Arm locking mechanism for aircraft and use method of arm locking mechanism

Abstract

The invention relates to the technical field of aircrafts, in particular to an aircraft arm locking mechanism and a using method thereof.The aircraft arm locking mechanism comprises a fuselage, rotating columns are rotationally arranged at the four corners of the upper surface of the fuselage, connecting rods are fixedly connected to the upper ends of the rotating columns, and a flight fan is fixedly connected to the ends, away from the rotating columns, of the connecting rods; and the locking mechanism is used for automatically locking the rotating column and is arranged at the bottom end of the rotating column. According to the arm locking mechanism for the aircraft and the using method of the arm locking mechanism, when the aircraft flies, due to air pressure, the connecting plate cannot rotate any more, arm dislocation in the flying process is prevented, meanwhile, an independent power source is not needed for driving, cost is saved, air is used for limiting, the overall weight can be reduced, and the aircraft can be lighter; and moreover, the non-Newtonian fluid is arranged, so that the situation that the arms are unlocked due to the fact that sundries such as branches violently touch the insertion rings during flying can be prevented.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a machine arm locking mechanism for an aircraft and a use method thereof. BACKGROUND

[0002] Multi-rotor aircraft has the advantages of flexible, fast response, strong environmental adaptability and low operation requirements. In order to enable the aircraft to switch between land driving state and air flight state, the machine arm of the aircraft needs to be able to fold and unfold.

[0003] In the prior art, after the machine arm of the aircraft is unfolded or folded, instability phenomenon occurs, so some aircrafts are equipped with independent locking mechanisms to lock the rotating machine arm. The locking mechanism needs to be equipped with a separate power source, which increases the complexity of the structure of the aircraft, and the increase of the power source reduces the overall endurance of the aircraft and is not conducive to the lightweight of the aircraft. SUMMARY

[0004] In order to solve the above problems, the present application provides a machine arm locking mechanism for an aircraft.

[0005] The present application adopts the following technical scheme, a machine arm locking mechanism for an aircraft, comprising a fuselage, rotating columns are rotatably arranged at the four corners of the upper surface of the fuselage, a connecting rod is fixedly connected to the upper end of the rotating column, and a flight fan is fixedly connected to the end of the connecting rod away from the rotating column, further comprising:

[0006] A plug ring can automatically release the lock, the plug ring is inserted into the lower surface of the fuselage, and a return spring is fixedly connected between the upper end of the plug ring and the fuselage;

[0007] A locking mechanism is used to automatically lock the rotating column, and the locking mechanism is arranged at the bottom end of the rotating column.

[0008] A jet mechanism can jet the flight fan, and the jet mechanism is arranged in the locking mechanism.

[0009] As a further description of the above technical solution: the locking mechanism comprises a rotating block fixed to the bottom end of the rotating column, the rotating block is rotatably arranged in the fuselage, a rotating column is fixed to the center of the bottom end of the rotating block, a rotating cavity is opened in the fuselage outside the rotating column, an adapter plate is fixed to the outer wall of the rotating column, the adapter plate is movably arranged in the rotating cavity, and the adapter plate is in contact with the inner wall of the rotating cavity, a fixed frame is fixed to the inner wall of the rotating cavity, the fixed frame is in contact with the outer wall of the rotating column, a lifting plug-in frame is movably inserted into the bottom end of the fixed frame, an outer gear is fixed to one side wall of the lifting plug-in frame, a straight gear rack is movably inserted into the lifting plug-in frame, a gear is meshed and connected between the straight gear rack and the outer gear, the gear is rotatably arranged in the fuselage, the bottom end of the straight gear rack is fixed to the upper end of the plug-in ring, a storage cavity is opened in the fixed frame, a sliding block is movably arranged in the storage cavity, the sliding block is fixed to the lifting plug-in frame, and a communication groove is opened in the fixed frame and the lifting plug-in frame.

[0010] As a further description of the above technical solution: the spraying mechanism comprises a connecting single plate fixed to the upper end of the lifting plug-in frame, the connecting single plate is movably inserted into the top of the fixed frame, the lower surface of the rotating block is provided with a ventilation hole, the lower outer wall of the adapter rod is provided with a spraying hole, the spraying hole is in communication with the ventilation hole, the top end of the fixed frame is fixed with a blocking block, the bottom end of the lifting plug-in frame is provided with a communication hole, the upper end of the communication hole is in communication with the communication groove, and the other end of the communication hole is in communication with the outside of the fuselage.

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

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

[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 block and the ventilation hole are both annularly and equally spaced with a plurality of.

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

[0016] In addition, the present application adopts the following technical scheme, a method for using the machine arm locking mechanism of the aircraft, comprising the following steps:

[0017] S1, first take the fuselage out of the containing device and put it on the ground, which makes the plug-in ring be pressed into the fuselage, air will be sprayed out of the spraying hole, which can spray the dirt on the flight fan, prevent the dirt on the flight fan from affecting the flight after a long time.

[0018] S2: after the flight fan is unfolded, the insertion ring is extended downward due to the force of the reset spring, the lifting insertion support moves upward, the communication grooves on the fixed support and the lifting insertion support are misaligned, the air pressure causes the connecting plate to be unable to rotate again, preventing the arm from misaligning during flight;

[0019] S3: after the flight is completed, the whole is landed on the ground, the insertion ring is pressed upward again, the communication grooves on the fixed support and the lifting insertion support are communicated, the rotating column can be rotated, after the flight fan is retracted, the whole is placed in the containing device, preventing the arm from shaking when being stored.

[0020] The arm locking mechanism for the aircraft and the use method thereof are provided by improving the prior art, and have the following improvements and advantages compared with the prior art:

[0021] Firstly, during flight, the air pressure causes the connecting plate to be unable to rotate again, preventing the arm from misaligning during flight, and a separate power supply is not needed to drive, saving cost, air is used for limiting, the overall weight can be reduced, the aircraft can be made lighter, the arm can be prevented from shaking when being stored, and the non-Newtonian fluid is arranged in the storage cavity, so that the arm is prevented from being unlocked due to the insertion ring being suddenly hit by branches and other sundries during flight.

[0022] Secondly, when the arm is taken out, the arm is placed on the ground, the insertion ring is pressed into the fuselage, the internal air is pressed into the air passage, the air is sprayed from the spray hole, the sundries on the flight fan can be sprayed, the flight of the flight fan is prevented from being affected by the sundries after being placed for a long time, and the spraying can be intermittent, so that the spraying force is large and small intermittently, and the spraying effect is improved.

[0023] In summary, when the arm is taken out, the arm is placed on the ground, the insertion ring is pressed into the fuselage, the internal air is pressed into the air passage, the air is sprayed from the spray hole, the sundries on the flight fan can be sprayed, the flight of the flight fan is prevented from being affected by the sundries after being placed for a long time, and the spraying can be intermittent, so that the spraying force is large and small intermittently, and the spraying effect is improved, during flight, the air pressure causes the connecting plate to be unable to rotate again, preventing the arm from misaligning during flight, and a separate power supply is not needed to drive, saving cost, air is used for limiting, the overall weight can be reduced, the aircraft can be made lighter, the arm can be prevented from shaking when being stored, and the non-Newtonian fluid is arranged in the storage cavity, so that the arm is prevented from being unlocked due to the insertion ring being suddenly hit by branches and other sundries during flight. BRIEF DESCRIPTION OF DRAWINGS

[0024] The application will be further explained in combination with the drawings and embodiments:

[0025] Figure 1 The structure of the application is shown in the drawings;

[0026] Figure 2 The structure diagram of the lifting ring block provided by the embodiment of the present application is shown in the figure.

[0027] Figure 3 The three-dimensional sectional view of the fuselage provided by the embodiment of the present application is shown in the figure.

[0028] Figure 4 The structure diagram of the locking mechanism provided by the embodiment of the present application is shown in the figure.

[0029] Figure 5 The three-dimensional sectional view of the fixing frame provided by the embodiment of the present application is shown in the figure.

[0030] Figure 6 The structure diagram of the fixing frame and the lifting plug-in frame separated provided by the embodiment of the present application is shown in the figure.

[0031] Figure 7 The Figure 3 The enlarged view of A in the figure.

[0032] In the figure: 1, fuselage; 2, rotating column; 3, connecting rod; 4, flight fan; 5, plug-in ring; 6, reset spring; 7, locking mechanism; 71, rotating block; 72, fixing frame; 73, rotating column; 74, connecting plate; 75, lifting plug-in frame; 76, straight rack; 77, gear; 78, storage cavity; 79, sliding block; 710, communication groove; 711, rotating cavity; 8, jetting mechanism; 81, connecting single plate; 82, air hole; 83, blocking block; 84, communication hole; 85, jetting hole. DETAILED DESCRIPTION

[0033] In order to make the technical means, creative features, purposes and effects realized by the present application easy to understand, the present application is further described below in combination with specific figures. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0034] Please refer to Figure 1 - Figure 7 The embodiment of the present application provides a technical solution: a machine arm locking mechanism for an aircraft, which comprises a fuselage 1, rotating columns 2 are arranged at four corners of the upper surface of the fuselage 1, connecting rods 3 are fixedly connected to the upper ends of the rotating columns 2, flight fans 4 are fixedly connected to the ends of the connecting rods 3 away from the rotating columns 2, and the machine arm locking mechanism further comprises:

[0035] A plug-in ring 5 can automatically release the locking, and the plug-in ring 5 is inserted into the lower surface of the fuselage 1 in an up-down manner, and a reset spring 6 is fixedly connected between the upper end of the plug-in ring 5 and the fuselage 1.

[0036] A locking mechanism 7 is used for automatically locking the rotating column 2, and the locking mechanism 7 is arranged at the bottom end of the rotating column 2.

[0037] And a jet mechanism 8 is arranged in the locking mechanism 7 and can jet the flying fan 4.

[0038] The bottom end of the ring 5 extends to the lower side of the fuselage 1.

[0039] Specifically, through the arrangement of the locking mechanism 7 and the jet mechanism 8, when taken out and placed on the ground, the ring 5 is pressed into the fuselage 1, the internal air is pressed into the air hole 82, and the air is jetted from the jet hole 85, so that the flying fan 4 can be jetted, the flying fan 4 is prevented from being affected by the flying fan 4 after being placed for a long time, and the jetting can be intermittent, so that the jetting force is large and small, and the jetting effect is improved. When flying, the abutment plate 74 cannot rotate due to air pressure, preventing the arm from being misaligned during flight, and a separate power source is not required to drive, saving costs, using air to limit can reduce the overall weight, can make the aircraft lighter, can also prevent the arm from shaking when storing, and the non-Newtonian fluid in the storage cavity 78 can prevent the arm from being unlocked when a branch or other debris hits the ring 5.

[0040] In another embodiment of the application, 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 arranged in the fuselage 1, the rotating column 73 is fixed to the center of the bottom end of the rotating block 71, the rotating cavity 711 is formed in the fuselage 1 outside the rotating column 73, the abutment plate 74 is fixed to the outer wall of the rotating column 73, the abutment plate 74 is movably arranged in the rotating cavity 711, and the abutment plate 74 is in contact with the inner wall of the rotating cavity 711. The fixed frame 72 is fixed to the inner wall of the rotating cavity 711, the fixed frame 72 is in contact with the outer wall of the rotating column 73, the lifting support 75 is movably inserted into the fixed frame 72, one side wall of the lifting support 75 is fixedly connected with the external tooth, the lifting support 75 is movably inserted into the straight tooth bar 76, the straight tooth bar 76 and the external tooth are meshed and connected with the gear 77, the gear 77 is rotatably arranged in the fuselage 1, the bottom end of the straight tooth bar 76 is fixedly connected with the upper end of the ring 5, the storage cavity 78 is formed in the fixed frame 72, the sliding block 79 is movably arranged in the storage cavity 78, the sliding block 79 is fixedly connected with the lifting support 75, and the fixed frame 72 and the lifting support 75 are both provided with the communication groove 710.

[0041] The non-Newtonian fluid is placed in the storage cavity 78.

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

[0043] Specifically, during flight, the abutment plate 74 cannot rotate due to air pressure, preventing misalignment of the arms during flight, and eliminating the need for a separate power source to drive, saving costs, using air for limiting, reducing overall weight, making the aircraft lighter, preventing the arms from shaking when storing, and the non-Newtonian fluid in the storage cavity 78 prevents the insertion ring 5 from being hit by branches and other debris during flight, causing the arms to unlock.

[0044] In another embodiment of the application, the spray mechanism 8 includes a connecting single plate 81 fixed to the upper end of the lifting bracket 75, the connecting single plate 81 is inserted into the top of the fixed frame 72, the lower surface of the rotating block 71 is provided with a ventilation hole 82, the lower side of the abutment rod 3 is provided with a spray hole 85, the spray hole 85 is in communication with the ventilation hole 82, the top end of the fixed frame 72 is fixed with a blocking block 83, the bottom end of the lifting bracket 75 is provided with a communication hole 84, the upper end of the communication hole 84 is in communication with the communication groove 710, and the other end of the communication hole 84 is in communication with the outside of the fuselage 1.

[0045] The blocking block 83 and the ventilation hole 82 are arranged in a ring shape at equal intervals.

[0046] The spacing of each ventilation hole 82 and the spacing of each blocking block 83 are different.

[0047] Specifically, when taking out, it is placed on the ground, which makes the insertion ring 5 be pressed into the fuselage 1, the internal air will be pressed into the ventilation hole 82, so that the air will be sprayed out of the spray hole 85, which can spray the debris on the flight fan 4, prevent the flight fan 4 from being affected by the debris after long-term placement, and can intermittently spray, so that the spraying force is large and small, thereby improving the spraying effect.

[0048] Working principle: when using the device, the fuselage 1 is taken out from the storage device and placed on the ground, which makes the insertion ring 5 be pressed into the fuselage 1, then the transmission of the insertion ring 5, the straight rack 76, the gear 77 and the lifting bracket 75 makes the lifting bracket 75 and the connecting single plate 81 move downward, so that the connecting single plate 81 does not block the ventilation hole 82, the communication groove 710 on the lifting bracket 75 and the communication groove 710 on the fixed frame 72 are in communication, at this time the rotating column 2 can be rotated, the rotating column 2 drives the abutment 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 spacing between the abutment plate 74 and the end of the fixed frame 72 without the communication groove 710 is small, the internal air will be pressed into the ventilation hole 82, so that the air will be sprayed out of the spray hole 85, which can spray the debris on the flight fan 4, prevent the flight fan 4 from being affected by the debris after long-term placement;

[0049] And the vent hole 82 will be intermittent and the blocking block 83 coincides, coincides when the vent hole 82 will be blocked by the blocking block 83, and then can intermittent spray, make the spray strength big or small, and then improve the spray effect, because the spacing of each vent hole 82 and the spacing of each blocking block 83 is different, so that the vent hole 82 will not be completely blocked by the blocking block 83, can smoothly rotate the rotating column 2;

[0050] When the flight fan 4 is unfolded, the flight is carried out, at this time the insertion ring 5 will be stretched downward due to the action force of the reset spring 6, the lifting insertion frame 75 will move upward, the communication groove 710 on the fixed frame 72 and the lifting insertion frame 75 is out of position, and the vent hole 82 is rotated to the upper side of the fixed frame 72, the vent hole 82 is blocked by the upper end of the fixed frame 72, due to air pressure, the connecting plate 74 cannot rotate again, preventing the arm from being out of position during flight, and a separate power supply is not needed to drive, saving cost, using air to limit can reduce the overall weight, can make the aircraft more lightweight, if the flight is completed, the whole is landed on the ground, the insertion ring 5 is pressed upward again, at this time the communication groove 710 on the fixed frame 72 and the lifting insertion frame 75 is communicated, the rotating column 2 can be rotated, when the flight fan 4 is retracted, the whole is placed in the containing device, the insertion ring 5 is not pressed, at this time the connecting single plate 81 also moves upward, blocking the vent hole 82, so that the space on both sides of the fixed frame 72 is in a closed state, thereby preventing the arm from shaking when being stored;

[0051] And the storage cavity 78 is provided with a non-Newtonian fluid, which can prevent the insertion ring 5 from being hit by branches and other debris during flight, so that the arm is unlocked, when an object quickly hits the insertion ring 5, the sliding block 79 will move quickly, the non-Newtonian fluid in the storage cavity 78 will harden, thereby preventing the movement of the sliding block 79 and the insertion ring 5, and the structure is simple and more convenient.

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

[0053] S1, first take the fuselage 1 out of the containing device and place it on the ground, which makes the insertion ring 5 be pressed into the fuselage 1, air will be sprayed out of the spray hole 85, which can spray the debris on the flight fan 4, preventing the debris on the flight fan 4 from affecting the flight after being placed for a long time;

[0054] S2: after unfolding the flight fan 4, the insertion ring 5 will be stretched downward due to the action force of the reset spring 6, the lifting insertion frame 75 will move upward, the communication groove 710 on the fixed frame 72 and the lifting insertion frame 75 is out of position, due to air pressure, the connecting plate 74 cannot rotate again, preventing the arm from being out of position during flight;

[0055] S3: after the flight is completed, the whole is landed on the ground, the ring 5 is pressed upward again, at this time the communication groove 710 on the fixed frame 72 and the lifting plug frame 75 is communicated, the rotating column 2 can be rotated, after the flight fan 4 is retracted, the whole is placed in the container, preventing the arm from shaking when being stored.

[0056] The basic principles, main features and advantages of the present application are shown and described above. Those skilled in the art should understand that the present application is not limited to the above-mentioned embodiments, and the above-mentioned embodiments and descriptions in the specification are only to illustrate the principles of the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. An aircraft arm locking mechanism, comprising a fuselage (1), wherein rotating columns (2) are rotatably disposed 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 inserted into the lower surface of the body (1) and 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), and the locking mechanism (7) is located at the bottom end of the rotating column (2); And a jetting mechanism (8) capable of jetting the flying fan (4), the jetting mechanism (8) being disposed within the locking mechanism (7).

2. The aircraft arm locking mechanism according to claim 1, characterized in that: 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 fixedly connected to the center of the bottom end of the rotating block (71). A rotating cavity (711) is opened on the outer side of the rotating column (73) inside 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 inside 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) abuts against the outer wall of the rotating column (73). A lifting bracket (75) is inserted vertically at the bottom end. An external tooth is fixed to one side wall of the lifting bracket (75). A straight rack (76) is inserted vertically on the side of the lifting bracket (75). A gear (77) meshes between the straight rack (76) and the external tooth. The gear (77) is rotatably disposed in 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 vertically in the fixed frame (72). A sliding block (79) is slidably disposed vertically in 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).

3. The aircraft arm locking mechanism according to claim 2, characterized in that: The spraying mechanism (8) includes a connecting plate (81) fixed to the upper end of the lifting bracket (75). The connecting plate (81) is inserted into the top of the fixed frame (72). A vent hole (82) is opened on the lower surface of the rotating block (71). A spraying hole (85) is opened on the lower outer wall of the connecting rod (3). The spraying hole (85) is connected to the vent hole (82). A blocking block (83) is fixed to the top of the fixed frame (72). A connecting hole (84) is opened 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 outside of the machine body (1).

4. The aircraft arm locking mechanism according to claim 3, characterized in that: The bottom end of the insert ring (5) extends to the lower side of the fuselage (1).

5. The aircraft arm locking mechanism according to claim 4, characterized in that: The storage chamber (78) contains a non-Newtonian fluid.

6. The aircraft arm locking mechanism according to claim 5, characterized in that: The width of the sliding block (79) is smaller than the width of the storage cavity (78).

7. The aircraft arm locking mechanism according to claim 6, characterized in that: The blocking block (83) and the vent (82) are arranged in a ring at equal intervals.

8. The aircraft arm locking mechanism according to claim 7, characterized in that: The spacing between the various vents (82) and the spacing between the various blocking blocks (83) are different.

9. A method of using an aircraft arm locking mechanism, based on the aircraft arm locking mechanism of claim 8, 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 frame (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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