A folding cruise missile with redundant lock and prevent wing surface unfolding interference structure

Abstract

The present application relates to the field of folding unmanned aerial vehicle structure, especially to a folding cruise missile with redundant locking and interference prevention wing unfolding structure, comprising a fuselage, a front wing structure, a rear wing structure, a vertical tail structure, a power system and an on-board device; the front wing structure is connected with the fuselage through a threaded nut, the rear wing structure is connected with the fuselage through a bearing seat cooperating with bolts, the vertical tail structure is connected with the fuselage through bolts, and the on-board device is fixed in the fuselage through bolts or adhesive bonding; before the cruise missile is launched, the wings are folded and attached to the surface of the fuselage, after the launch, the front wing structure and the rear wing structure are unfolded simultaneously until locked, when the rear wing structure is unfolded to the position, the vertical tail structure starts to unfold until locked. The present application has a double-redundant wing locking structure, and has a structure for preventing the front and rear wing structures and the vertical tail structure from interfering with each other during unfolding, which can effectively improve the success rate and stability of the folding cruise missile in the cylindrical launching, and has the advantages of simple and compact structure.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of folding unmanned aerial vehicle, and particularly relates to a folding cruise missile with redundant locking and interference prevention structure for wing surface unfolding. BACKGROUND

[0002] In recent years, there are many scenes of field battle and street battle in modern war or anti-terrorism action, and long-range support weapons have the task of accurately attacking targets. However, the front-line troops have insufficient real-time situation awareness ability on the battlefield, and it is difficult to simultaneously improve the real-time combat and the effectiveness of the combat. The cruise missile, as a weapon with small size, low cost and good attack effect, meets the demand of war on modern weapons. The existing cruise missile is usually launched by a launching tube or a launching frame. The launching tube has the advantages of flexible arrangement and simple operation, so the cruise missile is usually launched by the launching tube. Before launching, the cruise missile needs to be folded and placed in the launching tube, and then automatically unfolded and enters the climbing flight state after being launched out of the tube.

[0003] The existing cruise missile mainly adopts a conventional layout, a tandem wing layout and an X-shaped layout. The cruise missile with the X-shaped layout has relatively small loading capacity, higher structural strength requirement, higher structural complexity and higher probability of failure. In order to prevent the tail wing from interfering with the wing when the tail wing is unfolded, the cruise missile with the conventional layout is usually designed to be unfolded downward, and the wing span of the cruise missile with the conventional layout is relatively large, so that the overall size of the cruise missile and the size of the launching system are large. In order to prevent the wing from interfering with the tail wing when the wing and the tail wing are unfolded, the cruise missile with the tandem wing layout usually sets the front wing and the rear wing together under the fuselage, and the tail wing is designed to be unfolded upward. In this way, the wing design is limited, and a thin airfoil must be used for design, otherwise the wing will greatly compress the space of the fuselage, and greatly limit the overall layout of the machine. In addition, the front and rear wings are too close in the vertical direction, and the rear wing is greatly affected by the airflow of the front wing, which reduces the aerodynamic performance of the whole machine and increases the control difficulty. In addition, the existing cruise missile usually uses a single way to achieve the in-place locking of the wing. If a related part fails during launching, the wing of the cruise missile cannot be locked in place, which leads to the failure of launching the cruise missile.

[0004] Therefore, it is necessary to design a folding cruise missile with redundant locking and interference prevention structure for wing surface unfolding to solve the above problems. SUMMARY

[0005] The purpose of the present application is to provide a folding cruise missile with redundant locking and interference prevention structure for wing surface unfolding, so as to solve the problems of wing and tail wing interference and single locking structure when the tandem wing front and rear wings are arranged on the upper and lower sides of the fuselage, and the problem that the cruise missile cannot be successfully launched when a single locking structure fails.

[0006] To achieve the above object, the present invention provides the following solution: a folding cruise missile with redundant locking and anti-wing surface expansion interference structure, comprising

[0007] body;

[0008] a front wing structure, disposed on the fuselage, and located on top of the fuselage when the front wing structure is in a folded state;

[0009] A front wing deployment locking structure is provided on the front wing structure, and is used to lock the front wing structure when it is deployed;

[0010] a rear wing structure, disposed on the fuselage, and located at the bottom of the fuselage when the rear wing structure is in a folded state;

[0011] A rear wing deployment locking structure is provided on the rear wing structure, and is used to lock the rear wing structure when it is deployed;

[0012] a vertical tail structure, movably arranged on the fuselage, and located on both sides of the fuselage when the vertical tail structure is in a folded state;

[0013] A vertical tail deployment locking structure is provided on the vertical tail structure, and is used to lock the vertical tail structure when it is deployed;

[0014] an association structure disposed between the rear wing deployment locking structure and the vertical tail deployment locking structure, the association structure being used to ensure that the deployment action of the vertical tail structure is located after the rear wing structure is fully deployed, thereby preventing the vertical tail structure from interfering with the deployment process of the front wing structure;

[0015] The power system is arranged at the tail end of the fuselage.

[0016] Preferably, the front wing deployment locking structure includes a front wing rotation shaft, which is detachably mounted on the front wing structure mounting section of the fuselage, and the middle portion of the outer side wall of the front wing rotation shaft is fixedly connected to a front wing plane bearing, one end of the front wing rotation shaft is rotatably connected to a left front wing turntable, and the other end of the front wing rotation shaft is rotatably connected to a right front wing turntable, the left front wing turntable and the right front wing turntable are respectively located on both sides of the front wing plane bearing and are in rotational contact with the front wing plane bearing, a front wing deployment locking portion is provided between the left front wing turntable and the right front wing turntable, and the front wing structure is detachably mounted on the left front wing turntable and the right front wing turntable.

[0017] Preferably, a front wing spring pin slide groove and a front wing torsion spring first placement groove are provided on the left front wing turntable, the first front wing torsion spring placement groove is coaxially arranged on the inner side of the front wing spring pin slide groove, a front wing spring pin hole is provided at one end of the front wing spring pin slide groove, a front wing torsion spring first fixing hole is provided inside the first placement groove of the front wing, and a left front wing connecting hole for mounting the front wing structure is further provided on the left front wing turntable;

[0018] The right front wing turntable is provided with a second placement groove for the front wing torsion spring, a second fixing hole for the front wing torsion spring is provided in the second placement groove for the front wing torsion spring, a front wing spring pin mounting hole is provided outside the second placement groove for the front wing torsion spring, and the right front wing turntable is also provided with a right front wing connecting hole for mounting the front wing structure.

[0019] Preferably, the front wing deployment locking portion includes a front wing spring pin and a front wing torsion spring, one end of the front wing spring pin is threadedly connected to the front wing spring pin mounting hole, the other end of the front wing spring pin is movably arranged in the front wing spring pin slide groove, the front wing torsion spring is sleeved on the middle part of the outer side of the front wing rotation axis, one end of the front wing torsion spring is arranged in the first fixing hole of the front wing torsion spring, and the other end is arranged in the second fixing hole of the front wing torsion spring, and the front wing torsion spring is located in the first placement groove of the front wing torsion spring and the second placement groove of the front wing torsion spring.

[0020] Preferably, the rear wing deployment locking structure includes a rear wing rotation shaft, which is detachably mounted on the rear wing and vertical tail structure mounting section of the fuselage, and a rear wing plane bearing is fixedly connected to the middle portion of the outer side wall of the rear wing rotation shaft, and one end of the rear wing rotation shaft is rotatably connected to the left rear wing turntable, and the other end of the rear wing rotation shaft is rotatably connected to the right rear wing turntable, the left rear wing turntable and the right rear wing turntable are respectively located on both sides of the rear wing plane bearing and are in rotational contact with the rear wing plane bearing, a rear wing deployment locking portion is provided between the left rear wing turntable and the right rear wing turntable, and the rear wing structure is detachably mounted on the left rear wing turntable and the right rear wing turntable.

[0021] Preferably, a first placement slot for a rear wing torsion spring is provided on the left rear wing turntable, a first fixing hole for the rear wing torsion spring is provided in the first placement slot for the rear wing torsion spring, a rear wing spring pin mounting hole is provided on the outer side of the first placement slot for the rear wing torsion spring, and a left rear wing connecting hole for mounting the rear wing structure is further provided on the left rear wing turntable;

[0022] The right rear wing turntable is provided with a rear wing spring pin slide groove and a second placement groove for the rear wing torsion spring. The second placement groove for the rear wing torsion spring is coaxially arranged on the inner side of the rear wing spring pin slide groove. A through hole rear wing spring pin hole is provided at one end of the rear wing spring pin slide groove. A second fixing hole for the rear wing torsion spring is provided inside the second placement groove for the rear wing torsion spring. The right rear wing turntable is also provided with a right rear wing connecting hole for installing the rear wing structure.

[0023] Preferably, the rear wing deployment locking portion includes a rear wing spring pin and a rear wing torsion spring, one end of the rear wing spring pin is threadedly connected to the rear wing spring pin mounting hole, the other end of the rear wing spring pin is movably arranged in the rear wing spring pin slide groove, the rear wing torsion spring is sleeved on the middle part of the outer side of the rear wing rotation axis, one end of the rear wing torsion spring is arranged in the first fixing hole of the rear wing torsion spring, and the other end is arranged in the second fixing hole of the rear wing torsion spring, and the rear wing torsion spring is located in the first placement groove of the rear wing torsion spring and the second placement groove of the rear wing torsion spring.

[0024] Preferably, the vertical tail deployment locking structure includes a left vertical tail locking structure and a right vertical tail locking structure, both of which are detachably mounted on the rear wing and vertical tail structure mounting section of the fuselage;

[0025] The left vertical tail locking structure includes a left vertical tail rotating shaft, which is detachably mounted on the rear wing and vertical tail structure mounting section. A left vertical tail plane bearing is fixedly connected to the middle portion of the outer side wall of the left vertical tail rotating shaft. One end of the left vertical tail rotating shaft is rotatably connected to the left vertical tail rotating end, and the other end of the left vertical tail rotating shaft is fixedly connected to the left vertical tail fixed end. The left vertical tail rotating end and the left vertical tail fixed end are respectively located on both sides of the left vertical tail plane bearing and are in rotational contact with the left vertical tail plane bearing. A left vertical tail deployment locking portion is provided between the left vertical tail rotating end and the left vertical tail fixed end, and the vertical tail structure is detachably mounted on the left vertical tail rotating end.

[0026] Preferably, the left vertical tail deployment locking portion includes a left vertical tail torsion spring and a left vertical tail spring pin, the left vertical tail torsion spring is sleeved on the middle part of the outer side of the left vertical tail rotation axis, one end of the left vertical tail torsion spring is arranged in the left vertical tail rotation end, and the other end is arranged in the left vertical tail fixed end, one end of the left vertical tail spring pin is threadedly connected to the left vertical tail fixed end, and the other end of the left vertical tail spring pin is movably arranged in the left vertical tail rotation end.

[0027] Preferably, the associated structure includes a rotating sleeve, which is fixedly mounted on one end of the rear wing rotation shaft, and one end of a nylon line is fixedly connected to each of the two ears of the rotating sleeve. The other end of one nylon line is fixedly connected to the left vertical tail locking structure, and the other end of the other nylon line is fixedly connected to the right vertical tail locking structure.

[0028] Compared with the prior art, the present invention has the following advantages and technical effects:

[0029] 1. The folding cruise missile of the present invention, which has redundant locking and a structure to prevent wing surface deployment interference, can achieve dual redundant locking during the deployment of the front and rear wing structures. In the event of a sudden failure of the preferred front and rear wing deployment locking structures, the fuselage structure itself can be used to achieve locking. This can effectively improve the success rate of cruise missile launches without significantly increasing the structural complexity and weight.

[0030] 2. The folding loitering missile of the present invention, with redundant locking and anti-wing surface deployment interference structures, has a front wing structure positioned on the upper side of the fuselage and a rear wing structure positioned on the lower side, effectively reducing aerodynamic interference between the front and rear wings. A linkage structure is also designed to prevent wing surface deployment interference. The front and rear wings deploy simultaneously. Once the rear wing is fully deployed, the linkage structure releases the folding constraints of the vertical tail structure, allowing the vertical tail to begin its upward deployment. This prevents collision and interference between the vertical tail and front wing structures when deployed simultaneously. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive work.

[0032] Figure 1 This is a schematic diagram of the overall structure of the present invention in the unfolded state;

[0033] Figure 2 This is a schematic diagram of the overall structure of the present invention in a folded state;

[0034] Figure 3 It is a structural diagram of the fuselage;

[0035] Figure 4 This is a schematic diagram of the internal structure of the front wing mounting section in the unfolded state of the present invention;

[0036] Figure 5 A partially exploded schematic diagram of the front wing structure of the present invention in the deployed state;

[0037] Figure 6 This is an exploded view of the front wing deployment locking structure in the deployed state of the present invention;

[0038] Figure 7 This is a schematic diagram of the detailed features of the left front wing turntable;

[0039] Figure 8 This is a schematic diagram of the detailed features of the right front wing turntable;

[0040] Figure 9 Schematic diagram of the structure of the front wing spring pin;

[0041] Figure 10 Schematic diagram of the internal structure of the rear wing and vertical tail structure installation section in the unfolded state of the present invention;

[0042] Figure 11 A partially exploded schematic diagram of the rear wing structure of the present invention in the deployed state;

[0043] Figure 12 This is an exploded view of the rear wing deployment locking structure in the deployed state of the present invention;

[0044] Figure 13 This is a schematic diagram of the detailed features of the left rear wing turntable;

[0045] Figure 14 This is a schematic diagram of the detailed features of the right rear wing turntable;

[0046] Figure 15 It is a perspective schematic diagram of the assembly of the vertical tail structure, the rear wing and the vertical tail structure mounting section and the rear wing deployment locking structure in the deployed state of the present invention;

[0047] Figure 16 This is an exploded view of the structure of the left vertical tail locking structure in the deployed state of the present invention;

[0048] Figure 17 Schematic diagram of the detailed features of the left vertical tail rotating end;

[0049] Figure 18 This is a schematic diagram of the detailed features of the left vertical tail fixed end;

[0050] Figure 19 This is an exploded view of the right vertical tail locking structure in the deployed state of the present invention;

[0051] Figure 20 It is a three-dimensional schematic diagram of the assembly of the vertical tail structure, the rear wing, the vertical tail structure mounting section and the rear wing structure in the folded state of the present invention.

[0052] Among them, 1. Fuselage; 11. Load section; 12. Front wing structure installation section; 121. Front wing structure nose side installation ribs; 122. Front wing rotation axis first fixing piece; 123. Front wing rotation axis first fixing nut; 124. Front wing rotation axis second fixing nut; 125. Front wing rotation axis second fixing piece; 126. Front wing structure tail side installation ribs; 127. Radio installation plate; 128. Universal connector; 13. Function expansion section; 14. Airborne equipment section; 15. Energy system section; 16. Rear wing and vertical tail structure installation section; 161. Rear wing structure nose side installation ribs; 162. Rear wing rotation axis first fixing piece; 163. Right vertical tail fixed carbon fiber plate; 164. Left vertical tail fixed carbon fiber plate. Fiberboard; 165. Tail-side mounting rib for the rear wing mechanism; 166. First bearing seat for the rear wing rotating shaft; 167. Second fixing member for the rear wing rotating shaft; 168. Second bearing seat for the rear wing rotating shaft; 17. Power system mounting section; 2. Front wing structure; 21. Left front wing structure; 22. Carbon fiber tube for the left front wing; 23. Front wing deployment locking structure; 231A. First retaining spring for the front wing rotating shaft; 231B. Second retaining spring for the front wing rotating shaft; 232A. First flange bearing for the front wing rotating shaft; 232B. Second flange bearing for the front wing rotating shaft; 233. Left front wing turntable; 2331. Front wing spring pin slideway; 2332. Front wing spring pin hole; 2333. First fixing hole for the front wing torsion spring; 2334, first placement slot for front wing torsion spring; 2335, left front wing connecting hole; 2336, left front wing fixing hole; 234, front wing rotation axis; 235, front wing spring pin; 2351, pin; 2352, pin spring; 2353, outer cylinder; 236, front wing plane bearing; 237, front wing torsion spring; 238, right front wing turntable; 2381, right front wing connecting hole; 2382, right front wing fixing hole; 2383, front wing spring pin mounting hole; 2384, second placement slot for front wing torsion spring; 2385, second fixing hole for front wing torsion spring; 24, right front wing carbon fiber tube; 25, right front wing structure; 3. Rear wing structure; 31. Left rear wing structure; 32. Left rear wing carbon fiber Tube; 33, rear wing deployment locking structure; 331, rotating sleeve; 332A, first rear wing retaining spring; 332B, second rear wing retaining spring; 332C, rear wing flange bearing; 333, left rear wing turntable; 3331, rear wing spring pin mounting hole; 3332, jacking screw hole; 3333, first rear wing torsion spring fixing hole; 3334, first rear wing torsion spring placement slot; 3335, left rear wing connecting hole; 3336, left rear wing fixing hole; 334, jacking screw; 335, rear wing rotating shaft; 336, rear wing spring pin; 337, rear wing plane bearing; 338, rear wing torsion spring; 339, right rear wing turntable; 3391, right rear wing fixing hole; 3392, right rear wing connecting hole;3393, rear wing spring pin guide slot; 3394, rear wing spring pin hole; 3395, rear wing torsion spring second fixing hole; 3396, rear wing torsion spring second placement slot; 34, right rear wing carbon fiber tube; 35, right rear wing structure; 4, vertical tail structure; 41, left vertical tail wing structure; 42, right vertical tail wing structure; 43, left vertical tail wing carbon tube connector; 44, right vertical tail wing carbon tube connector; 45, left vertical tail locking structure; 45 1. Left vertical tail rotating end; 4511, left vertical tail torsion spring first mounting hole; 4512, left vertical tail torsion spring first placement slot; 4513, left vertical tail rotating end pin hole; 4514, left vertical tail spring column pin hole; 4515, left vertical tail spring column pin slide; 4516, left vertical tail wing mounting hole; 452A, left vertical tail first retaining spring; 452B, left vertical tail second retaining spring; 453A, left vertical tail first flange bearing; 453B, left vertical tail second flange bearing ; 454, left vertical tail plane bearing; 455, left vertical tail torsion spring; 456, left vertical tail rotation axis; 457, left vertical tail fixed end; 4571, left vertical tail fixed end pin hole; 4572, left vertical tail torsion spring second placement slot; 4573, left vertical tail torsion spring second mounting hole; 4574, left vertical tail spring column pin mounting threaded hole; 458, left vertical tail limit pin; 459, left vertical tail spring column pin; 46, right vertical tail locking structure; 461, right vertical tail limit Pin; 462, right vertical tail fixed end; 463, right vertical tail rotation axis; 464, right vertical tail torsion spring; 465, right vertical tail plane bearing; 466, right vertical tail rotation end; 4661, right vertical tail wing mounting hole; 467A, right vertical tail first retaining spring; 467B, right vertical tail second retaining spring; 468A, right vertical tail first flange bearing; 468B, right vertical tail second flange bearing; 469, right vertical tail spring pin; 5. Power system; 6. Airborne equipment. DETAILED DESCRIPTION

[0053] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0054] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0055] Reference Figures 1 to 20 As shown, the present invention provides a folding loitering missile with redundant locking and anti-wing surface expansion interference structure, including

[0056] Body 1;

[0057] a front wing structure 2, disposed on the fuselage 1, and located on top of the fuselage 1 when the front wing structure 2 is in a folded state;

[0058] A front wing deployment locking structure 23 is provided on the front wing structure 2. The front wing deployment locking structure 23 is used to lock the front wing structure 2 when it is deployed;

[0059] a rear wing structure 3, arranged on the fuselage 1, and located at the bottom of the fuselage 1 when the rear wing structure 3 is in a folded state;

[0060] A rear wing deployment locking structure 33 is provided on the rear wing structure 3 and is used to lock the rear wing structure 3 when it is deployed;

[0061] A vertical tail structure 4 is movably arranged on the fuselage 1 and is located on both sides of the fuselage 1 when the vertical tail structure 4 is in a folded state;

[0062] A vertical tail deployment locking structure is provided on the vertical tail structure 4 and is used to lock the vertical tail structure 4 when it is deployed;

[0063] The linkage structure is provided between the rear wing deployment locking structure 33 and the vertical tail deployment locking structure. The linkage structure is used to ensure that the deployment action of the vertical tail structure 4 is located after the rear wing structure 3 is fully deployed, thereby preventing the vertical tail structure 4 from interfering with the deployment process of the front wing structure 2;

[0064] The power system 5 is arranged at the tail end of the fuselage 1.

[0065] The front wing structure 2 is located on the upper side of the fuselage 1, near the nose, while the rear wing structure 3 is located on the lower side of the fuselage 1, near the tail. This arrangement increases the vertical distance between the front and rear wings, reducing the impact of the front wing's airflow on the rear wing's aerodynamic performance to a certain extent. It also improves the control of the rear wing structure 3's control surfaces. It also allows the vertical position of the aircraft's center of gravity to be designed between the front and rear wings, improving overall aircraft stability. The vertical tail structure 4 is located on the left and right sides of the fuselage 1, mounted near the rear wing structure 3. This arrangement effectively reduces the overall size of the aircraft and increases its space utilization. The power system 5 is located at the rear of the fuselage, providing power for the cruise missile. The onboard equipment 6 includes multiple electronic devices, which are fixed to the interior of the fuselage 1 via cable ties, adhesives, and screw connections. When the cruise missile is in the folded state, the two ends of the front wing structure 2 rotate toward the tail and fold on the upper side of the fuselage 1, the two ends of the rear wing structure 3 rotate toward the nose and fold on the lower side of the fuselage 1, and the vertical tail structure 4 rotates toward the nose to be parallel to the axis of the fuselage 1 and folds on the left and right sides of the fuselage 1; when the cruise missile needs to be deployed, the wing surface deployment order is that the front wing structure 2 and the rear wing structure 3 rotate and deploy at the same time. When the rear wing structure 3 rotates into place, the vertical tail structure 4 starts to rotate and deploy. This can avoid mutual interference between the deployment of the tail and the front wing, and reduce the unstable aerodynamic impact of the tail when the cruise missile is launched.

[0066] Furthermore, from the nose to the tail, the fuselage 1 includes a payload section 11, a front wing structure mounting section 12, a function expansion section 13, an onboard equipment section 14, an energy system section 15, a rear wing and vertical tail structure mounting section 16, and a power system mounting section 17. The payload section 11 is used to carry the warhead and optoelectronic pod, the function expansion section 13 is used to carry a parachute or other functional equipment as needed, the onboard equipment section 14 has an internal mounting plate for mounting the flight control system, the energy system section 15 has internal batteries, and the power system mounting section 17 is structured to mount the fixed power system 5.

[0067] The front wing structure installation section 12 includes a front wing structure nose side mounting rib 121, a front wing rotation axis first fixing member 122, a front wing rotation axis first fixing nut 123, a front wing rotation axis second fixing nut 124, a front wing rotation axis second fixing member 125, a front wing structure tail side mounting rib 126, and a radio station installation plate 127. The front wing structure installation section 12 is designed with a front wing structure nose side mounting rib 121 and a front wing structure tail side mounting rib 127. The rib 126 is installed, and other components are secured to the front wing structure nose-side mounting rib 121 and the front wing structure tail-side mounting rib 126. The front wing rotation axis first fixing member 122 is bolted to the front wing structure nose-side mounting rib 121, and the front wing rotation axis second fixing member 125 is screwed between the front wing structure nose-side mounting rib 121 and the front wing structure tail-side mounting rib 126 in conjunction with the universal connector 128. The first and second fixing members 122, 125 clamp the ends of the front wing rotation axis 234 via the first and second fixing nuts 123, 124, respectively, restricting the movement of the front wing rotation axis 234 and achieving a secure connection between the front wing structure 2 and the front wing structure mounting section 12.

[0068] A further optimized solution is provided, in which the front wing deployment locking structure 23 includes a front wing rotation shaft 234, which is detachably mounted on the front wing structure mounting section 12 of the fuselage 1, and a front wing plane bearing 236 is fixedly connected to the middle of the outer side wall of the front wing rotation shaft 234, and one end of the front wing rotation shaft 234 is rotatably connected to the left front wing turntable 233, and the other end of the front wing rotation shaft 234 is rotatably connected to the right front wing turntable 238. The left front wing turntable 233 and the right front wing turntable 238 are respectively located on both sides of the front wing plane bearing 236 and are in rotational contact with the front wing plane bearing 236, and a front wing deployment locking portion is provided between the left front wing turntable 233 and the right front wing turntable 238, and the front wing structure 2 is detachably mounted on the left front wing turntable 233 and the right front wing turntable 238.

[0069] The first flange bearing 232A of the front wing rotating shaft is placed above the left front wing turntable 233, the first retaining spring 231A of the front wing rotating shaft is clamped into the retaining spring groove at the upper end of the front wing rotating shaft 234, and the second flange bearing 232B of the front wing rotating shaft is placed below the right front wing turntable 238, the second retaining spring 231B of the front wing rotating shaft is clamped into the retaining spring groove at the lower end of the front wing rotating shaft 234, thereby limiting the axial movement of the mounted components on the front wing rotating shaft 234.

[0070] Further optimization scheme, the front wing spring pin sliding groove 2331 and the front wing torsion spring first placing groove 2334 are arranged on the left front wing rotating disc 233, the front wing torsion spring first placing groove 2334 is coaxially arranged on the inside of the front wing spring pin sliding groove 2331, the front wing spring pin sliding groove 2331 is provided with a front wing spring pin hole 2332 at one end, the inside of the front wing torsion spring first placing groove 2334 is provided with a front wing torsion spring first fixing hole 2333, and the left front wing rotating disc 233 is also provided with a left front wing connecting hole 2335 for mounting the front wing structure 2.

[0071] The front wing torsion spring second placing groove 2384 is arranged on the right front wing rotating disc 238, the front wing torsion spring second placing groove 2384 is provided with a front wing torsion spring second fixing hole 2385, the outside of the front wing torsion spring second placing groove 2384 is provided with a front wing spring pin mounting hole 2383, and the right front wing rotating disc 238 is also provided with a right front wing connecting hole 2381 for mounting the front wing structure 2.

[0072] Further optimization scheme, the front wing unfolding locking part includes the front wing spring pin 235 and the front wing torsion spring 237, one end of the front wing spring pin 235 is in threaded connection with the front wing spring pin mounting hole 2383, the other end of the front wing spring pin 235 is movably arranged in the front wing spring pin sliding groove 2331, the front wing torsion spring 237 is sleeved on the middle part of the outside of the front wing rotating shaft 234, one end of the front wing torsion spring 237 is arranged in the front wing torsion spring first fixing hole 2333, and the other end of the front wing torsion spring 237 is arranged in the front wing torsion spring second fixing hole 2385, and the front wing torsion spring 237 is located in the front wing torsion spring first placing groove 2334 and the front wing torsion spring second placing groove 2384.

[0073] The front wing structure 2 includes a left front wing structure 21, a left front wing carbon fiber pipe 22, a front wing unfolding locking structure 23, a right front wing carbon fiber pipe 24 and a right front wing structure 25. The left front wing carbon fiber pipe 22 penetrates through the left front wing structure 21 and is relatively fixed in a manner of cementing, the right front wing carbon fiber pipe 24 penetrates through the right front wing structure 25 and is relatively fixed in a manner of cementing, the front wing unfolding locking structure 23 is connected with the right front wing structure 25 and the left front wing structure 21 through the right front wing carbon fiber pipe 24 and the left front wing carbon fiber pipe 22 respectively, and plays a role of controlling automatic unfolding and locking of the front wing structure 2.

[0074] The left front wing carbon fiber tube 22 is inserted into the left front wing connecting hole 2335 and fixed with screws through the left front wing fixing hole 2336. The right front wing carbon fiber tube 24 is inserted into the right front wing connecting hole 2381 and fixed with screws through the right front wing fixing hole 2382. The left front wing turntable 233 and the right front wing turntable 238 are installed on the front wing rotating shaft 234 and are in direct contact with the upper and lower surfaces of the front wing plane bearing 236 respectively. Under the action of the plane bearing 236, the left front wing turntable 233 and the right front wing turntable 238 can rotate around the front wing rotation axis 234 with less resistance; the two ends of the front wing torsion spring 237 are respectively inserted into the first fixing hole 2333 of the front wing torsion spring and the second fixing hole 2385 of the front wing torsion spring to complete the position fixation of the two ends, and the front wing torsion spring 237 is placed as a whole in the first placement groove 2334 of the front wing torsion spring and the second placement groove 2384 of the front wing torsion spring to complete the front wing The overall position of the torsion spring 237 is restricted, wherein the front wing rotation axis 234 is the center, and the center of the projection of the first fixing hole 2333 of the front wing torsion spring and the second fixing hole 2385 of the front wing torsion spring in the aperture direction has an angle of 10°; the front wing spring pin 235 is fixed in the right front wing turntable 238 by the external thread on the outer cylinder 2353 and the internal thread in the front wing spring pin mounting hole 2383, and the pin 2351 can be fixed in the front wing spring pin slide groove 2331 slides; the first flange bearing 232A of the front wing rotating shaft is placed above the left front wing turntable 233, the first retaining spring 231A of the front wing rotating shaft is clamped into the retaining spring groove at the upper end of the front wing rotating shaft 234, and the second flange bearing 232B of the front wing rotating shaft is placed below the right front wing turntable 238, and the second retaining spring 231B of the front wing rotating shaft is clamped into the retaining spring groove at the lower end of the front wing rotating shaft 234, limiting the axial movement of the mounted parts on the front wing rotating shaft 234.

[0075] The deployment redundant locking principle of the front wing structure 2 is as follows:

[0076] When the cruise missile is deployed, the projection of the center of the circle between the first fixing hole 2333 and the second fixing hole 2385 of the front wing torsion spring, centered on the front wing rotation axis 234, in the direction of the aperture forms a 10° angle. Therefore, the spring legs at both ends of the front wing torsion spring 237 must rotate 190° in opposite directions to fold the right front wing structure 25 and the left front wing structure 21 onto the upper side of the fuselage 1. The launch tube constrains them to maintain the folded state. When the cruise missile is launched from the tube, the external restraint is removed, and the front wing torsion spring 237 tends to return to its initial state. The spring legs at both ends exert a restoring force on the left and right front wing turntables 233 and 238, driving the front wing deployment lock structure 23 from the folded state to the deployed state. During the transformation process, the pin 2351 is restricted by the front wing spring pin slot 2331 and slides in the slot. When the right front wing structure 25 and the left front wing structure 21 are rotated 90 degrees around the front wing rotation axis 234, the pin 2351 is aligned with the front wing spring pin hole 2332. The pin 2351 is quickly ejected by the elastic force of the pin spring 2352, locking the relative positions of the left front wing turntable 233 and the right front wing turntable 238. At this time, the deployment process of the front wing structure 2 stops. If the front wing spring pin 235 fails and the pin 2351 does not eject as planned when it is aligned with the front wing spring pin hole 2332, it is necessary to install the rib 121 on the nose side of the front wing structure to lock the position of the front wing structure 2. Since there is a 10° angle between the centers of the projections of the first fixing hole 2333 of the front wing torsion spring and the second fixing hole 2385 of the front wing torsion spring in the aperture direction, after the front wing structure 2 is actually deployed, the restoring force of the front wing torsion spring 237 still exists, which can keep the leading edges of the airfoils of the left front wing turntable 233 and the right front wing turntable 238 always close to the mounting rib 121 on the nose side of the front wing structure. Since the minimum distance between the leading edges of the airfoils of the left front wing turntable and the right front wing turntable and the mounting rib 121 on the nose side of the front wing structure is only 2 mm, which is a very short distance compared to the front wing structure 2, the angle between the right front wing structure 25 and the left front wing structure 21 can be considered to be 180°, which is the same as the normal deployment locking state.

[0077] The front wing spring pin 235 is the preferred locking solution for the front wing structure 2. When the pin spring 2352 fails, the use of the front wing structure nose-side mounting rib 121 for locking is an alternative solution. In this alternative solution, the leading edges of the left front wing turntable 233 and the right front wing turntable 238 directly collide with the front wing structure nose-side mounting rib 121. If the cruise missile is used for training or needs to be recovered for multiple uses, the repeated use of the alternative solution may affect the entire aircraft structure. Therefore, it is necessary to design the front wing spring pin 235 as the preferred locking solution. The alternative solution provides a redundant locking structure to ensure the smooth deployment and locking of the front wing structure 2 in the event of a failure of the preferred solution.

[0078] A further optimized solution is provided, in which the rear wing deployment locking structure 33 includes a rear wing rotation shaft 335, which is detachably mounted on the rear wing and vertical tail structure mounting section 16 of the fuselage 1, and a rear wing plane bearing 337 is fixedly connected to the middle part of the outer side wall of the rear wing rotation shaft 335, and one end of the rear wing rotation shaft 335 is rotatably connected to the left rear wing turntable 333, and the other end of the rear wing rotation shaft 335 is rotatably connected to the right rear wing turntable 339. The left rear wing turntable 333 and the right rear wing turntable 339 are respectively located on both sides of the rear wing plane bearing 337 and are in rotational contact with the rear wing plane bearing 337, and a rear wing deployment locking portion is provided between the left rear wing turntable 333 and the right rear wing turntable 339, and the rear wing structure 3 is detachably mounted on the left rear wing turntable 333 and the right rear wing turntable 339.

[0079] In a further optimized solution, a first placement slot 3334 for the rear wing torsion spring is provided on the left rear wing turntable 333, a first fixing hole 3333 for the rear wing torsion spring is provided in the first placement slot 3334, a rear wing spring pin mounting hole 3331 is provided outside the first placement slot 3334 for the rear wing torsion spring, and a left rear wing connecting hole 3335 for mounting the rear wing structure 3 is further provided on the left rear wing turntable 333;

[0080] The right rear wing turntable 339 is provided with a rear wing spring pin slide slot 3393 and a rear wing torsion spring second placement slot 3396. The rear wing torsion spring second placement slot 3396 is coaxially arranged on the inner side of the rear wing spring pin slide slot 3393. A through hole rear wing spring pin hole 3394 is provided at one end of the rear wing spring pin slide slot 3393. A rear wing torsion spring second fixing hole 3395 is provided inside the rear wing torsion spring second placement slot 3396. The right rear wing turntable 339 is also provided with a right rear wing connecting hole 3392 for installing the rear wing structure 3.

[0081] The first rear wing retaining spring 332A is inserted into the retaining groove above the left rear wing turntable 333, and the rear wing flange bearing 332C is installed from the bottom of the rear wing rotation shaft 335 to contact the right rear wing turntable 339. The second rear wing retaining spring 332B is inserted into the retaining spring below the rear wing flange bearing 332C, limiting the axial movement of the installed parts on the rear wing rotation shaft 335.

[0082] To further optimize the solution, the rear wing deployment locking part includes a rear wing spring pin 336 and a rear wing torsion spring 338. One end of the rear wing spring pin 336 is threadedly connected to the rear wing spring pin mounting hole 3331, and the other end of the rear wing spring pin 336 is movably set in the rear wing spring pin slide groove 3393. The rear wing torsion spring 338 is sleeved on the middle part of the outer side of the rear wing rotation axis 335. One end of the rear wing torsion spring 338 is set in the first fixing hole 3333 of the rear wing torsion spring, and the other end is set in the second fixing hole 3395 of the rear wing torsion spring. The rear wing torsion spring 338 is located in the first placement groove 3334 of the rear wing torsion spring and the second placement groove 3396 of the rear wing torsion spring.

[0083] The rear wing and vertical tail structure mounting section 16 is designed with a rear wing structure nose side mounting rib 161 and a rear wing mechanism tail side mounting rib 165. Other components are fixed by relying on these two ribs. The second fixing member 167 of the rear wing rotation axis is fixed to the rear wing mechanism tail side mounting rib 165 by bolts, and the first fixing member 162 of the rear wing rotation axis is fixed between the rear wing structure nose side mounting rib 161 and the rear wing mechanism tail side mounting rib 165 by screws. The first bearing seat 166 of the rear wing rotating shaft is fixed to the second fixing piece 167 of the rear wing rotating shaft close to the fuselage by bolts, and the second bearing seat 168 of the rear wing rotating shaft is fixed to the first fixing piece 162 of the rear wing rotating shaft close to the second fixing piece 167 of the rear wing rotating shaft by bolts. The two ends of the rear wing rotating shaft 335 are respectively inserted into the axial holes of the first bearing seat 166 of the rear wing rotating shaft and the second bearing seat 168 of the rear wing rotating shaft to limit the movement of the rear wing rotating shaft 335, thereby realizing the connection and fixation between the rear wing structure 3 and the rear wing and vertical tail structure mounting section 16.

[0084] The rear wing structure 3 comprises a left rear wing structure 31, a left rear wing carbon fiber tube 32, a rear wing deployment locking structure 33, a right rear wing carbon fiber tube 34, and a right rear wing structure 35. The left rear wing carbon fiber tube 32 extends through the left rear wing structure 31 and is secured relative to it by adhesive bonding. The right rear wing carbon fiber tube 34 extends through the right rear wing structure 35 and is secured relative to it by adhesive bonding. The rear wing deployment locking structure 33 connects the right rear wing structure 35 and the left rear wing structure 31 and controls the automatic deployment and locking of the rear wing structure 3.

[0085] The left rear wing carbon fiber tube 32 is inserted into the left rear wing connecting hole 3335 and fixed with screws inserted through the left rear wing fixing hole 3336; the right rear wing carbon fiber tube 34 is inserted into the right rear wing connecting hole 3392 and fixed with screws inserted through the right rear wing fixing hole 3391. The left rear wing turntable 333 and the right rear wing turntable 339 are installed on the rear wing rotation shaft 335 and are in direct contact with the upper and lower surfaces of the rear wing plane bearing 337 respectively. Under the action of the rear wing plane bearing 337, the left rear wing turntable 333 and the right rear wing turntable 339 can rotate relative to each other with relatively small resistance; the tightening screw 334 is screwed into the tightening screw hole 3332 until it contacts the flat groove on the rear wing rotation shaft 335, so that the left rear wing turntable 333 and the rear wing rotation shaft 335 rotate synchronously without relative displacement, and the right rear wing turntable 339 can rotate relative to each other around the rear wing rotation shaft 335; the two ends of the rear wing torsion spring 338 are respectively inserted into the first fixing hole 3333 of the rear wing torsion spring and the second fixing hole 3395 of the rear wing torsion spring to complete the fixing of the two ends. The rear wing torsion spring 338 is placed as a whole on the first fixing hole 3333 of the rear wing torsion spring The first retaining spring 332A of the rear wing is inserted into the retaining groove 3393 above the left rear wing turntable 333, and the second retaining spring 332C of the rear wing is installed from the bottom of the rear wing rotating shaft 335 to contact with the right rear wing turntable 339. The second retaining spring 332B of the rear wing is inserted into the retaining spring below the rear wing flange bearing 332C to limit the axial movement of the installed parts on the rear wing rotating shaft 335. The rotating sleeve 331 is located on the upper side of the left rear wing turntable 333 and is fixed relative to the rear wing rotating shaft 335 by bolt connection and rotates together.

[0086] The redundant locking principle for the deployment of the rear wing structure 3 is as follows:

[0087] When the cruise missile is deployed, the projections of the first and second fixing holes 3333 and 3395 of the rear wing torsion spring, centered on the rear wing's rotation axis 335, form a 10° angle in the diameter direction. External force acting on the rear wing torsion spring 338 requires the spring legs at both ends to rotate 190° in opposite directions in order for the right and left rear wing structures 35 and 31 to fold against the underside of the fuselage 1, where they are restrained by the launch tube to maintain their folded positions. When the cruise missile is launched from the tube, the external restraint is removed, and the rear wing torsion spring 338 tends to return to its initial position. The spring legs at both ends exert a restoring force on the left and right rear wing turntables 333 and 339, forcing the rear wing deployment lock structure 33 from its folded position to its deployed position. During the transformation process, the rear wing spring pin 336 is restricted by the rear wing spring pin slot 3393 and slides within the slot. After the right rear wing structure 35 and the left rear wing structure 31 have both rotated 90 degrees around the axis of the rear wing rotation axis 335 from their initial positions in the folded state, the rear wing spring pin 336 aligns with the rear wing spring pin hole 3394, and the pin of the rear wing spring pin 336 pops out, locking the left rear wing turntable 333 and the right rear wing turntable 339 relative to each other, thus stopping the deployment process of the rear wing structure 3. If the rear wing spring pin 336 malfunctions and the pin does not pop out as planned, the rear wing structure 3 will need to be locked in position by the rib 165 installed on the tail side of the rear wing mechanism. Since there is a 10° angle between the centers of the projections of the first fixing hole 3333 of the rear wing torsion spring and the second fixing hole 3395 of the rear wing torsion spring in the aperture direction, when the rear wing structure 3 is actually deployed, the restoring force of the rear wing torsion spring 338 still exists, which can keep the sides of the left rear wing turntable 333 and the right rear wing turntable 339 close to the rear wing rotation axis 335 always close to the side of the rear wing mechanism tail side mounting rib 165. At this time, the angle between the right rear wing structure 35 and the left rear wing structure 31 can be considered to be 180°, which is the same as the normal deployment locked state.

[0088] The rear wing spring pin 336 is the preferred locking solution for the rear wing structure 3. If the rear wing spring pin 336 fails, using the rear wing mechanism's tail-side mounting rib 165 to achieve locking is an alternative solution. This alternative solution involves the left and right rear wing turntables 333 and 339, whose sides are closest to the rear wing rotation axis 335, directly impacting the side of the rear wing mechanism's tail-side mounting rib 165. If the cruise missile is used for training or needs to be recovered for multiple uses, repeated use of the alternative solution could potentially impact the entire aircraft structure. Therefore, designing the rear wing spring pin 336 as the preferred locking solution is necessary. The alternative solution provides a redundant locking structure to ensure the smooth deployment and locking of the front wing structure 2 in the event of a failure of the primary solution.

[0089] In a further optimized solution, the vertical tail deployment locking structure includes a left vertical tail locking structure 45 and a right vertical tail locking structure 46, both of which can be detachably mounted on the rear wing and vertical tail structure mounting section 16 of the fuselage 1;

[0090] The left vertical tail locking structure 45 includes a left vertical tail rotating shaft 456, which is detachably mounted on the rear wing and vertical tail structure mounting section 16. A left vertical tail plane bearing 454 is fixedly connected to the middle of the outer side wall of the left vertical tail rotating shaft 456. One end of the left vertical tail rotating shaft 456 is rotatably connected to the left vertical tail rotating end 451, and the other end of the left vertical tail rotating shaft 456 is fixedly connected to the left vertical tail fixed end 457. The left vertical tail rotating end 451 and the left vertical tail fixed end 457 are respectively located on both sides of the left vertical tail plane bearing 454 and are in rotational contact with the left vertical tail plane bearing 454. A left vertical tail deployment locking portion is provided between the left vertical tail rotating end 451 and the left vertical tail fixed end 457, and the vertical tail structure 4 is detachably mounted on the left vertical tail rotating end 451.

[0091] The right vertical tail locking structure 46 includes a right vertical tail rotating shaft 463, which is detachably mounted on the rear wing and vertical tail structure mounting section 16. A right vertical tail plane bearing 465 is fixedly connected to the middle of the outer side wall of the right vertical tail rotating shaft 463. One end of the right vertical tail rotating shaft 463 is rotatably connected to the right vertical tail rotating end 466, and the other end of the right vertical tail rotating shaft 463 is fixedly connected to the right vertical tail fixed end 462. The right vertical tail rotating end 466 and the right vertical tail fixed end 462 are respectively located on both sides of the right vertical tail plane bearing 465 and are in rotational contact with the right vertical tail plane bearing 465. A right vertical tail deployment locking portion is provided between the right vertical tail rotating end 466 and the right vertical tail fixed end 462, and the vertical tail structure 4 is detachably mounted on the right vertical tail rotating end 466.

[0092] The first retaining spring 452A and the second retaining spring 452B of the left vertical tail are respectively inserted into the retaining grooves on the left vertical tail rotating shaft 456; the first flange bearing 453A of the left vertical tail is installed in contact with the left side of the left vertical tail rotating end 451, and the second flange bearing 453B of the left vertical tail is installed in contact with the right side of the left vertical tail fixed end 457.

[0093] One end of the right vertical tail rotating shaft 463 is provided with a right vertical tail first retaining spring 467A and a right vertical tail first flange bearing 468A, and the other end is provided with a right vertical tail second retaining spring 467B and a right vertical tail second flange bearing 468B.

[0094] The right vertical tail deployment locking part includes a right vertical tail torsion spring 464 and a right vertical tail spring pin 469. The right vertical tail torsion spring 464 is sleeved on the middle part of the outer side of the right vertical tail rotation axis 463. One end of the right vertical tail torsion spring 464 is set in the right vertical tail rotation end 466, and the other end is set in the right vertical tail fixed end 462. One end of the right vertical tail spring pin 469 is threadedly connected to the right vertical tail fixed end 462, and the other end of the right vertical tail spring pin 469 is movably set in the right vertical tail rotation end 466.

[0095] To further optimize the solution, the left vertical tail deployment locking part includes a left vertical tail torsion spring 455 and a left vertical tail spring pin 459. The left vertical tail torsion spring 455 is sleeved on the middle part of the outer side of the left vertical tail rotation axis 456. One end of the left vertical tail torsion spring 455 is set in the left vertical tail rotation end 451, and the other end is set in the left vertical tail fixed end 457. One end of the left vertical tail spring pin 459 is threadedly connected to the left vertical tail fixed end 457, and the other end of the left vertical tail spring pin 459 is movably set in the left vertical tail rotation end 451.

[0096] To further optimize the solution, the associated structure includes a rotating sleeve 331, which is fixedly mounted on one end of the rear wing rotation shaft 335. The two ears of the rotating sleeve 331 are respectively fixedly connected to one end of a nylon line, the other end of one nylon line is fixedly connected to the left vertical tail locking structure 45, and the other end of the other nylon line is fixedly connected to the right vertical tail locking structure 46.

[0097] The nylon line is fixedly connected to the right vertical tail limiting pin 461 of the right vertical tail locking structure 46 .

[0098] The right vertical tail fixed carbon fiber plate 163 and the left vertical tail fixed carbon fiber plate 164 used for installing and connecting the vertical tail structure 4 are fixed between the rear wing structure nose side mounting rib 161 and the rear wing structure tail side mounting rib 165 by screws. The left vertical tail wing structure 41 and the right vertical tail wing structure 42, the left vertical tail wing carbon tube connector 43 and the right vertical tail wing carbon tube connector 44, the left vertical tail locking structure 45 and the right vertical tail locking structure 46 are all plane-symmetrical structures.

[0099] The two ends of the left vertical tail torsion spring 455 are respectively inserted into the first mounting hole 4511 of the left vertical tail torsion spring and the second mounting hole 4573 of the left vertical tail torsion spring for fixing at both ends. The left vertical tail torsion spring 455 is placed in the first placement groove 4512 of the left vertical tail torsion spring and the second placement groove 4572 of the left vertical tail torsion spring to limit the overall position of the torsion spring. The left vertical tail rotating end 451 and the left vertical tail fixed end 457 are respectively installed in contact with the surfaces on both sides of the left vertical tail plane bearing 454. The left vertical tail first flange bearing 453A is installed in contact with the left side of the left vertical tail rotating end 451, and the left vertical tail second flange bearing 453B is installed in contact with the right side of the left vertical tail fixed end 457. The first tail retaining spring 452A and the second left vertical tail retaining spring 452B respectively engage slots on the left vertical tail rotating shaft 456, limiting axial movement of the mounting structure on the left vertical tail rotating shaft 456. The outer surface of the left vertical tail spring pin 459 is threaded and connected to the left vertical tail spring pin mounting threaded hole 4574. When the cruise missile is folded, the left vertical tail limit pin 458 is inserted into the left vertical tail rotating end pin hole 4513 and the left vertical tail fixed end pin hole 4571, limiting the rotation and deployment of the left vertical tail locking structure 45. The rear end of the left vertical tail limit pin 458 is connected to a nylon rope, the other end of which is connected to the two ends of the rotating sleeve 331. The left vertical tail wing carbon tube connector 43 is fixed to the left vertical tail wing mounting hole 4516 with a nut. The left vertical tail fixed end 457 is connected and fixed to the left vertical tail fixed carbon fiber plate 164 with bolts, completing the relative fixation between the vertical tail structure 4 and the rear wing and vertical tail structure mounting section 16.

[0100] The principle of locking the left vertical tail locking structure 45 and preventing interference with the front wing structure 2 during deployment is as follows:

[0101] When the cruise missile is deployed, since the center of the circle projected in the aperture direction by the first mounting hole 4511 of the left vertical tail torsion spring and the second mounting hole 4573 of the left vertical tail torsion spring with the left vertical tail rotation axis 456 as the center is at a 10° angle, the spring legs at both ends of the left vertical tail torsion spring 455 need to rotate 100° in opposite directions under the action of external force in order to fold the left vertical tail wing structure 41 to the left side of the fuselage 1, and the left vertical tail limit pin 458 constrains it to maintain the folded state. When the cruise missile is launched from the tube and the rear wing structure 3 is unfolded into place, the rotating sleeve 331 rotates 90° following the rear wing rotation axis 335, and the left vertical tail limit pin 458 is pulled out through the nylon rope at the rear end of the left vertical tail limit pin 458. The folding constraint of the left vertical tail locking structure 45 is cancelled, and the left vertical tail torsion spring 455 tends to restore to its initial state. The restoring force is applied to the left vertical tail rotating end 451 and the left vertical tail fixed end 457 through the spring feet at both ends, driving the left vertical tail locking structure 45 from a folded state to an unfolded state. During the transformation process, the left vertical tail spring pin 459 is restricted by the left vertical tail spring pin slide groove 4515 and slides in the groove. When the left vertical tail rotating end 451 rotates 90° around the left vertical tail rotating axis 456, the left vertical tail spring pin 459 is aligned with the left vertical tail spring pin hole 4514, and the pin of the left vertical tail spring pin 459 pops out, locking the relative position of the left vertical tail rotating end 451 and the left vertical tail fixed end 457. At this time, the deployment process of the left vertical tail locking structure 45 stops.

[0102] The right vertical tail locking structure 46 and the left vertical tail locking structure 45 are plane-symmetrical structures, so the principles of locking the right vertical tail locking structure 46 and preventing interference with the deployment of the front wing structure 2 are the same as those of the left vertical tail locking structure 45. The right vertical tail locking structure 46 and the left vertical tail locking structure 45 ensure that the vertical tail structure 4 is released from its folding constraint and deployed only after the rear wing structure 3 is fully deployed. This prevents the upward deployment of the vertical tail structure 4 from interfering with the deployment of the front wing structure 2, significantly improving the deployment success rate of all wing surfaces of the cruise missile. At the same time, the delayed deployment of the vertical tail structure 4 also reduces the unstable aerodynamic effects on the cruise missile during the transition from launch mode to normal climb mode.

[0103] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0104] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection of the present invention.

Claims

1. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure, characterized in that: include fuselage (1); a front wing structure (2) disposed on the fuselage (1), wherein the front wing structure (2) is located on top of the fuselage (1) when in a folded state; A front wing deployment locking structure (23) is provided on the front wing structure (2), and the front wing deployment locking structure (23) is used to lock the front wing structure (2) when it is deployed; a rear wing structure (3) disposed on the fuselage (1), wherein the rear wing structure (3) is located at the bottom of the fuselage (1) when in a folded state; A rear wing deployment locking structure (33) is provided on the rear wing structure (3), and the rear wing deployment locking structure (33) is used to lock the rear wing structure (3) when it is deployed; a vertical tail structure (4) movably arranged on the fuselage (1), wherein the vertical tail structure (4) is located on both sides of the fuselage (1) when in a folded state; A vertical tail deployment locking structure is provided on the vertical tail structure (4), and the vertical tail deployment locking structure is used to lock the vertical tail structure (4) when it is deployed; A linking structure is provided between the rear wing deployment locking structure (33) and the vertical tail deployment locking structure, and the linking structure is used to enable the deployment action of the vertical tail structure (4) to be located after the rear wing structure (3) is deployed in place, thereby preventing the vertical tail structure (4) from interfering with the deployment process of the front wing structure (2); A power system (5) is arranged at the tail end of the fuselage (1); The front wing deployment locking structure (23) comprises a front wing rotation shaft (234), the front wing rotation shaft (234) is detachably mounted on the front wing structure mounting section (12) of the fuselage (1), a front wing plane bearing (236) is fixedly connected to the middle of the outer side wall of the front wing rotation shaft (234), one end of the front wing rotation shaft (234) is rotatably connected to the left front wing turntable (233), and the other end of the front wing rotation shaft (234) is rotatably connected to the right front wing turntable (233). Wing turntable (238), the left front wing turntable (233) and the right front wing turntable (238) are respectively located on both sides of the front wing plane bearing (236) and are in rotational contact with the front wing plane bearing (236), a front wing deployment locking portion is provided between the left front wing turntable (233) and the right front wing turntable (238), and the front wing structure (2) is detachably mounted on the left front wing turntable (233) and the right front wing turntable (238); The left front wing turntable (233) is provided with a front wing spring pin slide groove (2331) and a first front wing torsion spring placement groove (2334); the first front wing torsion spring placement groove (2334) is coaxially arranged inside the front wing spring pin slide groove (2331); a front wing spring pin hole (2332) is provided at one end of the front wing spring pin slide groove (2331); a first front wing torsion spring fixing hole (2333) is provided inside the first front wing torsion spring placement groove (2334); and a left front wing connecting hole (2335) for mounting the front wing structure (2) is further provided on the left front wing turntable (233); The right front wing turntable (238) is provided with a second placement slot (2384) for the front wing torsion spring, a second fixing hole (2385) for the front wing torsion spring is provided in the second placement slot (2384), a front wing spring pin mounting hole (2383) is provided outside the second placement slot (2384) for the front wing torsion spring, and the right front wing turntable (238) is further provided with a right front wing connecting hole (2381) for mounting the front wing structure (2); The front wing unfolding locking portion includes a front wing spring pin (235) and a front wing torsion spring (237), one end of the front wing spring pin (235) is threadedly connected to the front wing spring pin mounting hole (2383), the other end of the front wing spring pin (235) is movably arranged in the front wing spring pin sliding groove (2331), the front wing torsion spring (237) is sleeved on the middle part of the outer side of the front wing rotating shaft (234), one end of the front wing torsion spring (237) is arranged in the first fixing hole (2333) of the front wing torsion spring, and the other end is arranged in the second fixing hole (2385) of the front wing torsion spring, and the front wing torsion spring (237) is located in the first placement groove (2334) of the front wing torsion spring and the second placement groove (2384) of the front wing torsion spring; There is an angle of 10° between the center of the projection of the first fixing hole (2333) of the front wing torsion spring and the second fixing hole (2385) of the front wing torsion spring in the aperture direction. When an external force is applied, the spring legs at both ends of the front wing torsion spring (237) need to rotate 190° in opposite directions in order to fold the right front wing structure (25) and the left front wing structure (21) respectively on the upper side of the fuselage (1), and the launch tube constrains them to maintain the folded state.

2. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 1, characterized in that: The rear wing deployment locking structure (33) includes a rear wing rotation shaft (335), which is detachably mounted on the rear wing and vertical tail structure mounting section (16) of the fuselage (1), a rear wing plane bearing (337) is fixedly connected to the middle of the outer side wall of the rear wing rotation shaft (335), one end of the rear wing rotation shaft (335) is rotatably connected to the left rear wing turntable (333), and the other end of the rear wing rotation shaft (335) is rotatably connected to the right rear wing turntable (333). The rear wing turntable (339) is provided with a rear wing structure (339), wherein the left rear wing turntable (333) and the right rear wing turntable (339) are respectively located on both sides of the rear wing plane bearing (337) and are in rotational contact with the rear wing plane bearing (337). A rear wing deployment locking portion is provided between the left rear wing turntable (333) and the right rear wing turntable (339). The rear wing structure (3) is detachably mounted on the left rear wing turntable (333) and the right rear wing turntable (339).

3. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 2, characterized in that: The left rear wing turntable (333) is provided with a first placement slot (3334) for a rear wing torsion spring, a first fixing hole (3333) for a rear wing torsion spring is provided in the first placement slot (3334), a rear wing spring pin mounting hole (3331) is provided outside the first placement slot (3334), and the left rear wing turntable (333) is further provided with a left rear wing connecting hole (3335) for mounting the rear wing structure (3); The right rear wing turntable (339) is provided with a rear wing spring pin slide groove (3393) and a rear wing torsion spring second placement groove (3396), the rear wing torsion spring second placement groove (3396) is coaxially arranged on the inner side of the rear wing spring pin slide groove (3393), one end of the rear wing spring pin slide groove (3393) is provided with a through hole rear wing spring pin hole (3394), the rear wing torsion spring second placement groove (3396) is provided with a rear wing torsion spring second fixing hole (3395), and the right rear wing turntable (339) is also provided with a right rear wing connecting hole (3392) for installing the rear wing structure (3).

4. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 3, characterized in that: The rear wing unfolding locking portion includes a rear wing spring pin (336) and a rear wing torsion spring (338), one end of the rear wing spring pin (336) is threadedly connected to the rear wing spring pin mounting hole (3331), the other end of the rear wing spring pin (336) is movably arranged in the rear wing spring pin sliding groove (3393), the rear wing torsion spring (338) is sleeved on the middle part of the outer side of the rear wing rotation axis (335), one end of the rear wing torsion spring (338) is arranged in the first fixing hole (3333) of the rear wing torsion spring, and the other end is arranged in the second fixing hole (3395) of the rear wing torsion spring, and the rear wing torsion spring (338) is located in the first placement groove (3334) of the rear wing torsion spring and the second placement groove (3396) of the rear wing torsion spring.

5. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 4, characterized in that: The vertical tail deployment locking structure includes a left vertical tail locking structure (45) and a right vertical tail locking structure (46), both of which can be detachably mounted on the rear wing and vertical tail structure mounting section (16) of the fuselage (1); The left vertical tail locking structure (45) includes a left vertical tail rotating shaft (456), which is detachably mounted on the rear wing and vertical tail structure mounting section (16); a left vertical tail plane bearing (454) is fixedly connected to the middle portion of the outer side wall of the left vertical tail rotating shaft (456); one end of the left vertical tail rotating shaft (456) is rotatably connected to the left vertical tail rotating end (451); the other end of the left vertical tail rotating shaft (456) is fixedly connected to the left vertical tail fixed end (457); the left vertical tail rotating end (451) and the left vertical tail fixed end (457) are respectively located on both sides of the left vertical tail plane bearing (454) and are in rotational contact with the left vertical tail plane bearing (454); a left vertical tail deployment locking portion is provided between the left vertical tail rotating end (451) and the left vertical tail fixed end (457); and the vertical tail structure (4) is detachably mounted on the left vertical tail rotating end (451).

6. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 5, characterized in that: The left vertical tail deployment locking portion includes a left vertical tail torsion spring (455) and a left vertical tail spring pin (459), wherein the left vertical tail torsion spring (455) is sleeved on the middle portion of the outer side of the left vertical tail rotation shaft (456), one end of the left vertical tail torsion spring (455) is arranged in the left vertical tail rotation end (451), and the other end is arranged in the left vertical tail fixed end (457), one end of the left vertical tail spring pin (459) is threadedly connected to the left vertical tail fixed end (457), and the other end of the left vertical tail spring pin (459) is movably arranged in the left vertical tail rotation end (451).

7. A folding loitering missile with redundant locking and anti-wing surface deployment interference structure according to claim 6, characterized in that: The associated structure comprises a rotating sleeve (331), the rotating sleeve (331) being fixedly sleeved on one end of the rear wing rotating shaft (335), one end of a nylon line being fixedly connected to the two lugs of the rotating sleeve (331), the other end of one of the nylon lines being fixedly connected to the left vertical tail locking structure (45), and the other end of the other of the nylon lines being fixedly connected to the right vertical tail locking structure (46).

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