A fusion cruise missile device suitable for long-range launch

Abstract

The present invention discloses a fusion cruise missile device suitable for long-range launch, which specifically relates to the field of overall aircraft design. A fusion cruise missile device suitable for long-range launch includes multiple cruise missiles and a flying wing fuel tank device. A mechanical clamp is connected between the multiple cruise missiles and the flying wing fuel tank device. A connecting pipeline is arranged in the mechanical clamp. A missile fuel tank is arranged in each cruise missile. An oil inlet pipeline connected to the connecting pipeline is connected to the missile fuel tank. A wing fuel tank is arranged in the flying wing fuel tank device. Multiple output oil pipes are arranged on the wing fuel tank. Each output oil pipe is provided with an oil pump. A quick docking mechanism is arranged between each mechanical clamp and the corresponding oil inlet pipeline. The quick docking mechanism is used to connect the oil inlet pipeline and the connecting pipeline. The technical solution of the present invention solves the problem that the carrier aircraft needs to go deep into the high-risk area during the execution of the cruise missile mission, which can increase the cruising range of the cruise missile in the execution of the mission and improve the safety of the cruise missile carrier aircraft.

Description

Technical Field

[0001] The invention relates to the field of overall design of aircraft, and in particular to a fusion cruise missile device suitable for long-range launch. Background Art

[0002] Cruise missiles are often used to attack enemy airports, ports, transportation hubs and other important measures, and are the main targets of enemy interception. Due to the increasingly improved ground air defense system, the flight of cruise missiles has been greatly hindered. If cruise missiles want to successfully complete the mission of attacking the enemy, they must take effective protective measures to escape enemy missile attacks. The methods currently used mainly include: stealth technology, ultra-low altitude flight, decoy ejection, maneuvering and changing trajectory, etc. However, even with these technologies, the probability of cruise missiles escaping from missile attacks is still relatively low.

[0003] Since cruise missiles have a short range, they are usually transported to designated areas by high-value manned aircraft or large unmanned aerial vehicles before being released to perform their missions. This also causes the carrier aircraft to penetrate deep into high-risk areas, increasing the risk of combat damage. Summary of the invention

[0004] The present invention is intended to provide a fusion cruise missile device suitable for long-range launch, which solves the problem that the carrier aircraft of the cruise missile needs to penetrate into high-risk areas during the execution of the mission.

[0005] In order to achieve the above-mentioned purpose, the technical scheme of the present invention is as follows: a fusion cruise missile device suitable for long-range launch, comprising a plurality of cruise missiles and a flying wing type fuel tank device, a mechanical clamp is connected between the plurality of cruise missiles and the flying wing type fuel tank device, a connecting pipeline is arranged in the mechanical clamp, a missile fuel tank is arranged in each of the cruise missiles, an oil inlet pipeline connected to the connecting pipeline is connected to the missile fuel tank, a wing fuel tank is arranged in the flying wing type fuel tank device, a plurality of output oil pipes are arranged on the wing fuel tank, an oil pump is arranged on each of the output oil pipes, a quick docking mechanism is arranged between each of the mechanical clamps and the corresponding oil inlet pipeline, and the quick docking mechanism is used for connecting the oil inlet pipeline and the connecting pipeline.

[0006] Furthermore, the quick docking mechanism comprises two magnetic components, a pressure sensor and two solenoid valves electrically connected to the pressure sensor, the two magnetic components are respectively installed on the cruise missile of the mechanical clamp and the oil inlet pipeline, the pressure sensor is arranged on the magnetic component at the mechanical clamp, and the two solenoid valves are respectively installed on the connecting pipeline and the oil inlet pipeline.

[0007] Furthermore, the operation method of the fusion cruise missile device is as follows: when the cruise missile is combined with the flying wing type fuel tank device, it is called a polymerization state, and the cruise missile and the flying wing type fuel tank device fly as a whole, the cruise missile provides thrust for the whole, and the tail wing of the cruise missile provides a control torque; when the cruise missile is separated from the flying wing type fuel tank device, it is called a separation state, and the cruise missile uses the fuel carried in the missile tank to fly.

[0008] Compared with the prior art, this solution has the following beneficial effects:

[0009] This scheme enhances the long-range attack capability of cruise missiles; this scheme has the characteristics of high elasticity, so that when this scheme approaches the target area, the number of targets in that direction suddenly increases several times, making it impossible for the enemy's air defense system to react in time, thereby achieving a saturation attack on the enemy. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a top view of a fusion cruise missile device suitable for long-range launch in a polymerized state according to the present invention;

[0011] Figure 2 It is a left view of a fusion cruise missile device suitable for long-range launch in a polymerized state according to the present invention;

[0012] Figure 3 This is a front view of a fusion cruise missile device suitable for long-range launch in a separated state according to the present invention;

[0013] Figure 4 Schematic diagram of the structure of the mechanical clamp in this embodiment. DETAILED DESCRIPTION

[0014] The present invention is further described in detail below through specific embodiments:

[0015] The reference numerals in the drawings of the specification include: cruise missile 1, flying wing type fuel tank device 2, mechanical clamp 3, missile fuel tank 4, wing fuel tank 5, oil inlet pipeline 6, output oil pipe 7, and oil pump 8.

[0016] Example

[0017] As attached Figure 1-4As shown: A fusion cruise missile device suitable for long-range launch, including multiple cruise missiles 1 and a flying wing fuel tank device 2. In this embodiment, three cruise missiles 1 are used. A mechanical clamp 3 is connected between each cruise missile 1 and the flying wing fuel tank device 2. A connecting pipeline is arranged in the mechanical clamp 3. The mechanical clamp 3 is fixedly arranged on the lower surface of the flying wing fuel tank device 2. The mechanical clamp 3 is composed of two clamping plates and a connecting plate connected between the two clamping plates. The two clamping plates are clamped with the cruise missile 1. A through hole is opened on the connecting plate, and a connecting pipeline is fixedly arranged in each through hole. A missile fuel tank 4 is arranged in each cruise missile 1, and an oil inlet pipeline 6 connected to the connecting pipeline is connected to the missile fuel tank 4. A wing oil tank 5 is provided in the wing-type oil tank device 2, and the wing-type oil tank device 2 has a control system but no power device. A plurality of output oil pipes 7 are provided on the wing oil tank 5, and each output oil pipe 7 is provided with an oil pump 8 electrically connected to the control system of the wing-type oil tank device 2. A quick docking mechanism is provided between each output oil pipe 7 and the connecting pipeline of the corresponding mechanical clamp 3, and the quick docking mechanism is used for connecting the connecting pipeline and the output oil pipe 7.

[0018] The quick docking mechanism includes two magnetic components, a pressure sensor and two solenoid valves electrically connected to the pressure sensor. The two magnetic components are respectively installed at the connecting pipeline of the mechanical clamp 3 and on the cruise missile 1 of the oil inlet pipeline 6. The magnetic components are existing equipment and are not improved in this embodiment. With the help of the magnetic components, the mechanical clamp 3 and the oil inlet pipeline 6 can be quickly connected; the pressure sensor is arranged on the magnetic component at the mechanical clamp 3, and the two solenoid valves are respectively installed on the connecting pipeline and the oil inlet pipeline 6.

[0019] Operation method of the fusion cruise missile 1 device: When the cruise missile 1 is combined with the flying wing type fuel tank device 2, it is called the aggregation state. The cruise missile 1 and the flying wing type fuel tank device 2 fly as a whole. At this time, the oil inlet pipeline 6, the connecting pipeline and the output oil pipe 7 are connected. With the help of the oil pump 8, the wing fuel tank 5 continuously supplies fuel to the missile fuel tank 4 to ensure that the missile fuel tank 4 is always full of oil, thereby ensuring that the center of gravity of the whole does not change significantly. At the same time, the engine in the cruise missile 1 provides thrust for the whole, and the tail of the cruise missile 1 provides a control torque. When the cruise missile 1 provides thrust, the whole has speed, thereby generating lift with the help of the flying wing type fuel tank device 2, and realizing the overall take-off. When the cruise missile 1 is separated from the flying wing type fuel tank device 2, it is called the separation state. The cruise missile 1 uses the fuel carried in the missile fuel tank 4 inside it to fly.

[0020] The above are only embodiments of the present invention, and the common knowledge such as the known specific structures and / or characteristics in the scheme are not described in detail here. It should be pointed out that for those skilled in the art, several deformations and improvements can be made without departing from the structure of the present invention, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicality of the patent. The scope of protection required by this application shall be based on the content of its claims, and the specific implementation methods and other records in the specification can be used to interpret the content of the claims.

Claims

1. A fusion cruise missile device suitable for long-range launch, characterized in that: It comprises a plurality of cruise missiles and a flying wing type fuel tank device, wherein a mechanical clamp is connected between the plurality of cruise missiles and the flying wing type fuel tank device, wherein a connecting pipeline is arranged in the mechanical clamp, wherein each of the cruise missiles is provided with a missile fuel tank, wherein an oil inlet pipeline communicating with the connecting pipeline is connected to the missile fuel tank, wherein the flying wing type fuel tank device has a control system but no power device, wherein a wing fuel tank is provided in the flying wing type fuel tank device, wherein a plurality of output oil pipes are arranged on the wing fuel tank, wherein each of the output oil pipes is provided with an oil pump, wherein a quick docking mechanism is provided between each of the mechanical clamps and the corresponding oil inlet pipeline, wherein the quick docking mechanism is used for connecting the oil inlet pipeline with the connecting pipeline.

2. A fusion cruise missile device suitable for long-range launch according to claim 1, characterized in that: The quick docking mechanism includes two magnetic components, a pressure sensor and two solenoid valves electrically connected to the pressure sensors. The two magnetic components are respectively installed on the mechanical clamp and the oil inlet pipeline on the cruise missile. The pressure sensor is arranged on the magnetic component at the mechanical clamp, and the two solenoid valves are respectively installed on the connecting pipeline and the oil inlet pipeline.

3. A fusion cruise missile device suitable for long-range launch according to claim 1 or 2, characterized in that: The operation method of the fusion cruise missile device is as follows: when the cruise missile is combined with the flying wing type fuel tank device, it is called the aggregation state, and the cruise missile and the flying wing type fuel tank device fly as a whole, the cruise missile provides thrust for the whole, and the tail wing of the cruise missile provides the control torque; when the cruise missile is separated from the flying wing type fuel tank device, it is called the separation state, and the cruise missile uses the fuel carried in the missile tank to fly.

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