Aircraft arm lock mechanism and method of use

Abstract

This invention relates to the field of aircraft technology, and particularly to an aircraft arm locking mechanism and its usage method. The mechanism includes a fuselage, with rotating columns rotatably mounted at each of the four corners of the fuselage's upper surface. A connecting rod is fixedly connected to the upper end of each rotating column, and a flight fan is fixedly connected to the end of the connecting rod furthest from the rotating column. The mechanism also includes a locking mechanism for automatically locking the rotating columns, located at the bottom end of the rotating columns. The aircraft arm locking mechanism and its usage method provided by this invention prevent the connecting plate from rotating during flight due to air pressure, thus preventing arm misalignment. It also eliminates the need for a separate power supply, saving costs. Using air for limiting the movement reduces overall weight, making the aircraft lighter, and prevents arm swaying during storage. Furthermore, the use of a non-Newtonian fluid prevents debris such as tree branches from suddenly hitting the locking ring during flight, thus unlocking the arm.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, specifically to an aircraft arm locking mechanism and its usage method. Background Technology

[0002] Multirotor aircraft have advantages such as maneuverability, rapid response, strong environmental adaptability and low operation requirements. In order for the aircraft to switch between land driving mode and air flight mode, the aircraft's arms need to be able to fold and unfold.

[0003] In existing technologies, instability can occur when the arms of an aircraft are extended or folded. Therefore, some aircraft are equipped with independent locking mechanisms to lock the rotating arms. The locking mechanism requires a separate power source, which increases the structural complexity of the aircraft. The addition of a power source reduces the overall range of the aircraft and is not conducive to the lightweighting of the aircraft. Summary of the Invention

[0004] To address the aforementioned problems, the present invention provides an arm locking mechanism for aircraft.

[0005] This invention adopts the following technical solution: an aircraft arm locking mechanism, comprising a fuselage, wherein rotating columns are rotatably disposed at the four corners of the upper surface of the fuselage, a connecting rod is fixedly connected to the upper end of each rotating column, and a flight fan is fixedly connected to the end of the connecting rod away from the rotating column; and further comprising:

[0006] The insert ring can automatically unlock. The insert ring is movably inserted into the lower surface of the machine body, and a return spring is fixedly connected between the upper end of the insert ring and the machine body.

[0007] A locking mechanism is provided for automatically locking the rotating column, and the locking mechanism is located at the bottom end of the rotating column;

[0008] And a jetting mechanism capable of jetting the flying fan, the jetting mechanism being disposed within the locking mechanism.

[0009] As a further description of the above technical solution: the locking mechanism includes a rotating block fixed to the bottom end of a rotating column, the rotating block being rotatably disposed within the machine body, a rotating column fixed to the center of the bottom end of the rotating block, a rotating cavity being formed on the outer side of the rotating column within the machine body, a connecting plate fixed to the outer wall of the rotating column, the connecting plate being movably disposed within the rotating cavity and abutting against the inner wall of the rotating cavity, a fixing frame fixed to the inner wall of the rotating cavity, the fixing frame abutting against the outer wall of the rotating column, a lifting bracket being movably inserted at the bottom end of the fixing frame, an external tooth being fixed to one side wall of the lifting bracket, a spur rack being movably inserted on one side of the lifting bracket, a gear meshing between the spur rack and the external tooth, the gear being rotatably disposed within the machine body, the bottom end of the spur rack being fixed to the upper end of the insert ring, a storage cavity being formed within the fixing frame, a sliding block being slidably disposed within the storage cavity, the sliding block being fixed to the lifting bracket, and a connecting groove being formed on both the fixing frame and the lifting bracket.

[0010] As a further description of the above technical solution: the spraying mechanism includes a connecting plate fixed to the upper end of the lifting bracket, the connecting plate being movably inserted into the top of the fixed frame, a vent hole being provided on the lower surface of the rotating block, a spraying hole being provided on the lower outer wall of the connecting rod, the spraying hole being connected to the vent hole, a blocking block being fixed to the top of the fixed frame, a connecting hole being provided at the bottom of the lifting bracket, the upper end of the connecting hole being connected to the connecting groove, and the other end of the connecting hole being connected to the outer side of the machine body.

[0011] As a further description of the above technical solution: the bottom end of the insertion ring extends to the lower side of the fuselage.

[0012] As a further description of the above technical solution: a non-Newtonian fluid is placed inside the storage cavity.

[0013] As a further description of the above technical solution: the width of the sliding block is smaller than the width of the storage cavity.

[0014] As a further description of the above technical solution: the blocking blocks and vents are arranged in a ring with equal spacing.

[0015] As a further description of the above technical solution: the spacing between each of the vent holes and the spacing between each blocking block are different.

[0016] Furthermore, the present invention adopts the following technical solution: a method for using an aircraft arm locking mechanism, comprising the following steps:

[0017] S1. First, remove the fuselage from the housing and place it on the ground. This causes the insert ring to be squeezed into the fuselage, and air will be ejected from the jet nozzle. This can spray out debris on the flight fan and prevent debris from affecting flight after being left for a long time.

[0018] S2: After the flight fan is deployed, the insertion ring will extend downward due to the force of the return spring, and the lifting bracket will move upward. The connecting slots on the fixed bracket and the lifting bracket will be misaligned. Due to air pressure, the connecting plate can no longer rotate, preventing the arm from being misaligned during flight.

[0019] S3: After the flight is completed, the entire unit will be lowered to the ground. The insertion ring will be pressed upwards again. At this time, the connecting slots on the fixed frame and the lifting insertion frame will be connected, allowing the rotating column to be rotated. After the flight fan is retracted, the entire unit will be placed in the container to prevent the arm from swaying during storage.

[0020] This invention provides an improved aircraft arm locking mechanism and its usage method, which, compared with the prior art, has the following improvements and advantages:

[0021] Firstly, during flight, the air pressure prevents the connecting plate from rotating, thus preventing the arm from becoming misaligned during flight. It also eliminates the need for a separate power source, saving costs. Using air for limiting reduces the overall weight, making the aircraft lighter and preventing the arm from wobbling during storage. Furthermore, the storage chamber contains non-Newtonian fluid, which prevents debris such as tree branches from suddenly hitting the insertion ring during flight and causing the arm to unlock.

[0022] Secondly, when taking it out, place it on the ground. This causes the insert ring to be squeezed into the fuselage, and the internal air will be forced into the vent. As a result, the air will be ejected from the jet nozzle, which can spray out debris on the flight fan. This prevents debris on the flight fan from affecting flight after being left for a long time. It can also spray intermittently, making the spray force fluctuate, thereby improving the spray effect.

[0023] In summary, through the design of the locking and jetting mechanisms, when the aircraft is removed and placed on the ground, the insertion ring is squeezed into the fuselage, forcing the internal air into the vent. This air is then ejected from the jetting holes, effectively jetting away debris from the flight fan. This prevents debris from affecting flight after prolonged storage and allows for intermittent jetting, with varying jetting force to enhance the jetting effect. During flight, the air pressure prevents the connecting plate from rotating, preventing arm misalignment. Furthermore, no separate power supply is required, saving costs. Using air for limiting the movement reduces overall weight, making the aircraft lighter and preventing arm swaying during storage. Additionally, the storage cavity contains a non-Newtonian fluid to prevent debris such as branches from suddenly hitting the insertion ring and unlocking the arm during flight. Attached Figure Description

[0024] The present invention will be further explained below with reference to the accompanying drawings and embodiments:

[0025] Figure 1 This is a schematic diagram of the structure of the present invention;

[0026] Figure 2 This is a schematic diagram of the insert ring provided in an embodiment of the present invention;

[0027] Figure 3 A perspective sectional view of the fuselage provided in an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of the locking mechanism provided in an embodiment of the present invention;

[0029] Figure 5 A perspective sectional view of the fixing frame provided in an embodiment of the present invention;

[0030] Figure 6 This is a schematic diagram of the structure where the fixing frame and the lifting bracket are separated, as provided in an embodiment of the present invention.

[0031] Figure 7 for Figure 3 Enlarged view of point A in the middle.

[0032] In the diagram: 1. Fuselage; 2. Rotating column; 3. Connecting rod; 4. Flight fan; 5. Insert ring; 6. Return spring; 7. Locking mechanism; 71. Rotating block; 72. Fixing frame; 73. Rotating column; 74. Connecting plate; 75. Lifting bracket; 76. Spur rack; 77. Gear; 78. Storage cavity; 79. Sliding block; 710. Connecting slot; 711. Rotating cavity; 8. Jet jet mechanism; 81. Connecting plate; 82. Vent hole; 83. Blocking block; 84. Connecting hole; 85. Jet jet hole. Detailed Implementation

[0033] To make the technical means, creative features, objectives, and effects of this invention readily understandable, the invention is further described below with reference to specific illustrations. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0034] Please see Figure 1 - Figure 7 This invention provides a technical solution: an aircraft arm locking mechanism, including a fuselage 1, with rotating columns 2 rotatably disposed at each of the four corners of the upper surface of the fuselage 1, a connecting rod 3 fixedly connected to the upper end of the rotating column 2, and a flight fan 4 fixedly connected to the end of the connecting rod 3 away from the rotating column 2, and further comprising:

[0035] The insert ring 5 can automatically unlock. The insert ring 5 is movably inserted into the lower surface of the body 1. A return spring 6 is fixedly connected between the upper end of the insert ring 5 and the body 1.

[0036] Locking mechanism 7 is used to automatically lock the rotating column 2. Locking mechanism 7 is located at the bottom end of rotating column 2.

[0037] And a jetting mechanism 8, which can jet the flying fan 4, is located inside the locking mechanism 7.

[0038] The bottom of the insert ring 5 extends to the lower side of the body 1.

[0039] Specifically, through the locking mechanism 7 and the jetting mechanism 8, when the device is removed and placed on the ground, the insert ring 5 is squeezed into the fuselage 1, and the internal air is forced into the vent 82. As a result, the air is ejected from the jetting hole 85, which can jet away debris on the flight fan 4, preventing debris from affecting flight after long-term storage. The jetting can also be intermittent, making the jetting force fluctuate, thereby improving the jetting effect. During flight, due to air pressure, the connecting plate 74 can no longer rotate, preventing the arm from misaligning during flight. At the same time, no separate power supply is needed to drive it, saving costs. Using air for limiting can reduce the overall weight, making the aircraft lighter, and also preventing the arm from shaking during storage. In addition, the storage cavity 78 contains a non-Newtonian fluid, which can prevent debris such as branches from suddenly hitting the insert ring 5 during flight, causing the arm to unlock.

[0040] In another embodiment of the present invention, the locking mechanism 7 includes a rotating block 71 fixedly connected to the bottom end of the rotating column 2. The rotating block 71 is rotatably disposed within the body 1. A rotating column 73 is fixedly connected to the center of the bottom end of the rotating block 71. A rotating cavity 711 is formed on the outer side of the rotating column 73 within the body 1. A connecting plate 74 is fixedly connected to the outer wall of the rotating column 73. The connecting plate 74 is movably disposed within the rotating cavity 711 and abuts against the inner wall of the rotating cavity 711. A fixing frame 72 is fixedly connected to the inner wall of the rotating cavity 711. The fixing frame 72 is in contact with the outer wall of the rotating column 73. The fixed frame 72 has a lifting bracket 75 movably inserted at its bottom end. An external tooth is fixed to one side wall of the lifting bracket 75. A straight rack 76 is movably inserted to one side of the lifting bracket 75. A gear 77 meshes between the straight rack 76 and the external tooth. The gear 77 is rotatably installed inside the body 1. The bottom end of the straight rack 76 is fixed to the upper end of the insert ring 5. A storage cavity 78 is opened inside the fixed frame 72. A sliding block 79 is slidably installed inside the storage cavity 78. The sliding block 79 is fixed to the lifting bracket 75. A connecting groove 710 is opened on both the fixed frame 72 and the lifting bracket 75.

[0041] The storage chamber 78 contains a non-Newtonian fluid.

[0042] The width of the sliding block 79 is smaller than the width of the storage cavity 78.

[0043] Specifically, during flight, the air pressure prevents the connecting plate 74 from rotating, thus preventing the arm from misaligning during flight. It also eliminates the need for a separate power source, saving costs. Using air for limiting reduces the overall weight, making the aircraft lighter and preventing the arm from wobbling during storage. Furthermore, the storage cavity 78 contains a non-Newtonian fluid, which prevents debris such as tree branches from suddenly hitting the insertion ring 5 during flight, thus unlocking the arm.

[0044] In another embodiment of the present invention, the spraying mechanism 8 includes a connecting plate 81 fixed to the upper end of the lifting bracket 75, the connecting plate 81 being movably inserted into the top of the fixed frame 72, a vent hole 82 being provided on the lower surface of the rotating block 71, a spraying hole 85 being provided on the lower outer wall of the connecting rod 3, the spraying hole 85 being connected to the vent hole 82, a blocking block 83 being fixed to the top of the fixed frame 72, a connecting hole 84 being provided at the bottom of the lifting bracket 75, the upper end of the connecting hole 84 being connected to the connecting groove 710, and the other end of the connecting hole 84 being connected to the outer side of the machine body 1.

[0045] The blocking block 83 and the vent hole 82 are arranged in a ring with equal spacing.

[0046] The spacing between each vent 82 and the spacing between each blocking block 83 are different.

[0047] Specifically, when it is taken out, it is placed on the ground, which causes the insert ring 5 to be squeezed into the fuselage 1. The internal air is forced into the vent 82, and the air is ejected from the jet hole 85. This can spray out debris on the flight fan 4, preventing debris from affecting flight after being left for a long time. It can also spray intermittently, making the spray force fluctuate, thereby improving the spray effect.

[0048] Working principle: When using this device, first remove the fuselage 1 from the housing and place it on the ground. This causes the insertion ring 5 to be squeezed into the fuselage 1. Then, through the transmission of the insertion ring 5, the rack 76, the gear 77 and the lifting bracket 75, the lifting bracket 75 and the connecting plate 81 move downward, so that the connecting plate 81 will not block the vent 82. The connecting groove 710 on the lifting bracket 75 and the connecting groove 710 on the fixed frame 72 are connected. At this time, the rotating column 2 can be rotated. The rotating column 2 drives the connecting rod 3 and the flight fan 4 to rotate outward, so that the flight fan 4 rotates to the outside of the fuselage 1. At this time, the distance between the connecting plate 74 and the end of the fixed frame 72 without the connecting groove 710 becomes smaller, and the internal air will be forced into the vent 82. Thus, the air will be ejected from the jet hole 85, which can spray the debris on the flight fan 4 and prevent the debris on the flight fan 4 from affecting the flight after being placed for a long time.

[0049] Furthermore, the vent 82 will intermittently overlap with the blocking block 83. When they overlap, the vent 82 will be blocked by the blocking block 83, thus allowing for intermittent spraying, which in turn increases or decreases the spraying force and improves the spraying effect. Since the spacing between each vent 82 and the spacing between each blocking block 83 are different, the vent 82 will not be completely blocked by the blocking block 83, and the rotating column 2 can be rotated smoothly.

[0050] When the flight fan 4 is deployed and flight begins, the insert ring 5 extends downward due to the force of the return spring 6, and the lifting bracket 75 moves upward. The connecting groove 710 on the fixed bracket 72 and the lifting bracket 75 is misaligned, and the vent 82 rotates to the upper side of the fixed bracket 72. The vent 82 is blocked by the upper end of the fixed bracket 72. Due to air pressure, the connecting plate 74 can no longer rotate, preventing the arm from misaligning during flight. At the same time, no separate power supply is needed to drive it, saving costs. Using air for limiting can reduce the overall weight and make the aircraft lighter. After the flight is completed, the entire aircraft is landed on the ground, and the insert ring 5 is pressed upward again. At this time, the connecting groove 710 on the fixed bracket 72 and the lifting bracket 75 are connected, and the rotating column 2 can be rotated. When the flight fan 4 is retracted, the entire aircraft is placed in the container. The insert ring 5 is not squeezed. At this time, the connecting plate 81 also moves upward, blocking the vent 82. This can make the space on both sides of the fixed bracket 72 closed, thus preventing the arm from shaking during storage.

[0051] Furthermore, the storage cavity 78 contains a non-Newtonian fluid, which can prevent debris such as tree branches from violently hitting the insertion ring 5 during flight, thus causing the arm to unlock. When an object quickly hits the insertion ring 5, the sliding block 79 will move quickly, and the non-Newtonian fluid in the storage cavity 78 will harden, thereby preventing the sliding block 79 and the insertion ring 5 from moving. The structure is simple and more convenient.

[0052] A method for using an aircraft arm locking mechanism includes the following steps:

[0053] S1. First, take the fuselage 1 out of the housing and place it on the ground. This causes the insert ring 5 to be squeezed into the fuselage 1. Air will be ejected from the jet nozzle 85, which can spray out the debris on the flight fan 4 and prevent the debris on the flight fan 4 from affecting the flight after being left for a long time.

[0054] S2: After the flight fan 4 is deployed, the insertion ring 5 will extend downward due to the force of the return spring 6, and the lifting bracket 75 will move upward. The connecting groove 710 on the fixed bracket 72 and the lifting bracket 75 will be misaligned. Due to air pressure, the connecting plate 74 can no longer rotate, preventing the arm from being misaligned during flight.

[0055] S3: After the flight is completed, the whole unit will be landed on the ground. The insertion ring 5 will be pressed upward again. At this time, the connecting groove 710 on the fixed frame 72 and the lifting insertion frame 75 will be connected, and the rotating column 2 can be rotated. After the flight fan 4 is retracted, the whole unit will be placed in the container to prevent the arm from shaking during storage.

[0056] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of this invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft arm locking mechanism, comprising a fuselage (1), a rotating column (2) is rotatably arranged at each of the four corners of the upper surface of the fuselage (1), a connecting rod (3) is fixedly connected to the upper end of the rotating column (2), and a flight fan (4) is fixedly connected to the end of the connecting rod (3) away from the rotating column (2), characterized in that, Also includes: The insert ring (5) can automatically unlock. The insert ring (5) is movably inserted into the lower surface of the body (1). A return spring (6) is fixed between the upper end of the insert ring (5) and the body (1). A locking mechanism (7) is used to automatically lock the rotating column (2). The locking mechanism (7) is located at the bottom end of the rotating column (2). The locking mechanism (7) includes a rotating block (71) fixed to the bottom end of the rotating column (2). The rotating block (71) is rotatably disposed inside the body (1). A rotating column (73) is fixed at the center of the bottom end of the rotating block (71). A rotating cavity (711) is opened on the outside of the rotating column (73) inside the body (1). A connecting plate (74) is fixed to the outer wall of the rotating column (73). The connecting plate (74) is movably disposed inside the rotating cavity (711) and abuts against the inner wall of the rotating cavity (711). A fixing frame (72) is fixed to the inner wall of the rotating cavity (711). 72) The fixed frame (72) is in contact with the outer wall of the rotating column (73). The bottom end of the fixed frame (72) is movably inserted with a lifting bracket (75). The side wall of the lifting bracket (75) is fixed with an external tooth. The side of the lifting bracket (75) is movably inserted with a straight rack (76). The straight rack (76) and the external tooth are meshed with a gear (77). The gear (77) is rotatably disposed in the body (1). The bottom end of the straight rack (76) is fixedly connected to the upper end of the insert ring (5). The fixed frame (72) is provided with a storage cavity (78). The storage cavity (78) is slidably disposed with a sliding block (79). The sliding block (79) is fixedly connected to the lifting bracket (75). The fixed frame (72) and the lifting bracket (75) are both provided with a connecting groove (710). And a jetting mechanism (8) is provided to jettison the flying fan (4). The jetting mechanism (8) is located in the locking mechanism (7). The jetting mechanism (8) includes a connecting plate (81) fixed to the upper end of the lifting bracket (75). The connecting plate (81) is movably inserted into the top of the fixed frame (72). A ventilation hole (82) is provided on the lower surface of the rotating block (71). A jetting hole (85) is provided on the lower outer wall of the connecting rod (3). The jetting hole (85) is connected to the ventilation hole (82). A blocking block (83) is fixed to the top of the fixed frame (72). A connecting hole (84) is provided at the bottom of the lifting bracket (75). The upper end of the connecting hole (84) is connected to the connecting groove (710). The other end of the connecting hole (84) is connected to the outer side of the fuselage (1).

2. The aircraft arm locking mechanism according to claim 1, characterized in that: The bottom end of the insert ring (5) extends to the lower side of the fuselage (1).

3. The aircraft arm locking mechanism according to claim 2, characterized in that: The storage chamber (78) contains a non-Newtonian fluid.

4. The aircraft arm locking mechanism according to claim 3, characterized in that: The width of the sliding block (79) is smaller than the width of the storage cavity (78).

5. The aircraft arm locking mechanism according to claim 4, characterized in that: The blocking block (83) and the vent (82) are arranged in a ring at equal intervals.

6. The aircraft arm locking mechanism according to claim 5, characterized in that: The spacing between the various vents (82) and the spacing between the various blocking blocks (83) are different.

7. A method of using an aircraft arm locking mechanism, based on the aircraft arm locking mechanism of claim 6, characterized in that: Includes the following steps: S1. First, take the fuselage (1) out of the housing and place it on the ground. This causes the insert ring (5) to be squeezed into the fuselage (1). Air will be ejected from the jet hole (85) to spray out debris on the flight fan (4) and prevent debris on the flight fan (4) from affecting flight after being placed for a long time. S2: After the flight fan (4) is deployed, the insert ring (5) will extend downward due to the force of the return spring (6), the lifting bracket (75) will move upward, the connecting groove (710) on the fixed bracket (72) and the lifting bracket (75) will be misaligned, and due to air pressure, the connecting plate (74) will no longer be able to rotate, thus preventing the arm from being misaligned during flight; S3: After the flight is completed, the whole thing is landed on the ground. The insert ring (5) is pressed upward again. At this time, the connecting groove (710) on the fixed frame (72) and the lifting insert (75) are connected, and the rotating column (2) can be rotated. After the flight fan (4) is retracted, the whole thing is placed in the container to prevent the arm from shaking when it is stored.

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