Low-altitude aircraft

Abstract

The utility model discloses a low-altitude aircraft which comprises an aircraft body, four fixed machine arm rods are arranged in the cross direction of the aircraft body, the surfaces of the fixed machine arm rods are movably connected with movable machine arm rods, one sides of the movable machine arm rods are provided with locking pieces, and the other sides of the movable machine arm rods are connected with the locking pieces. The locking piece comprises fixing frames fixed to the top and the bottom of one end of the movable machine arm rod, a connecting plate is arranged on one side of each fixing frame, and a clamping column is fixedly connected to the inner side of each connecting plate. The fixed machine arm rod can move in the inner cavity of the movable machine arm rod, so that the total length of the fixed machine arm rod and the movable machine arm rod can be changed, the length of the machine arm can be adjusted, the two clamping columns enter the through holes, the adjusted length can be locked, the length of the machine arm can be adjusted according to task requirements, and the machine arm is convenient to use. The aircraft arm is suitable for different terrains and weather conditions, dynamic adjustment of the arm of force of the propeller is achieved, lift and thrust efficiency is optimized, and the fixed aircraft arm rod and the movable aircraft arm rod can be rapidly detached and replaced.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a low-altitude aircraft. Background Technology

[0002] Aircraft are various instruments or devices that can fly in the air or in the outer space of the atmosphere. They achieve vertical take-off and landing, horizontal flight, hovering, gliding and other forms of motion through their own power, aerodynamic principles or external thrust. Low-altitude aircraft are aircraft that fly in airspace at a low altitude above the ground. These aircraft rely on a power system to generate lift and have the ability to take off and land vertically, hover or fly at low speed. They are widely used in civil, commercial and special fields.

[0003] The existing utility model patent with publication number CN206871374U discloses a quadcopter. It features an upper support frame located at the center of a cross-shaped support structure. Each end of the cross-shaped support frame is connected to a coreless motor. A flight control board is located on top of the upper support frame and is connected to a battery and the four coreless motors. The battery is housed within the upper support frame. The use of the flight control board integrates the chips, reducing the quadcopter's size. Furthermore, the use of coreless motors instead of brushless motors lowers production costs. While this solves the problem of high cost and large size associated with brushless motors due to power requirements, the fixed arm length limits performance during use. The arm length directly affects the propeller lever arm (the distance from the lift point to the center of gravity). The fixed length design cannot dynamically optimize the lever arm, making it difficult to meet different mission requirements. Users would need to purchase multiple models with different arm lengths. Therefore, a low-altitude quadcopter is proposed to address this issue. Utility Model Content

[0004] Therefore, it is necessary to provide a low-altitude aircraft that can adjust the length of its arms to address the aforementioned technical problems.

[0005] In order to solve the above-mentioned technical problems, the present invention solves the problems mentioned in the background art through the following technical solution.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A low-altitude aircraft comprising:

[0008] The aircraft fuselage has four fixed booms arranged in a cross direction. Movable booms are movably connected to the surfaces of the fixed booms. A locking component is provided on one side of each movable boom. The locking component includes a fixing frame fixed to the top and bottom of one end of the movable boom. A connecting plate is provided on one side of the fixing frame. A locking pin is fixedly connected to the inner side of the connecting plate. A wedge block is fixedly connected to the outer side of the connecting plate. A spring is installed between the connecting plate and the fixing frame.

[0009] A pressure component, wherein the pressure component has a surface for a movable boom, and the pressure component includes a sleeve and a connecting ring fitted onto the surface of the fixed boom.

[0010] In a preferred embodiment of the low-altitude aircraft provided by this utility model, a mounting block is fixedly installed at the cross-shaped position of the aircraft body, and the outer end of the mounting block is fixedly connected to the corresponding fixed boom.

[0011] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the two fixed frames are symmetrically distributed, and the locking post moves through the surface of the fixed frame.

[0012] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the fixing frame, connecting plate and wedge block have a certain curvature, which is adapted to the outer ring surface of the fixing boom.

[0013] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the surface of the fixed boom is provided with a plurality of through holes at equal intervals, and one end of the two locking pins penetrates into the inner cavity of the corresponding through hole.

[0014] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the screw sleeve is threaded onto the surface of the movable boom, and the side of the screw sleeve near the fixed boom is fixedly connected to the connecting ring.

[0015] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the connecting ring has an inclined surface on the side near the wedge block. Furthermore, the inclined surface of the wedge block contacts the inclined surface of the connecting ring.

[0016] In a preferred embodiment of the low-altitude aircraft provided by this utility model, the surface of the fixed boom is provided with a guide member, the guide member including a guide strip fixedly connected to both sides of the surface of the fixed boom, and both sides of the inner cavity of the movable boom are provided with guide grooves for the guide strips to move.

[0017] In a preferred embodiment of the low-altitude aircraft provided by this utility model, a rotor is provided at the outer end of the movable boom, the rotor including a mounting base fixed to the outer end of the movable boom, and a rotor is provided on the outer side of the mounting base.

[0018] In a preferred embodiment of the low-altitude aircraft provided by this utility model, a mounting plate is fixedly sleeved on the surface of the rotor, and the mounting plate and the mounting base are fixedly installed by two bolts.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] This utility model provides a low-altitude aircraft where the fixed boom can move within the inner cavity of the movable boom, thereby changing the total length of the fixed and movable booms and achieving boom length adjustment. Two locking pins enter through holes to lock the adjusted length. The boom length can be adjusted according to mission requirements to adapt to different terrains and weather conditions, enabling dynamic adjustment of the propeller arm, optimizing lift and thrust efficiency. Furthermore, the fixed and movable booms can be quickly disassembled and replaced, reducing maintenance costs.

[0021] The present invention provides a low-altitude aircraft in which the rotor can be disassembled by removing two bolts. The rotor can be disassembled and replaced with different models (such as rotors of different sizes and materials) to adapt to different mission requirements. After the rotor is disassembled, the size of the drone is reduced, making it easier to transport and store. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 A three-dimensional structural schematic diagram of the present invention is provided;

[0024] Figure 2 A bottom-view three-dimensional structural diagram of this utility model;

[0025] Figure 3 This is a partial three-dimensional structural schematic diagram provided for this utility model;

[0026] Figure 4 This is a schematic diagram of a partially disassembled three-dimensional structure provided by this utility model;

[0027] Figure 5This utility model provides a three-dimensional structural diagram showing the disassembled fixed boom and the movable boom;

[0028] Figure 6 A three-dimensional structural diagram of the locking component is provided for this utility model.

[0029] The markings in the diagram are explained as follows:

[0030] 1. Aircraft fuselage; 2. Fixed boom; 3. Movable boom; 4. Mounting block; 5. Locking component; 51. Fixing frame; 52. Connecting plate; 53. Locking post; 54. Wedge block; 55. Spring clip; 56. Through hole; 6. Pressure component; 61. Sleeve; 62. Connecting ring; 7. Guide component; 71. Guide strip; 72. Guide groove; 8. Rotor component; 81. Mounting base; 82. Rotor; 83. Mounting plate; 84. Bolt. Detailed Implementation

[0031] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention. Example

[0032] Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 A low-altitude aircraft includes: an aircraft body 1, four fixed booms 2 arranged in a cross direction on the aircraft body 1, movable booms 3 movably connected to the surfaces of the fixed booms 2, the movable booms 3 being movable to adapt to different mission requirements, such as extending the booms to enhance lift during aerial photography missions, and shortening the booms to reduce collision risk during indoor surveying, a locking component 5 is provided on one side of the movable boom 3, the locking component 5 includes a fixing frame 51 fixed to the top and bottom of one end of the movable boom 3, a connecting plate 52 is provided on one side of the fixing frame 51, a locking pin 53 is fixedly connected to the inner side of the connecting plate 52, a wedge block 54 is fixedly connected to the outer side of the connecting plate 52, a spring piece 55 is installed between the connecting plate 52 and the fixing frame 51, the locking pin 53 cooperates with the through hole 56 of the fixed boom 2 to achieve quick locking; the wedge block 54 cooperates with the pressure component 6 to achieve quick unlocking or locking;

[0033] Pressure component 6 has a surface on which the movable boom 3 is located. Pressure component 6 includes a rotating sleeve 61 and a connecting ring 62 that are sleeved on the surface of the fixed boom 2. When the rotating sleeve 61 is rotated, the inclined surface of the connecting ring 62 pushes the wedge block 54, causing the locking pin 53 to enter the through hole 56, thereby achieving quick locking.

[0034] In the embodiments of this application, an installation block 4 is fixedly installed at the cross-shaped position of the aircraft body 1. The outer end of the installation block 4 is fixedly connected to the corresponding fixed arm 2. Two fixed frames 51 are symmetrically distributed. The locking pins 53 are movably connected to the surface of the fixed frame 51. The fixed frame 51, the connecting plate 52, and the wedge block 54 have a certain curvature, which is adapted to the outer ring surface of the fixed arm 2. Several through holes 56 are evenly spaced on the surface of the fixed arm 2. The locking pins 53 are inserted into the through holes 56 at different positions to adjust the position of the movable arm 3. One end of the two locking pins 53 is inserted into the inner cavity of the corresponding through hole 56. The screw sleeve 61 is threaded onto the surface of the movable arm 3. The side of the screw sleeve 61 near the fixed arm 2 is fixedly connected to the connecting ring 62. The side of the connecting ring 62 near the wedge block 54 is set with an inclined surface. Furthermore, the inclined surface of the wedge block 54 contacts the inclined surface of the connecting ring 62, and the surface of the fixed boom 2 is provided with a guide 7. The guide 7 includes a guide strip 71 fixedly connected to both sides of the surface of the fixed boom 2. The inner cavity of the movable boom 3 is provided with guide grooves 72 on both sides, which allow the guide strips 71 to move. The guide strips 71 and the guide grooves 72 cooperate to restrict the rotation of the movable boom 3 and ensure that the locking part 5 and the through hole 56 are precisely aligned.

[0035] In the embodiments of this application, a rotor 8 is provided at the outer end of the movable boom 3. The rotor 8 includes a mounting base 81 fixed to the outer end of the movable boom 3. A rotor 82 is provided on the outer side of the mounting base 81. A mounting plate 83 is fixedly sleeved on the surface of the rotor 82. The mounting plate 83 and the mounting base 81 are fixedly installed by two bolts 84. When a single rotor 8 fails, it can be replaced by removing only two bolts 84, reducing maintenance time.

[0036] The operation of the low-altitude aircraft provided by this utility model is as follows: When adjusting the arm length, first unlock the fixed arm 2 and the movable arm 3. By rotating the rotating sleeve 61, the rotating sleeve 61 moves to one side during rotation. The rotating sleeve 61 drives the connecting ring 62 to move, and the connecting ring 62 disengages from the two wedge blocks 54, losing its force on the wedge blocks 54. At this time, the spring piece 55, under the action of elastic force, drives the locking pin 53, the connecting plate 52, and the wedge blocks 54 to move, so that one end of the locking pin 53 disengages from the inner cavity of the through hole 56, thereby removing the force on the fixed arm 2. Unlocking is achieved between the fixed boom 2 and the movable boom 3. By moving the movable boom 3, the total length of the fixed boom 2 and the movable boom 3 is adjusted so that when the movable boom 3 moves to the appropriate position, the rotating sleeve 61 is rotated in the opposite direction. The rotating sleeve 61 drives the connecting ring 62 to approach the wedge block 54 until it contacts the wedge block 54, applying pressure to the wedge block 54. The wedge block 54 drives the connecting plate 52 and the locking pin 53 into the inner cavity of the pressure member 6 at the corresponding position. The spring 55 is in a compressed state. At this time, the adjusted length of the fixed boom 2 and the movable boom 3 is locked.

[0037] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0038] Obviously, the embodiments described above are only some embodiments of this utility model, not all embodiments. The accompanying drawings show preferred embodiments of this utility model, but do not limit the patent scope of this utility model. This utility model can be implemented in many different forms; rather, the purpose of providing these embodiments is to provide a more thorough and comprehensive understanding of the disclosure of this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing specific embodiments, or make equivalent substitutions for some of the technical features. Any equivalent structures made using the content of this utility model specification and drawings, directly or indirectly applied to other related technical fields, are similarly within the patent protection scope of this utility model.

Claims

1. A low altitude aircraft, characterized in that, It includes: The aircraft body (1) is provided with four fixed arm rods (2) in cross direction, the surface of the fixed arm rod (2) is movably connected with a movable arm rod (3), one side of the movable arm rod (3) is provided with a locking piece (5), the locking piece (5) includes a fixed frame (51) fixed to the top and bottom of one end of the movable arm rod (3), one side of the fixed frame (51) is provided with a connecting plate (52), the inner side of the connecting plate (52) is fixedly connected with a clamping column (53), the outer side of the connecting plate (52) is fixedly connected with a wedge block (54), and a spring sheet (55) is installed between the connecting plate (52) and the fixed frame (51). The pressure piece (6) is provided on the surface of the movable arm rod (3), and the pressure piece (6) includes a rotating sleeve (61) sleeved on the surface of the fixed arm rod (2) and a connecting ring (62).

2. A low altitude aircraft according to claim 1, wherein, The mounting block (4) is fixedly installed at the cross direction position of the aircraft body (1), and the outer end of the mounting block (4) is fixedly connected with the corresponding fixed arm rod (2).

3. The low altitude aircraft of claim 1, wherein, The two fixed frames (51) are symmetrically distributed, and the clamping column (53) movably penetrates the surface of the fixed frame (51).

4. The low altitude vehicle of claim 1, wherein, The fixed frame (51), the connecting plate (52) and the wedge block (54) have a certain arc, which is matched with the outer ring surface of the fixed arm rod (2).

5. The low altitude aircraft of claim 1, wherein, A plurality of through holes (56) are formed on the surface of the fixed arm rod (2) at equal intervals, and one end of the two clamping columns (53) penetrates the inner cavity of the corresponding through hole (56).

6. The low altitude aircraft of claim 1, wherein, The rotating sleeve (61) is threadedly sleeved on the surface of the movable arm rod (3), and the side of the rotating sleeve (61) close to the fixed arm rod (2) is fixedly connected with the connecting ring (62).

7. The low altitude aircraft of claim 1, wherein, The side of the connecting ring (62) close to the wedge block (54) is provided with an inclined surface; and the inclined surface of the wedge block (54) is in contact with the inclined surface of the connecting ring (62).

8. The low altitude aircraft of claim 1, wherein, The surface of the fixed arm rod (2) is provided with a guide piece (7), the guide piece (7) includes guide strips (71) fixedly connected to the surfaces of the fixed arm rod (2) on both sides, and the inner cavities of the movable arm rod (3) on both sides are provided with guide grooves (72) for the movement of the guide strips (71).

9. The low altitude aircraft of claim 1, wherein, The outer end of the movable arm rod (3) is provided with a rotor piece (8), the rotor piece (8) includes a mounting seat (81) fixed to the outer end of the movable arm rod (3), and the outer side of the mounting seat (81) is provided with a rotor (82).

10. A low altitude aircraft according to claim 9, wherein, The surface of the rotor (82) is fixedly sleeved with a mounting plate (83), and the mounting plate (83) and the mounting seat (81) are fixedly installed through two bolts (84).

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