Foldable gliding assembly and rocket projectile

Abstract

The foldable gliding assembly comprises a vehicle body of a hollow structure and wings arranged on the two sides of the vehicle body, each wing comprises a wing surface, one end of each wing surface is connected with the vehicle body through a rotating assembly, and a wing folding locking mechanism is further arranged on each wing surface so that the wings can be kept in a folded state; the rotating assembly comprises a supporting seat with one end fixedly connected with the aircraft body, the other end of the supporting seat is connected with the wing through an obliquely-arranged space rotating shaft, the space rotating shaft is sleeved with a torsional spring, and the wing can rotate around the space rotating shaft under the action of the torsional spring so that the wing can have an unfolding position and a folding position. The defects that in the prior art, the flight path of a rocket projectile is uncontrollable, the operation cost of an unmanned aerial vehicle is high, flight guarantee is complex, the integrated design of a patrolling projectile and the unmanned aerial vehicle cannot keep the similar revolution body section design of the rocket projectile, machining and manufacturing are more complex, and the independent characteristic of the original rocket projectile cannot be kept can be overcome.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket gliding assemblies, and in particular to a foldable gliding assembly and a rocket. Background Art

[0002] Rockets are aircraft propelled by rocket engines and can be used in both military and civilian applications. In the military, they are primarily used to kill, suppress enemy personnel, and destroy fortifications and weaponry. In the civilian sector, they are primarily used for weather modification. Rockets typically consist of a payload, a rocket engine, and a stabilizer. The payload can be a warhead or a catalyst such as silver iodide. Rocket launchers include bazookas, rocket artillery, rocket launchers, and rocket launch vehicles.

[0003] Take, for example, rockets used in weather modification operations. During these operations, the rocket is launched from a launcher at high speed into the air at an altitude of 3,000 to 7,000 meters. The fuse burns, igniting the catalyst in the rocket's warhead. This combustion spreads the catalyst, thereby increasing rainfall and preventing hail. Weather modification rockets offer the advantages of easy transportation and high maneuverability, and they also have a good catalytic effect in terms of rain enhancement. However, due to their fixed trajectory, in actual use, the catalyst's distribution range is small, and the descent phase is significantly affected by wind, resulting in uncontrollable trajectories, making precise operations impossible. Furthermore, it's difficult to accurately guarantee the landing point, severely impacting operational efficiency and quality.

[0004] Drones can improve the effectiveness of weather modification operations and enrich their tools. Drone-based rain enhancement offers low safety risks, extended operation times, excellent maneuverability, and high execution rates. In recent years, large drones have complemented manned aircraft in rain enhancement and drought relief efforts, enhancing the ability to modify weather conditions across all terrains and timeframes. However, the downside is the high cost of drone operations and the complexity of flight support.

[0005] Conventional loitering missiles, such as a foldable loitering missile (Patent Publication No. CN 219956302U), feature a design in which the payload is directly integrated into the drone's fuselage. The loitering missile's wings and tail can be folded to create a smaller package, enabling similar launch methods to rockets, including from a launch tube or vehicle. Furthermore, the wings and tail can be deployed mid-air, generating lift and using control surfaces for flight control, enabling similar flight to a drone. While this design allows for drone flight control, it largely fails to maintain the rocket's spun-body cross-sectional design, complicates manufacturing, and maintains the original rocket's independent characteristics. The overall cost is high, as both the fuselage and wings require remanufacturing. Furthermore, the missile cannot be used solely as a rocket, as its folded shape differs significantly from that of a conventional rocket's spun-body configuration. Furthermore, its center of gravity is offset from its axis, making it incapable of stable, long-term flight in rocket mode. Summary of the Invention

[0006] Therefore, the present invention provides a foldable gliding assembly and a rocket, which can overcome the defects in the prior art such as the uncontrollable flight trajectory of the rocket, the high operating cost of the UAV, the relatively complicated flight support, the inability of the combined design of the cruise missile and the UAV to maintain a similar rotating body cross-section design of the rocket, the more complicated processing and manufacturing, and the inability to maintain the independent characteristics of the original rocket.

[0007] In order to solve the above problems, the present invention provides a foldable gliding assembly, including a body with a hollow structure, wings arranged on both sides of the body, the wings including wing surfaces, one end of the wing surfaces being connected to the body through a rotating assembly, and a wing folding locking mechanism being further provided on the wing surfaces to keep the wings in a folded state, the rotating assembly including a support base fixedly connected to the body at one end, the other end of the support base being connected to the wings through an inclined spatial rotating shaft, a torsion spring being sleeved on the spatial rotating shaft, and under the action of the torsion spring, the wings can rotate around the spatial rotating shaft so that the wings have an unfolded position and a folded position.

[0008] In some embodiments, the support seat has a first support portion and a second support portion arranged at intervals, the height of the first support portion is smaller than the height of the second support portion, the first support portion and the second support portion both have free ends, and the two ends of the spatial rotation axis are respectively connected to the two free ends.

[0009] In some embodiments, the wing further includes a wing deployment locking device, which includes a locking pin located at the rotational connection end of the wing surface, and the fuselage has a locking groove adapted to the locking pin, and the locking pin is engaged in the locking groove to keep the wing in the deployed state.

[0010] In some embodiments, the free end of the airfoil has an aileron, and the aileron is connected to an aileron servo for controlling the working position of the aileron.

[0011] In some embodiments, the wing folding locking mechanism includes a folding locking pin hole located on the wing surface, and a locking device fixed to the body, the locking device includes a driving device, the driving device has an output shaft, the driving device drives the output shaft to rotate, the output shaft is connected to the center position of the steering wheel, the two free ends of the steering wheel are respectively connected to the left wing pin puller and the right wing pin puller, the other end of the left wing pin puller is connected to the left wing locking pin, and the other end of the right wing pin puller is connected to the right wing locking pin, the rotation of the steering wheel drives the locking pin to move toward or away from the axis of the body through the pin puller, and the folding locking pin hole is adapted to the pin to keep the wing in a folded state.

[0012] In some embodiments, the tail of the fuselage has a tail rotating mechanism, the fuselage has a tail compartment for accommodating the tail rotating mechanism and the tail, and the wing surface has a tail folding stopper. When the tail rotating mechanism is subjected to force and pressed into the tail compartment, the tail folding stopper can prevent the tail from detaching from the tail compartment. When the tail folding stopper detaches from the tail, the tail rotating mechanism automatically unfolds to a flight position.

[0013] In some embodiments, the upper portion of the fuselage has a hatch, and the fuselage corresponding to the position of the hatch is equipped with an onboard data link device, a flight control computer, and an onboard battery.

[0014] The present application also provides a rocket comprising the above-mentioned foldable gliding assembly.

[0015] In some embodiments, the rocket body has a parachute system, and the flight control computer is in communication with the parachute system to control the ejection of the parachute system.

[0016] The present invention provides a foldable glide assembly and rocket, which utilize a folding wing design concept to add "wings" to the rocket. The split, independent design eliminates the need for modification to the rocket body and does not affect the original application of the rocket itself. During launch and ascent, the rocket is installed within the foldable glide assembly, which is equipped with a flight control system, electrical system, and navigation system. During launch and ascent, the wings and tail of the foldable glide assembly are folded, reducing the cross-sectional area of ​​the entire rocket. The rocket, propelled by the rocket engine, flies along a ballistic trajectory. Near the apex of flight, the wings and tail of the glide assembly rapidly deploy, and the rocket enters the gliding drone mode. The flight control and navigation systems utilize ailerons on the wings and a fully movable tail to control the rocket's attitude, allowing it to descend along the designated path. When the rocket reaches a certain altitude from the landing point, a built-in parachute deploys, allowing the rocket to land at the designated location. It has achieved controllable trajectory of the rocket during its descent phase without changing the rocket, enabling it to perform more precise missions, including attacking designated target points. At the same time, since the parachute opening speed and altitude during landing are greatly reduced, the accuracy of its landing point has been significantly improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic structural diagram of a foldable gliding assembly according to an embodiment of the present invention;

[0018] Figure 2 This is a schematic diagram of the assembly structure of a foldable gliding assembly and a rocket according to an embodiment of the present invention;

[0019] Figure 3 Schematic diagram of the structure of the rotating assembly of the foldable gliding assembly according to an embodiment of the present invention;

[0020] Figure 4 Schematic diagram of the locking device structure of the foldable gliding assembly according to an embodiment of the present invention;

[0021] Figure 5 A schematic diagram of the tail rotating assembly and tail structure of a foldable gliding assembly according to an embodiment of the present invention;

[0022] Figure 6 This is a schematic diagram of the installation of the main equipment of the foldable gliding assembly according to an embodiment of the present invention;

[0023] Figure 7 Schematic diagram of the structure of the foldable glider assembly in the folded state according to an embodiment of the present invention.

[0024] The reference numerals indicate:

[0025] 1. Airframe; 101. Tail compartment; 102. Hatch; 103. Onboard data link equipment; 104. Flight control computer; 105. Onboard battery; 106. Fixing threaded hole; 2. Wing surface; 201. Wing joint; 202. Aileron; 203. Aileron servo; 204. Tail folding stop; 3. Rotating assembly; 301. Support base; 302. Spatial rotation axis; 303. Rotating axis bolt; 304. Torsion spring; 4. Wing deployment locking device; 401. Locking groove; 402. Locking pin; 5. Folding Locking pin hole; 6. Locking device; 601. Drive device; 602. Steering wheel; 603. Right wing pin puller; 604. Left wing pin puller; 605. Right wing locking pin; 606. Left wing locking pin; 607. Right wing locking pin hole; 608. Left wing locking pin hole; 7. Tail rotation mechanism; 701. Servo mounting frame; 702. Tail control servo; 703. Connector ear; 704. Rotating shaft torsion spring; 705. Limiting plate; 8. Tail; 801. Tail nose; 9. Projectile body. DETAILED DESCRIPTION

[0026] See also Figures 1 to 7According to an embodiment of the present invention, a foldable glide assembly is provided, comprising a hollow body 1, wings disposed on either side of the body 1, the wings comprising airfoils 2, one end of which is connected to the body 1 via a rotating assembly 3. The airfoils 2 are also provided with a wing folding locking mechanism to maintain the wings in a folded state. The rotating assembly 3 comprises a support base 301 fixedly connected to the body 1 at one end, and the other end of the support base 301 is connected to the wings via an inclined spatial rotation axis 302. A torsion spring 304 is sleeved on the spatial rotation axis 302. Under the action of the torsion spring 304, the wings can rotate about the spatial rotation axis 302 to position the wings between an unfolded position and a folded position. Existing technologies typically use separate rockets or integrate drone designs into rockets or loitering missiles, resulting in uncontrollable flight trajectories for separate rocket designs. While integrating the mission payload directly into the drone body design achieves drone flight control, it essentially fails to maintain the rocket's similar spun-body cross-sectional design, complicates manufacturing, and fails to maintain the original rocket's independent characteristics. This application utilizes a uniquely designed foldable glide assembly, into which the rocket is loaded during use. This combines the advantages of both a rocket and a gliding drone while maintaining the rocket's independence. Existing rockets do not require modification; a simple assembly creates a gliding rocket system. The foldable glide assembly can also be simply removed to restore the rocket to its original form, reducing costs while retaining the rocket's ability to operate independently. The missile body and glide assembly are processed separately, making manufacturing relatively simple. This is particularly true for applications where a large number of rockets are already available, as only the glide assembly needs to be processed. The system is simple to use and can be easily installed, without interfering with the existing rocket launch method. This system also maintains the original rocket launch mode. If the rocket mode is the only option in certain scenarios, the glide assembly can be quickly removed to restore the rocket to its original form. The foldable wing structure provides a smaller cross-sectional area during the rocket's ascent, minimizing drag. The rocket, propelled by the rocket engine, flies along its trajectory. Near the apex of flight, the gliding assembly's wings and tail rapidly deploy, transforming the rocket into a gliding drone mode. The ailerons on the wings and the deployed, fully movable tail fins control the rocket's attitude, allowing it to descend along the path it was designed to follow. This allows the rocket's trajectory to be controlled during its descent without modifying the rocket, enabling more precise missions, including attacks on designated targets.

[0027] Specifically, the foldable glide assembly can be used to install rockets, cruise missiles, or any other devices required to achieve drone flight.

[0028] Specifically, the fuselage has grooves at the wings, and when the wings are folded, they are located in the grooves, which can minimize the cross-sectional area of ​​the fuselage during rocket launch and will not increase air resistance due to the exposed wings.

[0029] Specifically, the wing is rotatably connected to the spatial rotation shaft 302 via the wing joint 201 , and both ends of the spatial rotation shaft 302 are fixed via rotation shaft bolts 303 to prevent the torsion spring 304 from being separated from the spatial rotation shaft 302 .

[0030] In a specific embodiment, the support seat 301 has a first support portion and a second support portion that are spaced apart, the height of the first support portion is less than the height of the second support portion, the first support portion and the second support portion both have free ends, and the two ends of the spatial rotation axis 302 are respectively connected to the two free ends. In general, the unfolding of folding wings in the prior art is divided into two steps. First, the wings are unfolded, and then the wings are axially rotated to achieve a flying state. The operation is complicated, the structure is complex, and the production cost is high. The present application adopts the simplest spatial rotation axis 302 structure setting, and the heights of the two support portions are set to an unequal structure. The spatial rotation axis 302 is tilted to achieve the folding and unfolding of the wings. The structure is simple and the production cost is low.

[0031] Specifically, the wing can be folded and unfolded by rotating the wing along the spatial rotation axis 302 at a certain angle, for example, 121.17 degrees.

[0032] In a specific embodiment, the wing further includes a wing deployment locking device 4, which includes a locking pin 402 located at the rotational connection end of the wing surface 2. The fuselage 1 has a locking groove 401 adapted to the locking pin 402. The locking pin 402 is engaged in the locking groove 401 to keep the wing deployed. When the wing is in the open state, the wing will experience a certain amount of shaking due to air resistance. At this time, a locking pin 402 is provided on the wing surface 2, and a locking groove 401 is provided on the fuselage 1. After the wing is deployed, the locking pin 402 is engaged in the locking groove 401 to secure the wing, ensure the deployment stability of the foldable glider assembly, and improve flight stability.

[0033] In a specific embodiment, the free end of the wing surface 2 has an aileron 202, and the aileron 202 is connected to an aileron servo 203 for controlling the working position of the aileron 202. The aileron 202 is rotated by controlling the aileron 202 servo on the wing to perform roll control.

[0034] In a specific embodiment, the wing folding locking mechanism includes a folding locking pin hole 5 located on the wing surface 2, and a locking device 6 fixed to the body 1, the locking device 6 includes a driving device 601, the driving device 601 has an output shaft, the driving device 601 drives the output shaft to rotate, the output shaft is connected to the center position of the steering wheel 602, the two free ends of the steering wheel 602 are respectively connected to the left wing pin puller 604 and the right wing pin puller 603, the other end of the left wing pin puller 604 is connected to the left wing locking pin 606, and the other end of the right wing pin puller 603 is connected to the right wing locking pin 605, the rotation of the steering wheel 602 drives the locking pin to move closer to or away from the axis of the body 1 through the pin puller, and the folding locking pin hole 5 is adapted to the pin to keep the wing in a folded state. The driving device 601 drives the steering wheel 602 to rotate. The left wing pin puller 604 drives the left wing locking pin 606 to the right, while the right wing pin puller 603 drives the right wing locking pin 605 to the left. The pins disengage from the folding lock pin holes 5, and the wings automatically unfold under the action of the torsion spring 304. During the reverse movement, the pins are extended. Under the action of external force, the wings are compressed and move to the folded position. The pins then insert into the folding lock pin holes 5, achieving folded locking of the wings. This simple structure, coupled with the provision of the steering wheel 602, further shortens the pins' movement path, enabling installation operations under various installation conditions.

[0035] Specifically, the right wing locking pin 605 is slidably set in the right fixed block through the right wing locking pin hole 607, and the left wing locking pin 606 is slidably set in the left fixed block through the left wing locking pin hole 608, thereby realizing the left and right sliding of the pins.

[0036] In a specific embodiment, the tail of the fuselage 1 has a tail rotating mechanism 7, and the fuselage 1 has a tail compartment 101 for accommodating the tail rotating mechanism 7 and the tail 8. The wing surface 2 has a tail folding block 204. When the tail rotating mechanism 7 is subjected to force and pressed into the tail compartment 101, the tail folding block 204 can prevent the tail 8 from detaching from the tail compartment 101. When the tail folding block 204 detaches from the tail 8, the tail rotating mechanism 7 automatically unfolds to the flight position. Setting the tail 8 to the automatic unfolding mode can effectively reduce the drive module and reduce costs. During the installation stage, the tail 8 is pressed into the tail compartment 101, and then the wing is rotated. When the wing is in the folded state, the tail folding block 204 set on the wing surface 2 just presses against the tail 8 to prevent the tail 8 from detaching from the tail compartment 101, thereby achieving the folding of the tail. When the wings are opened, the tail folding block 204 is separated from the tail 8, and the tail is automatically unfolded under the action of a spring or other elastic device.

[0037] Specifically, the tail rotation mechanism 7 includes a servo mounting frame 701, a tail control servo 702, a tail joint ear 703, a shaft spring 704, and a limit plate 705. The output shaft of the driving servo 702 is connected to the tail nose 801 on the tail 8 to control the working position of the tail 8. By controlling the deflection of the tail 8, the flight attitude is controlled. The tail joint ear piece 703 is installed on the rotating shaft, and a rotating shaft spring 704 is installed on the rotating shaft. The rotating shaft spring 704 can ensure that the tail is quickly opened to the deployed position, and one end of the rotating shaft is tightly connected to the glider assembly body 1; the tail joint ear piece 703 is provided with a limit pin slot. When the tail is opened to the set angle, the limit piece 705 on the foldable glider assembly body is engaged with the limit pin slot on the tail joint ear piece 703 to prevent the tail from being deployed at too large an angle; the tail control servo 702 is installed in the servo mounting frame 701, and the servo rocker arm is connected to the tail nose to control the working position of the tail 8, and perform attitude control by controlling the deflection of the tail.

[0038] In a specific embodiment, the upper portion of the fuselage 1 has a hatch 102, and the fuselage 1 is equipped with an onboard data link device 103, a flight control computer 104, and an onboard battery 105, corresponding to the position of the hatch 102. The hatch 102 on the upper portion of the fuselage 1 facilitates the installation and maintenance of equipment within the fuselage 1. Furthermore, the installation of the onboard data link device 103, the flight control computer 104, and the onboard battery 105 on the upper portion of the fuselage 1 effectively prevents impacts on internal fuselage equipment during the recovery and landing of the foldable glider assembly, thereby improving the overall recovery rate of the equipment.

[0039] Specifically, a fixing threaded hole 106 is further provided in the body 1, and the rocket is fixed in the body 1 by screws, which makes disassembly and assembly convenient and quick.

[0040] The present application also provides a rocket comprising the above-mentioned foldable gliding assembly.

[0041] In one specific embodiment, the rocket body 9 includes a parachute system, and the flight control computer 104 is in communication with the parachute system to control its deployment. When the rocket system glides to a set position, the flight control computer 104 initiates a parachute deployment command, causing the parachute within the body to deploy and deploy, and the entire rocket system then descends under the parachute. This allows for the recycling of the rocket and its foldable glide assembly, reducing launch costs.

[0042] How the wing unfolds and folds:

[0043] When the wings are folded, their leading edges face downward and adhere to the sides of the fuselage 1. The wing's rotation axis is a spatial rotation axis 302. The wings rotate along this spatial rotation axis 302 at a certain angle (e.g., 121.17 degrees) to transform from the folded state to the horizontally deployed state, thereby providing lift for the rocket system.

[0044] Folding lock: The wing is rotated to the folded state by external force. At this time, the pin of the wing locking device 6 will be inserted into the folding locking pin hole 5 located at the leading edge of the wing. The torsion spring 304 (or other elastic components) at the spatial rotation axis 302 will be in a compressed state, and the entire wing will be locked and cannot rotate.

[0045] Deployment and Locking: The servo (i.e., drive unit 601) mounted on the fuselage rotates, driving the steering wheel 602 to rotate, which in turn drives the pin-pulling lever to translate inward. When the lever reaches a certain position, the locking pin is completely pulled out of the folding lock pin hole 5. The wing rapidly rotates about the spatial axis 302 under the action of the compressed torsion spring 304 on the spatial axis 302. When the wing rotates to a certain position, the deployment locking pin 402 located on the inner side of the wing root inserts into the locking groove 401 located on the fuselage 1, and the wing reaches the desired horizontal position and is locked.

[0046] How the tail wing unfolds and folds:

[0047] Folding lock: When the tail is folded, it rotates along the tail rotating mechanism 7 into the interior of the fuselage 1. The wings then rotate to the folded position and lock. At this time, the tail 8 is released and, under the action of the shaft torsion spring 704, it begins to unfold. However, when it rotates to a certain position, the trailing edge of the tail 8 wingtip will touch the tail folding stop 204 located on the wing, and the tail 8 is locked.

[0048] Deployment and locking: When the wings are unfolded, the tail 8 is quickly unfolded under the action of the shaft torsion spring 704 because there is no restriction on the tail folding block 204. However, when it is rotated to the specified position, the boss on the tail joint ear 703 contacts the limit block. At this time, the entire tail 8 is stuck, thereby achieving deployment and locking.

[0049] Installation and separation of rocket and glide assembly:

[0050] A hatch 102 is provided on the upper part of the body 1 of the foldable glider assembly. After the hatch 102 is opened, fixed threaded holes 106 reserved on the structure of the body 1 can be seen. Threaded holes are reserved on the rocket, and the rocket and the foldable glider assembly can be installed and fixed by screws.

[0051] Likewise, the foldable glide assembly can be separated from the rocket body if the retaining screws are removed.

[0052] The body 1 of the foldable glider assembly has equipment installation space and structural support inside, which can be used to install equipment such as airborne data link equipment 103, flight control computer 104 and airborne battery 105, providing a complete functional component for the rocket.

[0053] Flight mode and control principle:

[0054] Rocket flight: Launched from a ground launcher / launch vehicle, the entire rocket system automatically flies to the corresponding altitude along a predetermined trajectory. In this mode, the rocket's wings provide stability, and no active control is performed.

[0055] UAV glide flight: When the rocket reaches a specified altitude, the flight control computer 104 within the foldable glide assembly initiates wing and tail deployment commands, deploying the wings and tail. The onboard control and navigation equipment obtains information about the rocket system's speed, altitude, position, and attitude. The aileron servos 203 on the wings rotate the ailerons 202 for roll control, and the tail servos deflect the tail 8 for pitch control, thereby controlling the rocket system's attitude and trajectory.

[0056] Recovery: When the rocket system glides to the set position, the flight control computer 104 activates the parachute opening command, the parachute inside the missile body 9 pops out and unfolds, and then the entire rocket system lands by parachute.

[0057] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention. The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and variations without departing from the technical principles of the present invention, and such improvements and variations shall also be considered within the scope of protection of the present invention.

Claims

1. A foldable glider assembly, characterized in that: The invention comprises a body (1) with a hollow structure, and wings arranged on both sides of the body (1), wherein the wings comprise wing surfaces (2), one end of the wing surfaces (2) being connected to the body (1) via a rotating assembly (3), and a wing folding locking mechanism being further provided on the wing surface (2) so as to keep the wings in a folded state, and the rotating assembly (3) comprising a support seat (301) having one end fixedly connected to the body (1), and the other end of the support seat (301) being connected to the wings via an inclined spatial rotation shaft (302), and a torsion spring (304) being sleeved on the spatial rotation shaft (302), and under the action of the torsion spring (304), the wings can rotate around the spatial rotation shaft (302) so as to have an unfolded position and a folded position.

2. The foldable glider assembly according to claim 1, characterized in that: The support seat (301) comprises a first support portion and a second support portion which are spaced apart from each other, wherein the height of the first support portion is smaller than the height of the second support portion, and both the first support portion and the second support portion have free ends, and both ends of the spatial rotation axis (302) are respectively connected to the two free ends.

3. The foldable glider assembly according to claim 1, characterized in that: The wing further comprises a wing deployment locking device (4), the wing deployment locking device (4) comprising a locking pin (402) located at the rotation connection end of the wing surface (2), the fuselage (1) having a locking groove (401) adapted to the locking pin (402), the locking pin (402) being engaged in the locking groove (401) to keep the wing in the deployed state.

4. The foldable glider assembly according to claim 1, wherein: The free end of the wing surface (2) is provided with an aileron (202), and the aileron (202) is connected to an aileron servo (203) for controlling the working position of the aileron (202).

5. The foldable glider assembly according to claim 1, wherein: The wing folding locking mechanism comprises a folding locking pin hole (5) located on the wing surface (2), and a locking device (6) fixed on the body (1), wherein the locking device (6) comprises a driving device (601), wherein the driving device (601) has an output shaft, wherein the driving device (601) drives the output shaft to rotate, wherein the output shaft is connected to the center position of the steering wheel (602), and the two free ends of the steering wheel (602) are respectively connected to the left wing pin pull rod. (604) and the right wing pin pull rod (603), the other end of the left wing pin pull rod (604) is connected to the left wing locking pin (606), and the other end of the right wing pin pull rod (603) is connected to the right wing locking pin (605), the steering wheel (602) rotates through the pin pull rod to drive the locking pin to move toward or away from the axis of the body (1), and the folding locking pin hole (5) is adapted to the pin to keep the wing in a folded state.

6. The foldable glider assembly according to claim 1, wherein: The tail of the fuselage (1) is provided with a tail rotating mechanism (7), the fuselage (1) is provided with a tail compartment (101) for accommodating the tail rotating mechanism (7) and the tail (8), the wing surface (2) is provided with a tail folding stopper (204), when the tail rotating mechanism (7) is subjected to force and is pressed into the tail compartment (101), the tail folding stopper (204) can prevent the tail (8) from detaching from the tail compartment (101), and when the tail folding stopper (204) detaches from the tail (8), the tail rotating mechanism (7) is automatically unfolded to a flight position.

7. The foldable glider assembly according to claim 1, wherein: The upper portion of the fuselage (1) is provided with a hatch (102), and an onboard data link device (103), a flight control computer (104) and an onboard battery (105) are installed on the fuselage (1) corresponding to the position of the hatch (102).

8. A rocket, characterized in that: The invention comprises a foldable gliding assembly as described in any one of claims 1 to 7.

9. The rocket according to claim 8, characterized in that The rocket body is provided with a parachute system, and the flight control computer (104) is in communication connection with the parachute system and is used to control the ejection of the parachute system.

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