Folding patrolling bomb with redundant locking and airfoil unfolding interference preventing structure

Abstract

The invention relates to the field of folding unmanned aerial vehicle structures, in particular to a folding patrolling bomb with a redundant locking and airfoil unfolding interference prevention structure, which comprises a fuselage, a front airfoil structure, a rear airfoil structure, a vertical fin structure, a power system and airborne equipment, 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 matched with a bolt, the vertical fin structure is connected with the fuselage through a bolt, and airborne equipment is fixed in the fuselage through a bolt or in a glue joint mode; the front wing surfaces are folded and attached to the surface of a fuselage before the patrolling bomb is launched, the front wing structure and the rear wing structure are unfolded at the same time after the patrolling bomb is launched until in-place locking is achieved, and when the rear wing structure is unfolded in place, the vertical fin structure begins to be unfolded until in-place locking is achieved. The unmanned aerial vehicle is provided with a dual-redundancy wing locking structure, is also provided with a structure for preventing the front and rear wing structures and the vertical fin structure from unfolding interference, can effectively improve the success rate and the stability of the barrel type launching of the folding patrolling bomb, and has the advantage of simple and compact structure.

Description

Technical Field

[0001] The invention belongs to the technical field of foldable unmanned aerial vehicles, and in particular relates to a foldable cruise missile with a redundant locking and wing surface expansion interference prevention structure. Background Art

[0002] In recent years, there have been many field and street fighting scenes in both modern warfare and anti-terrorism operations. Long-range support weapons have the task of accurately striking targets, but the front-line troops are not strong enough in their ability to perceive the real-time situation on the battlefield, making it difficult to improve both the real-time nature and effectiveness of operations. Cruise missiles are small, low-cost, and effective weapons that meet the needs of war for modern weapons. Existing cruise missiles are usually launched from launch tubes or ejection racks. Launch tubes have the advantages of flexible layout and simple operation, so cruise missiles are mostly launched from launch tubes. Before launching, the cruise missile needs to be folded and placed in the launch tube. After being launched out of the tube, it will automatically unfold and enter a climbing flight state.

[0003] At present, the cruise missiles disclosed mainly adopt conventional layout, tandem wing layout and X-type layout. The X-type layout cruise missile has a relatively small loading capacity, higher structural strength requirements, higher structural complexity, and a higher probability of failure; in order to prevent the tail from conflicting with the wing when it is deployed, the conventional layout cruise missile is usually designed to be deployed downward, and the wingspan of the conventional layout is relatively large, resulting in a larger overall size of the cruise missile and the size of the launch system; in order to prevent the wings and tail from interfering with each other when deployed, the tandem wing layout cruise missile usually sets the front wing and the rear wing together under the fuselage, and the tail is designed to be deployed upward, which will limit the wing design and must be designed with a thin airfoil, otherwise the wing will compress the fuselage space to a large extent, which will greatly limit the overall layout of the aircraft. In addition, the front and rear wings are too close in the vertical direction, and the rear wing will be greatly affected by the airflow of the front wing, resulting in reduced aerodynamic performance of the entire aircraft and increased control difficulty. In addition, most existing cruise missiles use a single method to lock the wings in place. If a related part fails during the launch process, the wings of the cruise missile will not be able to be locked in place, causing the cruise missile launch to fail.

[0004] Therefore, it is necessary to design a folding cruise missile with redundant locking and anti-wing surface expansion interference structure to solve the above problems. Summary of the invention

[0005] The purpose of the present invention is to provide a folding cruise missile with redundant locking and anti-wing surface deployment interference structure, so as to solve the problem of wing and tail wing deployment interference when the front and rear wings of the tandem wing are respectively arranged on the upper and lower sides of the fuselage, and the problem that the wing surface locking structure is single and the launch cannot be successfully carried out when a single fault occurs in the locking structure.

[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, arranged 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, which is arranged on the front wing structure, and is used to lock the front wing structure when it is deployed;

[0010] A rear wing structure, arranged 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, which is arranged 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 associated structure is provided between the rear wing deployment locking structure and the vertical tail deployment locking structure, and the associated structure is used to make the deployment action of the vertical tail structure be located after the rear wing structure is deployed in place, so as to prevent the vertical tail structure from interfering with the deployment process of the front wing structure;

[0015] The power system is arranged at the rear 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, a front wing plane bearing is fixedly connected to the middle portion of the outer side wall of the front wing rotation shaft, 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 arranged 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 slot and a front wing torsion spring first placement slot are provided on the left front wing turntable, the front wing torsion spring first placement slot is coaxially arranged on the inner side of the front wing spring pin slide slot, a front wing spring pin pin hole is provided at one end of the front wing spring pin slide slot, a front wing torsion spring first fixing hole is provided inside the front wing torsion spring first placement slot, and a left front wing connecting hole for installing the front wing structure is also provided on the left front wing turntable;

[0018] A second placement groove for the front wing torsion spring is provided on the right front wing turntable, 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 column pin mounting hole is provided outside the second placement groove for the front wing torsion spring, and a right front wing connecting hole for mounting the front wing structure is also provided on the right front wing turntable.

[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, a rear wing plane bearing is fixedly connected to the middle portion of the outer side wall of the rear wing rotation shaft, one end of the rear wing rotation shaft is rotatably connected to a left rear wing turntable, and the other end of the rear wing rotation shaft is rotatably connected to a 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, the left rear wing turntable is provided with a first placement groove for a rear wing torsion spring, a first fixing hole for a rear wing torsion spring is provided in the first placement groove for the rear wing torsion spring, a rear wing spring column pin mounting hole is provided outside the first placement groove for the rear wing torsion spring, and the left rear wing turntable is also provided with a left rear wing connecting hole for mounting the rear wing structure;

[0022] The right rear wing turntable is provided with a rear wing spring pin slide slot and a second rear wing torsion spring placement slot, the second rear wing torsion spring placement slot is coaxially arranged on the inner side of the rear wing spring pin slide slot, a through hole rear wing spring pin hole is provided at one end of the rear wing spring pin slide slot, a second rear wing torsion spring fixing hole is provided inside the second rear wing torsion spring placement slot, and 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 comprises a left vertical tail locking structure and a right vertical tail locking structure, both of which can be detachably mounted on the rear wing of the fuselage and the vertical tail structure mounting section;

[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 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 arranged 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 part 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 rotating shaft, and one end of a nylon line is fixedly connected to two support 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 with redundant locking and anti-wing surface expansion interference structure of the present invention can achieve dual redundant locking during the expansion of the front wing structure and the rear wing structure. In the event of a sudden failure of the preferred front wing expansion locking structure and the rear wing expansion locking structure, the structure of the fuselage itself can be used to achieve locking, which can effectively improve the success rate of the cruise missile launch without significantly increasing the structural complexity and weight.

[0030] 2. The folding cruise missile with redundant locking and anti-wing surface expansion interference structure of the present invention has a front wing structure arranged on the upper side of the fuselage and a rear wing structure arranged on the lower side of the fuselage, which can effectively reduce the aerodynamic interference between the front and rear wings. At the same time, an associated structure is designed to prevent wing surface expansion interference. The front and rear wing structures are expanded at the same time. When the rear wing structure is fully expanded, the folding constraint of the vertical tail structure is released through the associated structure, and the vertical tail begins to expand upward, which can avoid the collision interference when the vertical tail structure and the front wing structure are expanded at the same time. 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 drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative labor:

[0032] Figure 1 It is a schematic diagram of the overall structure of the present invention in an 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 schematic diagram of the structure of the fuselage;

[0035] Figure 4 It 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 It is a partial exploded schematic diagram of the front wing structure of the present invention in the unfolded state;

[0037] Figure 6 It is a structural exploded diagram of the front wing deployment locking structure in the deployed state of the present invention;

[0038] Figure 7 It is a detailed feature diagram of the left front wing turntable;

[0039] Figure 8 It is a detailed feature diagram of the right front wing turntable;

[0040] Fig. 9 It is a schematic diagram of the structure of the front wing spring pin;

[0041] Fig.10 It is a schematic diagram of the internal structure of the rear wing and the vertical tail structure installation section in the unfolded state of the present invention;

[0042] Fig.11 It is a partial exploded schematic diagram of the rear wing structure of the present invention in the unfolded state;

[0043] Fig.12 It is a structural exploded diagram of the rear wing deployment locking structure in the deployed state of the present invention;

[0044] Fig.13 It is a detailed feature diagram of the left rear wing turntable;

[0045] Fig.14 It is a schematic diagram of the detailed features of the right rear wing turntable;

[0046] Fig.15 It is a three-dimensional schematic diagram of an assembly of a vertical tail structure, a rear wing and a vertical tail structure mounting section and a rear wing deployment locking structure in an unfolded state of the present invention;

[0047] Fig.16 It is a structural explosion diagram of the left vertical tail locking structure in the deployed state of the present invention;

[0048] Fig.17 It is a schematic diagram of the detailed features of the left vertical tail rotating end;

[0049] Fig.18 It is a schematic diagram of the detailed features of the left vertical tail fixed end;

[0050] Fig.19 It is a structural explosion diagram of the right vertical tail locking structure in the deployed state of the present invention;

[0051] Fig. 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. First fixing piece of front wing rotation axis; 123. First fixing nut of front wing rotation axis; 124. Second fixing nut of front wing rotation axis; 125. Second fixing piece of front wing rotation axis; 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. First fixing piece of rear wing rotation axis; 163. Carbon fiber plate for fixing the right vertical tail; 164. Carbon fiber plate for fixing the left vertical tail Fiberboard; 165, rib plate installed on the tail side of the rear wing mechanism; 166, first bearing seat of the rear wing rotation axis; 167, second fixing piece of the rear wing rotation axis; 168, second bearing seat of the rear wing rotation axis; 17, power system installation section; 2, front wing structure; 21, left front wing structure; 22, carbon fiber tube of the left front wing; 23, front wing deployment locking structure; 231A, first retaining spring of the front wing rotation axis; 231B, second retaining spring of the front wing rotation axis; 232A, first flange bearing of the front wing rotation axis; 232B, second flange bearing of the front wing rotation axis; 233, left front wing turntable; 2331, front wing spring pin slide groove; 2332, front wing spring pin hole; 2333, first fixing hole of the front wing torsion spring; 2334, first placement slot for torsion spring of front wing; 2335, connecting hole of left front wing; 2336, fixing hole of left front wing; 234, rotating shaft of front wing; 235, spring pin of front wing; 2351, pin; 2352, pin spring; 2353, outer cylinder; 236, plane bearing of front wing; 237, torsion spring of front wing; 238, turntable of right front wing; 2381, connecting hole of right front wing; 2382, fixing hole of right front wing; 2383, mounting hole for spring pin of front wing; 2384, second placement slot for torsion spring of front wing; 2385, second fixing hole for torsion spring of front wing; 24, carbon fiber tube of right front wing; 25, structure of right front wing; 3, structure of rear wing; 31, structure of left rear wing; 32, carbon fiber of left rear wing 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 column pin mounting hole; 3332, top screw hole; 3333, rear wing torsion spring first fixing hole; 3334, rear wing torsion spring first placement slot; 3335, left rear wing connecting hole; 3336, left rear wing fixing hole; 334, top screw; 335, rear wing rotating shaft; 336, rear wing spring column 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 slide 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. First mounting hole of left vertical tail torsion spring; 4512. First placement slot of left vertical tail torsion spring; 4513. Pin hole of left vertical tail rotating end; 4514. Pin hole of left vertical tail spring column; 4515. Slot of left vertical tail spring column pin; 4516. Mounting hole of left vertical tail wing; 452A. First retaining spring of left vertical tail; 452B. Second retaining spring of left vertical tail; 453A. First flange bearing of left vertical tail; 453B. Second flange bearing of left vertical tail ; 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 be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work 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 cruise missile with redundant locking and a structure to prevent wing surface expansion interference, including

[0056] Body 1;

[0057] A front wing structure 2 is arranged on the fuselage 1, and is located on the 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, and 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 is arranged on the fuselage 1 and is 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 the rear wing deployment locking structure 33 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 the vertical tail deployment locking structure is used to lock the vertical tail structure 4 when it is deployed;

[0063] The associated structure is arranged between the rear wing deployment locking structure 33 and the vertical tail deployment locking structure. The associated structure is used to make the deployment action of the vertical tail structure 4 be located after the rear wing structure 3 is deployed in place, so as to prevent 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 rear end of the fuselage 1 .

[0065] The front wing structure 2 is arranged on the upper side of the fuselage 1 near the nose, and the rear wing structure 3 is arranged on the lower side of the fuselage 1 near the tail. This arrangement can increase the vertical distance between the front and rear wings, and can reduce the impact of the front wing airflow on the aerodynamic performance of the tail wing to a certain extent. It can also improve the control effect of the rudder of the rear wing structure 3. At the same time, the vertical position of the center of gravity of the whole machine can be designed between the front and rear wings to improve the stability of the whole machine. The vertical tail structure 4 is arranged on the left and right sides of the fuselage 1, and the installation position is close to the rear wing structure 3. This arrangement can effectively reduce the size of the whole machine and increase the space utilization of the whole machine. The power system 5 is arranged at the rear of the fuselage to provide power for the cruise missile. The airborne equipment 6 includes multiple electronic equipment, which are fixed to the inside of the fuselage 1 by cable ties, adhesive connections and threaded connections. When the cruise missile is in the folded state, the two ends of the front wing structure 2 rotate toward the tail direction and fold on the upper side of the fuselage 1, the two ends of the rear wing structure 3 rotate toward the nose direction and fold on the lower side of the fuselage 1, and the vertical tail structure 4 rotates toward the nose direction 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, which can avoid mutual interference between the deployment of the tail and the front wing, and reduce the unstable aerodynamic effect of the tail when the cruise missile is launched.

[0066] Furthermore, the fuselage 1 includes a load section 11, a front wing structure installation section 12, a function extension section 13, an airborne equipment section 14, an energy system section 15, a rear wing and vertical tail structure installation section 16, and a power system installation section 17 from the head to the tail. The load section 11 is used to load the warhead and the optoelectronic pod, the function extension section 13 is used to load the parachute or other functional equipment according to the requirements, the airborne equipment section 14 is provided with a mounting plate inside for installing the flight control, the energy system section 15 is provided with a battery inside, and the structure of the power system installation section 17 is used to install the fixed power system 5.

[0067] The front wing structure installation section 12 includes a front wing structure nose side installation 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 installation 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 installation rib 121 and a front wing structure tail side installation rib 127. The rib plate 126 is installed, and other parts are fixed by relying on the front wing structure nose side mounting rib plate 121 and the front wing structure tail side mounting rib plate 126, wherein the front wing rotation axis first fixing member 122 is fixed on the front wing structure nose side mounting rib plate 121 by bolts, and the front wing rotation axis second fixing member 125 is fixed between the front wing structure nose side mounting rib plate 121 and the front wing structure tail side mounting rib plate 126 by screws in cooperation with the universal connecting member 128. The front wing rotation axis first fixing member 122 and the front wing rotation axis second fixing member 125 clamp the two ends of the front wing rotation axis 234 respectively through the front wing rotation axis first fixing nut 123 and the front wing rotation axis second fixing nut 124, restricting the movement of the front wing rotation axis 234, and realizing the connection and fixation 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, a front wing deployment locking portion is arranged 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 inserted into the retaining spring groove at the upper end of the front wing rotating shaft 234, 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 inserted 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, a front wing spring pin slide slot 2331 and a front wing torsion spring first placement slot 2334 are provided on the left front wing turntable 233, the front wing torsion spring first placement slot 2334 is coaxially arranged on the inner side of the front wing spring pin slide slot 2331, a front wing spring pin pin hole 2332 is provided at one end of the front wing spring pin slide slot 2331, a front wing torsion spring first fixing hole 2333 is provided inside the front wing torsion spring first placement slot 2334, and a left front wing connecting hole 2335 for installing the front wing structure 2 is also provided on the left front wing turntable 233;

[0071] A second placement slot 2384 for the front wing torsion spring is provided on the right front wing turntable 238, a second fixing hole 2385 for the front wing torsion spring is provided in the second placement slot 2384 for the front wing torsion spring, a front wing spring pin mounting hole 2383 is provided on the outer side of the second placement slot 2384 for the front wing torsion spring, and a right front wing connecting hole 2381 for mounting the front wing structure 2 is also provided on the right front wing turntable 238.

[0072] A further optimized solution is provided, in which 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 slide groove 2331, the front wing torsion spring 237 is sleeved in 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.

[0073] The front wing structure 2 includes: a left front wing structure 21, a left front wing carbon fiber tube 22, a front wing deployment locking structure 23, a right front wing carbon fiber tube 24 and a right front wing structure 25. The left front wing carbon fiber tube 22 penetrates the left front wing structure 21 and is relatively fixed by gluing, the right front wing carbon fiber tube 24 penetrates the right front wing structure 25 and is relatively fixed by gluing, and the front wing deployment locking structure 23 is connected to the right front wing structure 25 and the left front wing structure 21 through the right front wing carbon fiber tube 24 and the left front wing carbon fiber tube 22, respectively, and plays a role in controlling the automatic deployment and locking of the front wing structure 2.

[0074] The left front wing carbon fiber tube 22 is inserted into the left front wing connection hole 2335, and screws are inserted from the left front wing fixing hole 2336 to fix it. The right front wing carbon fiber tube 24 is inserted into the right front wing connection hole 2381, and screws are inserted from the right front wing fixing hole 2382 to fix it. The left front wing turntable 233 and the right front wing turntable 238 are installed on the front wing rotation shaft 234, and are directly in 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 projection centers 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 have 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 inserted 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 inserted into the retaining spring groove at the lower end of the front wing rotating shaft 234, thereby 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, since 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 is at an angle of 10°, the spring feet at both ends of the front wing torsion spring 237 need to rotate 190° in the opposite direction under the action of external force in order to fold the right front wing structure 25 and the left front wing structure 21 on the upper side of the fuselage 1 respectively, and the launch tube constrains them to maintain the folded state. When the cruise missile is launched out of the tube, the external force constraint is cancelled, and the front wing torsion spring 237 tends to restore the initial state, and the restoring force is applied to the left front wing turntable 233 and the right front wing turntable 238 through the spring feet at both ends, driving the front wing deployment locking 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° 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, when the pin 2351 is aligned with the front wing spring pin hole 2332, the pin 2351 does not pop out as planned, then the rib plate 121 needs to be installed on the nose side of the front wing structure to lock the position of the front wing structure 2. Since there is an angle of 10° 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 unfolded, 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, at this time, 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 unfolding and locking state.

[0077] The front wing spring pin 235 locking is the preferred locking solution for the front wing structure 2. When the pin spring 2352 fails, the locking is achieved by using the front wing structure nose side mounting rib 121 as an alternative solution. In the alternative solution, the leading edge of the airfoil of the left front wing turntable 233 and the right front wing turntable 238 directly hits 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 multiple uses of the alternative solution may affect the structure of the entire aircraft. Therefore, it is necessary to design the front wing spring pin 235 locking preferred solution, and the alternative solution provides a redundant locking structure, which can ensure the smooth deployment and locking of the front wing structure 2 when the preferred solution fails.

[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 portion 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, 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] Further optimized solution, a first placement groove 3334 of the rear wing torsion spring is provided on the left rear wing turntable 333, a first fixing hole 3333 of the rear wing torsion spring is provided in the first placement groove 3334 of the rear wing torsion spring, a rear wing spring column pin mounting hole 3331 is provided outside the first placement groove 3334 of the rear wing torsion spring, and a left rear wing connecting hole 3335 for mounting the rear wing structure 3 is also provided on the left rear wing turntable 333;

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

[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] A further optimized solution is provided, in which the rear wing deployment 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 slide groove 3393, the rear wing torsion spring 338 is sleeved in the middle part of the outer side of the rear wing rotation shaft 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, 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, and other components are fixed by relying on these two ribs, wherein the rear wing rotation axis second fixing member 167 is fixed to the rear wing mechanism tail side mounting rib 165 by bolts, and the rear wing rotation axis first fixing member 162 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 side 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 side of 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 includes: 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 penetrates the left rear wing structure 31 and is relatively fixed by gluing, the right rear wing carbon fiber tube 34 penetrates the right rear wing structure 35 and is relatively fixed by gluing, and the rear wing deployment locking structure 33 connects the right rear wing structure 35 and the left rear wing structure 31, and plays a role in controlling 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 screws are inserted from the left rear wing fixing hole 3336 to fix it; the right rear wing carbon fiber tube 34 is inserted into the right rear wing connecting hole 3392, and screws are inserted from the right rear wing fixing hole 3391 to fix it. 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 plane 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, and the rear wing torsion spring 338 is placed as a whole on the first placing hole 3395 of the rear wing torsion spring The rear wing torsion spring 338 is restricted in the placement groove 3334 and the second placement groove 3396 of the rear wing torsion spring, thereby limiting the overall position of the rear wing torsion spring 338; the rear wing spring pin 336 is screwed into the rear wing spring pin mounting hole 3331 for fixation, and the pin at the head of the rear wing spring pin 336 can slide in the rear wing spring pin slide groove 3393; the first rear wing retaining spring 332A is inserted into the retaining groove located 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 with the right rear wing turntable 339, and the second rear wing retaining spring 332B 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 rotation shaft 335; the rotating sleeve 331 is located on the upper side of the left rear wing turntable 333, and is relatively fixed to the rear wing rotation shaft 335 through bolt connection and rotates together.

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

[0087] When the cruise missile is deployed, since the center of the circle projected in the aperture direction by the first fixing hole 3333 of the rear wing torsion spring and the second fixing hole 3395 of the rear wing torsion spring is centered on the rear wing rotation axis 335, there is a 10° angle, and the spring feet at both ends of the rear wing torsion spring 338 need to rotate 190° in the opposite direction under the action of external force in order to fold the right rear wing structure 35 and the left rear wing structure 31 on the lower side of the fuselage 1 respectively, and the launch tube constrains them to maintain the folded state. When the cruise missile is launched out of the tube, the external force constraint is cancelled, and the rear wing torsion spring 338 tends to restore the initial state, and the restoring force is applied to the left rear wing turntable 333 and the right rear wing turntable 339 through the spring feet at both ends, driving the rear wing deployment locking structure 33 from the folded state to the deployed state. During the transformation process, the rear wing spring pin 336 is restricted by the rear wing spring pin slide slot 3393 and slides in the slot. When the right rear wing structure 35 and the left rear wing structure 31 are rotated 90° around the axis of the initial position of the rear wing rotation axis 335 in the folded state, the rear wing spring pin 336 is aligned with the rear wing spring pin pin hole 3394, and the pin of the rear wing spring pin 336 pops out, locking the relative positions of the left rear wing turntable 333 and the right rear wing turntable 339. At this time, the unfolding process of the rear wing structure 3 stops. If the rear wing spring pin 336 fails and the pin does not pop out as planned, it is necessary to install the rib plate 165 on the tail side of the rear wing mechanism to lock the position of the rear wing structure 3. Since there is an angle of 10° 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 unfolded, 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 unfolding and locking state.

[0088] The locking of the rear wing spring pin 336 is the preferred locking scheme for the rear wing structure 3. When the rear wing spring pin 336 fails, the locking is achieved by using the rib plate 165 installed on the tail side of the rear wing mechanism. In the alternative scheme, the left rear wing turntable 333 and the right rear wing turntable 339 close to the rear wing rotation axis 335 directly hit the side of the rib plate 165 installed on the tail side of the rear wing mechanism. If the cruise missile is used for training or needs to be recovered for multiple uses, the multiple uses of the alternative scheme may affect the structure of the entire machine. Therefore, it is necessary to design the preferred locking scheme of the rear wing spring pin 336, and the alternative scheme provides a redundant locking structure, which can ensure the smooth deployment and locking of the front wing structure 2 when the preferred scheme fails.

[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 of the fuselage 1 and the vertical tail structure mounting section 16;

[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 a right vertical tail rotating end 466; the other end of the right vertical tail rotating shaft 463 is fixedly connected to a 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 arranged in the right vertical tail rotation end 466, and the other end is arranged in the right vertical tail fixed end 462. One end of the right vertical tail spring pin 469 is threadedly connected with the right vertical tail fixed end 462, and the other end of the right vertical tail spring pin 469 is movably arranged 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 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.

[0096] A further optimized solution is that the associated structure includes a rotating sleeve 331, which is fixedly mounted on one end of the rear wing rotating shaft 335, and two ears of the rotating sleeve 331 are respectively fixedly connected with 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, and 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 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 clip spring 452A of the tail and the second clip spring 452B of the left vertical tail are respectively inserted into the slots on the left vertical tail rotation shaft 456 to limit the axial movement of the mounting structure on the left vertical tail rotation shaft 456; the outer surface of the left vertical tail spring pin 459 is processed with threads 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 rotation end pin hole 4513 and the left vertical tail fixed end pin hole 4571 to limit the rotation and deployment of the left vertical tail locking structure 45, and the rear end of the left vertical tail limit pin 458 is connected with a nylon rope, and the other end of the nylon rope 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 by a nut, and the left vertical tail fixed end 457 is connected and fixed to the left vertical tail fixed carbon fiber plate 164 by bolts to complete the relative fixation between the vertical tail structure 4 and the rear wing and vertical tail structure mounting section 16.

[0100] The principle of the left vertical tail locking structure 45 to lock the deployment and prevent the interference with the front wing structure 2 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 exists at an angle of 10°, the spring feet at both ends of the left vertical tail torsion spring 455 need to rotate 100° in opposite directions due to the external force in order for the left vertical tail wing structure 41 to be folded on 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 out of the tube and the rear wing structure 3 is unfolded, 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 slot 4515 and slides in the slot. 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 principle of the right vertical tail locking structure 46 to lock and prevent interference with the front wing structure 2 is the same as that of the left vertical tail locking structure 45. The right vertical tail locking structure 46 and the left vertical tail locking structure 45 can ensure that the vertical tail structure 4 is released from the folding constraint and unfolded only after the rear wing structure 3 is fully unfolded, which can avoid the interference of the vertical tail structure 4 on the unfolding of the front wing structure 2 when the vertical tail structure 4 is unfolded upward, and can well improve the success rate of the unfolding of all wing surfaces of the cruise missile. At the same time, the delayed unfolding of the vertical tail structure 4 can also reduce the unstable aerodynamic effects on the cruise missile when it transitions from the launch state to the normal climbing state.

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

[0104] The embodiments described above are only descriptions of the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should fall within the protection scope of the present invention.

Claims

1. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure, characterized in that: include Body (1); A front wing structure (2) is arranged on the fuselage (1), and 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 arranged 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) is arranged on the fuselage (1), and when the rear wing structure (3) is in a folded state, it is located at the bottom of the fuselage (1); A rear wing deployment locking structure (33) is arranged 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, arranged on the vertical tail structure (4), the vertical tail deployment locking structure being used to lock the vertical tail structure (4) when it is deployed; A correlation structure is arranged between the rear wing deployment locking structure (33) and the vertical tail deployment locking structure, and the correlation structure is used to make the deployment action of the vertical tail structure (4) be located after the rear wing structure (3) is deployed in place, so as to prevent 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 rear end of the fuselage (1).

2. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 1, characterized in that: 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). The front wing rotating disc (238) is provided with a front wing rotating disc (238), the left front wing rotating disc (233) and the right front wing rotating disc (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 unfolding locking portion is provided between the left front wing rotating disc (233) and the right front wing rotating disc (238), and the front wing structure (2) is detachably mounted on the left front wing rotating disc (233) and the right front wing rotating disc (238).

3. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 2, characterized in that: The left front wing turntable (233) is provided with a front wing spring pin slide groove (2331) and a first placement groove (2334) for a front wing torsion spring. The first placement groove (2334) for a front wing torsion spring 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 fixing hole (2333) for a front wing torsion spring is provided inside the first placement groove (2334). The left front wing turntable (233) is also provided with a left front wing connection hole (2335) for mounting the front wing structure (2). The right front wing turntable (238) is provided with a second placement groove (2384) for the front wing torsion spring, a second fixing hole (2385) for the front wing torsion spring is provided in the second placement groove (2384) for the front wing torsion spring, a front wing spring column pin mounting hole (2383) is provided outside the second placement groove (2384) for the front wing torsion spring, and the right front wing turntable (238) is also provided with a right front wing connecting hole (2381) for mounting the front wing structure (2).

4. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 3, characterized in that: The front wing unfolding locking part comprises 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 in 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; 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.

5. A folding cruise 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) comprises a rear wing rotation shaft (335), the rear wing rotation shaft (335) 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 unfolding 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).

6. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 5, characterized in that: The left rear wing turntable (333) is provided with a first placement groove (3334) for a rear wing torsion spring, a first fixing hole (3333) for a rear wing torsion spring is provided in the first placement groove (3334) for the rear wing torsion spring, a rear wing spring column pin mounting hole (3331) is provided outside the first placement groove (3334) for the rear wing torsion spring, and the left rear wing turntable (333) is also 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); a through hole rear wing spring pin hole (3394) is provided at one end of the rear wing spring pin slide groove (3393); a rear wing torsion spring second fixing hole (3395) is provided inside the rear wing torsion spring second placement groove (3396); and the right rear wing turntable (339) is also provided with a right rear wing connecting hole (3392) for mounting the rear wing structure (3).

7. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 6, characterized in that: The rear wing unfolding locking part comprises 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 in the middle part of the outer side of the rear wing rotating shaft (335); one end of the rear wing torsion spring (338) is arranged in the first fixing hole (3333) of the rear wing torsion spring; the other end is arranged 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.

8. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 7, characterized in that: The vertical tail deployment locking structure comprises a left vertical tail locking structure (45) and a right vertical tail locking structure (46), both of which are detachable and mountable on the rear wing and vertical tail structure mounting section (16) of the fuselage (1); The left vertical tail locking structure (45) comprises a left vertical tail rotating shaft (456), the left vertical tail rotating shaft (456) is detachably mounted on the rear wing and the 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 arranged 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).

9. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 8, characterized in that: The left vertical tail deployment locking part comprises 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 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).

10. A folding cruise missile with redundant locking and anti-wing surface deployment interference structure according to claim 9, characterized in that: The associated structure comprises a rotating sleeve (331), wherein the rotating sleeve (331) is fixedly sleeved on one end of the rear wing rotating shaft (335), and one end of a nylon line is fixedly connected to two support ears of the rotating sleeve (331), the other end of one of the nylon lines 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).

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