CN110588952A - A fixed-wing aircraft with rapidly detachable wings and a method for quick installation and removal of wings - Google Patents

Abstract

The invention relates to a fixed-wing aircraft whose wings can be quickly disassembled and a method for quickly installing and dismantling the wings. The aircraft includes a fuselage and wings, the two sides of the fuselage are symmetrically connected to the first crossbar, the inner side of the wing is symmetrically connected to the second crossbar and the third crossbar, and the side of the fixed block is provided with a crossbar for the third crossbar to pass through. In the rod hole, a number of overlapping threaded holes are provided on the overlapping part of the first crossbar and the second crossbar, the inner surface of the threaded hole is provided with internal threads, and the upper surface of the third crossbar is provided with a spring box with the same number and position as the threaded holes. The spring box is equipped with a spring and the top is opened. The lower end of the inverted T-shaped connecting rod is located inside the spring box. The outer surface of the upper part is provided with an external thread that meshes with the internal thread of the threaded hole. The lower part is a smooth surface, and the connecting rod passes from bottom to top. Through the sliding hole, the first cross bar and the second cross bar, the upper end is locked with a nut. The wings of the technical proposal can be quickly and accurately installed and disassembled without special tools, which is beneficial for staff to perform maintenance and inspection operations on the aircraft.

Description

A fixed-wing aircraft with rapidly detachable wings and rapid installation and removal of wings method

technical field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a fixed-wing aircraft whose wings can be quickly disassembled and a method for quickly installing and disassembling the wings.

Background technique

Unmanned aircraft, referred to as UAV, is an unmanned aircraft controlled by radio remote control equipment and its own program control device. UAV is actually a general term for unmanned aircraft. From a technical point of view, it can be divided into: Manned fixed-wing aircraft, unmanned vertical take-off and landing aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft and unmanned parawing aircraft, etc. Compared with manned aircraft, it has small size, low cost, and easy to use , Low requirements on the combat environment, strong battlefield survivability and other advantages. Since unmanned aircraft is of great significance to future air combat, all major military countries in the world are stepping up the development of unmanned aircraft. In addition, drones are widely used and have good development prospects in police, urban management, agriculture, geology, meteorology, electric power, emergency rescue and video shooting and other industries.

Unmanned aerial vehicles include fixed-wing aircraft and rotary-wing aircraft. Fixed-wing aircraft refers to aircraft whose wings are fixed to the fuselage and do not move relative to the fuselage. The lift is generated by the force of the air on the wings. A heavier-than-air aircraft flying in the atmosphere, where the power plant produces forward thrust or pull, and the fixed wings of the fuselage produce lift. In the existing fixed-wing aircraft, the fuselage and the wings are connected by welding, or connected by glue, and then beautified by skin. However, this connection method is a permanent fixed connection, which is inconvenient to disassemble. During the transportation or storage process of the UAV when not in use, the wings need to be removed, packaged and transported separately, so as to avoid collision damage to the fuselage or wings due to the large size of the UAV. At the same time, when the aircraft is inspected, repaired, and replaced, the fixed connection cannot quickly and accurately install and disassemble the flight wing, which is not conducive to the inspection and maintenance work of the staff.

Contents of the invention

In view of the above deficiencies, the present invention provides a fixed-wing aircraft with rapidly detachable wings and a quick installation and removal method for the wings. The wings can be quickly and accurately installed and disassembled, which is beneficial for the staff to perform maintenance and inspection operations on the aircraft.

Technical scheme of the present invention is:

A fixed-wing aircraft whose wings can be quickly disassembled. The fixed-wing aircraft includes a fuselage and wings on both sides of the fuselage. It is characterized in that fixed blocks are symmetrically fixed on both sides of the fuselage, and the fixed The outer side of the block is symmetrically connected to the first crossbar, and the inner side of the wing is symmetrically connected to the second crossbar and the third crossbar, and the first crossbar, the second crossbar and the third crossbar are parallel to each other and the first The crossbar is located in the middle of the second crossbar and the third crossbar, the first crossbar and the second crossbar overlap each other, the side of the fixed block is provided with a crossbar hole for the third crossbar to pass through, and the third crossbar The free end of the rod is located in the fixed block; the overlapping parts of the first cross bar and the second cross bar are provided with several overlapping threaded holes, the inner surface of the threaded holes is provided with internal threads, and the upper surface of the third cross bar is provided with threaded holes Spring boxes with the same quantity and position, springs are arranged in the spring box, a sliding hole is opened on the top of the spring box, the connecting rod is an inverted T-shaped bar, the lower end is located inside the spring box, and the diameter of the lower end is larger than the inner diameter of the sliding hole, the connecting rod The outer surface of the upper part is provided with an external thread that engages with the internal thread of the threaded hole, and the lower part is a smooth surface that can slide up and down in the sliding hole. Two cross bars, the upper ends are locked with nuts.

The bottom of the fixing block is provided with a threaded hole communicating with the hole of the cross bar, and a fixing bolt is arranged in the threaded hole.

The spring box is a cylindrical box, and the diameter of the lower end of the connecting rod is equal to the inner diameter of the spring box.

The number of spring boxes on one side of the fuselage is 2-3.

A method for quickly installing wings of a fixed-wing aircraft, comprising the following steps:

S1: Press down the connecting rod so that the lower half of the connecting rod is submerged in the spring box;

S2: Bring the wing closer to the fuselage, insert the first crossbar between the second crossbar and the third crossbar, and make the first crossbar and the second crossbar fit and overlap each other, and the threaded holes are aligned, and the third crossbar The cross bar is inserted into the cross bar hole on the outside of the fixed block;

S3: Loosen the connecting rod, the connecting rod rises under the action of the spring, and the top is aligned with the threaded hole directly above;

S4: Rotate the connecting rod from the side to screw it upward into the threaded hole, and the upper end of the connecting rod protrudes from the second cross bar;

S5: Screw the nut into the top of the connecting rod to lock it;

S6: Screw the fixing bolts into the threaded holes at the bottom of the fixing block to lock.

A method for rapidly dismantling wings of a fixed-wing aircraft, comprising the following steps:

S1: Remove the fixing bolts at the bottom of the fixing block;

S2: Remove the nut on the top of the connecting rod;

S3: Rotate the connecting rod from the side to screw it out of the threaded hole;

S4: Press down the connecting rod, pull the wing outwards, separate the first cross bar from the second cross bar, withdraw the third cross bar from the cross bar hole, and completely separate the fuselage from the wing.

The fuselage of the present invention and the wing are connected by the first cross bar, the second cross bar and the third cross bar arranged in parallel, the first cross bar is fixedly connected with the fixing blocks on both sides of the fuselage, and the second cross bar The rod and the third cross-bar are fixedly connected with the wing, the first cross-bar and the second cross-bar overlap each other, and the overlapped part is provided with several overlapping threaded holes, and the third cross-bar is inserted into the cross-bar holes on both sides of the fixed block middle. The first crossbar and the third crossbar are separated by a certain distance, and the upper surface of the third crossbar is provided with a spring box, and the inverted T-shaped connecting rod passes through the top of the spring box from bottom to top, and passes through the first crossbar and the top of the upper crossbar. The second cross bar, the outer surface of the upper part of the connecting rod is an external thread meshing with the internal thread of the threaded hole, and the lower part is a smooth surface that can slide up and down in the sliding hole. The connecting rod connects and fixes the first cross bar and the second cross bar. The upper end is locked with a nut.

When assembling the fuselage and the wing, press down the inverted T-shaped connecting rod so that the lower half of the connecting rod is submerged in the spring box, push the wing closer to the fuselage, and make the first crossbar and the second crossbar fit together Overlap, the threaded holes are aligned, insert the third crossbar into the crossbar holes on both sides of the fixed block, loosen the connecting rod, the connecting rod rises under the action of the spring, and the top end is aligned with the threaded hole directly above, turning the connecting rod from the side will It is screwed upwards into the threaded hole, and the upper end of the connecting rod protrudes from the second cross bar, which is locked with a nut. Finally, the fixing bolts at the bottom of the fixing block are screwed in to further fix the third crossbar, that is, to complete the connection and assembly of the fuselage and the wing.

When it is necessary to remove the wing from the fuselage, contrary to the above steps, first loosen the nut and the fixing bolt at the bottom of the fixing block, rotate the connecting rod from the side, and screw it down out of the threaded hole, the first cross bar and the second cross bar The connection and fixation between the two crossbars is lost, and the state of separation is present. Pull the wing to the outside to make the third crossbar withdraw from the crossbar hole, and the first crossbar is also separated from the second crossbar at the same time, which is completed. Removal of the fuselage and wings.

Description of drawings

Fig. 1 is the front view of the fixed wing aircraft that wing of the present invention can be quickly disassembled;

Fig. 2 is an enlarged view of part A in Fig. 1 .

Detailed ways

The idea, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings, so as to fully understand the purpose, features and effects of the present invention.

With reference to Fig. 1 and Fig. 2, the fixed-wing aircraft with wings of the present invention can be quickly disassembled. The fixed-wing aircraft includes a fuselage 10 and wings 20 positioned on both sides of the fuselage 10, and fixed blocks are symmetrically fixed on both sides of the fuselage 10. 12. The fixed block 12 is in the shape of a rectangular parallelepiped. The outer surface of the fixed block 12 is symmetrically connected with the first crossbar 11, and the inner surface of the wing 20 is symmetrically connected with the second crossbar 22 and the third crossbar 23. The first crossbar 11 , the second crossbar 22 and the third crossbar 23 are parallel to each other and the first crossbar 11 is located in the middle of the second crossbar 22 and the third crossbar 23, the first crossbar 11 and the second crossbar 22 overlap each other, The side of the fixed block 12 is provided with a cross bar hole for the third cross bar 23 to pass through. The third cross bar 23 is inserted into the cross bar hole, and its free end is located in the fixed block 12 .

The overlapping parts of the first crossbar 11 and the second crossbar 22 are provided with several overlapping threaded holes. For the convenience of installation, the number of threaded holes is 2-3, and the present embodiment is 2. The inner surface of the threaded hole is provided with internal threads, and the third cross bar 23 upper surface is provided with a spring box 24 corresponding to the number and position of the threaded holes. The spring box 24 is a cylindrical box, and the spring box 24 is provided with a spring 25. 24 tops have slide holes. The connecting rod 26 is an inverted T-shaped rod, and its lower end is located inside the spring box 24 , and the diameter of the lower end is greater than the inner diameter of the sliding hole. In this embodiment, the diameter of the lower end is equal to the inner diameter of the spring box 24 . The outer surface of the upper part of the connecting rod 26 is provided with an external thread engaged with the internal thread of the threaded hole, and the bottom is a smooth surface that can slide up and down in the slide hole. The connecting rod 26 passes through the slide hole from bottom to top, and passes through the first first The upper ends of the cross bar 11 and the second cross bar 22 are locked with nuts 27 .

Since the outer surface of the connecting rod 26 top is provided with external threads, and the inner surface of the threaded hole is provided with internal threads, the top of the connecting rod 26 is screwed into the threaded hole, and the end is locked with a nut 27, so that the first cross bar 11 and the second cross bar 11 can be connected to each other. The cross bar 22 is connected and fixed, that is, the fuselage 10 and the wing 20 are connected to each other. Spring box 24 interior is provided with spring 25, can provide upward thrust, under natural state, pushes connecting rod 26 to the top of spring box 24, because connecting rod 26 is an inverted T-shaped bar, its lower end diameter is greater than slide hole inner diameter, Therefore, the connecting rod 26 will not eject the spring box 24, but remains on the top of the spring box 24, which is convenient for installation. After the fuselage 10 and the wing 20 are connected, the third crossbar 23 is located in the crossbar hole of the fixed block 12. In order to further fix the third crossbar 23 and prevent its displacement, the bottom of the fixed block 12 is provided with a hole communicating with the crossbar hole. The threaded hole is provided with a fixing bolt 13 in the threaded hole, and the third cross bar 23 is locked.

The wing rapid installation method of fixed-wing aircraft of the present invention comprises the following steps:

S1: Press down the connecting rod 26 so that the lower half of the connecting rod 26 is submerged in the spring box 24;

S2: Bring the wing 20 closer to the fuselage 10, insert the first crossbar 11 between the second crossbar 22 and the third crossbar 23, and make the first crossbar 11 and the second crossbar 22 overlap each other , the threaded holes are aligned, and the third crossbar 23 is inserted into the crossbar hole on the outside of the fixing block 12;

S3: loosen the connecting rod 26, the connecting rod 26 rises under the action of the spring 25, and the top is aligned with the threaded hole directly above;

S4: Turn the connecting rod 26 from the side to screw it into the threaded hole upwards, and the upper end of the connecting rod 26 protrudes from the second cross bar 22;

S5: Screw the nut 27 into the top of the connecting rod 26 to lock it;

S6: Screw the fixing bolt 13 into the threaded hole at the bottom of the fixing block 12 for locking.

The wing rapid removal method of fixed-wing aircraft of the present invention comprises the following steps:

S1: Loosen the fixing bolt 13 at the bottom of the fixing block 12;

S2: Loosen the nut 27 on the top of the connecting rod 26;

S3: Rotate the connecting rod 26 from the side to unscrew the threaded hole downward;

S4: Press down the connecting rod 26 to pull the wing 20 outward, so that the first cross bar 11 is separated from the second cross bar 22, the third cross bar 23 withdraws from the cross bar hole, and the fuselage 10 and the wing 20 completely separated.

In the fixed-wing aircraft of the present invention, the wings can be installed and disassembled quickly and conveniently, and no special tools are needed in the assembly and disassembly process, which greatly simplifies the disassembly and assembly operations of staff. It is beneficial for the staff to carry out maintenance and inspection operations on the aircraft, and it is also convenient for the wings to be removed and packaged or transported separately when the aircraft needs to be transported or stored, so as to reduce the overall volume of the aircraft and avoid collision damage caused by excessive volume.

The above disclosures are only embodiments of the present invention, but the present invention is not limited thereto, and any changes conceivable by those skilled in the art shall fall within the protection scope of the present invention.

Claims (6)

1. A fixed-wing aircraft whose wings can be quickly disassembled, said fixed-wing aircraft comprises a fuselage (10) and wings (20) positioned at both sides of the fuselage (10), it is characterized in that said fuselage (10) fixed blocks (12) are symmetrically fixed on both sides, the outer surface of the fixed block (12) is symmetrically connected to the first crossbar (11), and the inner surface of the wing (20) is symmetrically connected to the second crossbar ( 22) and the third crossbar (23), the first crossbar (11), the second crossbar (22) and the third crossbar (23) are parallel to each other and the first crossbar (11) is located at the second crossbar In the middle of the bar (22) and the third cross bar (23), the first cross bar (11) and the second cross bar (22) fit and overlap each other, and the side of the fixed block (12) is provided with a third cross bar ( 23) The cross bar hole that passes through, the free end of the third cross bar (23) is located in the fixed block (12); the overlapping parts of the first cross bar (11) and the second cross bar (22) are provided with several overlapping threads hole, the inner surface of the threaded hole is provided with internal threads, the upper surface of the third crossbar (23) is provided with a spring box (24) with the same number and position as the threaded holes, and the spring box (24) is provided with a spring (25) , the top of the spring box (24) has a sliding hole, the connecting rod (26) is an inverted T-shaped bar, its lower end is located inside the spring box (24), and the diameter of the lower end is greater than the inner diameter of the sliding hole, and the upper part of the connecting rod (26) is outside The surface is provided with the external thread that engages with the internal thread of the threaded hole, and the bottom is a smooth surface that can slide up and down in the slide hole, and the connecting rod (26) passes through the slide hole from bottom to top, and passes through the first cross bar ( 11) and the second cross bar (22), the upper end is locked with a nut (27). 2. The fixed-wing aircraft according to claim 1, characterized in that, the bottom of the fixed block (12) is provided with a threaded hole communicating with the cross bar hole, and a fixing bolt (13) is arranged in the threaded hole. 3. The fixed-wing aircraft according to claim 1, wherein the spring box (24) is a cylindrical box, and the diameter of the lower end of the connecting rod (26) is equal to the inner diameter of the spring box (24). 4. The fixed-wing aircraft according to claim 1, characterized in that, the number of spring boxes (24) on one side of the fuselage (10) is 2-3. 5. A wing quick installation method of a fixed-wing aircraft, is characterized in that, comprises the following steps: S1: Press down the connecting rod (26), so that the lower half of the connecting rod (26) is submerged in the spring box (24); S2: move the wing (20) closer to the fuselage (10), insert the first crossbar (11) between the second crossbar (22) and the third crossbar (23), and make the first crossbar ( 11) The second crossbar (22) fits and overlaps each other, the threaded holes are aligned, and the third crossbar (23) is inserted into the crossbar hole on the outside of the fixing block (12); S3: loosen the connecting rod (26), the connecting rod (26) rises under the action of the spring (25), and the top is aligned with the threaded hole directly above; S4: Turn the connecting rod (26) from the side to screw it into the threaded hole upwards, and the upper end of the connecting rod (26) protrudes from the second cross bar (22); S5: Screw the nut (27) into the top of the connecting rod (26) to lock it; S6: Screw the fixing bolt (13) into the threaded hole at the bottom of the fixing block (12) to lock. 6. A method for rapidly removing wings of a fixed-wing aircraft, comprising the following steps: S1: remove the fixing bolt (13) at the bottom of the fixing block (12); S2: remove the nut (27) on the top of the connecting rod (26); S3: Rotate the connecting rod (26) from the side to screw it out of the threaded hole downwards; S4: Press down the connecting rod (26), pull the wing (20) outward, separate the first crossbar (11) from the second crossbar (22), and the third crossbar (23) from the crossbar hole Exit in middle, fuselage (10) and wing (20) separate completely.