, 3.33s, and 4.67s.

[0236] Accelerometer: At t=7.0s, a peak value of approximately 100-200ms will be recorded. The upward acceleration pulse.

[0237] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An aircraft training and production testing device, characterized in that, The test assembly (100), the tension assembly (200), and the drone (300) are included. The test assembly (100) includes a stand plate (130). The tension assembly (200) includes a mounting ball (210), a tension rope (220), a fracture component (230), a water pump (240), a delivery pipe (250), and a water bladder (260). The fracture component (230) includes a tension rope (231), a tension rope (232), a sliding shell (233), an electromagnet (234), and a magnet (235). There are multiple pull ropes (220), with their two ends set on the upright plate (130) and the mounting ball (210) respectively. The length of the pull ropes (220) increases from top to bottom. During the test, the tension ropes (220) are pulled straight from top to bottom. First, the tension rope (220) at the top is pulled straight, and then the tension ropes (220) below are pulled straight in turn, so that the tension is gradually increased. The two ends of the pull rope (231) are fixed to the sliding shell (233) and the mounting ball (210) respectively. The electromagnet (234) is fixed inside the sliding shell (233). One end of the pull rope (232) is fixed to the magnet (235). The magnet (235) is slidably set inside the sliding shell (233). In the initial state of the test, the electromagnet (234) is energized and attracts the magnet (235). When the test drone (300) is subjected to shock, the electromagnet (234) is de-energized, cancels the attraction to the magnet (235), and causes the pull rope one (231) and pull rope two (232) to break, immediately changing the stress state of the drone (300). The number of water pump (240), delivery pipe (250) and water bag (260) is the same as the number of pulling rope (220), and they correspond one-to-one; The water bladder (260) is ring-shaped and fixed to the outer ring of the pull rope (220); The first water pump (240) is fixed on one side of the two upright plates (130) that are close to each other. The output end of the first water pump (240) is fixed with a delivery pipe (250). The end of the delivery pipe (250) away from the first water pump (240) is connected to the water bag (260).

2. The aircraft training, production, and testing equipment as described in claim 1, characterized in that, The pull rope (220) is made of rubber.

3. The aircraft training, production, and testing equipment as described in claim 1, characterized in that, The sliding shell (233) is hollow inside and cylindrical in shape. A pull rope (231) is fixed to one end of the sliding shell (233). The electromagnet (234) is fixed inside the sliding shell (233) at one end near the pull rope (231); The fractured component (230) also includes a sliding opening (236), and the sliding shell (233) has a sliding opening (236) at the end away from the electromagnet (234), and the second pull rope (232) is set through the sliding opening (236); Multiple ventilation holes are opened on the surface of the sliding shell (233).

4. The aircraft training, production, and testing equipment as described in claim 1, characterized in that, The test component (100) also includes a platform (110) and a buffer pad (120). The buffer pad (120) is fixed on the platform (110), and there are two upright plates (130), which are symmetrically fixed on both sides of the buffer pad (120); It also includes a detector (400); The detector (400) is detachably mounted on the drone (300), and during detection, the drone (300) is placed on the buffer pad (120); The detector (400) includes a gyroscope, accelerometer, altimeter, magnetometer, and vibration sensor.

5. The aircraft training and production testing equipment as described in claim 1, characterized in that, There are four tension components (200), with two tension components (200) symmetrically arranged on the same vertical plate (130). The test component (100) also includes a binding component (150), the number of which is the same as the number of the tension component (200), and they correspond one-to-one; The fastener (150) includes a fixing ball (151), a binding rope (152), a fixing block (153), and a screw cap (154); The fixed ball (151) is fixed to the end of the second rope (232) away from the magnet (235); There are two binding ropes (152) and two fixing blocks (153), and they correspond one to one. One end of the binding rope (152) is fixed to the fixing ball (151), and the fixing block (153) is fixed to the end of the binding rope (152) away from the fixing ball (151). The fixing block (153) is a half-cylinder shape, and the outer ring of the fixing block (153) is threaded; When the two fixing blocks (153) are in contact with each other, they form a cylindrical shape. The screw cap (154) is threaded onto the two fixing blocks (153) and is used to lock the two fixing blocks (153).

6. The aircraft training and production testing equipment as described in claim 5, characterized in that, The test assembly (100) also includes adjustment components (140), the number of which is consistent with the sum of the number of pull ropes (220) in the multiple pull assemblies (200), and they correspond one-to-one; The adjusting component (140) includes a fixing plate (141), an airbag (142), a limiting telescopic rod (143), an air pump (144), and an air supply pipe (145). The airbag (142) is ring-shaped, and one end of the airbag (142) is fixed to the side of the upright plate (130) away from the buffer pad (120); The fixing plate (141) is fixed to the end of the airbag (142) away from the upright plate (130), and the two ends of the limiting telescopic rod (143) are fixed to the fixing plate (141) and the upright plate (130) respectively; The end of the pull rope (220) away from the mounting ball (210) passes through the fixed plate (130) and is fixed to the fixed plate (141) with the airbag (142); One end of the pull rope (220) is fixed to the mounting ball (210), and the pull rope (220) is slidably connected to the upright plate (130); The air pump (144) is fixed on the upright plate (130), and the air supply pipe (145) is fixed at the output end of the air pump (144). The end of the air supply pipe (145) away from the air pump (144) is connected to the air bag (142).

7. The aircraft training, production, and testing equipment as described in claim 1, characterized in that, The tensioning assembly (200) also includes a regulating pipe (270) and a second water pump (280); There is one regulating pipe (270) and one water pump (280), which correspond to the bottommost pull rope (220) and the bottommost fixing plate (141); The bottom pull rope (220) is hollow inside, and the adjusting tube (270) is fixed inside the pull rope (220). The two ends of the adjusting tube (270) are fixed on the bottom fixing plate (141) and the mounting ball (210). Pump 2 (280) is fixed on the bottom fixing plate (141), and the output end of pump 2 (280) is connected to the regulating pipe (270).

8. The aircraft training and production testing equipment as described in claim 7, characterized in that, The regulating tube (270) is a polyurethane hose.

9. The aircraft training and production testing equipment as described in claim 8, characterized in that, Height calculation: Where h(t) is the vertical displacement of the binding point of the UAV (300) relative to the take-off point, and the maximum flight height of the UAV (300) is the length of the bottom pull rope (220) plus the height of the bottom pull rope (220) from the ground. v is the speed at which the UAV (300) rises at a constant speed, and t is the time calculated from the start of takeoff; Calculation of tension in the 220-meter rope: in, Let be the tension generated by the i-th pulling rope (220); Let be the elastic coefficient of the i-th tension rope (220); h(t) is the vertical displacement of the UAV (300) binding point relative to the takeoff point. ; Let be the natural length of the i-th tension rope (220), the length when it is not under force; Calculation of the elastic coefficient of the tension rope (220): Where E is the Young's modulus of the tension rope (220) material; A is the cross-sectional area of ​​the tension rope (220). Original length; Sum of total tensile forces in a single tension component (200): Where n is the total number of pull ropes (220) in a single pull assembly (200), The total elastic tension of all the tension ropes (220) of a single tension component (200) acting on the drone (300); When the UAV (300) hovers or ascends at a constant speed, the total rotor thrust is balanced with the total downward force acting on it: Where m is the mass of the tested UAV (300), and g is the acceleration due to gravity. The total elastic tension of all the tension ropes (220) of a single tension component (200) acting on the drone (300); Additional load of water bladder (260): The total constraint force applied to the drone (300) is the sum of the elastic tensions of all the tension ropes (220) in the single tension assembly (200) currently being tested. Added gravity with water bladder (260) sum; in, Additional gravity exerted on the drone (300) by filling the water bladder (260) with water; The mass of water injected into the water bladder (260); g is the acceleration due to gravity; Acceleration after rope 1 (231) and rope 2 (232) break: Where a represents the sudden acceleration change of the UAV (300) at the moment of fracture; The sum of elastic tensions that will disappear at the moment of breakage is the total elastic tension exerted by the tension rope (220) on the drone (300) in the single tension component (200) that is about to break at the moment of breakage, excluding the additional gravity of the water bladder (260), which will become zero instantly after breakage; m is the mass of the UAV (300).

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