CN118062280A - Passively unfolding catapult aircraft - Google Patents

Abstract

The invention discloses a passively-unfolded catapulting aircraft, which comprises a flight rotor wing unit, an auxiliary tail wing, a wing passively-unfolded unit, a middle connecting module, a nose module and an auxiliary tail wing fixing seat, wherein the middle connecting module is connected with the nose module; the flying rotor wing unit is connected with the intermediate connection module through the passive wing unfolding unit, so that the flying rotor wing unit is in a first unfolded state and in a second folded state, and the aircraft nose module, the intermediate connection module, the auxiliary tail wing fixing seat and the auxiliary tail wing are sequentially connected. According to the invention, through the ingenious structural design of the flying rotor wing unit and the wing passive unfolding unit, the unfolding and folding of the rotor wing are realized; the problem that the rotor cannot be unfolded passively is solved, so that the rotor can be folded when not in use, and is convenient to carry; the device can be rapidly responded and passively unfolded to adapt to different transmitting environments during transmitting.

Description

A passively deployed catapult aircraft

Technical Field

The invention relates to a passively deployed ejection aircraft, belonging to the field of aircraft.

Background technique

UAVs are the most complex and widely used aircraft so far, with great differences in configuration, purpose, size, flight altitude, flight speed, etc. Fixed-wing UAVs have the advantages of long flight time, high flight speed, and strong load-bearing capacity; unmanned helicopters have the characteristics of hovering, flexible maneuverability, and high-angle shooting; rotary-wing micro UAVs have the characteristics of being small and convenient, with vertical take-off and landing capabilities, and ultra-low-speed flight.

However, existing rotorcraft UAVs generally have certain problems, such as being inconvenient to carry, being expensive, having many restrictions on take-off conditions, or being unable to respond and deploy quickly in emergency situations.

In view of this, the present invention is proposed.

Summary of the invention

The present invention provides a passive deployment catapult aircraft, which realizes the deployment and folding of the rotor through the ingenious structural design of the flight rotor unit and the wing passive deployment unit; solves the problem that the rotor cannot be passively deployed, so that the rotor can be folded up when not in use for easy carrying; and can quickly respond to passive deployment during launch to adapt to different launch environments.

The technical solution of the present invention is:

A passive deployment catapult aircraft comprises a flight rotor unit 1, an auxiliary tail 2, a wing passive deployment unit 3, an intermediate connection module 4, a nose module 5, and an auxiliary tail fixing seat 26; the flight rotor unit 1 is connected to the intermediate connection module 4 through the wing passive deployment unit 3, so that the flight rotor unit 1 has a first deployed state and a second folded state, and the nose module 5, the intermediate connection module 4, the auxiliary tail fixing seat 26, and the auxiliary tail 2 are connected in sequence.

The flight rotor unit 1 includes a first connecting pipe, a DC motor 6, a DC motor fixing part 7, a propeller 8 and a pipeline auxiliary pulley 9; the propeller 8 is installed at one end of the DC motor 6, and the other end of the DC motor 6, the DC motor fixing part 7 located at one end of the first connecting pipe, and the bracket of the pipeline auxiliary pulley 9 are fixedly connected, and the other end of the first connecting pipe is connected to the wing passive deployment unit 3; when the flight rotor unit 1 is in the second state, the pulley of the pipeline auxiliary pulley 9 contacts the wall surface of the launching device.

The wing passive deployment unit 3 includes a limit bolt 10, a torsion spring 11, an arm 12, a slide slot seat 14, and a double-headed spring pin 16; the limit bolt 10 is used to pass through the torsion spring 11, the arm 12, and the slide slot seat 14, and the double-headed spring pin 16 is used to pass through the arm 12, the slide slot seat 14 and realize the sliding of the double-headed spring pin 16 in the slide slot of the slide slot seat 14 under the action of the torsion spring 11.

The slide seat 14 includes a connecting plate, a first extension arm located at one end of the connecting plate and extending along the first direction, and a second extension arm located at the other end of the connecting plate and extending along the first direction; one end of the first extension arm and the second extension arm is used to connect the connecting plate, and the other ends of the first extension arm and the second extension arm form an opening, and the first extension arm and the second extension arm are provided with a slide groove near the end of the connecting plate, a through hole is provided on the first extension arm near the opening end, and a threaded hole is provided on the second extension arm near the opening end, an opening groove is provided on the connecting plate and the opening faces the head module 5, one end of the arm 12 is connected to the first connecting pipe of the flight rotor unit 1, and the other end of the arm 12 is used to cooperate with the opening groove.

The limiting bolt 10 passes through the first extension arm through hole, one side of the torsion spring 11, the first through hole of the machine arm 12, the other side of the torsion spring 11, and the second extension arm threaded hole in sequence, and the end of the torsion spring 11 extends into the through hole opened on the connecting plate, and the double-headed spring pin 16 passes through the first extension arm slide groove, the second through hole of the machine arm 12, and the second extension arm slide groove in sequence, and under the action of the torsion spring 11, the double-headed spring pin 16 slides in the slide groove.

The passive wing deployment unit 3 also includes an auxiliary fixing plate 25, and the two ends of the limiting bolt 10 extend from the through hole I of the auxiliary fixing plate 25 on both sides; when the flight rotor unit 1 is in the first state, the two ends of the double-headed spring pin 16 extend from the through hole II of the auxiliary fixing plate 25 on both sides; when the flight rotor unit 1 is in the second state, the two ends of the double-headed spring pin 16 are limited by the auxiliary fixing plates 25 on both sides.

It also includes an elastic fixing belt 15 , one end of which is provided with a sleeve connected to the first connecting pipe, and the other end of the elastic fixing belt 15 is connected to the head module 5 .

The intermediate connecting module 4 includes a second connecting pipe, a flight controller 17, an upper fixing plate 18, a battery 19, an intermediate fixing sleeve 20, and a lower fixing plate 21; one end of the upper fixing plate 18 is connected to one end of the lower fixing plate 21 through the intermediate fixing sleeve 20, the other end of the upper fixing plate 18 is installed with the flight controller 17, and the other end of the lower fixing plate 21 is installed with the battery 19, a sleeve is circumferentially provided between the upper fixing plate 18 and the lower fixing plate 21 for installing the second connecting pipe, and the two ends of the second connecting pipe pass through the upper fixing plate 18 and the lower fixing plate 21 respectively, the end of the second connecting pipe passing through the upper fixing plate 18 is used to connect the nose module 5, and the end of the second connecting pipe passing through the lower fixing plate 21 is used to connect the auxiliary tail fixing seat 26.

The head module 5 includes a nose cone cover 22, a connecting base 23, and a GPS module 24; wherein the nose cone cover 22 is connected to the connecting base 23, the GPS module 24 is fixed on the connecting base 23, and the connecting base 23 is connected to the second connecting pipe of the intermediate connecting module 4.

The auxiliary tail wing 2 includes a cone 2-2 and a support body 2-1. The support body 2-1 is arranged at intervals along the circumferential direction at the tip of the cone 2-2, and the other end of the cone 2-2 is connected to the auxiliary tail wing fixing seat 26. The cone 2-2 is provided with a channel for the propeller 8 in the flight rotor unit 1 to enter and exit.

The beneficial effects of the present invention are:

1. The present invention uses a wing passive unfolding unit structure to realize the folding and unfolding of the flight rotor unit. When the rotorcraft is in a folded state in the launch device, the wings are passively unfolded to realize flight when launched;

2. The present invention uses an auxiliary tail wing structure to achieve auxiliary support before the aircraft is launched, and at the same time can reduce the impact of tail spin during the launch process;

3. The present invention uses an intermediate connection module structure to connect the various parts of the aircraft. By placing the flight controller and the battery on the module, the space is reasonably utilized, and the center of gravity of the entire aircraft is located in the middle of the aircraft, avoiding top-heavy;

4. The present invention uses a nose module structure, placing the GPS module in a semi-elliptical nose cone structure on the top of the aircraft, thereby avoiding signal interference. At the same time, the semi-elliptical shape can reduce the impact of wind resistance during impact and ejection.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic diagram of the overall development of the present invention;

FIG2 is a schematic diagram of the overall folding of the present invention;

FIG3 is a schematic diagram of a flight rotor unit of the present invention;

FIG4 is a schematic diagram of a wing passive deployment unit of the present invention;

FIG5 is a schematic diagram of a wing passive deployment explosion unit of the present invention;

FIG6 is a schematic diagram of a slide seat of the present invention;

FIG7 is a schematic diagram of an intermediate connection module of the present invention;

FIG8 is a schematic diagram of a head module of the present invention;

FIG9 is a schematic diagram of an auxiliary tail wing of the present invention;

FIG10 is a schematic diagram of the installation of the auxiliary fixing plate of the present invention;

FIG11 is a schematic diagram of the installation of the auxiliary tail wing of the present invention;

The numbers in the figure are: 1-flight rotor unit, 2-auxiliary tail, 3-wing passive deployment unit, 4-middle connection module, 5-nose module, 6-DC motor, 7-DC motor fixing part, 8-propeller, 9-pipe auxiliary pulley, 10-limit bolt, 11-torsion spring, 12-machine arm, 13-gasket, 14-slide seat, 15-elastic fixing belt, 16-double-headed spring pin, 17-flight controller, 18-upper end fixing plate, 19-battery, 20-middle connection sleeve, 21-lower end fixing plate, 22-nose cone cover, 23-connection base, 24-GPS module, 25-auxiliary fixing plate, 26-auxiliary tail fixing seat.

Detailed ways

The invention will be further described below in conjunction with the accompanying drawings and embodiments, but the content of the invention is not limited to the scope of the embodiments.

Embodiment 1: As shown in FIG. 1-11, a passively deployed catapult aircraft comprises a flight rotor unit 1, an auxiliary tail 2, a wing passively deployed unit 3, an intermediate connection module 4, a nose module 5, and an auxiliary tail fixing seat 26; the flight rotor unit 1 is connected to the intermediate connection module 4 through the wing passively deployed unit 3, so that the flight rotor unit 1 has a first deployed state and a second folded state, and the nose module 5, the intermediate connection module 4, the auxiliary tail fixing seat 26, and the auxiliary tail 2 are connected in sequence. The auxiliary tail 2 is located at the bottom of the aircraft, and on the one hand, it is used for tail support before the catapult flight, and on the other hand, it can prevent tail spin from occurring during the catapult flight.

Furthermore, the flight rotor unit 1 includes a first connecting pipe, a DC motor 6, a DC motor fixing part 7, a propeller 8 and a pipeline auxiliary pulley 9; the propeller 8 is installed at one end of the DC motor 6, and the other end of the DC motor 6, the DC motor fixing part 7 fixed at one end of the first connecting pipe, and the bracket of the pipeline auxiliary pulley 9 are fixedly connected by bolts, and the other end of the first connecting pipe is connected to the wing passive deployment unit 3; when the flight rotor unit 1 is in the second state, the pulley of the pipeline auxiliary pulley 9 contacts the wall surface of the launch device, which can make the launch smoother; furthermore, it can avoid the motor directly contacting the launch device to cause wear (when placed in the launch device, it belongs to the folded state, that is, the second state). Among them, the first connecting pipe adopts a carbon tube. The DC motor fixing part 7 includes a motor seat part and a carbon tube connecting part, the motor base part is in a round cake shape, and a threaded hole is arranged on it to fix the motor; the carbon tube connecting part is cylindrical as a whole, and a threaded hole is provided at the upper end for fixing the carbon tube.

Specifically, as shown in Fig. 3, the propeller 8 is divided into a forward propeller and a reverse propeller, and each flight rotor unit 1 is equipped with a forward propeller or a reverse propeller. Among them, the number of flight rotor units 1 is 4, that is, the number of forward and reverse propellers in the entire catapult aircraft is the same, which can avoid the problem of unbalanced air torque caused by an odd number of propellers, thereby ensuring the normal flight of the aircraft.

Furthermore, as shown in Figures 4-6, the wing passive deployment unit 3 includes a limit bolt 10, a torsion spring 11, an arm 12, a slide slot seat 14, and a double-headed spring pin 16; the limit bolt 10 is used to pass through the torsion spring 11, the arm 12, and the slide slot seat 14, and the double-headed spring pin 16 is used to pass through the arm 12, the slide slot seat 14 and under the action of the torsion spring 11, the double-headed spring pin 16 slides in the slide slot of the slide slot seat 14.

Further, as shown in Figure 6, the slide seat 14 includes a connecting plate, a first extension arm located at one end of the connecting plate and extending along the first direction, and a second extension arm located at the other end of the connecting plate and extending along the first direction; one end of the first extension arm and the second extension arm is used to connect the connecting plate, and the other ends of the first extension arm and the second extension arm form an opening, the first extension arm and the second extension arm are provided with a slide groove near the end of the connecting plate, the first extension arm is provided with a through hole near the opening end, and the second extension arm is provided with a threaded hole near the opening end, the connecting plate is provided with an open groove and the opening faces the nose module 5, one end of the arm 12 is connected to the first connecting pipe of the flight rotor unit 1, and the other end of the arm 12 is used to cooperate with the open groove so that the flight When the rotor unit 1 is in the first state, the axis of the arm 12 is parallel to the bottom surface of the auxiliary tail fixing seat 26 (the other end of the arm 12 is a cylinder. When the flight rotor unit 1 moves from the second state to the first state, the cylinder cooperates with the bayonet of the open groove to make the axis of the arm 12 parallel to the bottom surface of the auxiliary tail fixing seat 26. Based on this cooperation, the flight controllability can be better, while limiting its ability to sway left and right) (if there is an auxiliary tail 2, it is parallel to the bottom support plane of the auxiliary tail 2); further, the slide groove is an arc-shaped slide groove, which serves as the running track of the double-headed spring pin 16; in an embodiment of the present invention, it is arranged that the flight rotor unit 1 is changed from the second state to the first state, and the first connecting pipe is rotated 90°.

Further, as shown in Figures 4-5, the limiting bolt 10 sequentially passes through the first extension arm through hole, one side of the torsion spring 11, the first through hole of the arm 12, the other side of the torsion spring 11, and the second extension arm threaded hole, and is threadedly connected to the second extension arm threaded hole, and the end of the torsion spring 11 extends into the through hole opened on the connecting plate (the limiting bolt 10 is installed with a gasket 13 between the torsion spring 11 and the connecting plate to prevent the torsion spring from shaking left and right), and the double-headed spring pin 16 sequentially passes through the first extension arm slide groove, the second through hole of the arm 12, and the second extension arm slide groove, and under the action of the torsion spring 11, the double-headed spring pin 16 slides in the slide groove (the second through hole of the arm 12 is a hole close to the end of the cylinder).

Further, as shown in FIG10 , the wing passive deployment unit 3 further includes an auxiliary fixing plate 25, and the two ends of the limiting bolt 10 extend from the through hole I of the auxiliary fixing plate 25 on both sides; when the flight rotor unit 1 is in the first state, the two ends of the double-headed spring pin 16 extend from the through hole II of the auxiliary fixing plate 25 on both sides; when the flight rotor unit 1 is in the second state, the two ends of the double-headed spring pin 16 are limited by the auxiliary fixing plates 25 on both sides. Further, the double-headed spring pin 16 is a column structure with a thick middle and thin ends. In the second state, the thin end passes through the through hole II of the auxiliary fixing plate 25 and the aperture of the through hole II of the auxiliary fixing plate 25 is smaller than the diameter of the thick end column of the spring pin 16.

Furthermore, the aircraft further comprises an elastic fixing belt 15 (such as rubber), one end of which is provided with a sleeve which is interference fit with the first connecting pipe, and the other end of which is connected to the head module 5. The elastic fixing belt 15 can provide a certain elastic force and prevent the arm 12 from shaking left and right when the elastic force of the torsion spring is insufficient.

Specifically, as shown in Figures 4-6, the slide seat 14 adopts an integrated design, on which the slide slot of the spring pin 16 and the limit opening slot of the arm 12 are provided, which limits its ability to swing left and right while providing a track for the arm to unfold, thereby increasing stability. Both ends of the double-headed spring pin 16 have elastic cylindrical heads and a smooth surface to prevent jamming during the sliding of the slide slot; the arm 12, the limit bolt 10, and the torsion spring 11 should be coaxial during installation, and the gasket 13 is installed on both sides to play a role of limiting and anti-slip; one end of the elastic fixing belt 15 is installed on the carbon tube, and the other end is fixed on the connecting base 23 to provide the role of limiting and auxiliary elastic force.

Furthermore, the surface of the slide groove of the slide groove seat 14 is smooth; the processing of the machine arm 12 as a whole can be printed with aluminum alloy, but the through hole position should be reamed and smoothed to facilitate the installation of the limit bolt 10 and the spring pin 16. Exemplarily, the present invention provides the lightweight processing result of the slide groove seat 14: the slide groove seat 14 is machined with high-strength and light-weight 6061, with an overall size of 24 mm*24 mm*20 mm, a wall thickness of 3 mm, and an overall mass of 80 g.

Further, the intermediate connection module 4 is located in the middle part of the aircraft, and includes a second connection pipe, a flight controller 17, an upper fixing plate 18, a battery 19, an intermediate fixing sleeve 20, and a lower fixing plate 21; one end of the upper fixing plate 18 is connected to one end of the lower fixing plate 21 through the intermediate fixing sleeve 20, the other end of the upper fixing plate 18 is installed with the flight controller 17, and the other end of the lower fixing plate 21 is installed with the battery 19, a sleeve is provided circumferentially between the upper fixing plate 18 and the lower fixing plate 21 for installing the second connection pipe, and the two ends of the second connection pipe pass through the upper fixing plate 18 and the lower fixing plate 21 respectively, one end of the second connection pipe passing through the upper fixing plate 18 is used to connect the nose module 5, and one end of the second connection pipe passing through the lower fixing plate 21 is used to connect the auxiliary tail fixing seat 26. Among them, the second connection pipe adopts a carbon tube.

Specifically, as shown in Figures 7 and 10, the flight controller 17 is adhered to the upper end surface of the upper fixing plate 18 by Velcro, and the battery 19 is adhered to the lower end surface of the lower fixing plate 21 by Velcro. According to experiments, this arrangement is easy to replace without affecting the flight test. Under the condition of ensuring the overall strength, the upper fixing plate 18 and the lower fixing plate 21 are cut from carbon fiber plates, and a connecting groove for connecting the wing passive deployment unit 3 is left on the upper fixing plate 18 and the lower fixing plate 21, and the wing passive deployment unit 3 can be fixed between the upper fixing plate 18 and the lower fixing plate 21. The first extension arm and the second extension arm of the slide seat 14 are provided with mounting holes for fixing with the upper fixing plate 18 and the lower fixing plate 21; a groove is provided on one end surface close to the upper fixing plate 18 and the lower fixing plate 21 for embedding the auxiliary fixing plate 25. Further, the upper fixing plate and the lower fixing plate can be processed with holes, and the arrangement of the wiring is considered without reducing the strength.

Furthermore, as shown in FIG8 , the nose module 5 is located at the top of the aircraft, and includes a nose cone cover 22, a connection base 23, and a GPS module 24; wherein the nose cone cover 22 and the connection base 23 are connected by screws, the GPS module 24 is adhered and fixed to the connection base 23, and the connection base 23 is connected to the second connection pipe of the intermediate connection module 4. It can be seen from the design of the intermediate connection module and the nose module that the flight controller, battery, and GPS of the present invention are arranged separately, which can effectively avoid the problem of uneven mass distribution, and at the same time, the GPS is separated from the nose cone cover to prevent positioning interference.

Furthermore, the head module 5 is in a semi-ellipsoidal shape as a whole, which can reduce impact and wind resistance. The intermediate connecting sleeve 20, the connecting base 23 and the head cone cover 21 can be 3D printed with PLA material, which saves costs and reduces the overall quality.

Furthermore, as shown in Figures 9 and 11, the auxiliary tail 2 adopts an integrated design, including a cone 2-2 and a support body 2-1. The support body 2-1 is arranged at intervals along the circumferential direction at the tip of the cone 2-2, and the other end of the cone 2-2 is connected to the auxiliary tail fixing seat 26 (which can be connected by bonding, bolts, etc.); a channel for the propeller 8 in the flight rotor unit 1 to enter and exit is opened on the cone 2-2.

Furthermore, in an embodiment of the present invention, the support body 2-1 is composed of four pieces arranged in a cross shape, and a support plane is formed at the bottom for tail support before ejection flight.

By applying the above technical solution, it can be seen that the overall semi-ellipsoidal shape of the nose cone cover can reduce airflow separation, reduce turbulence and resistance; at the same time, the design of the auxiliary tail wing 2 can reduce the negative pressure area at the tail, reduce the resistance caused by the tail, and reduce wind resistance.

The working principle is described below in combination with flight tests:

First, the arms of the passively deployable ejectable aircraft are manually folded, and then placed in a launch device (such as an ejection pipe), and the flight controller of the passively deployable ejectable aircraft is adjusted to the Throw mode by using the remote control lever pre-selected by the laptop. The aircraft pops out of the launch device under the push of an external force. At the moment of ejecting the launch device, the wing passive deployment unit 3 drives the flight rotor unit 1 to passively deploy, and the state of the aircraft is detected by the IMU sensor in the flight controller. When the aircraft is launched to the highest point, the flight controller intervenes to control the aircraft. According to the feedback of the IMU sensor, the attitude and altitude controller inside the flight controller are used to adjust the attitude and altitude of the aircraft, and finally the aircraft is hovered at a pre-designed altitude. Further, the remote controller can be used to control the flight of the aircraft, or the program pre-burned in the flight controller can be used to allow the aircraft to complete the pre-set work. Optionally, the model of the flight controller is: PX46C.

The specific implementation modes of the present invention have been described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above implementation modes, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims (10)

1. The passively-unfolding catapult aircraft is characterized by comprising a flight rotor wing unit (1), an auxiliary tail wing (2), a wing passively-unfolding unit (3), an intermediate connection module (4), a nose module (5) and an auxiliary tail wing fixing seat (26); the aircraft rotor unit (1) is connected with the intermediate connection module (4) through the passive unfolding unit (3) of wing, makes the aircraft rotor unit (1) have the first state of expansion, have folding second state, aircraft nose module (5) intermediate connection module (4) auxiliary fin fixing base (26) auxiliary fin (2) connect gradually.

2. The passively deployed catapult-assisted vehicle according to claim 1, characterized in that the flying rotor unit (1) comprises a first connection tube, a direct current motor (6), a direct current motor mount (7), a propeller (8) and a pipe auxiliary pulley (9); one end of the direct current motor (6) is provided with the propeller (8), the other end of the direct current motor (6), the direct current motor fixing piece (7) positioned at one end of the first connecting pipe and the bracket of the pipeline auxiliary pulley (9) are fixedly connected, and the other end of the first connecting pipe is connected with the wing passive unfolding unit (3); when the flying rotor unit (1) is in the second state, the pulley of the pipeline auxiliary pulley (9) is in contact with the wall surface of the launching device.

3. The passively deployed catapult aircraft according to claim 1, characterized in that the wing passive deployment unit (3) comprises a limit bolt (10), a torsion spring (11), a horn (12), a chute seat (14), a double-ended spring pin (16); the limit bolt (10) is used for penetrating the torsion spring (11), the arm (12) and the chute seat (14), and the double-ended spring pin (16) is used for penetrating the arm (12) and the chute seat (14) and realizing sliding of the double-ended spring pin (16) in a chute of the chute seat (14) under the action of the torsion spring (11).

4. A passively deployed catapult aircraft according to claim 3, wherein the chute seat (14) comprises a connecting plate, a first extension arm extending in a first direction at one end of the connecting plate, a second extension arm extending in the first direction at the other end of the connecting plate; one ends of the first extension arm and the second extension arm are used for connecting a connecting plate, openings are formed at the other ends of the first extension arm and the second extension arm, sliding grooves are formed on the ends, close to the connecting plate, of the first extension arm, through holes are formed on the ends, close to the openings, of the first extension arm, threaded holes are formed in the second extension arm, close to the opening end, of the second extension arm, an opening groove is formed in the connecting plate, the opening faces the machine head module (5), one end of the horn (12) is connected with the first connecting pipe of the flight rotor unit (1), and the other end of the horn (12) is matched with the opening groove.

5. A passively expanding catapult aircraft according to claim 3, wherein the limit bolt (10) sequentially passes through the through hole of the first extension arm, one side of the torsion spring (11), the first through hole of the horn (12), the other side of the torsion spring (11), the threaded hole of the second extension arm, and the end part of the torsion spring (11) stretches into the through hole formed in the connecting plate, the double-ended spring pin (16) sequentially passes through the sliding groove of the first extension arm, the second through hole of the horn (12) and the sliding groove of the second extension arm, and the double-ended spring pin (16) slides in the sliding groove under the action of the torsion spring (11).

6. A passively deployed catapult aircraft according to claim 3, wherein the wing passive deployment unit (3) further comprises an auxiliary fixing plate (25), the two ends of the limit bolt (10) protruding from the through holes i of the auxiliary fixing plates (25) on both sides; when the flying rotor unit (1) is in a first state, two ends of the double-ended spring pin (16) extend out of through holes II of the auxiliary fixing plates (25) at two sides; when the flying rotor unit (1) is in the second state, two ends of the double-ended spring pin (16) are limited through the auxiliary fixing plates (25) at two sides.

7. The passively deployed catapult-type aircraft according to claim 1, further comprising an elastic fixing band (15), wherein one end of the elastic fixing band (15) is provided with a sleeve and is connected with the first connecting pipe, and the other end of the elastic fixing band (15) is connected with the nose module (5).

8. The passively deployed catapult-assisted craft according to claim 1, characterized in that the intermediate connection module (4) comprises a second connection tube, a flight controller (17), an upper end fixing plate (18), a battery (19), an intermediate fixing sleeve (20), a lower end fixing plate (21); one end of the upper end fixing plate (18) is connected with one end of the lower end fixing plate (21) through a middle fixing sleeve (20), the other end of the upper end fixing plate (18) is provided with a flight controller (17), the other end of the lower end fixing plate (21) is provided with a battery (19), sleeves are circumferentially arranged between the upper end fixing plate (18) and the lower end fixing plate (21) and are used for installing a second connecting pipe, two ends of the second connecting pipe respectively penetrate out of the upper end fixing plate (18) and the lower end fixing plate (21), one end of the second connecting pipe penetrating from the upper end fixing plate (18) is used for being connected with the machine head module (5), and one end of the second connecting pipe penetrating from the lower end fixing plate (21) is used for being connected with the auxiliary tail wing fixing seat (26).

9. The passively deployed catapult-assisted aircraft according to claim 1, characterized in that the nose module (5) comprises a nose cone cover (22), a connection base (23), a GPS module (24); the head cone cover (22) is connected with the connecting base (23), the GPS module (24) is fixed on the connecting base (23), and the connecting base (23) is connected with the second connecting pipe of the middle connecting module (4).

10. The passively unfolding catapult aircraft according to claim 1, wherein the auxiliary tail wing (2) comprises a cone (2-2) and supporting bodies (2-1), wherein the tip ends of the cone (2-2) are circumferentially spaced with the supporting bodies (2-1), and the other end of the cone (2-2) is connected with the auxiliary tail wing fixing seat (26); the cone (2-2) is provided with a channel for the entry and exit of a propeller (8) in the flying rotor unit (1).