A high-speed cruise missile that can be quickly recovered

Abstract

The invention discloses a rapidly recoverable high-speed cruise missile, wherein a boundary layer suction-type propulsion device (2) is arranged at the tail of a cruise missile body (1), a streamlined radial constriction (11) is arranged on the cruise missile body (1), and the radial constriction (11) is arranged at the front end of the boundary layer suction-type propulsion device (2). The rapidly recoverable high-speed cruise missile disclosed by the invention has reduced flight energy consumption, is recoverable and can be reused, and has multiple attack modes on targets.

Description

Technical Field

[0001] The invention relates to a loitering missile, belonging to the technical field of aircraft. Background Art

[0002] A cruise missile is a product of the integration of guided munitions and drone technology. It has the capabilities of reconnaissance, detection, target positioning, aerial wireless relay, and precision strike. It can cruise on standby over a designated area, scout and track enemy targets, and accurately strike time-sensitive targets and hidden targets.

[0003] However, traditional cruise missiles use suicide attack methods and are used as a type of ammunition. They are consumed quickly, in large quantities, and cannot be reused.

[0004] Traditional cruise missiles use indiscriminate suicide strikes on targets they discover, regardless of the target's value or level of protection. This has the disadvantages of a single strike method and low cost-effectiveness.

[0005] Due to the above reasons, it is necessary to propose a high-speed cruise missile that can be quickly recovered. Summary of the invention

[0006] In order to overcome the above problems, the inventors have conducted in-depth research and designed a high-speed cruise missile that can be quickly recovered. A boundary layer suction propulsion device 2 is provided at the tail of the cruise missile body 1.

[0007] Preferably, a streamlined radial constriction 11 is provided on the cruise missile body 1.

[0008] The radial constriction 11 is arranged at the front end of the boundary layer suction propulsion device 2 .

[0009] Preferably, the length of the radial constriction 11 accounts for 10% to 15% of the overall length of the cruise missile body 1 .

[0010] Preferably, the boundary layer suction propulsion device 2 comprises a propeller housing 21, an engine and a rudder surface 23.

[0011] The engine is enclosed in the propeller housing 21 , and the rudder surface 23 is arranged at the tail of the propeller housing 21 .

[0012] Preferably, a plurality of groups of tail stabilizer surfaces 211 are arranged on the outer side of the thruster housing 21, each group of tail stabilizer surfaces 211 has two tail surfaces, and the two tail surfaces are symmetrically distributed on the circumferential outer side of the thruster housing 21, and the cross-section of the tail surface is triangular.

[0013] Preferably, a rotating shaft 24 is provided between the two tail surfaces of each set of tail stabilizer surfaces 211 , and the rudder surface 23 is provided on the rotating shaft 24 , and the rudder surface 23 can rotate around the rotating shaft 24 .

[0014] Preferably, a wing 3 is provided near the middle of the cruise missile body 1, and the wing 3 is rotatable so that the length direction of the wing 3 can be the same as or perpendicular to the length direction of the cruise missile.

[0015] Preferably, the ammunition in the cruise missile body is separable from the cruise missile body 1 .

[0016] On the other hand, the present invention also provides a method for using a high-speed cruise missile that can be quickly recovered, comprising the following steps:

[0017] Step 1: Launch cruise missiles vertically;

[0018] Step 2: The cruise missile's wings unfold and fly;

[0019] Step 3: The cruise missile cruises or attacks the target.

[0020] Preferably, there is also a step four, recovery of the cruise missile.

[0021] The beneficial effects of the present invention include:

[0022] (1) Cruise missiles are recoverable and can be reused;

[0023] (2) There are various ways to attack targets, with high cost-effectiveness;

[0024] (3) The flight energy consumption of cruise missiles is reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A schematic diagram of the overall structure of a high-speed cruise missile that can be quickly recovered according to a preferred embodiment of the present invention is shown;

[0026] Figure 2 A schematic diagram of the structure of a boundary layer suction propulsion device in a high-speed cruise missile capable of rapid recovery according to a preferred embodiment of the present invention is shown;

[0027] Figure 3 A schematic diagram of the wing folding structure of a rapidly recoverable high-speed cruise missile according to a preferred embodiment of the present invention is shown.

[0028] Explanation of symbols:

[0029] 1- Cruise missile body;

[0030] 2-Boundary layer suction propulsion device;

[0031] 3- Wing;

[0032] 11- radial shrinkage;

[0033] 21-thruster housing;

[0034] 23-rudder surface;

[0035] 24-rotating shaft;

[0036] 25-tie rod;

[0037] 211-Tail stabilizer. DETAILED DESCRIPTION

[0038] The present invention will be further described in detail below through the accompanying drawings and embodiments. Through these descriptions, the characteristics and advantages of the present invention will become more clear and distinct.

[0039] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0040] Traditional cruise missiles are all disposable ammunition, which are difficult to recover after use, resulting in a waste of resources. In order to solve this problem, the present invention improves the traditional cruise missiles so that they can be recycled.

[0041] Traditional cruise missiles, because they do not consider the issue of recovery for secondary use, mostly use propellers as propulsion. Propellers have a low flying speed and high power consumption. The inventors found that in order to achieve the recovery of cruise missiles, it is first necessary to solve the problem of energy utilization so that the cruise missiles have enough energy to fly back and land after completing their mission.

[0042] In addition, the difficulty of autonomous landing of cruise missiles needs to be considered. Traditional fixed-wing aircraft generally use autonomous taxiing landing or parachute-type deceleration landing. However, taxiing landing requires a dedicated runway, and parachuting may cause damage to the cruise missile body. After recovery, the parachute needs to be re-folded and re-installed, which is not conducive to the secondary use of cruise missiles.

[0043] In view of the above problems, the present invention provides a high-speed cruise missile that can be quickly recovered, wherein a boundary layer suction propulsion device 2 is provided at the tail of the cruise missile body 1. Figure 1 As shown, the energy consumption of the cruise missile can be reduced by using a boundary layer suction propulsion device, and the cruise missile can be vertically landed and recovered.

[0044] Traditional propulsion devices are generally installed forward. In the present invention, a boundary layer suction propulsion device is arranged at the tail of the cruise missile body 1 to provide flight power for the cruise missile, so that the cruise missile can take off and land vertically, thereby realizing the recoverable function of the cruise missile.

[0045] In the present invention, the cruise missile body 1 is cylindrical, and its front end is a smooth axisymmetric body. When the cruise missile is flying, the airflow forms a boundary layer airflow on the outer wall surface of the cruise missile body 1. Figure 1 As shown, the boundary layer suction propulsion device 2 is placed at the tail, which can effectively absorb all boundary layer airflows formed on the surface of the cruise missile body 1, suppress the wake behind the body and the propeller, and thus save power consumption during cruise flight.

[0046] Furthermore, in order to enable the boundary layer suction propulsion device 2 to better suppress the downstream jet and body wake generated during the flight of the cruise missile body 1, in the present invention, a streamlined radial constriction 11 is provided at the front end of the boundary layer suction propulsion device 2 on the cruise missile body 1.

[0047] Furthermore, the length of the radial constriction 11 accounts for 10% to 15% of the overall length of the cruise missile body 1.

[0048] Furthermore, the radial constriction 11 is arranged at the 65% to 80% position of the cruise missile body, wherein the cruise missile head is at the 0% position and the tail of the boundary layer suction propulsion device is at the 100% position.

[0049] Preferably, the outer diameter of the radially tapered tail end is 80% to 150% of the outer diameter of the cylindrical body of the cruise missile. The above dimensions are conducive to the propeller to completely inhale the boundary layer airflow and can suppress the wake flow to the greatest extent.

[0050] The position and size of the radial constriction 11 ensure the stability and suction effect of the engine of the boundary layer suction propulsion device 2 in capturing the boundary layer airflow of the fuselage, greatly reducing the power consumption of the cruise missile during high-speed flight.

[0051] In the present invention, further, in order to realize the secondary utilization of the cruise missile, the boundary layer suction propulsion device 2 is specially designed in the present invention so that it can realize the vertical launch, recovery and cruise requirements of the cruise missile.

[0052] Specifically, the boundary layer suction propulsion device 2 includes a propeller housing 21, an engine and a rudder surface 23. Figure 2 shown.

[0053] Furthermore, the thruster housing 21 is a hollow cylindrical structure, the outer diameter of the front end of the thruster housing 21 is larger than the outer diameter of the rear end, and it is streamlined and radially contracted from the front end to the rear end to better reduce the resistance of the thruster housing.

[0054] Further preferably, the front end outer diameter of the thruster housing 21 is 80% to 150% of the outer diameter of the cruise missile body 1, and the rear end outer diameter of the thruster housing 21 is 70% to 120% of the outer diameter of the cruise missile body 1, so that when the thruster is in a cruising state, most of the inhaled airflow is the boundary layer airflow of the body.

[0055] Furthermore, the engine is wrapped at the axial center position inside the propeller housing 21, and fan blades are installed thereon to inhale boundary layer air and generate thrust.

[0056] Specifically, a plurality of groups of tail stabilizers 211 are arranged on the outside of the thruster housing 21. The cross-section of the tail stabilizer 211 is a triangular or trapezoidal flat plate structure. The tail stabilizer 211 is perpendicular to the circumferential outer section of the thruster housing 21. Two tail stabilizers 211 form a group, and the two tail stabilizers 211 in a group are symmetrically distributed on the circumferential outer side of the thruster housing 21.

[0057] Preferably, the tail stabilizer surfaces 211 are in two groups, evenly distributed on the circumferential outer side of the propeller housing 21 .

[0058] Preferably, in the circumferential direction of the thruster housing 21, the length of the tail stabilizer 211 protruding from the thruster housing 21 is 0.5 to 2 times the diameter of the fuselage. This length setting can not only meet the pitch and heading stability of the cruise missile, but also support the cruise missile to land smoothly.

[0059] According to the present invention, the boundary layer suction propulsion device 2 further includes a rotating shaft 24 and a pull rod 25 .

[0060] Preferably, a rotating shaft 24 is provided between each set of tail stabilizer surfaces 211, one end of the rudder surface 23 is hinged to the rotating shaft 24, so that the rudder surface 23 can rotate around the rotating shaft 24, and the other end of the rudder surface 23 is connected to a tie rod 25, and the rotation angle of the rudder surface 23 is controlled by the tie rod 25. In the present invention, the rotating shaft is provided at the stabilizer surface position, which shortens the force transmission distance, makes the rudder surface / engine structure compact, and is conducive to reducing the energy consumption of cruising.

[0061] In the present invention, the rotation of the rudder surface 23 around the rotating shaft 24 is achieved by extending or rotating the pull rod, and the direction of the airflow ejected by the boundary layer suction propulsion device 2 is controlled by controlling the rotation angle of the rudder surface 23, thereby realizing vector control of the thrust, and further realizing the pitch, roll and yaw control of the cruise missile.

[0062] The rudder surface 23 is in the shape of a flat plate. Preferably, the cross-section of the rudder surface 23 is a rectangular shape with a missing vertex. The rectangle with a missing vertex means that a vertex near the tail of the rectangle is cut off, and the shape of the cut corner is a right triangle. The cut corner of the rudder surface can avoid interference when adjacent rudder surfaces are deflected in the same direction.

[0063] Preferably, the length of the rectangle is 40% to 100% of the diameter of the fuselage, and the width is 40% to 80% of the diameter of the fuselage; the length of the cut right triangle is 30% to 0.7% of the diameter of the fuselage, and the width is 15% to 35% of the diameter of the fuselage, so that the deflection angle of the rudder surface is greater than 30 degrees, which is conducive to generating sufficient control torque during vertical landing.

[0064] Furthermore, the hinged end between the rudder surface 23 and the rotating shaft 24 is located in the middle of the rectangular edge of the rudder surface.

[0065] According to the present invention, the control surface 23, the tail stabilizer 211 and the engine are integrated into one body through the propeller housing 21, so that the cruise missile has an axisymmetric shape, so that the boundary layer suction propulsion device can better and more stably capture the boundary layer airflow of the fuselage.

[0066] According to the present invention, a wing 3 is also provided near the middle of the cruise missile body 1. Figure 3 As shown, the wing 3 can rotate relative to the cruise missile body 1, so that the length direction of the wing 3 can be the same as or perpendicular to the length direction of the cruise missile.

[0067] Furthermore, the width of the wing 3 is not greater than the maximum circumferential diameter of the cruise missile, and the length of the wing 3 is not greater than the length of the cruise missile body 1.

[0068] Furthermore, when the cruise missile is launched and landed, the wing 3 is rotated so that the length direction of the wing 3 is the same as the length direction of the cruise missile, which is convenient for launching and recovering, and avoids the wing causing airflow disturbance and thus affecting the launch and recovery flight trajectory of the cruise missile; after the cruise missile is launched, the wing 3 is rotated so that the length direction of the wing 3 is perpendicular to the length direction of the cruise missile, so that the cruise missile can fly at high speed and stably.

[0069] According to the present invention, the rotating storage method of the wing 3, compared with other wing storage methods, does not occupy the internal space of the cruise missile body 1, so that the usable space inside the cruise missile body 1 is increased, thereby increasing the amount of ammunition that the cruise missile can carry and providing a feasible space for the separation of ammunition.

[0070] According to the present invention, when performing a mission, one can choose to use a cruise missile for a suicide attack, or one can choose to throw the ammunition inside to achieve a more flexible attack method.

[0071] According to the present invention, an ammunition separation component is provided in the cruise missile body 1, and the ammunition is ejected through the ammunition separation component.

[0072] The ammunition separation assembly can be any kind of clamping and separation device, for example, a hatch is provided, and when ammunition separation is required, the hatch is opened to throw out the ammunition, or a push rod is provided, and when ammunition separation is required, the ammunition is pushed out of the cruise missile to achieve ammunition separation.

[0073] Furthermore, the arrangement that the ammunition in the cruise missile body can be separated from the cruise missile body 1 also improves the safety of cruise missile recovery. The recovered cruise missile does not have ammunition inside, avoiding accidents and casualties during the recovery process.

[0074] On the other hand, the present invention also provides a method for using a high-speed cruise missile that can be quickly recovered, comprising the following steps:

[0075] Step 1: Launch cruise missiles vertically;

[0076] Step 2: The cruise missile's wings unfold and fly;

[0077] Step 3: The cruise missile cruises or attacks the target;

[0078] Preferably, there is also a step four, recovery of the cruise missile.

[0079] In step one, before the cruise missile is launched, the wing is rotated so that the length direction of the wing is the same as the length direction of the cruise missile.

[0080] Furthermore, the cruise missile is launched vertically through a boundary layer suction propulsion device.

[0081] In step two, after the cruise missile is launched, the wings are rotated so that the length direction of the wings is perpendicular to the length direction of the cruise missile, that is, the wings are unfolded, which speeds up the stabilization rate of the cruise missile and enables the cruise missile to fly stably at high speed.

[0082] In step three, the flight status of the cruise missile is controlled by the ground station to patrol the target area.

[0083] Furthermore, when a target is found, the ground station operator determines the attack mode of the cruise missile, and the cruise missile attacks the target with its main body or separated ammunition.

[0084] Specifically, when the target is large or difficult to destroy, the ground station operator controls the cruise missile body to directly attack the target; when the target is small or easy to destroy, the ground station operator controls the cruise missile to separate the ammunition and attack the target with the separated ammunition.

[0085] When the cruise missile fails to attack the target in step three, or attacks the target through separated ammunition, the cruise missile can be recovered.

[0086] In step four, preferably, when the cruise missile has not attacked a target, before recovering the cruise missile, the ammunition in the cruise missile body is separated from the cruise missile body to improve the safety of recovering the cruise missile.

[0087] Furthermore, when the cruise missile is recovered, the wing is rotated so that the length direction of the wing is the same as the length direction of the cruise missile, that is, the wing is retracted.

[0088] Furthermore, the direction of thrust is adjusted through the boundary layer suction propulsion device so that the cruise missile can land vertically and be recovered.

[0089] The cruise missile described in the present invention can reduce cruise energy consumption by 5-20% compared to traditional propeller cruise missiles. The cruise missile described in the present invention can generate vector thrust, so that the cruise missile has vertical landing capability and its recovery is not restricted by ground sites. In actual use, each cruise missile can be recovered and used no less than 3 times.

[0090] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front", "rear", etc. indicate positions or positional relationships based on the working state of the present invention, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", "third", and "fourth" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0091] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0092] The present invention has been described above in conjunction with preferred embodiments, but these embodiments are only exemplary and serve only as an illustration. On this basis, the present invention may be subjected to a variety of substitutions and improvements, all of which fall within the scope of protection of the present invention.

Claims

1. A high-speed cruise missile that can be quickly recovered, characterized in that: A boundary layer suction-type propulsion device (2) is arranged at the tail of the cruise missile body (1) to achieve vertical landing and recovery of the cruise missile; A streamlined radial constriction (11) is provided on the cruise missile body (1). The radial constriction (11) is arranged at the front end of the boundary layer suction propulsion device (2); The length of the radial constriction (11) accounts for 10% to 15% of the overall length of the cruise missile body (1); The boundary layer suction propulsion device (2) comprises a propeller housing (21), an engine and a control surface (23). The engine is enclosed within a propeller housing (21), and the rudder surface (23) is arranged at the tail of the propeller housing (21); The outer diameter of the front end of the propeller housing (21) is larger than the outer diameter of the rear end, and the propeller housing (21) is streamlined and radially contracted from the front end to the rear end. The outer diameter of the front end of the propeller housing (21) is 80% to 150% of the outer diameter of the cruise missile body (1), and the outer diameter of the rear end of the propeller housing (21) is 70% to 120% of the outer diameter of the cruise missile body (1). The ammunition in the cruise missile body is separable from the cruise missile body (1); A plurality of groups of tail fin stabilizer surfaces (211) are arranged outside the thruster housing (21), each group of tail fin stabilizer surfaces (211) having two tail fin surfaces, the two tail fin surfaces being symmetrically distributed outside the thruster housing (21) in the circumferential direction, and the tail fin surfaces having a triangular cross-section; In the circumferential direction of the propeller housing (21), the tail stabilizer surface (211) protrudes from the propeller housing (21) by a length of 0.5 to 2 times the diameter of the fuselage, which can support the cruise missile to land smoothly; The cross-section of the rudder surface (23) is a rectangular shape with a missing vertex, a vertex of the rectangle near the tail is cut, and the cut corner shape is a right triangle, the length of the rectangle is 40% to 100% of the fuselage diameter, and the width is 40% to 80% of the fuselage diameter; the length of the cut right triangle is 30% of the fuselage diameter, and the width is 15% to 35% of the fuselage diameter, so that the rudder surface deflection angle is greater than 30 degrees.

2. The rapidly recoverable high-speed cruise missile according to claim 1, characterized in that: A rotating shaft (24) is arranged between the two tail surfaces of each group of tail stabilizer surfaces (211), the rudder surface (23) is arranged on the rotating shaft (24), and the rudder surface (23) can rotate around the rotating shaft (24).

3. The rapidly recoverable high-speed cruise missile according to claim 1, characterized in that: A wing (3) is arranged near the middle of the cruise missile body (1), and the wing (3) is rotatable so that the length direction of the wing (3) can be the same as or perpendicular to the length direction of the cruise missile.

4. A method for using a high-speed cruise missile that can be quickly recovered, using the cruise missile as claimed in any one of claims 1 to 3, comprising the following steps: Step 1: Launch cruise missiles vertically; Step 2: The cruise missile's wings unfold and fly; Step 3: The cruise missile cruises or attacks the target.

5. The method for using the rapidly recoverable high-speed cruise missile according to claim 4, characterized in that: There is also step four, cruise missile recovery.

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