Gliding unmanned aerial vehicle with folding wings

Abstract

The utility model discloses a gliding unmanned aerial vehicle with folding wings. A canard-type middle-single-wing aerodynamic layout is adopted; the full-moving front wing can be folded downwards by 90 degrees; the two main wings are an outer main wing and an inner main wing, the outer main wing can be folded downwards by 180 degrees at the joint of the outer main wing and the inner main wing, and the lower surfaces of the wings are opposite; the inner main wing can be folded upwards by 90 degrees at the joint of the inner main wing and the main wing reinforcing rib; main wing reinforcing ribs on two sides of the fuselage are fixed with main wing rotating shafts and can rotate around the main wing rotating shafts, so that the main wing reinforcing ribs are switched between a horizontal state and a vertical state; when the two sections of main wings are folded and placed in parallel to the fuselage, the front edges of the folded main wings are below; the vertical empennage can be retracted into the fuselage. Compared with a conventional layout, the canard layout has better maneuverability, the canard wings and the main wings generate lift force, and the folded wings have a large aspect ratio after being unfolded, so that the large lift-drag ratio is favorably provided, and gliding flight of the unmanned aerial vehicle is facilitated.

Description

TECHNICAL FIELD

[0001] The utility model provides a gliding unmanned plane with folding wings, duck type single wing aerodynamic layout, the full -time movable front wing can fold down, there are two main wings of outer main wing and inner main wing, the outer main wing can fold down 180 DEG at the joint with the inner main wing, the lower surface of the wing is opposite, the inner main wing can fold up 90 DEG at the joint with the main wing reinforcing rib, the main wing reinforcing rib on both sides of the fuselage has main wing rotating shaft, can rotate around main wing rotating shaft, makes the main wing reinforcing rib convert in horizontal and vertical state, when the two main wings are placed in parallel position after folding, the front edge of the folding main wing is below, adopts mechanical type lock mechanism to realize reliable lock after the wing unfolding, the vertical tail can be received in the fuselage. BACKGROUND

[0002] At present, the quality of the power device and the energy system of the small and medium-sized unmanned plane accounts for a large proportion of the overall quality of the unmanned plane, reduces the task load of the unmanned plane. SUMMARY

[0003] The utility model provides a gliding unmanned plane with folding wings, duck type single wing aerodynamic layout, the full -time movable front wing can fold down 90 DEG, there are two main wings of outer main wing and inner main wing, the outer main wing can fold down 180 DEG at the joint with the inner main wing, the lower surface of the wing is opposite, the inner main wing can fold up 90 DEG at the joint with the main wing reinforcing rib, the main wing reinforcing rib on both sides of the fuselage has main wing rotating shaft, can rotate around main wing rotating shaft, makes the main wing reinforcing rib convert in horizontal and vertical state, when the two main wings are placed in parallel position after folding, the front edge of the folding main wing is below, adopts mechanical type lock mechanism to realize reliable lock after the wing unfolding, the vertical tail can be received in the fuselage.

[0004] The utility model has the advantages that: the unfolded wing has a large aspect ratio, which helps to provide a large lift-drag ratio, the folding direction of the front wing and the main wing is the same as the longitudinal direction of the fuselage, and the vertical tail is stored in the fuselage, which is convenient for loading. BRIEF DESCRIPTION OF DRAWINGS

[0005] Figure 1is a top view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 2 is a front wing reinforcing rib; 3 is a folding movable front wing rotating shaft; 4 is a fixed front wing, the wing span length of which is the same as the fuselage; 5 is an aileron; 6 is an outer main wing; 7 is an inner main wing; 8 is a main wing reinforcing rib, the two sides of the main wing reinforcing rib have a main wing rotating shaft (9); 9 is a main wing rotating shaft; 10 is a fuselage; 11 is a vertical tail. Figure 2 is a front view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 4 is a fixed front wing; 6 is an outer main wing; 7 is an inner main wing; 10 is a fuselage; Figure 3 is a left view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 5 is an aileron; 6 is an outer main wing; 7 is an inner main wing; 10 is a fuselage; 11 is a vertical tail; 12 is a rudder. Figure 4 is a front view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 2 is a front wing reinforcing rib; 5 is an aileron; 6 is an outer main wing; 7 is a side main wing; 10 is a fuselage; the leading edge of the main wing is down. Figure 5 is a top view of a gliding unmanned aerial vehicle with folding wings, wherein 2 is a front wing reinforcing rib; 3 is a folding movable front wing rotating shaft; 4 is a fixed front wing; 5 is an aileron; 6 is an outer main wing; 7 is an inner main wing; 8 is a main wing reinforcing rib; 9 is a main wing rotating shaft; 10 is a fuselage; 11 is a vertical tail retracted into the fuselage; 12 is a rudder; the folded outer main wing (6) and inner main wing (7) are on both sides of the fuselage. Figure 6 is a left view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a downwardly folded movable front wing; 3 is a folding movable front wing rotating shaft; 4 is a fixed front wing; 6 is an outer main wing; 7 is an inner main wing; 10 is a fuselage; the folded outer main wing (6) and inner main wing (7) are on both sides of the fuselage. Figure 7 is a cross-sectional view of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 2 is a front wing reinforcing rib; 3 is a folding movable front wing rotating shaft; 4 is a fixed front wing; 10 is a fuselage; 13 is a folding driving motor of the movable front wing (1); 14 is a folding hinge of the foldable movable front wing (1) and the front wing reinforcing rib (2); 15 is a fixed worm gear of the folding movable front wing rotating shaft (3), the worm gear shaft is the movable front wing rotating shaft (3); 16 is a driving worm of the fixed worm gear (16) of the folding movable front wing rotating shaft (3), the worm bearing seat and the driving motor are fixed on the fuselage. Figure 8 is a front view of a fuselage front part of a gliding unmanned aerial vehicle with folding wings, wherein 1 is a foldable movable front wing; 2 is a front wing reinforcing rib; 10 is a fuselage. Figure 9A kind of glider unmanned aerial vehicle with folding wing, the section view of the front wing when it is unfolded horizontally, wherein, 1 is the full movable front wing that can be folded;2 is the front wing reinforcing wing rib;3 is the rotation shaft of the folded full movable front wing, used for attitude control;4 is the fixed front wing, the wing span of the fixed front wing is the same as the diameter of the fuselage, ensuring the full movable front wing to be folded downward by 90°;10 is the fuselage;14 is the folding hinge of the full movable front wing (1) and the front wing reinforcing wing rib (2);15 is the fixed worm wheel of the rotation shaft (3) of the folded full movable front wing, the worm wheel shaft is the rotation shaft (3) of the full movable front wing;16 is the driving worm of the fixed worm wheel (16) of the rotation shaft (3) of the folded front wing, the worm bearing seat and the driving motor are fixed on the fuselage. Figure 10 A kind of glider unmanned aerial vehicle with folding wing, the front view of the front wing when it is unfolded horizontally, wherein, 1 is the full movable front wing that can be folded;2 is the front wing reinforcing wing rib;10 is the fuselage. Figure 11 A kind of glider unmanned aerial vehicle with folding wing, the section view of the main wing when it is folded on both sides of the fuselage, wherein, 6 is the outer main wing;7 is the inner main wing;8 is the main wing reinforcing wing rib;9 is the main wing rotation shaft, the bearing seat of which is fixed on the fuselage (10);10 is the fuselage;17 is the worm wheel of the main wing rotation shaft, the worm wheel shaft is the main wing rotation shaft (9), the bearing seat of which is fixed on the fuselage;18 is the meshing worm of the worm wheel (17) of the main wing rotation shaft (9), the worm bearing seat and the driving motor are fixed on the fuselage;At this time, the chord direction of the main wing reinforcing wing rib (8) is vertical, the wing leading edge of the folded outer main wing (6) and the inner main wing (7) is downward, and the span direction is the same as the longitudinal axis direction of the fuselage. Figure 12 A kind of glider unmanned aerial vehicle with folding wing, the front view of the main wing when it is folded horizontally on both sides of the fuselage, wherein, 7 is the inner main wing;8 is the main wing reinforcing wing rib;10 is the fuselage;At this time, the chord direction of the main wing reinforcing wing rib (8) is vertical, the wing leading edge of the folded outer main wing (6) and the inner main wing (7) is downward, and the span direction is the same as the longitudinal axis direction of the fuselage. Figure 13 A kind of glider unmanned aerial vehicle with folding wing, the section view of the main wing when it is folded vertically upward, wherein, 6 is the outer main wing;7 is the inner main wing;8 is the main wing reinforcing wing rib;9 is the main wing rotation shaft, 10 is the fuselage;17 is the worm wheel of the main wing rotation shaft, the worm wheel shaft is the main wing rotation shaft (9), the bearing seat of which is fixed on the fuselage;18 is the meshing worm of the worm wheel (17) of the main wing rotation shaft, the worm bearing seat and the driving motor are fixed on the fuselage;At this time, the main wing reinforcing wing rib (8) is in horizontal state, and the span direction of the folded outer main wing (6) and the inner main wing (7) is upward. Figure 14 A kind of glider unmanned aerial vehicle with folding wing, the front view of the main wing when it is folded vertically upward, wherein, 7 is the inner main wing;8 is the main wing reinforcing wing rib;10 is the fuselage;At this time, the main wing reinforcing wing rib (8) is in horizontal state, and the span direction of the folded outer main wing (6) and the inner main wing (7) is upward.Figure 15 A gliding unmanned aerial vehicle with folding wings, the cross-sectional view of the main wings unfolded horizontally, wherein 7 is the inner main wing; 8 is the main wing stiffening rib; 9 is the main wing rotating shaft, the bearing seat of which is fixed on the fuselage; 10 is the fuselage; 17 is the worm gear of the main wing rotating shaft, the worm shaft being the main wing rotating shaft (9); 18 is the meshing worm of the worm gear (18) of the main wing rotating shaft, the worm bearing seat and the driving motor being fixed on the fuselage; the wingspans of the folded outer main wing (6) and the inner main wing (7) are in the same direction as the lateral axis of the fuselage. Figure 16 A gliding unmanned aerial vehicle with folding wings, the front view of the main wings unfolded horizontally, wherein 6 is the outer main wing; 7 is the inner main wing; 10 is the fuselage; the wingspans of the folded outer main wing (6) and the inner main wing (7) are in the same direction as the lateral axis of the fuselage. Figure 17 A gliding unmanned aerial vehicle with folding wings, the front view of the folding hinge position of the full-motion front wing (1) and the front wing stiffening rib (2), wherein 1 is the full-motion front wing; 2 is the front wing stiffening rib; 13 is the folding hinge driving motor, the shell (stator) of the motor being fixed with the front wing stiffening rib (2), the motor (rotor) shaft being fixed with the full-motion front wing folding hinge (14), the motor driving the full-motion front wing (1) to fold; 14 is the folding hinge; the full-motion front wing (1) is folded downward by 90° relative to the front wing stiffening rib (2). Figure 18 A gliding unmanned aerial vehicle with folding wings, the top view of the folding hinge position of the front wing stiffening rib (2) and the full-motion front wing (1), wherein 1 is the full-motion front wing; 2 is the front wing stiffening rib; 13 is the folding hinge driving motor; 14 is the folding hinge; 20 and 21 are the folding joints. Figure 19 A gliding unmanned aerial vehicle with folding wings, the left view of the folding hinge position of the front wing stiffening rib (2) and the full-motion front wing (1), wherein 1 is the full-motion front wing; 2 is the front wing stiffening rib; 13 is the folding hinge driving motor; 14 is the folding hinge; 20 and 21 are the folding joints. Figure 20 A gliding unmanned aerial vehicle with folding wings, the front view of the folding hinge position of the inner main wing (7), wherein 7 is the inner main wing; 8 is the main wing stiffening rib; 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding driving motor, the shell (stator) of the motor being fixed with the main wing stiffening rib (8), the motor (rotor) shaft being fixed with the inner main wing (7) folding hinge (19), the motor driving the inner main wing (7) to fold, the inner main wing (7) being folded upward by 90°. Figure 21A gliding unmanned aerial vehicle with folding wings, the left view of the folding hinge position of the inner main wing (7), wherein 7 is the inner main wing; 8 is the main wing stiffening rib; 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor; the inner main wing (7) is folded upward by 90°. Figure 22 A gliding unmanned aerial vehicle with folding wings, the left view of the folding hinge position of the inner main wing (7), wherein 7 is the inner main wing; 8 is the main wing stiffening rib; 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor; the inner main wing (7) is folded upward by 90°. Figure 23 A gliding unmanned aerial vehicle with folding wings, the front view of the folding hinge position of the outer main wing (6) and the inner main wing (7), wherein 6 is the outer main wing; 7 is the inner main wing; 23 is the folding hinge; 24 and 25 are the folding joints; 26 is the folding drive motor; the outer main wing (6) is folded upward by 180°; 27 is the folding hinge. Figure 24 A gliding unmanned aerial vehicle with folding wings, the front view of the folding hinge position of the outer main wing (6) and the inner main wing (7), wherein 7 is the inner main wing; 23 is the folding hinge; 26 is the folding drive motor; 27 is the folding hinge. Figure 25 A gliding unmanned aerial vehicle with folding wings, the left view of the folding hinge position of the outer main wing (6) and the inner main wing (7), wherein 6 is the outer main wing; 7 is the inner main wing; 23 is the folding hinge; 24 and 25 are the folding joints; 26 is the folding drive motor; the wing lower skin of the outer main wing (6) and the inner main wing (7) is opposite. Figure 26 A gliding unmanned aerial vehicle with folding wings, the cross-sectional view of the folding downward by 90° of the full-motion front wing (1) and the front wing stiffening rib (2), wherein 1 is the full-motion front wing; 2 is the front wing stiffening rib; 3 is the full-motion front wing rotating shaft; 4 is the fixed front wing; 13 is the folding drive motor; 14 is the folding hinge; 20 and 21 are the folding joints. Figure 27 A gliding unmanned aerial vehicle with folding wings, the cross-sectional view of the folding horizontally unfolded of the full-motion front wing (1) and the front wing stiffening rib (2), wherein 1 is the full-motion front wing; 2 is the front wing stiffening rib; 3 is the full-motion front wing rotating shaft; 4 is the fixed front wing; 13 is the folding drive motor; 14 is the folding hinge; 20 and 21 are the folding joints. Figure 28A gliding unmanned aerial vehicle with folding wings, structural section view when the inner main wing (7) and the stiffening wing ribs (8) are folded upwards, wherein 7 is the inner main wing; 8 is the main wing stiffening wing rib; 9 is the main wing rotating shaft; 10 is the fuselage, bearing fixing the main wing rotating shaft (9); 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor. Figure 29 A gliding unmanned aerial vehicle with folding wings, structural section view when the inner main wing (7) and the stiffening wing ribs (8) are unfolded horizontally, wherein 7 is the inner main wing; 8 is the main wing stiffening wing rib; 9 is the main wing rotating shaft; 10 is the fuselage, bearing fixing the main wing rotating shaft (9); 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor. Figure 30 A gliding unmanned aerial vehicle with folding wings, structural section view when the inner main wing (7) and the stiffening wing ribs (8) are folded upwards, wherein 7 is the inner main wing; 8 is the main wing stiffening wing rib; 9 is the main wing rotating shaft; 10 is the fuselage, bearing fixing the main wing rotating shaft (9); 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor. Figure 31 A gliding unmanned aerial vehicle with folding wings, structural section view when the inner main wing (7) and the stiffening wing ribs (8) are folded upwards, wherein 7 is the inner main wing; 8 is the main wing stiffening wing rib; 9 is the main wing rotating shaft; 10 is the fuselage, bearing fixing the main wing rotating shaft (9); 19 is the folding hinge; 20 and 21 are the folding joints; 22 is the folding drive motor. Figure 32 A schematic diagram of the folding joint locking structure, wherein 28 is a compression spring, the elastic force of which ensures that the sliding block (32) is in a position to prevent the movement of the locking pin (30); 29 is a compression spring, the elastic force of which ensures that the locking pin (30) is pushed to move to the locking position during locking; 30 is the locking pin, which is in the hole of the two folding joints during locking; 31 is the sliding seat of the locking pin (30), which also limits the sliding of the sliding block (32); 32 is the sliding block, which prevents the movement of the locking pin (30) in the folded state. Figure 33is the structure diagram of the folding joint locking, in which 28 is the compression spring, during the folding joint closing, the folding joint (33) pushes the slider (32), the compression spring (28) is compressed, the slider (32) moves to the left, when the slider (32) moves to the position beyond the locking pin (30), the elastic force of the compression spring (29) pushes the locking pin (30) to move into the hole of the folding joint (28, 33), realizing the locking of the folding joint (28, 33); 29 is the compression spring, during the folding joint (28, 33) closing, its elastic force makes the locking pin (30) enter the hole of the folding joint, realizing the locking of the folding joint; 30 is the locking pin, during the locking, it is in the hole of the two folding joints (28, 33); 31 is the sliding seat of the locking pin (30), which also limits the sliding of the slider (32); 32 is the slider, which removes the movement limitation of the locking pin (30) during the closing of the folding joint (28, 33). Figure 34 is the forward diagram of the folding joint locking structure, in which 28 is the folding joint; 29 is the compression spring; 30 is the locking pin; 31 is the sliding seat of the locking pin (30); 32 is the slider, which removes the movement limitation of the locking pin (30) during the closing of the folding joint (28, 33). Figure 35 is the left diagram of the folding joint locking structure, in which 28 is the folding joint, which has four holes fixed with the reinforced wing ribs; 29 is the compression spring; 30 is the locking pin. Figure 36 is the assembly front view of the folding hinge, whose rotating shaft is hollow and engages with the shaft of the folding hinge driving motor, the rotating hinge has half rotating, realizing the unfolding of the folding wing. Figure 37 is the assembly left view of the folding hinge, which is used for the folding linkage of the full-motion front wing (1) and the front wing reinforced wing rib (2), the outer main wing (6) and the inner main wing (7), the inner main wing (7) and the main wing reinforced wing rib (8). Figure 38 is the assembly left view of the folding hinge in folding. Figure 39 is the front view of the folding hinge part, the upper hole of which is used for fixing. Figure 40 is the top view of the folding hinge part. Figure 41 is the left view of the folding hinge part. Figure 42 is the front view of the folding joint part, the upper hole of which is used for the locking of the locking pin during the folding and unfolding. Figure 43 is the top view of the folding joint part, the upper hole of which is used for fixing. Figure 44 is the left view of the folding joint part. Figure 45 is the installation diagram of the folding joint locking structure, the lower folding joint has the locking mechanism, the upper folding joint is misaligned with the lower folding joint, when the lower folding joint unfolds upward, the upper folding joint pushes the slider (32) to move out of the position limiting the locking pin (30) during the closing, until the locking pin (30) completes the locking. Figure 46is an elevation view of the folding joint lock structure part with holes for fastening. Figure 47 is a left side view of the folding joint lock structure part. Figure 48 is a left side view of the folding joint lock structure part. Figure 49 is an elevation view of the slider (32) part. Figure 50 is a top view of the slider (32) part. Figure 51 is a left side view of the slider (32) part. DETAILED DESCRIPTION

[0006] The utility model provides a kind of gliding unmanned aerial vehicle with folding wing, duck type middle single wing aerodynamic layout;Its full-motion front wing (1) can be folded 90 ° downwards;Inner main wing (7) can be folded 90 ° upwards at the joint with main wing stiffening rib (8), at this time, outer main wing (6) can be folded 180 ° downwards at the joint with inner main wing (7);Main wing stiffening rib (8) is fixed with main wing rotating shaft (9), can rotate 90 ° around main wing rotating shaft (9), so that main wing stiffening rib (8) is converted from horizontal to vertical;Make outer main wing (6) and inner main wing (7) fold and place in parallel position on both sides of fuselage, wing leading edge is below;Vertical tail has motor-driven rotating shaft, can be retracted into fuselage;Above is the process that full-motion front wing and main wing are unfolded to fold.In leaving carrier aircraft, the unfolding sequence of folding main wing is as follows: 1, control system connects the power supply of worm drive motor of worm and gear of main wing rotating shaft (9), so that main wing stiffening rib (8) is rotated 90 °, and is converted from vertical to horizontal;Outer main wing (6) and inner main wing (7) are rotated 90 ° upwards together, and are converted from the horizontal position close to fuselage to vertical position with fuselage, and the leading edge of outer main wing (6) and inner main wing (7) is in front;2, when outer main wing (6) and inner main wing (7) are converted from the horizontal position close to fuselage to vertical position with fuselage, control system connects the rotation of folding drive motor (22) of inner main wing (7), so that inner main wing (7) is unfolded by turning over 90 ° downwards, until horizontal unfolding is completed with main wing stiffening rib (8);When inner main wing (7) is completed with main wing stiffening rib (8) horizontal docking, folding joint (20,21) is completely closed, corresponding folding joint locking structure locking pin (30) is completely inserted into the hole of folding joint to realize locking, and the power supply of worm drive motor is disconnected;3, after folding locking of inner main wing (7) and main wing stiffening rib (8) is completed, control system connects the power supply of folding drive motor (26) of outer main wing (6), so that outer main wing (6) is rotated 180 ° upwards, and is completed with inner main wing (7) folding unfolding docking, folding joint (24,25) is completely closed, corresponding folding joint locking structure locking pin (30) is completely inserted into the hole of folding joint to realize locking, and the power supply of folding drive motor (26) is disconnected;When outer main wing (6) is unfolded, outer main wing (6) will generate lift due to the action of airflow, which is conducive to the unfolding of outer main wing (6).Worm and gear transmission mechanism is used to realize the rotation of main wing rotating shaft (9), worm shaft is main wing rotating shaft (9), worm bearing seat and worm drive motor, bearing seat of main wing rotating shaft (9) are fixed on fuselage, and the rotation and stop of main wing rotating shaft (9) are realized by the control system of unmanned aerial vehicle.The length of wing span direction of fixed front wing (4) is same with the diameter of fuselage, to ensure that full-motion front wing (1) can be folded 90 ° downwards;The rotating shaft (3) of front wing stiffening rib (2) drives the rotation of full-motion front wing (1);Under the control of flight control system, full-motion front wing is used for attitude stabilization and flight control of unmanned aerial vehicle.After leaving the carrier, under the control of the control system, the power supply of the front wing folding drive motor (13) is turned on, and the full-motion front wing (1) is folded upward by 90° and is in a horizontal position with the front wing reinforced wing rib (2); under the control of the control system, the rotation of the rotating shaft (3) of the full-motion front wing (1) is realized by using a worm gear transmission mechanism, and the rotating shaft (3) of the movable front wing (1) is the shaft of the worm gear (15); the bearing seat of the worm gear (16) and the drive motor, the bearing seat of the rotating shaft (3) of the movable front wing (1) are all fixed on the fuselage, and the rotation and stop of the rotating shaft (3) of the full-motion front wing (1) are realized by the control system of the unmanned aerial vehicle. At the same time of unfolding the inner and outer main wings, the control system turns on the power supply of the folding hinge drive motor (13) of the full-motion front wing, and the full-motion front wing (1) is turned upward by 90° to the horizontal position, completing the unfolding of the full-motion front wing; since the full-motion front wing is unfolded upward, the lift generated under the action of the airflow is beneficial to the unfolding of the full-motion front wing. The folding and unfolding of the vertical tail is realized by using a motor, and after leaving the carrier, the folding and unfolding motor of the vertical tail (11) is turned on by the control system of the unmanned aerial vehicle to realize the unfolding of the vertical tail (11). After the vertical tail (11) is turned to the normal working position, the power supply of the folding and unfolding motor is automatically turned off. The worm gear drive motor of the rotating full-motion front wing (1), the aileron and rudder equipped with the corresponding rudder are all controlled by the flight control system of the unmanned aerial vehicle to realize the stability and control of the flight attitude. The main wing rotating shaft (9) is fixed with the main wing reinforced wing rib (8) and is a load-bearing component of the entire wing, and the bearing seat of the main wing rotating shaft (9) is fixed on the fuselage; the inner main wing (7) is linked with the main wing reinforced wing rib (8) by a hinge, and the outer main wing (6) is linked with the inner main wing (7) by a hinge; when the folding hinges are linked, the center lines of all the folding hinges at the folding positions should completely coincide, and the center lines should also be parallel to the chord of the wing. During folding, the misalignment of the surface of the wing cannot occur.

[0007] The gliding unmanned aerial vehicle has a remote control system and a flight control system, which are similar to those of a common unmanned aerial vehicle, and are composed of uplink and downlink communication devices of wireless remote control signals, attitude sensors for sensing the attitude changes of the unmanned aerial vehicle, atmospheric pressure sensors, air speed sensors, flight control data processors, flight navigation positioning devices, control mechanisms, power supplies, etc.

Claims

1. A gliding unmanned aerial vehicle with folding wings, canard-midwing aerodynamic layout; has a movable front wing (1) for attitude stabilization and control; has two main wings, an outer main wing (6) and an inner main wing (7), the outer main wing can be folded downward 180° at the connection with the inner main wing, the lower surfaces of the wings are opposite; the inner main wing (7) can be folded upward 90° at the connection with the main wing stiffening ribs (8); the main wing stiffening ribs (8) on both sides of the fuselage are fixed with the main wing rotating shaft (9) and can rotate around the main wing rotating shaft (9), so that the main wing stiffening ribs (8) can be converted between horizontal and vertical states; characterized in that: The full-movable front wing (1) can be folded down 90°, and the two-section main wing is folded and placed in parallel position forward of the fuselage, with the folded main wing leading edge below. ​ 2. The gliding unmanned aerial vehicle with folding wings according to claim 1, characterized in that, The mechanical locking mechanism is used to realize reliable locking after the wing is unfolded, and the mechanism is characterized in that: the elastic force of the compression spring (29) ensures that the sliding block (32) is in a position to prevent the locking pin (30) from moving; the elastic force of the compression spring (29) ensures that the locking pin (30) is pushed to move to the locking position during locking; the locking pin (30) is in the hole of the two folding joints during locking; the sliding seat (31) of the locking pin (30) also makes the sliding block (32) slide and limit; the sliding block (32) prevents the locking pin (30) from moving in the folded state.

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