An electrically powered aircraft landing device

Abstract

The application discloses an electric aircraft landing device and relates to the technical field of aircrafts. The electric aircraft landing device comprises two first landing frames and two second landing frames which are symmetrically distributed from front to back. Positioning beams are arranged on the opposite sides of the first landing frames and the second landing frames in the same column. The positioning beams are provided with struts which are connected with the frames of the aircrafts. Straight-line cylinders one and two are arranged on the positioning beams and can control the first landing frames and the second landing frames to adjust the spacing respectively. The first landing frames and the second landing frames can adjust the spacing. In the process of the emergency landing of the aircraft, the aircraft can be provided with a large range of supporting force, so that the aircraft can be stably landed on the uneven ground, and the shaking phenomenon caused by the landing of the aircraft on the ground and the leaving of the pilot from the aircraft can be effectively avoided. After the aircraft is landed on the ground, the aircraft can be in a stable state, and the influence of the ground environment on the aircraft can be reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to an electric aircraft landing device. BACKGROUND

[0002] An electric aircraft is an aircraft that uses electrical energy as a power source. There are various types of electric aircraft, including electric vertical take-off and landing aircraft, electric fixed-wing aircraft, electric helicopters, etc. Electric aircraft do not produce tail gas emissions, are environmentally friendly, and help reduce air pollution and greenhouse gas emissions. Compared with traditional fuel aircraft, electric aircraft produce less noise when running, which can reduce noise pollution. The energy conversion efficiency of the electric propulsion system of the electric aircraft is relatively high, which can more effectively utilize energy, and the maintenance cost is relatively low. Electric vertical take-off and landing aircraft are currently a popular type of electric aircraft. They combine the characteristics of helicopters and fixed-wing aircraft, can achieve vertical take-off and landing, do not require a runway, and can operate in limited urban environments for air taxis, tourism, logistics transportation, etc.

[0003] In the landing process of the existing small electric aircraft, two landing gears under the aircraft shell are mostly used to contact the ground to maintain the stability of the entire electric aircraft. The landing gear structure is simple and mostly consists of one or more skid plates. The skid landing gear has relatively poor ground maneuverability. During flight, if emergency landing is required, the outdoor landing environment is complex, and the landing surface is mostly uneven. The stability of the landing gear cannot be guaranteed after the aircraft lands on the ground, which can easily cause the aircraft to shake, affecting the safety of the aircraft. Therefore, the present application provides an electric aircraft landing device to meet the needs. SUMMARY

[0004] To solve the above problems, the present application provides an electric aircraft landing device.

[0005] To achieve the above purpose, the present application provides the following technical solution: an electric aircraft landing device, comprising two first landing gears and two second landing gears symmetrically distributed from front to back, a positioning beam is arranged on the opposite side of the first landing gear and the second landing gear in the same column, a support column connected with the aircraft frame is arranged on the positioning beam, and a linear cylinder one and a linear cylinder two for respectively controlling the first landing gear and the second landing gear to adjust the spacing are arranged on the positioning beam.

[0006] Further comprising a support strip arranged at the bottom end of the positioning beam and a connecting frame arranged at the bottom end of the support strip, and the bottom end of the first landing gear and the second landing gear is provided with a receiving cavity for placing both ends of the connecting frame.

[0007] The relative space of the first landing stand and the second landing stand is provided with two ground-touching blocks capable of lifting movement along with the movement of the first landing stand and the second landing stand, the bottom end of the ground-touching block is provided with an anti-skid block, when the first landing stand and the second landing stand move away from the ground-touching block, the two ground-touching blocks originally above the connecting stand are lowered below the connecting stand until the anti-skid block abuts against the ground.

[0008] Further, the bottom end of the positioning beam is provided with a positioning column, the bottom end of the positioning column is provided with a rotatable guide screw, the bottom end of the guide screw is arranged on the connecting stand and exposed below the connecting stand, and the guide screw is provided with a lifting movement connecting sleeve, the connecting sleeve is provided with two driving arms capable of synchronous movement with the ground-touching block, along with the lowering of the connecting sleeve, the driving arms are lowered synchronously with the ground-touching block.

[0009] Further, the bottom of the connecting stand is provided with a driving gear connected with the bottom end of the guide screw, the inside of the accommodating cavity of the first landing stand and the second landing stand is respectively provided with a first rack and a second rack located on both sides of the driving gear and engaged with the driving gear, when the first landing stand and the second landing stand move, the first rack and the second rack can be engaged to drive the driving gear and the guide screw above the driving gear to rotate synchronously.

[0010] Further, the positioning column is provided with limiting rods distributed on both sides thereof, the driving arm is provided with a guide frame capable of synchronous lifting movement therewith, the guide frame is sleeved on the limiting rods, along with the lifting movement of the connecting sleeve and the driving arm, the guide frame moves synchronously along the distribution direction of the limiting rods.

[0011] Further, the two ends of the ground-touching block are both inclined surface structures that shrink upwards, the inclined surfaces are both provided with limiting blocks perpendicular thereto, the limiting blocks are circular truncated cone structures, and the smaller end of the diameter thereof faces the ground.

[0012] Further, the top of the ground-touching block is provided with a positioning sleeve, the bottom end of the driving arm is provided with a positioning rod extending into the inside of the positioning sleeve and coaxially distributed with the positioning sleeve, the positioning rod is provided with a pressure spring coaxially distributed with the positioning rod, the two ends of the pressure spring are respectively provided with mounting rings, and the upper and lower mounting rings are respectively connected with the driving arm and the positioning sleeve.

[0013] Further, the top end of the first landing stand and the second landing stand is respectively provided with a first follower and a second follower, the two ends of the positioning beam are both provided with receiving cavities accommodating the first follower and the second follower, when the first landing stand and the second landing stand are controlled to move by the linear cylinder one and the linear cylinder two, the first follower and the second follower are both located in the receiving cavities and slide.

[0014] Further, the first landing frame and the second landing frame are both provided with an avoiding groove in communication with the accommodating cavity, and the connection frame is provided with an accommodating channel opposite to the avoiding groove, when the first landing frame and the second landing frame move away from the ground contact pressing block, the avoiding groove moves away from the accommodating channel, and a space for the ground contact pressing block to pass through the accommodating channel is left.

[0015] Further, the connection frame is provided with two groups of guide rollers, and the first rack and the second rack are both provided with a straight channel for accommodating the guide rollers, when the first rack and the second rack move synchronously, the relative positions of the two straight channels and the guide rollers can be adjusted.

[0016] In summary, the technical effects and advantages of the present application are as follows:

[0017] 1. The first landing frame and the second landing frame can adjust the distance, in the process of emergency landing of the aircraft, a large range of supporting force can be provided for the aircraft, so that the aircraft can land stably on the uneven ground, and the shaking phenomenon caused by the landing of the aircraft on the ground and the departure of the pilot from the aircraft can be effectively avoided. After the aircraft lands on the ground, the aircraft can be in a stable state, the influence of the ground environment on the aircraft can be reduced, and the aircraft can be stably and safely waiting for maintenance and rescue work.

[0018] 2. The first landing frame and the second landing frame are provided with two ground contact pressing blocks and two groups of anti-skid blocks which can move up and down with the movement of the first landing frame and the second landing frame. When the first landing frame and the second landing frame provide a large range of supporting force for the aircraft, the two ground contact pressing blocks originally above the connection frame descend below the connection frame, and the anti-skid blocks abut against the ground. The anti-skid blocks and the ground contact pressing blocks can be located below the aircraft on both sides to improve the anti-skid ability and the grip of the aircraft, effectively avoid the sliding and deviation of the first landing frame, the second landing frame and the whole aircraft body in extreme weather, and keep the aircraft in a stable state in the external environment. BRIEF DESCRIPTION OF DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0020] Figure 1 It is a three-dimensional structure schematic diagram of the present application.

[0021] Figure 2 It is a second perspective structure schematic diagram of the present application.

[0022] Figure 3 It is a single side structure schematic diagram of the landing device of the present application.

[0023] Figure 4 For the application Figure 3 Enlarged view of structure at A in the application.

[0024] Figure 5 For the application

[0025] Figure 6 For the application

[0026] Figure 7 For the application

[0027] Figure 8 For the application

[0028] Figure 9 For the application

[0029] Figure 10 For the application Figure 9 Enlarged view of structure at A in the application.

[0030] In the figure: 1, first landing frame; 2, second landing frame; 3, positioning beam; 31, support bar; 32, adapter frame; 321, accommodating channel; 322, guide roller set; 4, support column; 5, linear cylinder one; 6, linear cylinder two; 7, ground contact block; 71, alignment sleeve; 8, anti-skid block; 9, limit block; 10, positioning column; 11, guide screw; 12, drive gear; 13, first rack frame; 14, second rack frame; 15, drive arm; 151, positioning rod; 16, adapter sleeve; 17, guide frame; 18, limit rod; 19, first follow-up rod; 20, second follow-up rod; 21, pressure spring; 22, mounting ring. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the application.

[0032] Embodiment 1: refer to Figures 1-4The electric aircraft landing device shown in the figure comprises two first landing frames 1 and two second landing frames 2 symmetrically distributed from front to back. Positioning beams 3 are arranged on the opposite sides of the first landing frames 1 and the second landing frames 2 in the same column. In order to maintain the stability of the whole landing device, the positioning beams 3 are provided with struts 4 connected with the aircraft frame, so as to achieve the purpose of stably installing the landing device on the aircraft frame.

[0033] Before the implementation of the emergency landing operation, the aircraft needs to implement landing preparation in the flight process, observe the landing environment, confirm whether the topographic features of the landing environment meet the landing safety requirements, and ensure that the aircraft can be safely landed, and then the pilot implements the landing operation. In the present application, the positioning beams 3 are provided with straight-line cylinders 5 and 6 which can respectively control the first landing frames 1 and the second landing frames 2 to adjust the spacing. If the ground in the landing environment is uneven, in order to improve the stability in the landing process, the straight-line cylinders 5 and 6 can respectively control the first landing frames 1 and the second landing frames 2 to extend, so as to expand the support surface until the aircraft lands stably.

[0034] In the landing process, the first landing frames 1 and the second landing frames 2 after adjusting the spacing can provide a larger range of support force for the aircraft, effectively avoiding the shaking phenomenon caused by the aircraft landing on the ground and the pilot leaving the aircraft. When the aircraft lands on the ground, the aircraft can be in a stable state, reducing the influence of the ground environment on the aircraft, so that the aircraft can safely wait for maintenance and rescue work. Therefore, according to different landing environments, the first landing frames 1 and the second landing frames 2 can be adjusted to ensure the stability of the aircraft.

[0035] At the same time, the present application also comprises a support strip 31 arranged at the bottom end of the positioning beam 3 and a connecting frame 32 arranged at the bottom end of the support strip 31. The bottom end of the first landing frame 1 and the second landing frame 2 is provided with a receiving cavity for accommodating both ends of the connecting frame 32. In the flight process of the aircraft, the connecting frame 32 is located inside the receiving cavity.

[0036] Two ground-touching blocks 7 which can ascend and descend with the movement of the first landing frames 1 and the second landing frames 2 are arranged in the opposite space of the first landing frames 1 and the second landing frames 2. The bottom end of the ground-touching block 7 is provided with an anti-skid block 8. When the aircraft implements landing preparation, the first landing frames 1 and the second landing frames 2 adjust the spacing and move away from the ground-touching blocks 7. In this process, the two ground-touching blocks 7 originally located above the connecting frame 32 descend below it. After the aircraft lands on the ground, the anti-skid block 8 abuts against the ground.

[0037] The movement of the ground contact block 7 and the anti-skid block 8 can provide a supporting force between the first landing frame 1 and the second landing frame 2. After the aircraft lands on the ground, the anti-skid ability of the aircraft is improved, the sliding and deviation of the first landing frame 1, the second landing frame 2 and the entire aircraft body in extreme weather is effectively avoided, the stability of the aircraft is maintained, and the safety of the aircraft in the landing environment is further improved.

[0038] Specifically, as shown in Figures 5-7 The bottom end of the positioning beam 3 is provided with a positioning column 10, the bottom end of the positioning column 10 is provided with a rotating guide screw 11, the bottom end of the guide screw 11 is arranged on the connection frame 32 and exposed below the connection frame 32, and the guide screw 11 is provided with a lifting connection sleeve 16, and the connection sleeve 16 is provided with two driving arms 15 which move synchronously with the ground contact block 7. When the guide screw 11 rotates, the driving arms 15 and the ground contact block 7 descend synchronously with the descent of the connection sleeve 16.

[0039] Further, as shown in Figures 5-7 The bottom end of the guide screw 11 is connected with a driving gear 12 arranged below the connection frame 32, and the inside of the accommodating cavity of the first landing frame 1 and the second landing frame 2 is respectively provided with a first rack 13 and a second rack 14 arranged on both sides of the driving gear 12 and engaged with the driving gear 12. Therefore, when the linear cylinder one 5 and the linear cylinder two 6 drive the first landing frame 1 and the second landing frame 2 to move away from the ground contact block 7, the first rack 13 and the second rack 14 can be engaged and drive the driving gear 12 and the guide screw 11 above the driving gear 12 to rotate synchronously, so as to achieve the purpose of driving the connection sleeve 16 to descend.

[0040] In the landing process of the aircraft, the positioning column 10 is provided with limiting rods 18 distributed on both sides of the positioning column 10, and the driving arm 15 is provided with a guide frame 17 which moves synchronously with the driving arm 15, the guide frame 17 is sleeved on the limiting rod 18, and the guide frame 17 moves synchronously along the distribution direction of the limiting rod 18 with the lifting movement of the connection sleeve 16 and the driving arm 15. Further improve the stability and precision of the driving arm 15 in the process of descending along the straight line path, and ensure the stability of the ground contact block 7 and the anti-skid block 8.

[0041] Embodiment 2: as Figures 3-6As shown, on the basis of embodiment 1, the two ends of the ground contact block 7 are both in the form of an upwardly converging inclined surface structure, and a limiting block 9 perpendicular to the inclined surface is arranged on each inclined surface. The limiting block 9 is in the form of a circular truncated cone structure, and the end with a smaller diameter faces the ground. After the aircraft lands, based on the ground conditions, if the anti-skid block 8 is embedded into the muddy ground together with the limiting block 9, since the two limiting blocks 9 are arranged in an inclined manner on the two sides of the anti-skid block 8, the limiting block 9 and the anti-skid block 8 embedded into the muddy ground can improve the tightness of the connection between the ground contact block 7 and the ground. When the aircraft is subjected to wind impact, the limiting block 9 and the anti-skid block 8 are not prone to deviation, which improves the ground gripping capacity of the ground contact block 7 and further improves the anti-skid performance of the ground contact block 7, the connecting frame 32, the first landing frame 1 and the second landing frame 2.

[0042] Embodiment 3: as shown in Figures 3-6 As shown, on the basis of embodiments 1 and 2, the top of the ground contact block 7 is provided with a positioning sleeve 71, and the bottom end of the driving arm 15 is provided with a positioning rod 151 extending into the inside of the positioning sleeve 71 and arranged in a coaxial manner with the positioning sleeve 71. The positioning rod 151 is externally provided with a pressure spring 21 arranged in a coaxial manner with the positioning rod 151. The two ends of the pressure spring 21 are respectively provided with mounting rings 22, and the two mounting rings 22 arranged in an upper and lower manner are respectively connected with the driving arm 15 and the positioning sleeve 71.

[0043] During the landing process of the aircraft, when the anti-skid block 8 contacts the ground, the positioning sleeve 71 slides along the surface of the positioning rod 151. Under the connection action of the mounting ring 22, the pressure spring 21 is in a contracted state, which has a buffering effect on the ground contact block 7 and the anti-skid block 8, effectively reducing the impact damage to the driving arm 15 caused by the collision of the ground contact block 7 and the anti-skid block 8 after they descend to the ground.

[0044] As shown in Figures 7-8 In order to ensure the impact resistance strength of the first landing frame 1 and the second landing frame 2 during the flight of the aircraft and improve the tightness of the connection between the first landing frame 1, the second landing frame 2 and the positioning beam 3, the first landing frame 1 and the second landing frame 2 are respectively provided with a first follower rod 19 and a second follower rod 20 at the top ends thereof. The two ends of the positioning beam 3 are both provided with a receiving cavity for accommodating the first follower rod 19 and the second follower rod 20. When the linear cylinder one 5 and the linear cylinder two 6 control the movement of the first landing frame 1 and the second landing frame 2, the first follower rod 19 and the second follower rod 20 slide in the receiving cavity. The combination of the first follower rod 19, the second follower rod 20 and the receiving cavity can improve the stability of the first landing frame 1 and the second landing frame 2 during the movement thereof in the landing state of the aircraft.

[0045] As shown in Figure 5 , Figure 6As shown, in order to make the ground pressure block 7 to pass through the adapter frame 32 smoothly, the first landing frame 1 and the second landing frame 2 are both provided with an avoiding slot which is in communication with the accommodating cavity, and the adapter frame 32 is provided with an accommodating channel 321 which is opposite to the position of the avoiding slot, when the first landing frame 1 and the second landing frame 2 move away from the ground pressure block 7, the avoiding slot moves away from the accommodating channel 321, and there is a space for the ground pressure block 7 to pass through the accommodating channel 321.

[0046] As shown, Figure 9 As shown, the adapter frame 32 is provided with two groups of guide rollers 322, the first rack frame 13 and the second rack frame 14 are both provided with a linear channel which can accommodate the guide rollers 322 to pass through, when the first rack frame 13 and the second rack frame 14 move synchronously, the relative position of the two linear channels and the guide rollers 322 can be adjusted. The combination of the linear channel and the guide rollers 322 can improve the precise movement of the first rack frame 13 and the second rack frame 14 along the linear path, and improve the precision of the first rack frame 13 and the second rack frame 14 when they are engaged with the driving gear 12.

[0047] Finally, it should be noted that: the above only for the preferred embodiments of the present application, and not for limiting the present application, although the foregoing detailed description of the present application is made with reference to the foregoing embodiments, for those skilled in the art, it still can be modified, or part of the technical features of the equivalent replacement, within the spirit and principles of the present application, any modification, equivalent replacement, improvement, etc., should be included in the scope of protection of the present application.

Claims

1. An electrically powered aerial vehicle landing device, characterized by: The application relates to a landing gear for an aircraft, which comprises two first landing gears (1) and two second landing gears (2) symmetrically arranged from front to back, positioning beams (3) are arranged on the opposite sides of the first landing gears (1) and the second landing gears (2) in the same column, supports (4) connected with the aircraft frame are arranged on the positioning beams (3), linear cylinders one (5) and linear cylinders two (6) for respectively controlling the first landing gears (1) and the second landing gears (2) to adjust the spacing are arranged on the positioning beams (3); The application further comprises support strips (31) arranged at the bottom ends of the positioning beams (3) and connecting frames (32) arranged at the bottom ends of the support strips (31), the bottom ends of the first landing gears (1) and the second landing gears (2) are provided with accommodating cavities for the two ends of the connecting frames (32) to be inserted into; Two ground-touching pressing blocks (7) are arranged in the opposite spaces of the first landing gears (1) and the second landing gears (2) and can move up and down along with the movement of the first landing gears (1) and the second landing gears (2), the bottom ends of the ground-touching pressing blocks (7) are provided with anti-skid blocks (8), when the first landing gears (1) and the second landing gears (2) move away from the ground-touching pressing blocks (7), the two ground-touching pressing blocks (7) originally above the connecting frames (32) drop below the connecting frames (32) until the anti-skid blocks (8) abut against the ground; The bottom ends of the positioning beams (3) are provided with positioning columns (10), the bottom ends of the positioning columns (10) are provided with rotatable guide screws (11), the bottom ends of the guide screws (11) are arranged on the connecting frames (32) and exposed below the connecting frames (32), the guide screws (11) are provided with connecting sleeves (16) capable of moving up and down, the connecting sleeves (16) are provided with two driving arms (15) capable of moving synchronously with the ground-touching pressing blocks (7), along with the descending of the connecting sleeves (16), the driving arms (15) synchronously descend with the ground-touching pressing blocks (7); The bottom ends of the guide screws (11) are connected with driving gears (12) arranged below the connecting frames (32), the inner sides of the accommodating cavities of the first landing gears (1) and the second landing gears (2) are respectively provided with first rack frames (13) and second rack frames (14) arranged on the two sides of the driving gears (12) and meshed with the driving gears (12), when the first landing gears (1) and the second landing gears (2) move, the first rack frames (13) and the second rack frames (14) can be driven to mesh and drive the driving gears (12) and the guide screws (11) above the driving gears (12) to synchronously rotate.

2. The electrically powered aerial landing device of claim 1, wherein: The positioning columns (10) are provided with limiting rods (18) arranged on the two sides of the positioning columns (10), the driving arms (15) are provided with guide frames (17) capable of moving up and down synchronously with the driving arms (15), the guide frames (17) are sleeved on the limiting rods (18), along with the up-and-down movement of the connecting sleeves (16) and the driving arms (15), the guide frames (17) synchronously move along the distribution direction of the limiting rods (18).

3. The electrically powered aerial landing device of claim 1, wherein: The two ends of the ground-touching pressing blocks (7) are provided with inclined surfaces which are contracted upwards, the inclined surfaces are provided with limiting blocks (9) perpendicular to the inclined surfaces, the limiting blocks (9) are provided with circular truncated cone structures, and the ends with smaller diameters face the ground.

4. The electrically powered aerial landing device of claim 1, wherein: The top of the ground contact block (7) is provided with a positioning sleeve (71), the bottom end of the driving arm (15) is provided with a positioning rod (151) extending into the inside of the positioning sleeve (71) and coaxially distributed with the positioning sleeve (71), the positioning rod (151) is provided with a pressure spring (21) coaxially distributed outside the positioning rod (151), the two ends of the pressure spring (21) are respectively provided with a mounting ring (22), the upper and lower distributed two mounting rings (22) are respectively connected with the driving arm (15) and the positioning sleeve (71).

5. The electrically powered aerial landing device of claim 1, wherein: The top end of the first landing frame (1) and the second landing frame (2) is respectively provided with a first follower rod (19) and a second follower rod (20), the two ends of the positioning beam (3) are provided with receiving cavities accommodating the first follower rod (19) and the second follower rod (20), when the linear cylinder one (5) and the linear cylinder two (6) control the movement of the first landing frame (1) and the second landing frame (2), the first follower rod (19) and the second follower rod (20) are located in the receiving cavities and slide.

6. The electrically powered aerial landing device of claim 1, wherein: The first landing frame (1) and the second landing frame (2) are provided with avoidance grooves communicating with the receiving cavities, the connection frame (32) is provided with a containing channel (321) opposite to the position of the avoidance groove, when the first landing frame (1) and the second landing frame (2) move away from the ground contact block (7), the avoidance groove moves away from the containing channel (321), leaving a space for the ground contact block (7) to pass through the containing channel (321).

7. The electrically powered aerial landing device of claim 1, wherein: The connection frame (32) is provided with two groups of guide roller groups (322), the first rack (13) and the second rack (14) are provided with linear channels accommodating the guide roller groups (322) to pass through, when the first rack (13) and the second rack (14) move synchronously, the relative positions of the two linear channels and the guide roller groups (322) can be adjusted.

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