Auxiliary take-off device based on fixed-wing micro air vehicle

Abstract

The application relates to an auxiliary take-off device based on a fixed-wing micro air vehicle, which comprises an air vehicle loading mechanism, an auxiliary propulsion mechanism and an acceleration buffer mechanism. The air vehicle loading mechanism is used for storing the fixed-wing micro air vehicle and loading the same onto a loading slide; the auxiliary propulsion mechanism is installed on the lower side of the loading drum loading mechanism; the auxiliary propulsion mechanism comprises a loading slide mechanism and a crank slide propulsion mechanism, and is used for realizing the auxiliary take-off propulsion of the micro air vehicle; and the acceleration buffer mechanism comprises a three-stage acceleration mechanism and a buffer static mechanism, and is used for providing the take-off kinetic energy of the micro air vehicle and the buffer static state of the loading slide. The application has high compatibility with the fixed-wing micro air vehicle, realizes the stable auxiliary take-off function of the general fixed-wing micro air vehicle taking off at a constant initial speed, and can load three micro air vehicles at a time due to the use of the air vehicle loading mechanism, so that the auxiliary take-off is more efficient.

Description

Technical Field

[0001] This invention relates to an auxiliary takeoff device for fixed-wing micro-aircraft, belonging to the field of micro-aircraft technology. Background Technology

[0002] Micro-aircraft are a new type of aircraft that are small in size and light in weight. Due to their advantages such as easy portability, low cost and good stealth, they have quickly become a very popular research field. They have important application value in urban and local unknown environments, as well as in the precise attack on small targets.

[0003] Existing takeoff aids for fixed-wing micro-aircraft typically employ a manual, hand-launched method. However, in the laboratory, accurate quantitative testing of micro-aircraft performance is required. The takeoff kinetic energy provided by the manual run-assisted hand-launch method is unstable, making quantitative analysis difficult, and it is unsuitable for continuous, large-scale testing.

[0004] This invention provides a new and feasible solution for continuous assisted takeoff of fixed-wing micro-aircraft. Summary of the Invention

[0005] Technical Problem: Based on the above analysis, the present invention provides an auxiliary take-off device for fixed-wing micro-aircraft, which can continuously achieve stable assisted take-off of three fixed-wing micro-aircraft, solving the problems of poor stability and continuity of manual-assisted hand-launched take-off and uncontrollable initial kinetic energy of micro-aircraft.

[0006] Technical Solution: To achieve the above objectives, the technical solution adopted by this invention is as follows: an auxiliary takeoff device based on a fixed-wing micro-aircraft, comprising an aircraft loading mechanism for storing the fixed-wing micro-aircraft and assisting its takeoff loading, including a drum mechanism, a left lift-limiting mechanism, and a right lift-limiting mechanism, wherein the left lift-limiting mechanism and the right lift-limiting mechanism are arranged in a mirror-symmetric manner; an auxiliary propulsion mechanism, located below the drum mechanism, for assisting the micro-aircraft to a three-stage acceleration mechanism, including a loading slider mechanism and a crank-slider propulsion mechanism, wherein the entire auxiliary propulsion mechanism is installed within the alloy frame of the auxiliary takeoff device; and an acceleration buffer mechanism for providing the initial kinetic energy of the micro-aircraft and buffering the loading slider to a stationary state, including a three-stage acceleration mechanism and a buffer stationary mechanism.

[0007] Preferably, in the left lifting limiting mechanism, the limiting pad is fixed to the three-stage acceleration fixing plate to limit the position of the drum mechanism's descent; the lower end of the MA cylinder is fixed to the right-angle bracket via an isolation column using plug bolts, and then fixed to the three-stage acceleration fixing plate; the upper end of the MA cylinder is connected to the lifting fixing square tube of the drum mechanism via a fisheye bearing and a right-angle bracket.

[0008] Preferably, in the drum mechanism, the motor is fixed to the motor mounting base, and the motor mounting base, the motor mounting base connecting square tube, and the lifting fixing square tube are all fixed to the fixed motor carbon plate. The motor mounting base connecting square tubes on both sides are reinforced and fixed to the lifting fixing square tube via the adapter carbon plate. The motor shaft is connected to the longitudinal optical shaft via a coupling. The longitudinal optical shaft is fixed to the lifting fixing square tube via a vertical bearing seat and passes through the encoder, and is sequentially connected to the fixed storage mechanism, the flange coupling, and the optical shaft cross fixing bracket. The encoder is fixed to the side of the lifting fixing square tube via the encoder fixing carbon plate. The longitudinal optical shaft is fixed to the transverse optical shaft via the optical shaft cross fixing bracket. The two optical shafts are respectively limited on both sides of the optical shaft cross fixing bracket by fastening rings. The transverse optical shaft is fixed to the drum-frame connecting square tube via a diamond bearing seat, and then fixed to the frame via the drum-frame connecting plate. The diamond bearing seat is fixed to the drum-frame connecting square tube by bolts.

[0009] Preferably, in the drum mechanism, the first fixed-wing aircraft, the second fixed-wing aircraft, and the third fixed-wing aircraft are respectively stored in a fixed storage mechanism in a circumferential array via their corresponding tail wing limiting guide wheel, fixed-wing limiting connecting block, side wing fixing carbon plate, and pin carbon plate.

[0010] Preferably, the fixed storage mechanism includes a tail fin limiting guide wheel, a fixed fin limiting connecting block, a side fin fixing carbon plate, a rotor main board, and a pin carbon plate; the tail fin limiting guide wheel is symmetrically connected to the fixed fin limiting connecting block; the side fin fixing carbon plates are distributed in a mirror symmetrical manner; the side fin fixing carbon plates are fixed to the rotor main board via the fixed fin limiting connecting block; the front and rear rotor main boards are completely identical and are reinforced by bolts through threaded nylon isolation columns; any side fin fixing carbon plate is sequentially fixed to the rotor main board and reinforced by pin carbon plates; the fixed storage mechanism adopts a mortise and tenon structure for lightweight design to improve loading rate.

[0011] Preferably, the loading slider mechanism consists of a front carbon plate, a side plate, and a rear carbon plate connected by mortise and tenon joints, and reinforced longitudinally and laterally by supporting copper and aluminum columns, forming the main structure of the loading slider. The supporting copper columns are fixed to the front and rear carbon plates of the loading slider by bolts. The supporting aluminum columns are fixed to the left and right side plates of the loading slider by bolts. Linear bearings are symmetrically arranged and fixed to the front carbon plate of the loading slider. Supporting guide wheels are symmetrically arranged and fixed to the ends of the side plates of the loading slider. The traction aluminum column is fixed to the main structure of the loading slider via the aircraft loading block. The fixed-wing micro-aircraft with hooks at the bottom is loaded by the aircraft loading block and the supporting guide wheels via the traction aluminum column. The carbon round tube serves as an acceleration track, passing through the loading slider mechanism via the linear bearings, thereby enabling the loading slider mechanism to drive the fixed-wing micro-aircraft to achieve auxiliary acceleration.

[0012] Preferably, the crank-slider propulsion mechanism includes a front carbon plate for the propulsion slider, a rear carbon plate for the propulsion slider, four-sided aluminum strip connectors, a connecting rod carbon plate, a crank carbon plate, a crank motor, and a crank motor fixing carbon plate. The front carbon plate, rear carbon plate, and base plate of the propulsion slider are fixed by the four-sided aluminum strip connectors, and the propulsion slider structure is reinforced by hexagonal copper pillars. The propulsion slider is fixed to the crank motor rotor via the connecting rod carbon plate and the crank carbon plate. The crank motor stator is fixed to the crank motor fixing carbon plate. Each 360° rotation of the crank motor completes one auxiliary propulsion of the fixed-wing micro-aircraft.

[0013] Preferably, the three-stage acceleration mechanism includes a three-stage acceleration fixing plate, a three-stage acceleration connecting carbon plate, a set of primary friction wheels, a set of secondary friction wheels, and a set of tertiary friction wheels; the three-stage acceleration mechanism is divided into two mirror-symmetrical parts; in the left part of the three-stage acceleration, one primary friction wheel, one secondary friction wheel, and one tertiary friction wheel are fixed to the frame via two layers of tertiary acceleration connecting carbon plates and one layer of tertiary acceleration fixing plate; during the assisted takeoff acceleration process, the acceleration of the loading slider-fixed-wing micro-aircraft system is achieved through the mirror-symmetrical three-stage acceleration mechanism.

[0014] Preferably, the buffer stationary mechanism includes a linear bearing, a buffer carbon plate, a compression spring, and a flange fixing seat; the flange fixing seat is fixed on the front frame carbon plate; the linear bearing is fixed to the buffer carbon plate and passes through a carbon round tube, and is connected to the flange fixing seat via the compression spring; the compression spring is used to absorb the kinetic energy when the loading slider collides with the buffer carbon plate and decelerates.

[0015] Preferably, after the loading slider completes a launch mission of a fixed-wing micro-aircraft, it decelerates and rebounds through a buffer stationary mechanism, and then is finally brought to a standstill by an electromagnetic lock; the electromagnetic lock is fixed to the frame via an electromagnetic lock mounting plate.

[0016] Preferably, the frame of the fixed-wing micro aircraft uses aluminum square tubes as the basic frame, and the aluminum square tubes are connected to each other by extruded corner pieces, stainless steel straight pieces, alloy corner pieces, and adapter carbon plates; parallel carbon round tubes are located inside the frame as auxiliary take-off guides; the two ends of the carbon round tubes are fixed to the aluminum profile basic frame by flange fixing seats via the front frame carbon plate and the rear frame carbon plate, respectively.

[0017] Beneficial Effects: The above-mentioned technical solution of the present invention has the following beneficial technical effects: 1. The aircraft loading mechanism of the present invention can load three fixed-wing micro aircraft at one time, realizing continuous assisted take-off tests for multiple fixed-wing micro aircraft. Moreover, the present invention has high compatibility with fixed-wing micro aircraft, effectively enhancing the continuity of assisted take-off tests for different fixed-wing micro aircraft; 2. In the three-stage acceleration mechanism, the friction wheel motors used for acceleration are all arranged in a horizontal parallel manner, further compressing the volume of the acceleration mechanism. Furthermore, the motor uses a 3508 motor without a gearbox, which has high torque and self-feedback speed; the friction wheel rubber is a custom-made flat polyurethane, which can better fit the side surface of the loading slider, providing a more stable acceleration effect; combined with a three-stage acceleration strategy, namely primary acceleration, secondary assistance, and tertiary stabilization, it provides a more stable initial takeoff kinetic energy for the fixed-wing micro-aircraft, effectively improving the acceleration kinetic energy stability of the micro-aircraft takeoff; 3. The loading mechanism of the fixed-wing micro-aircraft combines cylinder lifting and drum loading to realize the loading of the fixed-wing aircraft, effectively reducing the space required for multiple continuous loading of the micro-aircraft, resulting in a smaller size and higher space utilization; 4. The auxiliary propulsion mechanism uses lightweight materials and combines mortise and tenon structures, thus... 5. A lightweight design of the slider during assisted propulsion and accelerated takeoff effectively reduces the additional kinetic energy loss during the takeoff of fixed-wing micro-aircraft; 6. The same loading slider mechanism is used for the launch of different aircraft, and the launch process of different micro-aircraft is a single variable, further ensuring single-variable testing of fixed-wing micro-aircraft; 7. In the assisted propulsion process of micro-aircraft, a carbon round tube double slide rail crank slider mechanism is adopted, which makes the assisted propulsion effect more stable and effectively avoids the problem of micro-aircraft easily falling off during single slide rail assisted takeoff; 8. The functions of each mechanism in this invention are structurally independent but interconnected in the control process. Different mechanisms have a high degree of integration and modularity, which facilitates assembly and maintenance, and makes the assisted takeoff process faster and more coherent. Attached Figure Description

[0018] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0020] Figure 2 This is a schematic diagram of the aircraft loading mechanism of the present invention;

[0021] Figure 3 This is a schematic diagram of the drum mechanism of the present invention;

[0022] Figure 4 This is a schematic diagram of the fixed storage mechanism of the present invention;

[0023] Figure 5 This is a schematic diagram of the loading slider mechanism of the present invention;

[0024] Figure 6 This is a schematic diagram of the crank-slider propulsion mechanism of the present invention;

[0025] Figure 7 This is a schematic diagram of the acceleration buffer mechanism of the present invention.

[0026] Reference numerals: 1-Aircraft loading mechanism; 2-Acceleration buffer mechanism; 3-Auxiliary propulsion mechanism; 4-Drum mechanism; 5-Limiting pad; 6-Fisheye bearing; 7-MA cylinder; 8-Three-stage acceleration fixing plate; 9-Motor; 10-Motor mounting base; 11-Motor base connecting square tube; 12-Adapter carbon plate; 13-Lifting fixing square tube; 14-Fixing motor carbon plate; 15-Coupling; 16-Vertical bearing seat; 17-Encoder fixing carbon plate; 18-Encoder; 19-Fixing storage mechanism; 20-Flange coupling; 21-Optical axis cross fixing bracket; 22-Rhomboid bearing seat; 23-Drum-frame connecting square tube; 24-Transverse optical axis; 25-Longitudinal optical axis; 26-Fastening ring; 27-Drum-frame connecting plate; 28-First fixed-wing aircraft; 29-Second fixed-wing aircraft; 30-Third fixed-wing aircraft; 31-Threaded nylon isolation column; 32 - Tail fin limiting guide wheel; 33 - Fixed wing limiting connecting block; 34 - Side wing fixing carbon plate; 35 - Rotor main board; 36 - Pin carbon plate; 37 - Aircraft loading block; 38 - Loading slider front carbon plate; 39 - Loading slider side plate; 40 - Loading slider rear carbon plate; 41 - Support copper column; 42 - Support aluminum column; 43 - Linear bearing; 44 - Carbon round tube; 45 - Support guide wheel; 46 - Propulsion slider front carbon plate; 47 - Propulsion slider rear carbon plate Carbon plate; 48-Four-sided aluminum busbar connector; 49-Connecting rod carbon plate; 50-Crank carbon plate; 51-Crank motor; 52-Crank motor fixing carbon plate; 53-Third-stage acceleration connection carbon plate; 54-First-stage friction wheel; 55-Second-stage friction wheel; 56-Third-stage friction wheel; 57-Buffer carbon plate; 58-Compression spring; 59-Flange fixing seat; 60-Front frame carbon plate; 61-Electromagnetic lock; 62-Electromagnetic lock mounting plate; 63-Rear frame carbon plate. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to specific embodiments and the accompanying drawings. It should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0028] To enhance understanding of the present invention, we will now describe it in further detail with reference to the accompanying drawings. These embodiments are for illustrative purposes only and do not constitute a limitation on the scope of protection of the present invention.

[0029] Example 1:

[0030] The diagram illustrates an auxiliary takeoff device for a fixed-wing micro-aircraft, comprising an aircraft loading mechanism 1 for storing and loading the fixed-wing micro-aircraft for assisted takeoff, a drum mechanism 4, a left lift limit mechanism, and a right lift limit mechanism, with the left and right lift limit mechanisms arranged in a mirror-symmetric configuration; an auxiliary propulsion mechanism 3, located below the drum mechanism 4, for assisting in propulsion of the micro-aircraft to a three-stage acceleration mechanism, and also including a loading slider mechanism and a crank-slider propulsion mechanism, the entire auxiliary propulsion mechanism being installed within the alloy frame of the auxiliary takeoff device; and an acceleration buffer mechanism 2 for providing initial kinetic energy to the micro-aircraft and buffering the loading slider to a stationary state, and also including a three-stage acceleration mechanism and a buffer stationary mechanism.

[0031] Preferably, for the aircraft loading mechanism 1, in the left lifting limiting mechanism, the limiting pad 5 is fixed to the three-stage acceleration fixing plate 8 to limit the descent position of the drum mechanism 4; the lower end of the MA cylinder 7 is fixed to the right-angle bracket via a plug bolt through an isolation column, and then fixed to the three-stage acceleration fixing plate 8; the upper end of the MA cylinder 7 is connected to the lifting fixing square tube 13 of the drum mechanism 4 via a fisheye bearing 6 and a right-angle bracket. In the fixed storage mechanism 19, the tail fin limiting guide wheel 32 is symmetrically connected to the fixed fin limiting connecting block 33; the side fin fixing carbon plates 34 are distributed in a mirror symmetrical manner; the side fin fixing carbon plates 34 are fixed to the rotor main plate 35 via the fixed fin limiting connecting block 33; each side fin fixing carbon plate 34 is fixed to two identical rotor main plates 35 respectively, and reinforced by a pin carbon plate 36; the entire fixed storage mechanism 19 adopts a mortise and tenon structure for lightweight design to improve loading rate. In the drum mechanism 4, the motor 9 is fixed to the motor mounting base 10. The motor mounting base 10, the motor mounting base connecting square tube 11, and the lifting and fixing square tube 13 are all fixed on the fixed motor carbon plate 14. The motor mounting base connecting square tubes 11 on both sides are reinforced and fixed to the lifting and fixing square tube 13 via the adapter carbon plate 12. The motor shaft is connected to the longitudinal optical shaft 25 via the coupling 15. The longitudinal optical shaft 25 is fixed to the lifting and fixing square tube 13 via the vertical bearing seat 16, and passes through the encoder 18, and is connected in sequence to the fixed storage mechanism 19, the flange coupling 20, and the optical shaft cross fixing bracket 21. The encoder 18 is fixed to the side of the lifting and fixing square tube 13 via the encoder fixing carbon plate 17. The longitudinal optical shaft 25 is fixed to the side of the lifting and fixing square tube 13 via the encoder fixing carbon plate 17. The axis 25 is fixed to the transverse optical axis 24 via the optical axis cross fixing bracket 21; the two optical axes are respectively limited on both sides of the optical axis cross fixing bracket 21 by fastening rings 26; the transverse optical axis 24 is fixed to the drum-frame connecting square tube 23 via the rhomboid bearing seat 22, and then fixed to the frame via the drum-frame connecting plate 27; the rhomboid bearing seat 22 is fixed to the drum-frame connecting square tube 23 by bolts; the first fixed-wing aircraft 28, the second fixed-wing aircraft 29, and the third fixed-wing aircraft 30 are respectively stored in a circumferential array on the fixed storage mechanism 19 via their corresponding tail wing limiting guide wheel 32, fixed wing limiting connecting block 33, side wing fixing carbon plate 34, and pin carbon plate 36.

[0032] Preferably, for the auxiliary propulsion mechanism 3, in the loading slider mechanism, the front carbon plate 38, the side plate 39, and the rear carbon plate 40 of the loading slider are connected by mortise and tenon joints, and are reinforced longitudinally and laterally by the supporting copper column 41 and the supporting aluminum column 42, respectively, to form the main structure of the loading slider; the supporting copper column 41 is fixed to the front carbon plate 38 and the rear carbon plate 40 of the loading slider by bolts; the supporting aluminum column 42 is fixed to the left and right side plates 39 of the loading slider by bolts; the linear bearing 43 is symmetrically arranged and fixed on the front carbon plate 38 of the loading slider; the supporting guide wheel 45 is symmetrically arranged and fixed to the end of the side plate 39 of the loading slider; the traction aluminum column is fixed to the main structure of the loading slider via the aircraft loading block 37; then, the aircraft loading block 37 and the supporting guide wheel 45 load the fixed-wing micro-aircraft with hooks at the bottom via the traction aluminum column; the carbon round tube 44 serves as an acceleration track, passing through the loading slider mechanism via the linear bearing 43, thereby enabling the loading slider mechanism to drive the fixed-wing micro-aircraft to achieve auxiliary acceleration. In the crank-slider propulsion mechanism, the front carbon plate 46, the rear carbon plate 47, and the bottom plate of the propulsion slider are fixed by four-sided aluminum strip connectors 48, and the propulsion slider structure is reinforced by hexagonal copper pillars; the propulsion slider is fixed to the rotor of the crank motor 51 by the crank carbon plate 50 via the connecting rod carbon plate 49; the stator of the crank motor 51 is fixed to the crank motor fixing carbon plate 52; each time the crank motor 51 rotates 360°, it completes one auxiliary propulsion of the fixed-wing micro-aircraft.

[0033] Preferably, for the acceleration buffer mechanism 2, the three-stage acceleration mechanism consists of two mirror-symmetrical parts. The first-stage friction wheel 54, the second-stage friction wheel 55, and the third-stage friction wheel 56 are fixed to the frame via the three-stage acceleration connecting carbon plate 53 and the three-stage acceleration fixing plate 8. The acceleration of the loading slider-fixed-wing micro-aircraft system is achieved through the mirror-symmetrical three-stage acceleration mechanism. In the buffer stationary mechanism, the flange fixing seat 59 is fixed to the front frame carbon plate 60; the linear bearing is fixed to the buffer carbon plate 57 and passes through the carbon round tube 44, and is connected to the flange fixing seat 59 via the compression spring 58; the compression spring 58 is used to absorb the kinetic energy when the loading slider collides with the buffer carbon plate 57 and decelerates.

[0034] The specific working process and principle of this embodiment are as follows:

[0035] At the initial moment, the fixed-wing micro-aircraft auxiliary take-off device is at an angle of 20 to 40 degrees to the horizontal plane, the aircraft loading mechanism 1 is in a raised state, and the loading slider and the propulsion slider are both located at their respective ends.

[0036] First, the three fixed-wing micro-aircraft test models are loaded into the fixed storage mechanism 19. After the power is turned on, the initial angle is calculated by the motor 9 and the encoder 18. At the initial moment, the first fixed-wing micro-aircraft 28 is directly facing the auxiliary propulsion mechanism 3. When the MA cylinder 7 descends to the lowest point, the descent position of the drum mechanism 4 is controlled by the left and right limit pads 5, thus completing the accurate positioning of the preset position of the first fixed-wing micro-aircraft 28. At the same time, the three sets of friction wheel acceleration motors all start to rotate to a uniform and stable rotation state.

[0037] Secondly, the crank motor 51 in the crank-slider propulsion mechanism drives the crank carbon plate 50 to rotate 360° in one revolution. When the crank motor rotates 180°, the propulsion slider, together with the loading slider, moves forward to contact the first-stage friction wheel 54; when the crank motor 51 completes its 360° rotation, the propulsion slider returns to its initial position. During the forward movement of the loading slider, it completes the loading of the fixed-wing micro-aircraft with hooks at the bottom.

[0038] Furthermore, the loading slider, through a three-stage acceleration mechanism and a three-stage acceleration strategy, utilizes the acceleration track formed by the dual carbon tubes 44 to accelerate the loading slider-fixed-wing micro-aircraft system. At this time, the electromagnetic lock 61 is in the closed state. After reaching the buffer stationary mechanism, the loading slider contacts the buffer carbon plate 57, and the kinetic energy of the loading slider is buffered and absorbed by the compression spring 58. After deceleration and rebound, the electromagnetic lock 61 brings it back to a standstill. Meanwhile, the fixed-wing micro-aircraft loaded on the loading slider continues to move forward and separates from the loading slider, completing one launch mission of the fixed-wing micro-aircraft.

[0039] Finally, electromagnetic lock 61 opens, and all motors in the three-stage acceleration mechanism rotate in opposite directions. The loading slider slides down under its own weight and, after being assisted by the three-stage acceleration mechanism, returns to its initial position. Simultaneously, the drum mechanism 4 is lifted again by the MA cylinder 7, and motor 9 rotates, with the encoder 18 controlling the angle, causing the fixed storage mechanism 19 to rotate 120° so that the second fixed-wing aircraft 29 is aligned with the auxiliary propulsion mechanism 3, reaching the same reset state as the initial position. The assisted takeoff processes for the second fixed-wing aircraft 29, the third fixed-wing aircraft 30, and the first fixed-wing aircraft 28 are then identical and will not be described in detail below.

[0040] In this embodiment, based on the overall operating principle of the mechanism, the three assisted take-off processes mentioned above will not affect each other. Therefore, the device can be compatible with three fixed-wing micro-aircraft at one time, that is, the device can realize continuous assisted take-off tests for three fixed-wing micro-aircraft experiments.

[0041] The above specific embodiments are only for illustrating the technical concept and structural features of the present invention, and are intended to enable those skilled in the art to implement them. However, the above content does not limit the scope of protection of the present invention. Any equivalent changes or modifications made in accordance with the spirit and essence of the present invention should fall within the scope of protection of the present invention.

Claims

1. An auxiliary takeoff device based on a fixed-wing micro-aircraft, characterized in that: include: The aircraft loading mechanism (1) is used to store fixed-wing micro-aircraft and assist them in takeoff loading. It includes a drum mechanism (4), a left lifting limit mechanism, and a right lifting limit mechanism, with the left and right lifting limit mechanisms arranged in a mirror symmetrical manner. The drum mechanism (4) includes a motor (9), a motor mounting base (10), a motor mounting base connecting square tube (11), a transfer carbon plate (12), a lifting and fixing square tube (13), a fixing motor carbon plate (14), a coupling (15), a vertical bearing seat (16), an encoder fixing carbon plate (17), an encoder (18), a fixing storage mechanism (19), a flange coupling (20), an optical axis cross fixing bracket (21), and a rhomboid bearing seat (2). 2) Drum-frame connecting square tube (23), transverse optical axis (24), longitudinal optical axis (25), fastening ring (26), drum-frame connecting plate (27), first fixed-wing aircraft (28), second fixed-wing aircraft (29), third fixed-wing aircraft (30); motor (9) is fixed to motor mounting base (10), motor mounting base (10), motor mounting base connecting square tube (11), and lifting fixing square tube (13) are all fixed on the fixed motor carbon plate (14), and the motor mounting base connecting square tubes (11) on both sides are reinforced and fixed to the lifting fixing square tube (13) through the adapter carbon plate (12); the motor shaft is connected to the longitudinal optical axis (25) through the coupling (15); the longitudinal optical axis (25) is connected to the longitudinal optical axis (25) through the coupling (15). The vertical bearing housing (16) is fixed to the lifting and fixing square tube (13) and passes through the encoder (18), and is connected in sequence to the fixed storage mechanism (19), the flange coupling (20), and the optical axis cross fixing bracket (21); the encoder (18) is fixed to the side of the lifting and fixing square tube (13) via the encoder fixing carbon plate (17); the longitudinal optical axis (25) is fixed to the transverse optical axis (24) via the optical axis cross fixing bracket (21); the two optical axes are respectively limited on both sides of the optical axis cross fixing bracket (21) by fastening rings (26); the transverse optical axis (24) is fixed to the drum-frame connecting square tube (23) via the diamond bearing housing (22), and then fixed to the frame via the drum-frame connecting plate (27); the first fixing The first fixed-wing aircraft (28), the second fixed-wing aircraft (29), and the third fixed-wing aircraft (30) are respectively stored in a fixed storage mechanism (19) via their corresponding tail wing limiting guide wheel (32), fixed wing limiting connecting block (33), side wing fixed carbon plate (34), and pin carbon plate (36). The acceleration buffer mechanism (2) is used to provide the initial kinetic energy of the micro aircraft and the buffer station of the loading slider, including a three-stage acceleration mechanism and a buffer station mechanism. The auxiliary propulsion mechanism (3) is located below the drum mechanism (4) and is used to assist the micro aircraft in propulsion to the acceleration mechanism, which includes a loading slider mechanism and a crank slider propulsion mechanism. The entire auxiliary propulsion mechanism is installed in the alloy frame of the auxiliary take-off device.

2. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The left lifting limiting mechanism includes a limiting pad (5), a fisheye bearing (6), and an MA cylinder (7); the limiting pad (5) is fixed to the three-stage acceleration fixing plate (8) to limit the position of the descent of the drum mechanism (4); the lower end of the MA cylinder (7) is fixed to the right angle bracket by means of a plug bolt through an isolation column, and then fixed to the three-stage acceleration fixing plate (8); the upper end of the MA cylinder (7) is connected to the lifting fixing square tube (13) of the drum mechanism (4) by means of a fisheye bearing (6) through a right angle bracket.

3. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The fixed storage mechanism (19) includes a tail wing limiting guide wheel (32), a fixed wing limiting connecting block (33), a side wing fixing carbon plate (34), and a pin carbon plate (36). The tail wing limiting guide wheel (32) is symmetrically connected to the fixed wing limiting connecting block (33). The side wing fixing carbon plates (34) are distributed in a mirror symmetry. The side wing fixing carbon plates (34) are fixed to the rotor main board (35) via the fixed wing limiting connecting block (33). The front and rear rotor main boards (35) are completely identical and are supported and reinforced by bolts through threaded nylon isolation columns (31). Each side wing fixing carbon plate (34) is fixed to the rotor main board (35) in sequence and reinforced by pin carbon plates (36). The fixed storage mechanism (19) adopts a mortise and tenon structure for lightweight design to improve loading rate.

4. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The loading slider mechanism includes an aircraft loading block (37), a traction aluminum column, a front carbon plate (38) of the loading slider, a side plate (39) of the loading slider, a rear carbon plate (40) of the loading slider, a support copper column (41), a support aluminum column (42), a linear bearing (43), and a support guide wheel (45). In the loading slider mechanism, the aircraft loading block (37) and the support guide wheel (45) load a fixed-wing micro aircraft with a hook at the bottom through the traction aluminum column. The carbon round tube (44) serves as an acceleration track and passes through the loading slider mechanism through the linear bearing (43), thereby enabling the loading slider mechanism to drive the fixed-wing micro aircraft to achieve auxiliary acceleration.

5. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, In the crank-slider propulsion mechanism, the front carbon plate (46), the rear carbon plate (47), and the bottom plate of the propulsion slider are fixed by four aluminum strip connectors (48), and the propulsion slider structure is reinforced by hexagonal copper columns; the propulsion slider is fixed to the rotor of the crank motor (51) by the crank carbon plate (50) via the connecting rod carbon plate (49); the stator of the crank motor (51) is fixed to the crank motor fixing carbon plate (52); the crank-slider propulsion mechanism completes one auxiliary propulsion of the fixed-wing micro-aircraft every time the crank motor (51) rotates 360°.

6. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The three-stage acceleration mechanism includes a three-stage acceleration fixing plate (8), a three-stage acceleration connecting carbon plate (53), a set of first-stage friction wheels (54), a set of second-stage friction wheels (55), and a set of third-stage friction wheels (56). The three-stage acceleration mechanism is divided into two mirror-symmetrical parts. The left part of the three-stage acceleration includes a first-stage friction wheel (54), a second-stage friction wheel (55), and a third-stage friction wheel (56), which are fixed to the frame via two layers of three-stage acceleration connecting carbon plates (53) and a layer of three-stage acceleration fixing plate (8).

7. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The buffer stationary mechanism includes a linear bearing, a buffer carbon plate (57), a compression spring (58), and a flange fixing seat (59); the flange fixing seat (59) is fixed on the front frame carbon plate (60); the linear bearing is fixed to the buffer carbon plate (57) and passes through the carbon round tube (44), and is connected to the flange fixing seat (59) via the compression spring (58); in the buffer stationary mechanism, the compression spring (58) is used to absorb the kinetic energy when the loading slider collides with the buffer carbon plate and decelerates.

8. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, After completing a launch mission of a fixed-wing micro-aircraft, the loading slider decelerates and rebounds through a buffer stationary mechanism, and then returns to a stationary position via an electromagnetic lock (61); the electromagnetic lock is fixed to the frame via an electromagnetic lock mounting plate (62).

9. The auxiliary takeoff device based on a fixed-wing micro-aircraft according to claim 1, characterized in that, The frame of the fixed-wing micro aircraft uses aluminum square tubes as the basic framework, and the various aluminum square tubes are connected by extruded corner pieces, stainless steel straight pieces, alloy corner pieces, and adapter carbon plates. The parallel carbon round tube (44) is located inside the frame as an auxiliary takeoff guide rail; the two ends of the carbon round tube (44) are fixed to the aluminum profile basic frame via the front frame carbon plate (60) and the rear frame carbon plate (63) through the flange fixing seat (59).

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