Low-altitude aircraft capable of preventing rotor wing from being broken

Abstract

The invention relates to the technical field of low-altitude aircrafts, in particular to a low-altitude aircraft capable of preventing rotor wing breakage. Comprising a base; the connecting frame is fixedly connected to the base; the lifting mechanisms are arranged on the adjacent connecting frames, each lifting mechanism comprises a power motor, and an output shaft of each power motor is fixedly connected with a rotor wing; the hydraulic telescopic rod is fixedly connected to the base, and a supporting frame is hinged to the telescopic end of the hydraulic telescopic rod; the communicating shell is fixedly connected to the base, and the hydraulic telescopic rod communicates with the communicating shell through a first liquid conveying pipe; and the sealing assembly is arranged on the communicating shell and used for adjusting the communicating relation among the four hydraulic telescopic rods. The four hydraulic telescopic rods communicate with the communicating shell, so that the extension amount of the telescopic ends of the hydraulic telescopic rods is adjusted in the descending process of the aircraft, the aircraft is kept in a horizontal state after landing, the aircraft adapts to the uneven ground, and the probability that rotors are damaged in the descending process of the aircraft is reduced.

Description

Technical Field

[0001] The invention relates to the technical field of low-altitude aircraft, and in particular to a low-altitude aircraft with an anti-rotor wing breakage function. Background Art

[0002] Low-altitude aircraft refers to aircraft that mainly operate within a range below 1,000 meters. Existing low-altitude aircraft mainly include fixed-wing aircraft and rotary-wing aircraft. Among them, rotary-wing aircraft have the function of vertical ascent and descent, have low requirements for the take-off and landing environment, and can also take off and take off in the wild. Therefore, they are widely used in the fields of surveying and exploration. Existing rotary-wing aircraft (referred to as aircraft) mostly adopt a multi-rotor structure, and in order to ensure the stability of the aircraft during flight and facilitate the inspection and maintenance of the rotor, the rotor is mostly located at the lower part of the aircraft. Since most of the existing aircraft support frames are fixed U-shaped structures, when an emergency situation occurs during the flight of the aircraft and an emergency landing is required, if the ground where the aircraft lands is uneven, the aircraft's support frame will be in contact with the ground, and the aircraft's rotor will be in contact with the ground, resulting in damage to the rotor and inability to continue to be used. Summary of the invention

[0003] The invention provides a low-altitude aircraft with an anti-rotor wing breakage, in order to overcome the problem that the rotor wing of the aircraft is easily in contact with the ground and damaged when the aircraft lands on an uneven ground.

[0004] The technical implementation scheme of the present invention is: a low-altitude aircraft for preventing rotor wing breakage, comprising: a base, a shell is arranged on the upper side of the base; four connecting frames, all of which are fixedly connected to the base; a lifting mechanism, the number of which is the same as the number of the connecting frames, respectively arranged on adjacent connecting frames, the lifting mechanism is used to drive the base to move, the lifting mechanism comprises: a power motor, the output shaft of the power motor is fixedly connected to the rotor; a hydraulic telescopic rod, the number of which is the same as the number of the connecting frames, all of which are fixedly connected to the base, the telescopic end of the hydraulic telescopic rod is hinged with a support frame, and a first torsion spring is arranged between the two; a connecting shell, fixedly connected to the base, the hydraulic telescopic rod is connected to the connecting shell through a first infusion tube; a sealing assembly, arranged on the connecting shell, for adjusting the connection relationship between the four hydraulic telescopic rods.

[0005] Furthermore, the sealing assembly includes: a sealing ring, which is rotatably connected in the connecting shell, a sealing shell is slidably connected in the connecting shell, a first spring is arranged between the sealing shell and the connecting shell, and the sealing shell is slidably connected to the sealing ring; there are two sealing plates, both of which are slidably connected to the sealing shell, a first tension spring is arranged between the sealing plate and the sealing shell, and the connecting shell and the sealing ring are both slidably connected to the sealing plate; a power assembly is arranged on the base, and is used to drive the sealing plate to move; a rotating assembly is arranged on the base, and is used to drive the sealing shell to rotate.

[0006] Furthermore, the power assembly includes: a sliding rod, which is slidably connected to the sealing shell, a second spring is arranged between the sealing shell and the sliding rod, and the sliding rod is slidably connected to the connecting shell; an extrusion block, which is fixed to the sliding rod, and the sealing plate is extruded and matched with the extrusion block; a first electric push rod, which is fixed to the base, and the telescopic end of the first electric push rod is fixedly connected to an adjustment frame, and the adjustment frame is rotatably connected to the sliding rod.

[0007] Furthermore, the rotating component includes: a transmission motor fixedly connected to the base; a spline shell fixedly connected to the output shaft of the transmission motor, the spline shell is rotationally connected to the base, and the spline shell is spline-connected to the sealing shell; a detection component is arranged on the support frame, and is used to detect whether the support frame is in contact with the ground.

[0008] Furthermore, the detection component includes: detection plates, the number of which is the same as the number of the support frames, which are respectively slidably connected to adjacent support frames, the support frames are provided with detection cavities, the detection plates are located in the detection cavities, a third spring is provided between the detection plates and the support frames, and the detection cavity of the support frames is connected to the connecting shell through a connecting pipe; a limit ring, which is slidably connected in the connecting shell, the limit ring is slidably connected to the sealing shell, and a fourth spring is provided between the sealing shell and the limit ring; a limit assembly, which is provided on adjacent hydraulic telescopic rods and is used to limit the moving distance of the telescopic portion of the hydraulic telescopic rod.

[0009] Furthermore, the limit assembly includes: limit shells, the number of which is the same as the number of the hydraulic telescopic rods, which are respectively fixed to and connected to the fixed parts of the adjacent hydraulic telescopic rods, and the limit shells are connected to the connecting shells through air pipes; a limit rod, which is slidably connected in the limit shell, and a second tension spring is arranged between the limit rod and the limit shell, and the limit rod is limitedly matched with the telescopic part of the hydraulic telescopic rod.

[0010] Furthermore, it also includes: an electric slide rail, which is fixedly connected to the connecting frame, a slider is arranged in the electric slide rail, and the power motor is fixedly connected to the slider; fixing components, the number of which is the same as the number of the power motors, are respectively arranged on adjacent connecting frames, and are used to strengthen the fixation of the power motors; adjustment mechanisms, the number of which is the same as the number of the power motors, are respectively arranged on adjacent connecting frames, and are used to detect the moving distance of the telescopic end of the hydraulic telescopic rod.

[0011] Furthermore, the fixing assembly includes: a second electric push rod, fixedly connected in the connecting frame, the telescopic end of the second electric push rod is fixedly connected with an adjustable telescopic rod, and the adjustable telescopic rod is slidably connected to the connecting frame; a fixing plate, fixedly connected to the telescopic end of the adjustable telescopic rod, and the fixing plate is slidably connected to the connecting frame; a fixing frame, the number of which is twice that of the connecting frame, hinged to the connecting frame, and a second torsion spring is arranged between the fixing frame and the connecting frame, the fixing frame is limitedly matched with the power motor, and the fixing frame is extrusion-matched with the fixing plate.

[0012] Furthermore, the adjusting mechanism includes: a sliding tube, fixed in the connecting frame, the sliding tube is slidably connected with a lifting frame, the lifting frame is fixed to the power motor, an adjusting plate is slidably connected in the sliding tube, and the adjusting plate is squeezed and matched with the lifting frame; an extrusion rod, fixed to the telescopic end of the hydraulic telescopic rod; a liquid storage tube, fixed to the base, the adjusting telescopic rod and the sliding tube are both connected to the liquid storage tube through a second liquid infusion tube, the liquid storage tube is slidably connected to a limiting frame, a third tension spring is arranged between the liquid storage tube and the limiting frame, and the limiting frame is squeezed and matched with the extrusion rod; an adjusting block, slidably connected in the liquid storage tube, a fourth tension spring is arranged between the adjusting block and the liquid storage tube, and the limiting frame is limitedly matched with the adjusting block.

[0013] Furthermore, a through hole is provided on the portion of the lifting frame located inside the sliding tube.

[0014] The beneficial effects of the present invention are as follows: 1. During the descent of the aircraft, the present invention connects with the connecting shell through four hydraulic telescopic rods, so that the extension amount of the telescopic ends of the hydraulic telescopic rods can be adjusted during the descent of the aircraft, so that the aircraft can maintain a horizontal state after landing, thereby adapting to the unevenness of the ground and reducing the probability of damage to the rotor during the descent of the aircraft.

[0015] 2. When the aircraft deviates, the present invention separates the connecting shell by a sliding rod and adjusts the connection relationship between the four hydraulic telescopic rods, so that only the two hydraulic telescopic rods on the deviated side of the aircraft are connected, thereby individually leveling the deviated side of the aircraft to ensure that the rotor does not contact the ground.

[0016] 3. When the aircraft deviates, the present invention detects the direction of the aircraft deflection through a gyroscope and activates the electric slide rail at the corresponding position, so that the electric slide rail drives the rotor at that position to move upward away from the ground, thereby reducing the probability of the rotor contacting the ground. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention; Figure 2 It is a three-dimensional structural schematic diagram of the connecting frame, hydraulic telescopic rod and supporting frame of the present invention; Figure 3 It is a schematic diagram of the three-dimensional structure of the connecting shell, the first electric push rod and the adjustment frame of the present invention; Figure 4 It is a schematic diagram of the three-dimensional structure of the sealing ring, the sealing shell and the sliding rod of the present invention; Figure 5 It is a three-dimensional structural cross-sectional view of the connecting shell, the sealing ring and the limiting ring of the present invention; Figure 6 It is a three-dimensional structural cross-sectional view of the sealing ring, the sealing shell and the sealing plate of the present invention; Figure 7 It is a three-dimensional structural cross-sectional view of the hydraulic telescopic rod and the limiting shell of the present invention; Figure 8 It is a schematic diagram of the three-dimensional structure of the power motor, rotor and fixing frame of the present invention; Fig. 9 It is a schematic diagram of the three-dimensional structure of the power motor, the fixing plate and the lifting frame of the present invention; Fig.10 It is a three-dimensional structural cross-sectional view of the connecting frame, the adjustable telescopic rod and the fixing frame of the present invention; Fig.11 It is a three-dimensional structural schematic diagram of the fixing frame, the sliding tube and the lifting frame of the present invention; Fig.12 It is a three-dimensional structural schematic diagram of the connecting frame, the electric slide rail and the power motor of the present invention; Fig.13 It is a three-dimensional structural cross-sectional view of the liquid storage tube and the regulating block of the present invention.

[0018] Figure markings: 1-base, 2-casing, 3-connecting frame, 4-lifting mechanism, 5-hydraulic telescopic rod, 6-support frame, 7-connecting shell, 8-sealing ring, 9-sealing shell, 10-sealing plate, 11-sliding rod, 12-extrusion block, 13-first electric push rod, 14-adjusting frame, 15-transmission motor, 16-spline shell, 17-detection plate, 18-limiting ring, 19-limiting shell, 20-limiting rod, 401-electric slide rail, 402-power motor, 403-rotor, 404-second electric push rod, 405-adjusting telescopic rod, 406-fixed plate, 407-fixed frame, 408-sliding tube, 409-lifting frame, 410-adjusting plate, 411-extrusion rod, 412-liquid storage tube, 413-limiting frame, 414-adjusting block. DETAILED DESCRIPTION

[0019] The present invention will be further described below in conjunction with specific embodiments. The illustrative embodiments and descriptions of the present invention are used to explain the present invention but are not intended to limit the present invention.

[0020] A low-altitude aircraft with a rotor wing breakage prevention function, such as Figure 1-Figure 6 As shown, it includes: a base 1, a housing 2 is arranged on the upper side of the base 1; four connecting frames 3 are provided, all of which are fixedly connected to the base 1; a lifting mechanism 4, the number of which is the same as the number of the connecting frames 3, and is respectively arranged on adjacent connecting frames 3, the lifting mechanism 4 is used to drive the base 1 to move, and the lifting mechanism 4 includes: a power motor 402, the output shaft of the power motor 402 is fixedly connected to a rotor 403; hydraulic telescopic rods 5, the number of which is the same as the number of the connecting frames 3, all of which are fixedly connected to the base 1, the telescopic ends of the hydraulic telescopic rods 5 are hinged to a support frame 6, and a first torsion spring is arranged between the two; a connecting shell 7, which is fixedly connected to the base 1, and the hydraulic telescopic rod 5 is connected to the connecting shell 7 through a first infusion tube; a sealing component is arranged on the connecting shell 7, and is used to adjust the connection relationship between the four hydraulic telescopic rods 5.

[0021] In the above scheme, a method is proposed to keep the aircraft level on uneven ground, aiming to solve the problem that when the existing aircraft lands on uneven ground, the fuselage cannot be kept level during the landing process, which makes the rotor 403 easily contact with the ground and damaged; the left and right sides of the lower part of the base 1 are chamfered, and the edge of the chamfer of the lower part of the base 1 is rounded to reduce the resistance of the airflow to it when the base 1 moves; the upper part of the casing 2 is streamlined to reduce the resistance of the airflow when it moves, and the front and rear sides of the casing 2 are provided with doors for the staff to enter the casing 2, and the connecting frame 3 is a hollow structure to reduce the total weight of the device; the lifting mechanism 4 is used to drive the bottom The seat 1 rises, and the power motor 402 is a dual-axis motor. The two output shafts of the power motor 402 are fixedly connected to the rotor 403, which is used to ensure that the device has sufficient power when rising; the hydraulic telescopic rod 5 is used to adjust the distance between the support frame 6 and the base to ensure that the base 1 is in a horizontal state during the descent, and in this process, the telescopic end of the hydraulic telescopic rod 5 in a high position is retracted, and the hydraulic oil therein flows into the hydraulic telescopic rod 5 at a lower position through the connecting shell 7, so that the telescopic end of the hydraulic telescopic rod 5 at a lower position extends, so that the support frame 6 here can contact the ground in advance and provide support, so that the base 1 is level, and the support frame 6 is used to adapt to the inclination angle of the ground and increase the contact area between the support frame 6 and the ground.

[0022] Further, such as Figure 4-Figure 6 As shown, the sealing assembly includes: a sealing ring 8, which is rotatably connected in the connecting shell 7, a sealing shell 9 is slidably connected in the connecting shell 7, a first spring is arranged between the sealing shell 9 and the connecting shell 7, and the sealing shell 9 is slidably connected to the sealing ring 8; there are two sealing plates 10, both of which are slidably connected to the sealing shell 9, a first tension spring is arranged between the sealing plate 10 and the sealing shell 9, and the connecting shell 7 and the sealing ring 8 are both slidably connected to the sealing plate 10; a power assembly, which is arranged on the base 1, and is used to drive the sealing plate 10 to move; a rotating assembly, which is arranged on the base 1, and is used to drive the sealing shell 9 to rotate.

[0023] In the above scheme, when the aircraft is deflected by strong wind, the connection relationship between the four hydraulic telescopic rods 5 is controlled so that the side that lands first when the aircraft deflects is level, the axes of the connecting shell 7, the sealing ring 8 and the sealing shell 9 are coaxial, and the sealing shell 9 is used to drive the two sealing plates 10 to move; the sealing ring 8 divides the connecting shell 7 into two upper and lower chambers, and the hydraulic telescopic rod 5 is connected to the upper chamber of the connecting shell 7, and the sealing shell 9 cooperates with the two sealing plates 10 to further divide the upper chamber of the connecting shell 7 into two front and rear chambers (with Figure 6, so that the four hydraulic telescopic rods 5 are connected in pairs. The outer sides of the two sealing plates 10 are both arc surfaces, and the curvature of the arc surfaces is the same as the curvature of the inner side surfaces of the connecting shell 7, so that the sealing plate 10 and the connecting shell 7 can fit tightly, thereby ensuring the sealing between the sealing plate 10 and the connecting shell 7. The sealing ring 8 is provided with two sliding grooves, and the sealing plate 10 can cover the adjacent sliding grooves of the sealing ring 8. After the sealing plate 10 divides the upper chamber of the connecting shell 7 into two, the hydraulic oil in the two chambers cannot circulate with each other through the sliding grooves of the sealing ring 8, and the lower part of the sealing plate 10 is always located in the sliding groove of the sealing ring 8, so that there is no relative rotation between the sealing plate 10 and the sealing ring 8. The power component is used to drive the sealing plate 10 to move, so that the sealing plate 10 separates the upper chamber of the connecting shell 7; the rotating component is used to drive the sealing shell 9 to rotate, so that the angle of the sealing plate 10 changes, thereby adjusting the connection relationship between the four hydraulic telescopic rods 5.

[0024] Working process: When the aircraft encounters an emergency and needs to land, if there is no strong wind affecting the landing of the aircraft, the aircraft maintains a horizontal and vertical movement downward. If the ground is level, the four support frames 6 are in contact with the ground at the same time, the extension distance of the telescopic part of the hydraulic telescopic rod 5 remains unchanged, and the aircraft lands normally. If the ground is not level, for example, the left side of the ground is lower than the right side, as the aircraft moves downward, the support frame 6 on the right side first contacts the ground and stops moving after contact. As the aircraft continues to move downward, the telescopic part of the hydraulic telescopic rod 5 on the right is compressed, and the hydraulic oil in the hydraulic telescopic rod 5 on the right side enters the hydraulic telescopic rod 5 on the left side through the connecting shell 7, so that the telescopic end of the left hydraulic telescopic rod 5 extends and drives the support frame 6 on it to move downward, until the support frame 6 on the left side contacts the ground and stops moving. At this time, all four support frames 6 stop moving, and the support frame 6 completes the landing.

[0025] When the aircraft is tilted to one side due to the influence of wind during the descent process, taking the case where the right side of the aircraft is tilted downward and the front side of the ground is higher than the rear side as an example, after the fuselage tilt is detected, the power assembly and the rotating assembly are started at the same time, and the power assembly drives the two sealing plates 10 to move, so that the sealing plates 10 move and stretch the first tension spring until the outer side surface of the sealing plate 10 fits with the inner side surface of the connecting shell 7 and stops moving. The two sealing plates 10 and the sealing shell 9 divide the upper chamber of the connecting shell 7 into two. During this process, the rotating assembly drives the sealing shell 9 to rotate, and the sealing shell 9 drives the sealing plate 10 to rotate and adjust the position of the two upper chambers of the connecting shell 7 until the sealing plate 10 is facing front and back. The upper chamber of the connecting shell 7 is divided into two left and right chambers, so that the two hydraulic telescopic rods 5 on the right side are connected to the upper right chamber of the connecting shell 7, and the two hydraulic telescopic rods 5 on the left side are connected to the upper left chamber of the connecting shell 7. As the aircraft moves downward, when the right front support frame 6 contacts the ground, the telescopic end of the right front hydraulic telescopic rod 5 is compressed, and the hydraulic oil therein enters the right After the vehicle is level, the hydraulic oil in the four hydraulic telescopic rods 5 stops flowing, and then the rotating assembly drives the sealing shell 9 and the parts thereon to move in the opposite direction and reset.

[0026] Further, such as Figure 3-Figure 6 As shown, the power assembly includes: a sliding rod 11, which is slidably connected to the sealing shell 9, a second spring is arranged between the sealing shell 9 and the sliding rod 11, and the sliding rod 11 is slidably connected to the connecting shell 7; an extrusion block 12, which is fixed to the sliding rod 11, and the sealing plate 10 is extruded and matched with the extrusion block 12; a first electric push rod 13, which is fixed to the base 1, and the telescopic end of the first electric push rod 13 is fixedly connected to the adjustment frame 14, and the adjustment frame 14 is rotatably connected to the sliding rod 11.

[0027] The above scheme is used to adjust the connection relationship between the four hydraulic telescopic rods 5 when the aircraft is deflected by strong wind during the landing process of the aircraft, so that the part of the aircraft that first contacts the ground remains horizontal, reducing the probability of the rotor 403 being damaged by contact with the ground. The elastic coefficient of the second spring on the sliding rod 11 is smaller than the elastic coefficient of the first spring on the sealing shell 9, so that when the sliding rod 11 moves downward, the sealing shell 9 and the parts thereon do not move; the side of the extrusion block 12 is set as an inclined surface, and the edge of the inclined surface gradually approaches the axis of the sliding rod 11 from top to bottom, and the sealing plate 10 is provided with a limiting groove, and the inner side of the limiting groove is provided with a There is an inclined surface, and the extrusion block 12 is always located in the limiting groove of the sealing plate 10; the adjustment frame 14 is used to drive the sliding rod 11 to move, so that the sliding rod 11 drives the extrusion block 12 to move downward and squeeze the sealing plate 10. A gyroscope is arranged in the base 1. The gyroscope is an existing device and will not be described in detail. The gyroscope is used to check whether the aircraft itself is deflected. The first electric push rod 13 is electrically connected to the gyroscope. When the aircraft is deflected by wind during descent, the gyroscope detects the direction of the aircraft's deflection and transmits a signal to the first electric push rod 13. The first electric push rod 13 is started and its telescopic end drives the sliding rod 11 to move.

[0028] Further, such as Figure 4-Figure 5 As shown, the rotating component includes: a transmission motor 15, fixedly connected to the base 1; a spline shell 16, fixedly connected to the output shaft of the transmission motor 15, the spline shell 16 is rotationally connected to the base 1, and the spline shell 16 is spline-connected to the sealing shell 9; a detection component is arranged on the support frame 6, and is used to detect whether the support frame 6 is in contact with the ground.

[0029] The above scheme is used to adjust the connectivity of the four hydraulic telescopic rods 5 according to the direction of the aircraft's deflection. After the gyroscope detects the direction of the aircraft's deflection, it transmits a signal to the transmission motor 15. The output shaft of the transmission motor 15 drives the spline housing 16 to rotate a specified angle according to the received signal. A spline groove is provided in the spline housing 16. The sealing housing 9 is composed of a spline rod and a piston rod, and the piston rod is located in the connecting housing 7. Initially, the upper side surface of the piston rod on the sealing housing 9 is in contact with the upper side of the connecting housing 7, and the spline rod slides in the spline groove in the spline housing 16. The detection component is used to detect whether the four support frames 6 are in contact with the ground. After the four support frames 6 are in contact with the ground, the sealing plate 10 is released to separate the upper chamber of the connecting housing 7, so that the four hydraulic telescopic rods 5 are connected to each other through the connecting housing 7.

[0030] Further, such as Figure 3-Figure 6As shown, the detection component includes: detection plates 17, the number of which is the same as the number of support frames 6, which are respectively slidably connected to adjacent support frames 6, the support frame 6 is provided with a detection cavity, the detection plate 17 is located in the detection cavity, a third spring is arranged between the detection plate 17 and the support frame 6, and the detection cavity of the support frame 6 is connected with the connecting shell 7 through a connecting pipe; a limit ring 18, which is slidably connected in the connecting shell 7, the limit ring 18 is slidably connected to the sealing shell 9, and a fourth spring is arranged between the sealing shell 9 and the limit ring 18; a limit assembly, which is arranged on the adjacent hydraulic telescopic rod 5, and is used to limit the moving distance of the telescopic part of the hydraulic telescopic rod 5.

[0031] The above scheme is used to detect whether the four support frames 6 are in contact with the ground. The detection plate 17 is located below the support frame 6 and is used to detect whether the support frame 6 is in contact with the ground. The detection chamber of the support frame 6 is filled with gas. A limit ring 18 is slidably connected in the connecting shell 7. The limit ring 18 is located between the piston plate and the sealing ring 8 of the sealing shell 9, so that the limit ring 18 squeezes the sealing shell 9 downward, thereby pushing the sealing shell 9 to move downward. The connecting point between the connecting shell 7 and the support frame 6 is located between the sealing ring 8 and the limit ring 18, and the elastic coefficient of the fourth spring on the limit ring 18 is smaller than the elastic coefficient of the first spring on the sealing shell 9, which is used to compress the fourth spring on the limit ring 18 first and then push the sealing shell 9 to move; the limit assembly is used to limit the distance moved by the telescopic end of the hydraulic telescopic rod 5 to prevent the telescopic end of the hydraulic telescopic rod 5 from shrinking too much when the ground drop is too large, resulting in the risk of the rotor 403 still contacting the ground.

[0032] Further, such as Figure 3 and Figure 7 As shown, the limit assembly includes: limit shells 19, the number of which is the same as the number of hydraulic telescopic rods 5, which are respectively fixedly connected to and connected to the fixed parts of adjacent hydraulic telescopic rods 5, and the limit shells 19 are connected to the connecting shell 7 through an air pipe; a limit rod 20, which is slidably connected in the limit shell 19, and a second tension spring is arranged between the limit rod 20 and the limit shell 19, and the limit rod 20 is limitedly matched with the telescopic part of the hydraulic telescopic rod 5.

[0033] The above scheme is used to limit the moving distance of the telescopic part of the hydraulic telescopic rod 5, to prevent the telescopic end of the hydraulic telescopic rod 5 from contracting excessively and causing the rotor 403 to be damaged by contact with the ground. The connection between the connecting shell 7 and the limiting shell 19 is located at the bottom of the connecting shell 7. In the process of the sealing shell 9 gradually moving downward, the limiting rod 20 gradually leaves the upper side of the telescopic part of the hydraulic telescopic rod 5, thereby releasing the limitation of the telescopic part of the hydraulic telescopic rod 5. One end of the limiting rod 20 located in the hydraulic telescopic rod 5 is a ball head, which is used to reduce the wear caused by friction between the limiting rod 20 and the hydraulic telescopic rod 5.

[0034] Working process: When the above-mentioned aircraft is deflected and moves downward due to strong wind, the gyroscope transmits signals to the first electric push rod 13 and the transmission motor 15, and the telescopic end of the first electric push rod 13 drives the adjustment frame 14 to move downward, and the adjustment frame 14 drives the sliding rod 11 to move downward and compress the second spring, and the sliding rod 11 drives the extrusion block 12 to move downward to squeeze the sealing plate 10, until the sealing plate 10 is in contact with the inner side of the connecting shell 7, the first electric push rod 13 is closed, and the sliding rod 11 stops moving. While the telescopic end of the first electric push rod 13 moves, the output shaft of the transmission motor 15 drives the spline shell 16 to rotate, and the spline shell 16 drives the sealing shell 9 to rotate, so that the sealing shell 9 drives the two sealing plates 10 to rotate synchronously, thereby adjusting the position where the upper chamber of the connecting shell 7 is separated, until the direction of the sealing plate 10 is front-to-back, and the output shaft of the transmission motor 15 stops driving.

[0035] As the aircraft moves downward, the detection plate 17 on the right side contacts the ground, and the detection plate 17 moves upward relative to the support frame 6 and compresses the third spring. The gas in the support frame 6 enters between the sealing ring 8 and the limit ring 18, causing the limit ring 18 to move downward and compress the fourth spring. Until the fourth spring is fully compressed, the telescopic end of the hydraulic telescopic rod 5 begins to be compressed. If the ground deflection is small, during this process, when the telescopic part of the hydraulic telescopic rod 5 does not contact the limit rod 20, the left part of the aircraft moves downward and contacts the ground. If the ground deflection is large, as the telescopic part of the hydraulic telescopic rod 5 moves upward, when the telescopic part of the hydraulic telescopic rod 5 contacts the limit rod 20, the telescopic parts of the two hydraulic telescopic rods 5 on the right side stop moving. At this time, the right front hydraulic telescopic rod The position of the retraction rod 5 is higher than that of the right rear hydraulic telescopic rod 5. The aircraft first deflects backward to make the right rear detection plate 17 contact the ground to avoid excessive compression of the right front hydraulic telescopic rod 5, which causes the rotor 403 to contact the ground and be damaged. When the detection plates 17 on the right side are in contact with the ground, the detection plate 17 on the right rear side moves upward relative to the adjacent support frame 6, so that the gas in the right rear support frame 6 enters between the sealing ring 8 and the limit ring 18, the limit ring 18 moves downward and the fourth spring is compressed again, and the left part of the aircraft moves downward and contacts the ground, and the two detection plates 17 on the left repeat the above process and contact the ground, and the gas in the two left support frames 6 gradually enters between the sealing ring 8 and the limit ring 18 to push the limit ring 18 to move downward.

[0036] During the downward movement of the above-mentioned limit ring 18, when the fourth spring on the limit ring 18 cannot be compressed, the limit ring 18 pushes the sealing shell 9 downward through the fourth spring, and the sealing shell 9 drives the sealing plate 10 to move downward and compresses the first spring, so that the chambers on both sides of the upper part of the connecting shell 7 are connected, and the sealing plate 10 is reset under the drive of the first tension spring. During the downward movement of the sealing shell 9 by the limit ring 18, the gas in the lower chamber of the connecting shell 7 enters the four limit shells 19, pushing the limit rod 20 to move and stretching the second tension spring, and the limit rod 20 leaves from above the telescopic part of the hydraulic telescopic rod 5, releasing the limit on the telescopic parts of the four hydraulic telescopic rods 5, and the hydraulic oil in the four hydraulic telescopic rods 5 flows to each other to finally level the aircraft, and then the first electric push rod 13 drives the sliding rod 11 to move upward and reset, and the output shaft of the transmission motor 15 drives the sealing shell 9 to rotate and reset.

[0037] Further, such as Fig.11 and Fig.12 As shown, it also includes: an electric slide rail 401, which is fixedly connected to the connecting frame 3, a slider is arranged in the electric slide rail 401, and a power motor 402 is fixedly connected to the slider; a fixing component, the number of which is the same as the number of the power motors 402, which are respectively arranged on adjacent connecting frames 3, and are used to strengthen the fixation of the power motors 402; an adjusting mechanism, the number of which is the same as the number of the power motors 402, which are respectively arranged on adjacent connecting frames 3, and are used to detect the moving distance of the telescopic end of the hydraulic telescopic rod 5.

[0038] The above scheme is used to adjust the height of the rotor 403 in advance according to the direction of the aircraft deflection, thereby further reducing the probability of damage to the rotor 403. The connecting frame 3 is composed of a round tube and a rectangular block. The electric slide rail 401 is located on the rectangular block. The slider of the electric slide rail 401 can be pushed when it is powered off, and is used to drive the slider on it when the electric slide rail 401 fails or has other problems. The electric slide rail 401 is electrically connected to the gyroscope. After the gyroscope detects the deflection of the aircraft, the gyroscope transmits a signal to the two electric slide rails 401 in the direction of the aircraft deflection, so that the slider of the electric slide rail 401 drives the rotor 403 to move upward through the power motor 402, thereby increasing the distance between the rotor 403 on this side and the ground; the fixing component is used to strengthen the fixation of the power motor 402 to ensure the stable connection between the power motor 402 and the electric slide rail 401 during the flight of the aircraft; the adjustment mechanism is used to drive the power motor 402 at the corresponding position to move when the tilt direction of the ground is different from the deflection direction of the aircraft.

[0039] Further, such as Figure 8-Figure 11As shown, the fixing assembly includes: a second electric push rod 404, which is fixed in the connecting frame 3, and the telescopic end of the second electric push rod 404 is fixed with an adjusting telescopic rod 405, and the adjusting telescopic rod 405 is slidably connected to the connecting frame 3; a fixing plate 406, which is fixed to the telescopic end of the adjusting telescopic rod 405, and the fixing plate 406 is slidably connected to the connecting frame 3; a fixing frame 407, which is twice the number of the connecting frame 3, is hinged to the connecting frame 3, and a second torsion spring is arranged between the fixing frame 407 and the connecting frame 3, the fixing frame 407 is limitedly matched with the power motor 402, and the fixing frame 407 is squeezed with the fixing plate 406.

[0040] The above scheme is used to increase the connection strength between the power motor 402 and the electric slide rail 401 to prevent the two from sliding relative to each other during flight, thereby reducing the wear between the two. The connecting frame 3 is provided with a slide groove, and the fixed plate 406 is located in the slide groove for sliding. Both sides of the fixed plate 406 are provided with rounded corners to reduce the wear during its movement; the fixed frame 407 is composed of a U-shaped frame and a V-shaped rod, wherein the V-shaped rod has a long stem and a short rod, and the short rod is located on the side close to the U-shaped frame, which is used to amplify the squeezing force of the fixed plate 406 on the fixed frame 407 and act on the power motor 402 through the U-shaped frame. The second torsion spring of the fixed frame 407 is initially in a stored force state, and limiting blocks are provided at both ends of the U-shaped frame on the fixed frame 407. The power motor 402 is provided with a limiting groove, and the U-shaped frame limiting block is located in the limiting groove for fixing the power motor 402.

[0041] Working process: During the landing process of the above-mentioned aircraft, taking the right side of the ground tilting upward and the right side of the aircraft tilting downward as an example, the gyroscope detects the direction of the overall deflection of the fuselage, and then the gyroscope transmits the detection signal to the two electric slide rails 401 and the second electric push rod 404 on the right side, and the telescopic end of the second electric push rod 404 drives the fixed plate 406 to move by adjusting the telescopic rod 405, so that the fixed plate 406 reduces the squeezing force on the fixed frame 407, and the fixed frame 407 rotates under the action of the second torsion spring and separates from the limit groove of the power motor 402, thereby releasing the fixation of the power motor 402, and the electric slide rail 401 starts and drives the power motor 402 to move upward through the slider thereon, so that the power motor 402 drives the rotor 403 to move upward, so that The rotor 403 is moved away from the ground, thereby increasing the distance between the rotor 403 and the ground at this point. When the slider in the electric slide rail 401 moves upward to the limit position, the electric slide rail 401 is closed to complete the adjustment of the position of the rotor 403 on that side. After the position adjustment of the rotor 403 is completed, the staff repeats the above process to drive the aircraft to land. After the aircraft has landed, the staff moves the aircraft to a relatively flat position, and then starts the electric slide rail 401 to make the slider drive the power motor 402 to move downward and reset, and then starts the second electric push rod 404 to retract its telescopic end, adjusts the telescopic rod 405 to drive the fixing plate 406 to move and squeeze the fixing frame 407, and the fixing frame 407 rotates to store force in the second torsion spring and fix the power motor 402 again.

[0042] Further, such as Figure 8-Figure 13 As shown, the adjustment mechanism includes: a sliding tube 408, which is fixed in the connecting frame 3, the sliding tube 408 is slidably connected to the lifting frame 409, the lifting frame 409 is fixed to the power motor 402, and an adjustment plate 410 is slidably connected in the sliding tube 408, and the adjustment plate 410 is squeezed and matched with the lifting frame 409; an extrusion rod 411, which is fixed to the telescopic end of the hydraulic telescopic rod 5; a liquid storage tube 412, which is fixed to the base 1, the adjustment telescopic rod 405 and the sliding tube 408 are both connected to the liquid storage tube 412 through the second infusion tube, the liquid storage tube 412 is slidably connected to the limiting frame 413, a third tension spring is arranged between the liquid storage tube 412 and the limiting frame 413, and the limiting frame 413 is squeezed and matched with the extrusion rod 411; an adjustment block 414, which is slidably connected in the liquid storage tube 412, a fourth tension spring is arranged between the adjustment block 414 and the liquid storage tube 412, and the limiting frame 413 is limitedly matched with the adjustment block 414.

[0043] Further, such as Fig.12 As shown, the portion of the lifting frame 409 located inside the sliding tube 408 is provided with a through hole.

[0044] The above scheme is used to drive the rotor 403 of the aircraft which is at a high place and whose position is not adjusted to move upward when the deflection direction of the aircraft is different from the tilt direction of the ground and the gyroscope cannot adjust the position of the rotor 403 at a high place. A through hole is provided at the position of the lifting frame 409 located in the sliding tube 408. The through hole is used to make the part of the lifting frame 409 located in the sliding tube 408 communicate with each other up and down, so that when the power motor 402 moves upward, the lifting frame 409 can move upward together. The adjustment plate 410 is used to push the lifting frame 409 to move upward. After the hydraulic oil on the liquid storage tube 412 enters the sliding tube 408, the adjustment plate 410 squeezes the lifting frame 409 upward, so that the lifting frame 409 drives the power motor 402 to move upward, thereby The rotor 403 moves upward; the extrusion rod 411 is provided with an inclined surface, and the inclined surface faces upward, which is used to push the limit frame 413 to move. The limit frame 413 is composed of two round rods and a vertical plate. The two round rods are one long and one short and are both set as ball heads. The long round rod is located outside the liquid storage tube 412, and the long round rod of the limit frame 413 is squeezed and matched with the extrusion rod 411; the adjustment block 414 is provided with a limiting hole, and the depth of the limiting hole is greater than the radius of the short rod in the limiting frame 413, which is used to ensure the stability of the limiting frame 413 on the adjustment block 414. The elastic coefficient of the fourth tension spring on the adjustment block 414 is greater than the elastic coefficient of the elastic part in the adjustment telescopic rod 405, which ensures that the telescopic end of the adjustment telescopic rod 405 can drive the fixed plate 406 to move.

[0045] Working process: In the process of the above-mentioned aircraft descent, taking the case where the right side of the aircraft deflects downward and the rear side of the ground deflects upward as an example, during the descent of the aircraft, the gyroscope detects the direction of the aircraft fuselage deflection, and then the gyroscope transmits the detected signal to the two electric slide rails 401 on the right, so that the two rotors 403 on the right move upward, and then the aircraft gradually moves downward, and after the four detection plates 17 contact the ground, since the two hydraulic telescopic rods 5 on the rear side of the aircraft are in a high position, the telescopic ends of the two hydraulic telescopic rods 5 on the rear side are gradually retracted, and the telescopic ends of the two hydraulic telescopic rods 5 on the front side are gradually extended, so that the two rotors 403 on the rear side both move downward, and the two liquid storage tubes 412 on the rear side drive the parts thereon to move downward, and when the extrusion rod 411 contacts the limit frame 413, the extrusion rod 411 squeezes the limit frame 413 to the left, so that the limit frame 413 stretches the first The third tension spring releases the limit on the adjustment block 414. The adjustment block 414 moves upward under the drive of the fourth tension spring, and the hydraulic oil in the liquid storage tube 412 is sent into the adjustment telescopic rod 405, so that the telescopic end of the adjustment telescopic rod 405 extends and drives the fixed plate 406 to move. The squeezing force of the fixed plate 406 on the fixed frame 407 is reduced, so that the fixed frame 407 rotates under the action of the second torsion spring and releases the fixation of the power motor 402. Then the hydraulic oil enters the sliding tube 408. Since the rotor 403 on the right rear side has moved upward, the adjustment plate 410 there is separated from the lifting frame 409. At this time, the adjustment plate 410 on the right rear side only moves upward, and the adjustment plate 410 on the left rear side moves upward and pushes the lifting frame 409 to move synchronously, so that the lifting frame 409 drives the power motor 402 to move upward relative to the hydraulic telescopic rod 5, so that the rotor 403 on the left rear side rises and moves away from the ground.

[0046] The technical principles of the embodiments of the present invention are described above in conjunction with specific embodiments. These descriptions are only for explaining the principles of the embodiments of the present invention and cannot be interpreted in any way as limiting the protection scope of the embodiments of the present invention. Based on the explanations herein, those skilled in the art can think of other specific implementation methods of the embodiments of the present invention without creative work, and these methods will fall within the protection scope of the embodiments of the present invention.

Claims

1. A low-altitude aircraft with a rotor wing breakage prevention function. Its characteristics are: Included are: A base (1), wherein a housing (2) is provided on the upper side of the base (1); There are four connecting frames (3), all of which are fixedly connected to the base (1); The lifting mechanisms (4) are the same in number as the connecting frames (3) and are respectively arranged on adjacent connecting frames (3). The lifting mechanisms (4) are used to drive the base (1) to move. The lifting mechanisms (4) include: A power motor (402), wherein an output shaft of the power motor (402) is fixedly connected to a rotor (403); The number of hydraulic telescopic rods (5) is the same as that of the connecting frame (3), and both are fixedly connected to the base (1); the telescopic ends of the hydraulic telescopic rods (5) are hingedly connected to the supporting frame (6), and a first torsion spring is arranged between the two; A communication shell (7) is fixedly connected to the base (1), and the hydraulic telescopic rod (5) is connected to the communication shell (7) via a first liquid infusion tube; A sealing assembly is arranged on the communication shell (7) and is used to adjust the communication relationship between the four hydraulic telescopic rods (5).

2. A low-altitude aircraft for preventing rotor wing breakage according to claim 1, Its characteristics are: The sealing component comprises: A sealing ring (8) is rotatably connected in the connecting shell (7), a sealing shell (9) is slidably connected in the connecting shell (7), a first spring is provided between the sealing shell (9) and the connecting shell (7), and the sealing shell (9) is slidably connected to the sealing ring (8); There are two sealing plates (10), both of which are slidably connected to the sealing shell (9); a first tension spring is provided between the sealing plate (10) and the sealing shell (9); and both the connecting shell (7) and the sealing ring (8) are slidably connected to the sealing plate (10); A power assembly, arranged on the base (1) and used to drive the sealing plate (10) to move; A rotating assembly is arranged on the base (1) and is used to drive the sealing shell (9) to rotate.

3. A low-altitude aircraft for preventing rotor wing breakage according to claim 2, Its characteristics are: The power assembly includes: A sliding rod (11) is slidably connected to the sealing shell (9), a second spring is provided between the sealing shell (9) and the sliding rod (11), and the sliding rod (11) is slidably connected to the connecting shell (7); An extrusion block (12) is fixedly connected to the sliding rod (11), and the sealing plate (10) is extruded and matched with the extrusion block (12); A first electric push rod (13) is fixedly connected to the base (1); a telescopic end of the first electric push rod (13) is fixedly connected to an adjustment frame (14); and the adjustment frame (14) is rotatably connected to the sliding rod (11).

4. A low-altitude aircraft for preventing rotor wing breakage according to claim 3, Its characteristics are: The rotating assembly comprises: A transmission motor (15) is fixedly connected to the base (1); A spline housing (16) is fixedly connected to the output shaft of the transmission motor (15), the spline housing (16) is rotatably connected to the base (1), and the spline housing (16) is spline-connected to the sealing housing (9); A detection component is arranged on the support frame (6) and is used to detect whether the support frame (6) is in contact with the ground.

5. A low-altitude aircraft for preventing rotor wing breakage according to claim 4, Its characteristics are: The detection component includes: The number of detection plates (17) is the same as the number of the support frames (6), and they are respectively slidably connected to adjacent support frames (6); the support frames (6) are provided with detection cavities, the detection plates (17) are located in the detection cavities, a third spring is provided between the detection plates (17) and the support frames (6), and the detection cavities of the support frames (6) are connected to the connecting shell (7) via connecting pipes; a limiting ring (18) slidably connected in the connecting shell (7), the limiting ring (18) being slidably connected to the sealing shell (9), and a fourth spring being provided between the sealing shell (9) and the limiting ring (18); A limit assembly is arranged on an adjacent hydraulic telescopic rod (5) and is used to limit the moving distance of the telescopic portion of the hydraulic telescopic rod (5).

6. A low-altitude aircraft for preventing rotor wing breakage according to claim 5, Its characteristics are: The limit assembly includes: The limiting shells (19) are the same in number as the hydraulic telescopic rods (5), and are respectively fixedly connected to and communicated with the fixing parts of adjacent hydraulic telescopic rods (5); the limiting shells (19) are communicated with the communication shell (7) via an air pipe; The limiting rod (20) is slidably connected in the limiting shell (19), a second tension spring is provided between the limiting rod (20) and the limiting shell (19), and the limiting rod (20) is in limiting cooperation with the telescopic part of the hydraulic telescopic rod (5).

7. A low-altitude aircraft for preventing rotor wing breakage according to claim 1, Its characteristics are: Also included are: An electric slide rail (401) is fixedly connected to the connecting frame (3), a slider is provided inside the electric slide rail (401), and the power motor (402) is fixedly connected to the slider; Fixing components, the number of which is the same as the number of the power motors (402), are respectively arranged on adjacent connecting frames (3) and are used to strengthen the fixation of the power motors (402); The number of the adjustment mechanisms is the same as the number of the power motors (402), and they are respectively arranged on adjacent connecting frames (3) and are used to detect the moving distance of the telescopic end of the hydraulic telescopic rod (5).

8. A low-altitude aircraft for preventing rotor wing breakage according to claim 7, Its characteristics are: The fixing assembly comprises: A second electric push rod (404) is fixedly connected in the connecting frame (3); an adjustable telescopic rod (405) is fixedly connected to the telescopic end of the second electric push rod (404); and the adjustable telescopic rod (405) is slidably connected to the connecting frame (3); A fixed plate (406) is fixedly connected to the telescopic end of the adjustable telescopic rod (405), and the fixed plate (406) is slidably connected to the connecting frame (3); The number of the fixing frames (407) is twice that of the connecting frames (3), and they are hinged to the connecting frames (3). A second torsion spring is provided between the fixing frames (407) and the connecting frames (3). The fixing frames (407) are position-limitedly matched with the power motor (402), and the fixing frames (407) are press-fitted with the fixing plate (406).

9. A low-altitude aircraft for preventing rotor wing breakage according to claim 8, Its characteristics are: The regulating mechanism comprises: A sliding tube (408) is fixedly connected in the connecting frame (3); the sliding tube (408) is slidably connected to a lifting frame (409); the lifting frame (409) is fixedly connected to the power motor (402); an adjusting plate (410) is slidably connected in the sliding tube (408); the adjusting plate (410) is extrusion-fitted with the lifting frame (409); An extrusion rod (411) is fixedly connected to the telescopic end of the hydraulic telescopic rod (5); A liquid storage tube (412) is fixedly connected to the base (1); the adjustable telescopic rod (405) and the sliding tube (408) are both connected to the liquid storage tube (412) via a second liquid infusion tube; the liquid storage tube (412) is slidably connected to a limiting frame (413); a third tension spring is provided between the liquid storage tube (412) and the limiting frame (413); and the limiting frame (413) is extrusion-matched with the extrusion rod (411); The adjusting block (414) is slidably connected in the liquid storage tube (412), a fourth tension spring is provided between the adjusting block (414) and the liquid storage tube (412), and the limiting frame (413) and the adjusting block (414) are limitedly matched.

10. A low-altitude aircraft for preventing rotor wing breakage according to claim 9, Its characteristics are: A through hole is provided in the portion of the lifting frame (409) located inside the sliding tube (408).

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