A rocket-boosted aircraft with penetration function

Abstract

The application provides a rocket-assisted aircraft with penetration function, which comprises a rocket propelling device (1) and an aircraft body (2), the rocket propelling device (1) is provided with a rocket engine, the speed of the aircraft is increased before the aircraft penetrates a defense layer, and the rocket propelling device (1) is separated from the aircraft body (2) after the aircraft penetrates the defense layer. The rocket-assisted aircraft with penetration function can achieve the purpose of penetrating a specific area.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of aircraft, in particular to a rocket-boosted aircraft with penetration function, belong to unmanned aerial vehicle field. BACKGROUND

[0002] In some areas, with defense layer, will form interception or block to aircraft, so that traditional aircraft cannot approach the area.

[0003] To effectively approach target area, aircraft needs to break through defense layer, how to break through defense, become the key factor whether aircraft can normally investigate. SUMMARY

[0004] In order to solve the above problems, the present application has been keenly researched, by boosting rapid speed of aircraft before entering defense layer, actively decelerate to normal working speed of aircraft after passing through defense layer, so as to complete the present application.

[0005] The present application aims to provide the following aspects:

[0006] In one aspect, the present application provides a rocket-boosted aircraft with penetration function, comprising rocket propulsion device 1 and aircraft body 2.

[0007] Rocket propulsion device 1 has rocket engine, which increases the speed of aircraft before passing through the inner edge of defense layer.

[0008] Mechanical separation device 12 is provided on rocket propulsion device 1, so that rocket propulsion device 1 can be separated from aircraft body 2 after passing through the inner edge of defense layer.

[0009] The mechanical separation device 12 and the aircraft body 2 are connected by the first explosive bolt 121,

[0010] A direction-changing device is provided on the rocket propulsion device 1, so that the rocket propulsion device 1 can quickly change direction after being separated from the aircraft body 2.

[0011] A direction-changing plate 13 is provided at the lower end of the rocket propulsion device 1, which is retracted inside the rocket propulsion device 1 before the rocket propulsion device 1 is separated from the aircraft body 2, and extends out of the rocket propulsion device 1 after the rocket propulsion device 1 is separated from the aircraft body 2.

[0012] A slot 14 is provided on the mechanical separation device 12, a tail end protrusion 21 corresponding to the slot 14 is provided at the tail of the aircraft body 2, and a separation acceleration plate 15 is provided in the slot 14, which is connected to the mechanical separation device 12 by a strong spring 16,

[0013] In the tail of the rocket propulsion device 1, a rocket propulsion tail wing 11 is arranged, which plays a role in maintaining the balance of the aircraft and steering before the aircraft passes through the defense layer.

[0014] A wing 22 is arranged on the aircraft body 2, and the wing 22 is arranged with a wing unfolding unit 23, so that the wing 22 is retracted inside the shell of the aircraft body 2 before the aircraft passes through the defense layer, and is extended outside the shell of the aircraft body 2 after passing through the defense layer.

[0015] Preferably, the wing unfolding unit 23 has a slide rod 231, a slide block 232, and a wing opening spring 233 sleeved on the slide rod 231, the slide rod 231 is fixed inside the aircraft body 2 in parallel with the aircraft body 2,

[0016] The slide block 232 is sleeved on the slide rod 231 and can slide forward and backward along the slide rod 231,

[0017] One end of the wing opening spring 233 is fixed to the front end of the slide rod 231, and the other end is fixed to the slide block 232,

[0018] Preferably, one side of the tail of the wing 22 is connected to the shell of the aircraft body 2 through a pin, and the wing 22 can rotate around the pin, and the other side of the tail of the wing 22 is connected to the slide block 232, when the slide block 232 slides forward, the slide block 232 drives the wing 22 to rotate and rotate out of the shell of the aircraft body 2.

[0019] On the other hand, the present application provides a method for a rocket-assisted aircraft with penetration function to break through the defense layer of a target area, comprising the following steps:

[0020] S1. Determine the outer edge position and inner edge position of the defense layer of the target area, and set them in the aircraft.

[0021] S2. When the aircraft is 10km away from the outer edge position of the defense layer of the target area to be broken through, the rocket engine in the rocket propulsion device 1 starts to work, increases the speed of the aircraft, so that the aircraft can pass through the defense layer at a speed higher than 2000km / h, and avoid being intercepted by the target area to be broken through.

[0022] S3. After the aircraft reaches the inner edge position of the defense layer of the target area to be broken through, the rocket engine stops working, and the rocket propulsion device 1 is separated from the aircraft body 2.

[0023] S4. The wing 22 is ejected from the aircraft body 2 to slow down and slow down the rotation of the aircraft body 2.

[0024] According to the rocket-assisted aircraft with penetration function provided by the present application, the following beneficial effects are obtained:

[0025] (1) Can break through the target area defense layer;

[0026] (2) Can realize the separation of the propulsion device and the aircraft body, increase the flexibility of the aircraft;

[0027] (3) The aircraft body has a retractable pop-up wing 22, which reduces the influence of air resistance in high-speed flight stage. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 The overall structure schematic diagram of the rocket-assisted aircraft with penetration function in a preferred embodiment is shown;

[0029] Figure 2 The schematic diagram of the connection structure of the rocket propulsion device and the aircraft body in a preferred embodiment is shown;

[0030] Figure 3 The schematic diagram of the connection structure of the rocket propulsion device and the aircraft body in a preferred embodiment is shown;

[0031] Figure 4 The schematic diagram of the rocket propulsion device in a preferred embodiment is shown;

[0032] Figure 5 The schematic diagram of the rocket propulsion device structure in a preferred embodiment is shown;

[0033] Figure 6 The schematic diagram of the wing and wing expansion unit structure in a preferred embodiment is shown;

[0034] Figure 7 The schematic diagram of the wing and wing expansion unit structure in a preferred embodiment is shown;

[0035] Figure 8 The schematic diagram of the limiting mechanism structure in a preferred embodiment is shown;

[0036] Figure 9 The schematic diagram of the limiting mechanism structure in a preferred embodiment is shown;

[0037] Figure 10 The schematic diagram of the limiting mechanism structure in a preferred embodiment is shown;

[0038] Figure 11 The schematic diagram of the limiting mechanism structure in a preferred embodiment is shown;

[0039] Figure 12 The schematic diagram of the limiting mechanism structure in a preferred embodiment is shown;

[0040] Figure 13 The schematic diagram of the aircraft body tail structure in a preferred embodiment is shown.

[0041] REFERENCE NUMBERS

[0042] 1 - rocket propelling device

[0043] 11 - rocket propelling tail wing

[0044] 12 - mechanical separation device

[0045] 121 - first explosive bolt

[0046] 13 - deflection plate

[0047] 131 - deflection release groove

[0048] 132 - deflection auxiliary spring

[0049] 14 - slot body

[0050] 15 - separation accelerating plate

[0051] 16 - strong spring

[0052] 17 - starting rod

[0053] 2 - aircraft body

[0054] 21 - tail end protrusion

[0055] 211 - second explosive bolt

[0056] 22 - wing

[0057] 23 - wing unfolding unit

[0058] 231 - sliding rod

[0059] 232 - sliding block

[0060] 2321 - sliding groove

[0061] 233 - wing opening spring

[0062] 24 - limiting mechanism

[0063] 241 - first limiting member

[0064] 2411 - straight rod segment

[0065] 2412 - protrusion segment

[0066] 2413 - first limiting spring

[0067] 242 - second limiting member

[0068] 2423 - second limiting spring

[0069] 243 - third limiting rod

[0070] 25-Small tail wing Detailed Implementation

[0071] The features and advantages of the present invention will become clearer and more apparent from the following detailed description.

[0072] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.

[0073] In this invention, unless otherwise specified, "front" refers to the direction of the aircraft's head and "back" refers to the direction of the aircraft's tail.

[0074] On the one hand, the present invention provides a rocket-boosted aircraft with penetration capability.

[0075] The rocket-boosted aircraft with penetration capability, such as Figure 1 As shown, it includes a rocket propulsion device 1 and a spacecraft body 2.

[0076] The rocket propulsion device 1 can propel the main body 2 of the aircraft before it reaches the outer edge of the defense layer of the area to be breached and during the process of passing through the defense layer, so that the main body 2 of the aircraft can obtain a higher speed and thus successfully pass through the defense layer.

[0077] Furthermore, the rocket propulsion device 1 has a rocket engine to provide power during the flight of the aircraft through the defense layer. At the tail of the rocket propulsion device 1, a rocket propulsion tail fin 11 is provided. The rocket propulsion tail fin 11 plays a role in maintaining the balance and turning of the aircraft before the aircraft passes through the inner edge of the defense layer.

[0078] After the spacecraft passes through the inner edge of the defense layer, the rocket engine stops working, and the rocket propulsion device 1 detaches from the main body 2 of the spacecraft to reduce the weight of the main body 2 and improve its endurance.

[0079] Furthermore, a mechanical separation device 12 is provided at the front end of the rocket propulsion device 1. The mechanical separation device 12 is connected to the main body 2 of the aircraft. After the aircraft passes through the inner edge of the defense layer, the mechanical separation device 12 can separate from the main body 2 of the aircraft, thereby allowing the rocket propulsion device 1 to detach from the aircraft.

[0080] In a preferred embodiment, the mechanical separation device 12 is annular, with an outer diameter smaller than that of the rocket propulsion device 1 and larger than that of the aircraft body 2, so that the rocket propulsion device 1 experiences less wind resistance during flight.

[0081] In a preferred embodiment, the mechanical separation device 12 is connected to the aircraft body 2 by a first explosive bolt 121, as shown in Figure 2 When the aircraft passes through the defense layer, the first explosive bolt 121 explodes, causing the rocket propulsion device 1 to separate from the aircraft body 2.

[0082] According to the present application, on the rocket propulsion device 1, a turning device is also provided, so that after the rocket propulsion device 1 separates from the aircraft body 2, the rocket propulsion device 1 can quickly turn to avoid the rocket propulsion device 1 after separation colliding with the aircraft body 2, thereby affecting the flight state of the aircraft body 2,

[0083] In a preferred embodiment, at the tail end of the rocket propulsion device 1, a turning plate 13 is provided, as shown in Figure 4 Before the rocket propulsion device 1 separates from the aircraft body 2, the turning plate 13 is retracted inside the rocket propulsion device 1, and after the rocket propulsion device 1 separates from the aircraft body 2, the turning plate 13 extends from the rocket propulsion device 1,

[0084] When the turning plate 13 extends out of the rocket propulsion device 1, the turning plate 13 is subjected to air resistance, which acts on the rocket propulsion device 1 through the turning plate 13, adding additional force to the rocket propulsion device 1, causing its movement direction to be deflected,

[0085] More preferably, the turning plate 13 is located at the tail of the rocket propulsion device 1, so that the force generated by air resistance has a large moment, thereby achieving the turning function faster,

[0086] In a more preferred embodiment, the turning plate 13 is located at the bottom of the rocket propulsion device 1, so that the rocket propulsion device 1 deflects downward, thereby quickly landing.

[0087] In a preferred embodiment, the turning plate 13 is a plate structure with a circular arc cross-section, as shown in Figure 5 So that it is subjected to greater wind resistance, thereby accelerating the turning speed of the rocket propulsion device 1.

[0088] In a preferred embodiment, a slot 14 is provided on the mechanical separation device 12, as shown in Figure 3 , Figure 4 A tail end protrusion 21 corresponding to the slot 14 is provided at the corresponding position at the tail of the aircraft body 2, and a separation acceleration plate 15 is provided in the slot 14, which is connected to the mechanical separation device 12 by a strong spring 16. The separation acceleration plate 15 is a flat plate structure, preferably with the same structure as the cross-section of the slot 14.

[0089] A direction-changing starting rod 17 is arranged on the separation accelerating plate 15, as shown in the figure. Figure 4 A direction-changing plate 13 is arranged at the bottom of the rocket propelling device 1, one end of the direction-changing plate 13 is rotatably fixed inside the rocket propelling device 1, and the other end has a direction-changing releasing groove 131, one end of the direction-changing starting rod 17 is fixed on the separation accelerating plate 15, and the other end is inserted into the direction-changing releasing groove 131 to lock the direction-changing plate 13.

[0090] When the mechanical separation device 12 is not separated from the aircraft body 2, the tail end protrusion 21 is tightly attached to the separation accelerating plate 15 and compresses the strong spring 16, and when the mechanical separation device 12 is separated from the aircraft body 2, the strong spring 16 releases the elasticity, so that the mechanical separation device 12 and the aircraft body 2 are quickly separated,

[0091] With the release of the elastic force of the strong spring 16, the separation accelerating plate 15 moves towards the head of the rocket propelling device 1, driving the direction-changing starting rod 17 to move towards the head, so that the direction-changing starting rod 17 slides out of the direction-changing releasing groove 131, releasing the lock of the direction-changing plate 13, and the direction-changing plate 13 is stretched out from the inside of the rocket propelling device 1 under the action of gravity, thereby playing a role of changing direction.

[0092] In a more preferred embodiment, a direction-changing auxiliary spring 132 is further arranged above the direction-changing plate 13, and the direction-changing auxiliary spring 132 is arranged at the connecting end of the direction-changing plate 13 and the starting rod 17, which can pop the direction-changing plate 13 out of the inside of the rocket propelling device 1 after the direction-changing starting rod 17 slides out of the direction-changing releasing groove 131, so as to avoid the direction-changing plate 13 from being unable to stretch out.

[0093] After the aircraft passes through the inner edge of the defense layer, the rocket propelling device 1 is separated from the aircraft body 2, and the flight speed of the aircraft body 2 is relatively high, much higher than its normal working speed, and preferably, a speed reducing device is further arranged on the aircraft body 2 to reduce the speed of the aircraft body 2, so that it can perform reconnaissance and other work.

[0094] Further, the speed reducing device is preferably a spring wing 22, which can not only reduce the speed of the aircraft body 2, but also has the effect of reducing the rotation.

[0095] The spring wing 22 is a plate or sheet structure, which can stabilize the flight direction of the aircraft.

[0096] Further, a spring wing unfolding unit 23 is arranged on the aircraft body 2, so that the spring wing 22 is retracted inside the shell of the aircraft body 2 before the aircraft passes through the defense layer, and is stretched out outside the shell of the aircraft body 2 after passing through the defense layer,

[0097] In a preferred embodiment, the spring wing unfolding unit 23 is arranged inside the aircraft body 2 and connected with the spring wing 22, as shown in the figure. Figure 6、 Figure 7 As shown,

[0098] The tail side of the wing 22 is hinged to the shell of the aircraft body 2, preferably through a pin, so that the wing 22 can rotate around the pin to rotate from the inside to the outside of the aircraft body 2 until the desired deployment position, and for this purpose, a slot is formed in the shell of the aircraft body 2 near the wing 22, the width of the slot is slightly larger than the thickness of the wing 22, and the length of the slot is slightly larger than the length of the wing 22, so that the wing 22 can be smoothly rotated out of the shell of the aircraft body 2.

[0099] The wing deployment unit 23 has a slide rod 231, a slide block 232, and a wing opening spring 233 sleeved on the slide rod 231, the slide rod 231 is fixed inside the aircraft body 2 parallel to the aircraft body 2,

[0100] The slide block 232 is connected to the other side of the tail of the wing 22, and when the slide block 232 slides forward, the slide block 232 drives the wing 22 to rotate and rotate out of the shell of the aircraft body 2.

[0101] In a preferred embodiment, a sliding groove 2321 is provided on the slide block 232, the length direction of the sliding groove 2321 points to the pin connecting the wing 22 and the aircraft body 2, a short pin is provided at the tail of the wing 22, the short pin is embedded in the sliding groove 2321 and can reciprocate in the sliding groove 2321 with the up and down movement of the slide block 232, thereby realizing the rotation of the wing 22 out of the shell of the aircraft body 2.

[0102] The slide block 232 is sleeved on the slide rod 231 and can slide forward and backward along the slide rod 231,

[0103] One end of the wing opening spring 233 is fixed to the front end of the slide rod 231, and the other end is fixed to the slide block 232, and through the rebound of the wing opening spring 233, the slide block 232 can be driven to slide forward along the slide rod 231, and in turn drive the wing 22 to rotate out of the shell of the aircraft body 2.

[0104] In a preferred embodiment, the spring linear zone of the wing opening spring 233 is not less than 100mm, and the linear zone tension is not less than 20N.

[0105] Further, a limiting mechanism 24 is further provided on the wing deployment unit 23, such as Figures 8-11 As shown, the limiting mechanism 24 is located in the slide rod 231, and from front to back includes a first limiting piece 241, a second limiting piece 242, and a third limiting rod 243,

[0106] The first limiting member 241 is used to fix the wing 22 by limiting the sliding block 232 after the wing 22 is unfolded, so as to prevent the wing 22 from rebounding into the aircraft body 2.

[0107] The first limiting member 241 has a straight rod section 2411 and a protruding section 2412. The straight rod section 2411 is rod-shaped, one end of the straight rod section 2411 is fixed in the sliding rod 231 by a pin, and the other end is connected with the protruding section 2412, so that the protruding section 2412 can rotate along the pin. Further, the protruding section 2412 is a plate-shaped structure, has a right-angle edge, so that the protruding section 2412 can limit the sliding block 232 to slide towards the tail of the missile body. The side of the protruding section 2412 close to the tail has an inclined surface, so that the sliding block 232 can slide from the tail end of the protruding section 2412 to the front end of the protruding section 2412.

[0108] Below the protruding section 2412, a first limiting spring 2413 is arranged, which supports the protruding section 2412, so that during the sliding of the sliding block 232 from the tail end of the protruding section 2412 to the front end of the protruding section 2412, the protruding section 2412 is pressed into the sliding rod 231. When the sliding block 232 slides to the front end of the protruding section 2412, the protruding section 2412 pops out of the sliding rod 231, achieving the effect of limiting the sliding block 232 to slide towards the tail.

[0109] The second limiting member 242 is used to lock the wing 22 before the wing 22 rotates out, and fix the wing 22 by limiting the sliding block 232, so as to prevent the wing 22 from rotating out of the aircraft body 2.

[0110] Further, the shape of the second limiting member 242 is the same as that of the first limiting member 241, and a second limiting spring 2423 is arranged below the protruding section. The second limiting spring is a tension spring, which can pull the protruding section of the second limiting member 242 into the sliding rod 231, so that the sliding block 232 can slide from the tail end of the second limiting member 242 to the front end of the second limiting member 242.

[0111] The third limiting rod 243 is a long rod structure, which is used to control the locking state of the second limiting member 242. A groove is arranged on the second limiting member 242, and the third limiting rod 243 is inserted into the groove to fix the second limiting member 242, so that it cannot be pulled into the sliding rod 231 by the second limiting spring 2423.

[0112] Further, the third limiting rod 243 is connected with the rocket propulsion device 1, as shown in Figure 2 、 Figure 3 , and

[0113] When the rocket propulsion device 1 is separated from the aircraft body 2, the third limiting rod 243 is separated from the groove of the second limiting member 242, so that the second limiting member 242 is retracted into the sliding rod 231, the sliding block 232 is released from the limiting, and the sliding block 232 is slid from the rear end to the front end of the first limiting member 241 and is fixed by the first limiting member 241, thereby driving the rotation of the wings 22 out of the shell of the aircraft body 2.

[0114] The inventor found that it takes a long time to reduce the speed of the aircraft body 2 from the high-speed movement through the defense layer to the normal working speed only by the deceleration of the wings 22, and in a preferred embodiment, a deceleration parachute is arranged on the aircraft body 2, and the deceleration parachute is opened 1-5 seconds after the rocket propulsion device 1 is separated from the aircraft body 2, so as to achieve the effect of quickly reducing the flight speed of the aircraft body 2.

[0115] More preferably, the deceleration parachute is arranged in the tail end protrusion 21, so that the aircraft body 2 is uniformly stressed after the deceleration parachute is opened, and the flight direction of the aircraft body 2 is not affected.

[0116] According to the present application, the use of the deceleration device is stopped when the speed of the aircraft body 2 is reduced to a certain value, so that the aircraft body 2 can work normally.

[0117] In a preferred embodiment, as shown in Figure 13 the second explosive bolt 211 is arranged between the tail end protrusion 21 and the aircraft body 2, and when the speed of the aircraft body 2 is reduced to the normal working speed, the second explosive bolt 211 is exploded, so that the tail end protrusion 21 is separated from the aircraft body 2.

[0118] The aircraft body 2 is also provided with a small tail wing 25, which is used to maintain the flight balance and steering function of the aircraft body 2.

[0119] On the other hand, the present application provides a method for a rocket-assisted aircraft with penetration function to break through the defense layer of a region to be broken through, which comprises the following steps:

[0120] S1. Determine the outer edge position and inner edge position of the defense layer of the target region, and set them in the aircraft.

[0121] S2. When the aircraft is 10 km away from the outer edge position of the defense layer of the target region, the rocket engine in the rocket propulsion device 1 starts to work, and the speed of the aircraft is increased, so that the aircraft can pass through the defense layer at a speed higher than 2000 km / h.

[0122] Preferably, the aircraft can pass through the defense layer at a speed higher than 2248 km / h.

[0123] S3. After the aircraft reaches the target area defense layer inner edge position, the rocket engine stops working, and the rocket propulsion device 1 is separated from the aircraft body 2.

[0124] Specifically, when the aircraft reaches the target area defense layer inner edge position, the first explosive bolt 121 explodes, the first explosive bolt 121 breaks, so that the rocket propulsion device 1 is separated from the aircraft body 2,

[0125] Preferably, the separation acceleration plate 15 is ejected by the strong spring 16, accelerating the speed of the rocket propulsion device 1 and the aircraft body 2.

[0126] S4. The wings 22 are ejected from the aircraft body 2 to slow down and slow down the aircraft body 2. In a preferred embodiment, after the rocket propulsion device 1 is separated from the aircraft body 2, the third limiting rod 243 on the rocket propulsion device 1 is separated from the aircraft body 2, the second limiting piece 242 is released, the convex section of the second limiting piece 242 is retracted into the slide rod 231, the slide block 232 is limited, so that the slide block 232 can slide to the front of the first limiting piece 241, thereby driving the wings 22 to eject from the aircraft body 2.

[0127] In a preferred embodiment, between step S3 and step S4, there is also step S3.1. After the rocket propulsion device 1 is separated from the aircraft body 2, the rocket propulsion device 1 quickly changes lane to avoid collision with the aircraft body 2.

[0128] Specifically, after the rocket propulsion device 1 is separated from the aircraft body 2, the turning plate 13 on the rocket propulsion device 1 is ejected, so that the rocket propulsion device 1 changes lane.

[0129] Preferably, when the separation acceleration plate 15 is ejected by the strong spring 16, the turning starting rod 17 is driven to move towards the head, the turning starting rod 17 slides out of the turning release groove 131, the turning plate 13 is unlocked, the turning plate 13 extends from the inside of the rocket propulsion device 1 under the action of gravity,

[0130] More preferably, after the turning starting rod 17 unlocks the turning plate 13, the turning auxiliary spring 132 ejects the turning plate 13 from the inside of the rocket propulsion device 1.

[0131] S3.2. After the rocket propulsion device 1 is separated from the aircraft body 2 for 1-5s, the deceleration parachute is opened to achieve the effect of rapidly reducing the flight speed of the aircraft body 2, and when the aircraft body 2 is decelerated to the normal working speed, the deceleration parachute is separated from the aircraft body 2.

[0132] Preferably, when the aircraft body 2 is decelerated to the normal working speed, the second explosive bolt 211 explodes, so that the deceleration parachute is separated from the aircraft body 2.

[0133] In the description of the present application, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "back", etc. indicate the orientation or positional relationship based on the working state of the present application, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third", "fourth" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0134] The present application has been described in detail above in conjunction with specific embodiments and exemplary examples, but these descriptions cannot be understood as a limitation on the present application. Those skilled in the art understand that various equivalent substitutions, modifications or improvements can be made to the technical solutions and embodiments of the present application without departing from the spirit and scope of the present application, and these all fall within the scope of the present application. The scope of protection of the present application is subject to the appended claims.

Claims

1. A rocket-boosted aircraft having a penetration function, characterized by, The rocket propulsion device (1) and the aircraft body (2) are included. The rocket propulsion device (1) is provided with a rocket engine, which improves the speed of the aircraft and enables the aircraft to pass through the defense layer at a speed higher than 2000km / h. A turning plate (13) is arranged at the lower end of the rocket propulsion device (1), which can be retracted into the rocket propulsion device (1) and popped out of the rocket propulsion device (1). A deceleration device is arranged on the aircraft body (2), which is a wing (22). The wing deployment unit (23) is further provided with a limiting mechanism (24), which includes a first limiting piece (241), a second limiting piece (242) and a third limiting rod (243) from front to back. The first limiting piece (241) is used to fix the wing (22) by limiting the sliding block (232) after the wing (22) is deployed, preventing the wing (22) from rebounding into the aircraft body (2). The second limiting piece (242) is used to lock the wing (22) before it rotates out. The third limiting rod (243) is a long rod structure used to control the locking state of the second limiting piece (242). The third limiting rod (243) is connected with the rocket propulsion device (1) and drives the rotation of the wing (22) out of the aircraft body (2) shell after the rocket propulsion device (1) is separated from the aircraft body (2). The wing deployment unit (23) has a sliding rod (231), a sliding block (232) and a wing opening spring (233) sleeved on the sliding rod (231). The sliding block (232) is sleeved on the sliding rod (231) and can slide forward and backward along the sliding rod (231). One end of the wing opening spring (233) is fixed to the front end of the sliding rod (231), and the other end is fixed to the sliding block (232). The tail side of the wing (22) is connected with the aircraft body (2) shell through a pin, and the wing (22) can rotate around the pin.

2. The rocket-assisted aircraft with penetration function according to claim 1, wherein the mechanical separation device (12) is connected with the aircraft body (2) through a first explosive bolt (121).

3. The rocket-assisted aircraft with penetration function according to claim 1, wherein the turning plate (13) is a plate structure with a circular arc cross section.

4. The rocket-assisted aircraft with penetration function according to claim 1, wherein A slot body (14) is arranged on the mechanical separation device (12), a tail end protrusion (21) corresponding to the slot body (14) is arranged at a corresponding position of the tail of the aircraft body (2), a separation acceleration plate (15) is arranged in the slot body (14), and the separation acceleration plate (15) is connected with the mechanical separation device (12) through a strong spring (16).

5. The rocket-boosted aircraft with penetration function according to claim 4, characterized in that, One end of the direction-changing plate (13) is rotatably fixed in the rocket boosting device (1), and the other end has a direction-changing release groove (131); a direction-changing starting rod (17) is further arranged on the separation acceleration plate (15), one end of the direction-changing starting rod (17) is fixed on the separation acceleration plate (15), and the other end is inserted into the direction-changing release groove (131).

6. The rocket-boosted aircraft with penetration function according to claim 1, characterized in that, A rocket boosting tail wing (11) is arranged at the tail of the rocket boosting device (1).

7. A method for a rocket-boosted aircraft with penetration function to break through the defense layer of an air defense system, using the rocket-boosted aircraft with penetration function according to any one of claims 1-6, characterized in that, The method comprises the following steps: S1. determining the outer edge position and the inner edge position of the target area defense layer and arranging them in the aircraft; S2. when the aircraft is 10 km away from the outer edge position of the target area defense layer, the rocket engine in the rocket boosting device starts to work, the speed of the aircraft is increased, and the aircraft can pass through the defense layer at a speed higher than 2000 km / h; S3. after the aircraft reaches the inner edge position of the target area defense layer, the rocket engine stops working, and the rocket boosting device is separated from the aircraft body; S4. the wings are ejected from the aircraft body, so that the aircraft body is decelerated and de-rotated.

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