Side wing synchronous separation structure

Abstract

The present invention provides a wing-synchronized separation structure that can synchronously separate two wings from the fuselage, achieving a stable flight trajectory. Wing-release springs are provided between the wings and the fuselage on both sides. The structure also includes a rotating screw driven by a drive motor. A transmission gear is axially and perpendicularly disposed above the rotating screw and located on the outer periphery of a transmission drum. The transmission drum has an axial travel groove, a wing-fixing column disposed within the transmission drum, and a travel clamping shaft is disposed on the wing-fixing column. The travel clamping shaft slides in the travel groove. The rotating drum also has an open groove corresponding to the travel clamping shaft for sliding. The rotating screw drives the transmission gear, which drives the transmission drum to rotate, achieving pressurized fixation or wing release control. When the travel clamping shaft reaches a position corresponding to the open groove, the wings are synchronously released by a spring disposed between the wing and the fuselage. This allows both wings to be installed or released simultaneously, resulting in extremely stable and reliable flight attitude control.

Description

Technical Field

[0001] The present invention relates to a wing structure of an unmanned aerial vehicle (UAV), and more particularly to a synchronous separation structure of wings on both sides of a winged UAV. Background Art

[0002] In the prior art, drones typically use a rotating rotor structure for ascent. However, this propulsion system, which relies on rotating propellers to achieve ascent, is extremely energy-intensive. Consequently, those skilled in the art have designed fixed-wing drones that utilize a wing-lift aerodynamic lift structure, increasing the flight range of drones with comparable payloads. However, prior art winged drones require certain drop capabilities during flight, and in the later stages of flight, they also require the ability to rapidly dive toward a specific target. This requires a wing-discarding feature in the latter stages of flight. This design allows for acceleration in the latter stages and better adjusts the aircraft's attitude for impact. However, wing-discarding requires both wings to detach simultaneously to prevent them from asynchronously affecting the dive airflow, thus enabling a more direct dive toward the target. The technical challenge to be overcome in this area is to reduce the drag generated by the drone's wings during a dive, enabling the drone to achieve higher speeds. Furthermore, the art requires that when the drone locks onto a target, a wing-discarding spring releases potential energy, ejecting the wings. This allows the drone to rapidly dive toward the target in a wingless state. Summary of the Invention

[0003] The technical purpose of the present invention is to overcome the technical defect of the inflexible wing structure of the UAV wings in the prior art, and to provide a side wing synchronous separation structure that can synchronously separate the wings on both sides from the fuselage body to achieve a stable flight trajectory.

[0004] In order to achieve the above technical objectives, the technical solution of the present invention is:

[0005] The wing synchronous separation structure includes wings on both sides, and wing-off springs are provided between the wings on both sides and the fuselage; it also includes a rotating screw, which is driven by a driving motor, and a transmission gear is axially and vertically arranged above the rotating screw, and the transmission gear is arranged on the outer periphery of a transmission roller, and an axial stroke groove is provided in the transmission roller, and a wing fixing column is provided in the transmission roller, and a stroke clamping shaft is provided on the wing fixing column, and the stroke clamping shaft slides in the stroke groove, and an open groove corresponding to the stroke clamping shaft is also provided on the rotating roller for sliding of the stroke clamping shaft; the rotating screw drives the transmission gear, and the transmission gear drives the transmission roller to rotate, so as to realize pressurized fixation or wing-off control of the stroke groove and the stroke clamping shaft. When the stroke clamping shaft reaches the position corresponding to the opening groove, the wing is synchronously detached by the wing-off spring provided between the wing and the fuselage.

[0006] Furthermore, wing horizontal fixing columns are provided between the wings on both sides and the fuselage, and the wing horizontal fixing columns are inserted into the sockets of the fuselage to fix the wings.

[0007] Furthermore, two front and rear wing horizontal fixing columns are provided on each wing.

[0008] The beneficial technical effect of the present invention is that when on the ground, the wings can be installed by means of the wing release springs between the compressor wings and the fuselage, the wings are locked and obtain the potential energy provided by the wing release springs. The use of wings during flight achieves a better energy to flight mileage ratio, that is, with the same battery power or fuel tank capacity, a longer delivery distance can be achieved by using wings. A rotating screw is used to simultaneously drive the installation or detachment of the wings between the two sides and the fuselage, thereby achieving the installation or detachment of the wings on both sides, thereby avoiding the airflow changes caused by the wings detaching from the fuselage one after the other, which affects the aiming target. The flight attitude control is extremely stable and reliable. In the absence of wing resistance, the present invention can increase the flight speed of the aircraft to 2 to 3 times the original speed, and after the wings are detached, it can achieve an extremely fast dive speed. The aircraft's canards and the elevators at the tail are used to control the dive angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 Schematic diagram of the internal structure of the transmission roller in one embodiment of the present invention.

[0010] Figure 2 Schematic diagram of the external structure of the transmission roller in one embodiment of the present invention.

[0011] Figure 3 It is a structural schematic diagram of a transmission roller and its base in one embodiment of the present invention.

[0012] Figure 4 It is a schematic structural diagram of a transmission roller connecting two side wings in one embodiment of the present invention.

[0013] Figure 5 It is a schematic structural diagram of a wing and its travel clamping shaft in one embodiment of the present invention. DETAILED DESCRIPTION

[0014] Combine Figures 1 to 5 , describes in detail the specific implementation methods of the present invention, but does not limit the claims.

[0015] The wing synchronous separation structure of the present invention includes wings 100 on both sides, and wing release springs 101 are provided between the wings 100 on both sides and the fuselage 101; it also includes a rotating screw 201, which is driven by a driving motor, and a transmission gear 202 is provided axially vertically above the rotating screw 201; see the attached Figure 3During implementation, the rotating screw 201 matches the gear of the transmission gear 202. The rotation of the rotating screw 201 drives the rotation of the transmission gear 202. The transmission gear is provided on the outer periphery of a transmission roller 203, and the transmission roller 203 is provided with an axial stroke groove 204.

[0016] The driving drum 203 is provided with a wing fixing column 301, see the attached Figure 5 The wing fixing column 301 is provided with a travel clamping shaft 311. The travel clamping shaft 311 slides in the travel groove 204 to achieve the purpose of pulling the wings on both sides toward the fuselage or loosening and popping out the wings. The rotating drum 203 is also provided with an opening groove 205 corresponding to the travel clamping shaft 311, which is used for the travel clamping shaft 311 to be inserted or ejected.

[0017] That is, when installing the wings on both sides, the stroke clamping shaft 311 is aligned with the opening of the opening groove 205 and inserted, the driving motor drives the rotating screw 201 to rotate in the forward direction, the rotating screw 201 drives the transmission gear 202 to rotate, and the transmission gear 202 drives the transmission roller 203 to rotate; the stroke clamping shaft 311 slides in the stroke groove 204 in the transmission roller 203 and moves axially inward. After reaching the clamping position, the wings on both sides are pressed inward for installation. At this time, the wing release springs 206 arranged between the wings and the fuselage on both sides are compressed to form potential energy.

[0018] When the wings are released, the drive motor drives the rotating screw 201 to rotate in the opposite direction, which in turn drives the transmission gear 202 to rotate, which in turn drives the transmission roller 203 to rotate. The travel clamping shaft 311 slides in the travel groove 204 in the transmission roller 203 and moves axially outward. When the travel clamping shaft 311 rotates to the corresponding notch in the opening groove 205, the potential energy of the wing release spring 206 is released, and the wing is ejected by the wing release spring 206. During implementation, wing horizontal fixing columns 210 are provided between the wings on both sides and the fuselage. The wing horizontal fixing columns 210 are inserted into the sockets of the fuselage to fix the wings. Two wing horizontal fixing columns 210 are provided on each wing, one at the front and one at the back.

[0019] In the present invention, the transmission gear 202 drives the transmission roller 203 to rotate, realizing the synchronous pressurization and fixation of the travel grooves 204 and the travel clamping shaft 311 on both sides or the synchronous wing removal control. The present invention simultaneously realizes the installation or removal of the wings on both sides, avoiding the airflow changes caused by the two wings separating from the fuselage one after the other and affecting the aiming target, and the flight attitude control is extremely stable and reliable.

Claims

1. The flank synchronous separation structure is characterized by: The invention comprises wings on both sides, and wing-off springs are provided between the wings on both sides and the fuselage; the invention also comprises a rotating screw, which is driven by a driving motor, and a transmission gear is axially and vertically arranged above the rotating screw, and the transmission gear is arranged on the outer periphery of a transmission roller, and an axial stroke groove is provided in the transmission roller, and a wing fixing column is provided in the transmission roller, and a stroke clamping shaft is provided on the wing fixing column, and the stroke clamping shaft slides in the stroke groove, and an open groove corresponding to the stroke clamping shaft is further provided on the rotating roller for sliding of the stroke clamping shaft; the rotating screw drives the transmission gear, and the transmission gear drives the transmission roller to rotate, so as to realize pressurized fixation or wing-off control of the stroke groove and the stroke clamping shaft, and when the stroke clamping shaft reaches the position corresponding to the opening groove, the wing is synchronously detached by the spring arranged between the wing and the fuselage.

2. The wing synchronous separation structure according to claim 1, characterized in that: Wing horizontal fixing columns are provided between the wings on both sides and the fuselage, and the wing horizontal fixing columns are inserted into the sockets of the fuselage to fix the wings.

3. The wing synchronous separation structure according to claim 2, characterized in that: The wings are each provided with two front and rear wing horizontal fixing columns.

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