Overall aerodynamic layout method and launching method of long-distance aggressive patrolling bomb

Abstract

The embodiment of the invention discloses an overall aerodynamic layout method of a long-distance aggressive patrolling bomb and a launching mode of the long-distance aggressive patrolling bomb. A specific implementation method of the method comprises the steps that the patrolling bomb adopts a single-wing layout, a fuselage is divided into three cabin sections, and the three cabin sections can be quickly disassembled and assembled respectively. A warhead, a power battery, avionics equipment and the like are installed in the patrolling bomb. Wherein the large warhead can effectively enhance the aggressiveness of the patrolling bomb; a long-distance target can be attacked in a large voyage; the launching modes are diversified, and aerial launching and ground launching can be achieved; disassembly and assembly are fast, and use and maintenance are convenient. The patrolling bomb adopts multi-node two-way information transmission, can be used singly, and can also be used for cluster combat.

Description

TECHNICAL FIELD

[0001] The present application relates to the unmanned aerial vehicle technology, and especially to a general aerodynamic layout of a long-distance attack cruise missile and a launching method thereof. BACKGROUND

[0002] The cruise missile is a kind of precision ammunition that can perform cruise flight and execute combat orders in the target area, is one of the front technologies and practical application directions in the field of unmanned aerial vehicles, and has the performance and advantages of cruise missiles and unmanned aerial vehicles. The cruise missile has been widely used in the military field at present and has strong reconnaissance and attack functions. However, most of the existing cruise missiles are ground barrel launching at present, the take-off weight is about 10 kg, the carrying load capacity is low, the attack ability to the enemy is weak, and the enemy target cannot be well damaged; the flight distance of the existing cruise missiles is within 20 km, and the target in the long-distance range cannot be attacked; most of the cruise missiles are ground launching or air launching at present, the launching barrel is needed in the ground launching, and the air platform is needed to carry the cruise missile to the air for launching in the air launching, and the two flight modes cannot be considered at the same time; most of the cruise missiles have the tandem wing layout, and the flight speed is 20-30 m / s, and the target area cannot be quickly reached to perform the task. SUMMARY

[0003] In order to solve the above problems of the cruise missile, the embodiment of the present application provides a long-distance cruise missile with a large warhead, which can be launched by air and ground barrel, and a general aerodynamic layout method of a long-distance attack cruise missile is provided.

[0004] In the first aspect, the present application provides a general aerodynamic layout method of a long-distance attack cruise missile, which comprises a front part, a middle part and a tail part of a fuselage; the front part of the fuselage is a warhead cabin (2) which is quickly installed with the middle part of the fuselage through bolts; a seeker (1) is installed in front of the warhead cabin; the middle part of the fuselage comprises a battery cabin (3), an ear (5), a control surface (6), a wing (7), a tail wing and a propeller; the tail part of the fuselage comprises an equipment cabin, and a power device (8) and an avionics equipment cabin (4) are installed.

[0005] In some embodiments, the battery cabin (3) further comprises a power battery for installation; the power battery is a high-energy-density battery or a large-volume power battery.

[0006] In some embodiments, the cruise missile further comprises that the wing, the tail wing and the propeller are foldable.

[0007] In some embodiments, the warhead cabin (2) comprises that the weight of the warhead cabin is 7 kg.

[0008] In some embodiments, the wing (7) comprises: the wing (7) is a flat wing; the wing (7) is connected to the fuselage by a folding mechanism (10).

[0009] In some embodiments, further comprising: the wing and the tail are connected to the fuselage by a torsion spring, and the propeller is connected to the power device by a hub.

[0010] In the second aspect, the embodiment provides a launching method of the long-range attack cruise missile.

[0011] In some embodiments, further comprising: after folding the wing, the tail and the propeller, launching the cruise missile by a ground cylinder.

[0012] The embodiment of the present application discloses a general aerodynamic layout method of a long-range attack cruise missile. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 The general aerodynamic layout of the cruise missile provided by the embodiment of the present application is shown in the figure.

[0014] Figure 2 The two launching methods of the cruise missile provided by the embodiment of the present application are shown in the figure.

[0015] Figure 3 The wing of the cruise missile provided by the embodiment of the present application is shown in the figure. DETAILED DESCRIPTION

[0016] The present application will be further described below in conjunction with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related application, and not to limit the application. In addition, it should be noted that, for the convenience of description, only the parts related to the application are shown in the drawings.

[0017] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and embodiments.

[0018] Figure 1 The general aerodynamic layout method of the cruise missile of one embodiment of the present application is shown.

[0019] The body of the flying bomb adopts a three-section structure, which is divided into a front body section, a middle body section and a tail body section. The three sections are connected by metal pieces through screwing to ensure the connection strength and installation accuracy.

[0020] The front body section is a warhead cabin (2) which can be quickly installed with the middle body section through bolts. A seeker (1) is installed at the front of the warhead cabin. The middle body section includes a battery cabin (3) for installing power batteries, a lug (5), a control surface (6) and a wing (7). The tail body section includes an equipment cabin, which is installed with a power device (8) and an avionics equipment cabin (4).

[0021] In this embodiment, the front warhead cabin (2) of the flying bomb is a large warhead, and the weight after charging reaches 7 kg. The tail body is an avionics equipment, and the overall weight of the avionics equipment is about 0.5 kg. Therefore, the center of gravity of the flying bomb of this embodiment is relatively forward compared with the conventional flying bomb, and a large-capacity battery can be arranged in the middle, which is beneficial to the range and time of the flying bomb. Since the warhead and the battery are located on both sides of the center of gravity, the warhead is located in the front part of the center of gravity, the battery is located in the rear part of the center of gravity, the weight of the warhead is 7 kg, the weight of the battery is about 4 kg, and the tail avionics equipment and the motor are far away from the center of gravity. Therefore, the total amount of the warhead and the weight of the battery can be increased to maintain the center of gravity unchanged, increase the endurance time and killing power, and have good expansibility.

[0022] Further, as shown in Figure 3 , the wing area of the flying bomb is about 0.19 square meters, and the wing shape is a flat wing. The wing is connected to the body through a folding mechanism (10). In order to maintain the lift, the cruising speed is faster than that of the conventional flying bomb, which reaches 200 km / h at a height of 1 km. After launching, it can quickly approach the target and launch an attack.

[0023] Further, the flying bomb adopts a lower single-wing layout, and a lug (5) can be arranged on the upper part of the center of gravity to meet the relevant standard design and be launched from an air platform through a rack. Further, the wing, the tail wing and the propeller can be folded. The wing and the tail wing are connected to the body through torsional springs, and the propeller is connected to the power device through a hub, which can be launched from the ground in a barrel type.

[0024] Further, the flying bomb adopts a multi-node communication link, which can not only be used single, but also can be used in cluster combat according to actual needs.

[0025] Further, the power battery is a large-capacity battery, and the large-capacity battery is a high-energy-density battery or a power battery with increased volume, such as a high-specific-energy primary battery. The endurance time of the flying bomb is longer, and the range is longer.

[0026] Referring to Figure 2 , a schematic diagram of the air platform launch mode and the ground barrel type launch of the flying bomb is shown.

[0027] The above description is merely exemplary of the application and the application principles. It is to be understood that the application scope of the present application is not limited to the above-described technical solutions formed by the specific combinations of the technical features, but also covers other technical solutions formed by the combinations of the above technical features or equivalent features without departing from the above-mentioned inventive concept. For example, the above technical features are replaced with the technical features disclosed in the present application (but not limited to) having similar functions to form technical solutions.

Claims

1. A method for the overall aerodynamic layout of a long-range offensive loitering munition, characterized in that, include: Front of fuselage, middle of fuselage, and rear of fuselage; The front part of the fuselage is the combat compartment (2), which is quickly installed to the middle part of the fuselage via a screw; A guidance head (1) is installed in front of the combat compartment; The fuselage includes a battery compartment (3), a lifting lug (5), a control surface (6), a wing (7), a tail fin, and a propeller. The tail section of the fuselage includes an equipment bay, which houses the power plant (8) and the avionics equipment bay (4); The wings, tail, and propeller are foldable.

2. The method according to claim 1, characterized in that, The battery compartment (3) also includes: Used for installing power batteries; the power batteries are high-energy-density batteries or large-volume power batteries.

3. The method according to claim 1, characterized in that, The combat compartment (2) includes: The weight of the combat compartment is 7 kg.

4. The method according to claim 1, characterized in that, The wing (7) includes: The wing (7) is a straight wing; The wing (7) is connected to the fuselage via a folding mechanism (10).

5. The method according to claim 1, characterized in that, Also includes: The wings and tail are connected to the fuselage via torsion springs, and the propeller is connected to the power unit via a hub.

6. A method for launching a long-range attack loitering munition, characterized in that... The long-range attack loitering munition constructed using the overall aerodynamic layout method of the long-range attack loitering munition according to claims 1-5 specifically includes: The device is mounted on the launch platform via the aforementioned lugs and is launched from the air.

7. The method according to claim 5, characterized in that, Also includes: After folding the wings, tail, and propeller, the aircraft is launched from a ground-based tube.

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