High-speed large-maneuvering target drone

Abstract

The utility model discloses a high-speed large-maneuvering target drone, which relates to the field of unmanned aerial vehicles and comprises a drone body, wings, a horizontal tail, a vertical tail and an air inlet channel. The fuselage can reduce resistance to a great extent to realize high-speed flight; the wings adopt sweepback upper single wings to reduce the resistance during high-speed flight, the problem of overlarge transverse stability caused by sweepback and high placement of the wings can be avoided through the downward reverse design, and meanwhile, the wings can be integrally disassembled and assembled and have better operability and convenience; the control efficiency of a full-motion horizontal tail is high, and the heading stability under a large-angle-of-attack attitude can be improved through the design of the inverted-V-shaped tail; the vertical fin without the control surface can improve the course stability and ensure the matching property of the transverse course stability, and is light in structural weight and small in flight resistance; the bearing separation channel type air inlet channel can avoid landing damage of the air inlet channel in the parachute landing recovery process, and meanwhile the requirements for high total pressure recovery, low air inlet distortion, radar stealth and the like are met.

Description

Technical Field

[0001] The utility model belongs to the field of unmanned aerial vehicles and relates to a high-speed and highly maneuverable target drone. Background Art

[0002] As a dynamic physical simulator for the attack targets of various weapon systems, the target drone has the same motion characteristics and target detectability as the simulated object, and is used to test the development tests, appraisals, combat effectiveness evaluations, etc. of various aviation weapons. The threat targets that air defense weapons have to deal with are fighter jets and cruise missiles. During the development process, it is necessary to attack such targets to test the effectiveness of air defense weapons. Therefore, there must be a target drone with performance similar to that of the threat targets to simulate real targets of different models and types.

[0003] In recent years, weapon systems have been continuously developed, and technical performances have been continuously broken through, which puts forward higher requirements for testing the strike effects of air defense weapons. The threat targets are developing towards high speed, high maneuverability, etc., while there is currently a lack of target drones with high-speed and highly maneuverable characteristics. Content of the Utility Model

[0004] The purpose of this part is to outline some aspects of the embodiments of the utility model and briefly introduce some preferred embodiments. Simplifications or omissions may be made in this part, as well as in the abstract and the title of the utility model of this application, to avoid obscuring the purpose of this part, the abstract, and the title of the utility model, and such simplifications or omissions shall not be used to limit the scope of the utility model.

[0005] In view of the deficiencies of the existing target drone technology as described above, the present utility model is proposed.

[0006] To solve the above technical problems, the present utility model provides the following technical solutions:

[0007] A high-speed and highly maneuverable target drone, comprising: a fuselage, wings, horizontal tails, vertical tails, and an air intake. The wings are located in the middle of the fuselage, the horizontal tails and vertical tails are located at the rear of the fuselage, and the air intake is located in the mid-rear of the fuselage.

[0008] As a preferred scheme of the high-speed and highly maneuverable target drone of the present utility model, wherein: the fuselage is divided into three parts: a front fuselage, a middle fuselage, and a rear fuselage. The front fuselage is spherical and arc-shaped, the cross-section of the middle fuselage is trapezoidal, with a smooth longitudinal transition, and the rear fuselage is a converging fairing shape.

[0009] As a preferred scheme of the high-speed and highly maneuverable target drone of the present utility model, wherein: the wings are swept-back upper single wings, adopting supercritical airfoils, with a wing root installation angle of 1.5°, a leading-edge sweep angle of 33°, a dihedral angle of 4°, a spanwise negative twist of 2°, and the wings are integral wings.

[0010] As a preferred solution of the high-speed and highly maneuverable target drone of the present utility model, the following applies: The horizontal tail adopts a fully movable inverted V layout and can be used as a rudder and an elevator simultaneously. When the left and right wing surfaces deflect in the same direction, it serves as an elevator, and when they deflect in opposite directions, it serves as a rudder. It adopts a symmetric airfoil, with a wing root setting angle of -1.5°, a leading edge sweep angle of 35°, and a dihedral angle of 30°.

[0011] As a preferred solution of the high-speed and highly maneuverable target drone of the present utility model, the following applies: The vertical tail adopts a symmetric airfoil and a design without control surfaces, with a leading edge sweep angle of 40°.

[0012] As a preferred solution of the high-speed and highly maneuverable target drone of the present utility model, the following applies: The air intake adopts a dorsal separated-channel air intake.

[0013] Advantages of the present utility model:

[0014] 1. The fuselage design can greatly reduce resistance and achieve high-speed flight.

[0015] 2. The wing adopts a swept-back high-mounted single wing to reduce resistance during high-speed flight; the wing has a dihedral to avoid excessive lateral stability caused by wing sweep and high mounting; the wing can be disassembled and assembled as a whole, with good operability and convenience.

[0016] 3. The fully movable horizontal tail has high control efficiency, and the inverted V tail design can improve the course stability at large angle of attack.

[0017] 4. The vertical tail without control surfaces can increase course stability, ensure the matching of lateral and directional stability, and has a light structural weight and low flight resistance.

[0018] 5. The dorsal separated-channel air intake can avoid landing damage to the air intake during parachute recovery, and at the same time meet requirements such as high total pressure recovery, low intake distortion, and radar stealth. Description of the Drawings

[0019] To more clearly illustrate the technical solutions of the embodiments of the present utility model, the following will briefly introduce the drawings required for description in the embodiments. Obviously, the following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings. Among them:

[0020] Figure 1 It is a schematic diagram of the composition of a preferred embodiment of a high-speed and highly maneuverable target drone of the present utility model;

[0021] Figure 2 For Figure 1 The side view of the illustrated embodiment;

[0022] Figure 3For Figure 1 Top view of the embodiment shown;

[0023] Figure 4 For Figure 1 Front view of the embodiment shown;

[0024] Figure 5 For Figure 1 Schematic diagram of the fuselage of the embodiment shown;

[0025] Figure 6 For Figure 1 Schematic diagram of the wing of the embodiment shown;

[0026] Figure 7 For Figure 1 Schematic diagram of the horizontal tail of the embodiment shown;

[0027] Figure 8 For Figure 1 Schematic diagram of the vertical tail of the embodiment shown;

[0028] Figure 9 For Figure 1 Schematic diagram of the air intake of the embodiment shown.

[0029] In the figure: 1, fuselage; 2, wing; 3, horizontal tail; 4, vertical tail; 5, air intake. Detailed implementation manners

[0030] To make the above objects, features and advantages of the present utility model more obvious and understandable, the following detailed description of the specific implementation manners of the present utility model will be given in conjunction with the accompanying drawings of the specification.

[0031] In the following description, many specific details are set forth to facilitate a full understanding of the present utility model. However, the present utility model may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the connotation of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed below.

[0032] Secondly, the so-called "one embodiment" or "embodiment" herein refers to a specific feature, structure or characteristic that may be included in at least one implementation manner of the present utility model. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that excludes other embodiments.

[0033] Furthermore, the present utility model is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present utility model, for the convenience of explanation, the cross-sectional views showing the device structure will be enlarged locally out of the general proportion, and the schematic diagrams are only examples and should not limit the scope of protection of the present utility model herein. In addition, in actual production, three-dimensional spatial dimensions including length, width and depth should be included.

[0034] Referring to Figures 1 - 7 , which is an embodiment of the present utility model, a high-speed and highly maneuverable target drone is provided. The aerodynamic layout of this target drone includes: a fuselage 1, a wing 2, a horizontal tail 3, a vertical tail 4, and an air intake 5. The wing 2 is located in the middle of the fuselage 1, the horizontal tail 3 and the vertical tail 4 are located at the rear of the fuselage 1, and the air intake 5 is located in the middle and rear of the fuselage 1.

[0035] The fuselage 1 is divided into three parts: the front fuselage, the middle fuselage, and the rear fuselage. The front fuselage is designed with a spherical head and arc shape to reduce the headwind resistance and improve the aerodynamic efficiency; the cross-section of the middle fuselage is trapezoidal, with a smooth longitudinal transition, further reducing the aerodynamic resistance and optimizing the air flow distribution to ensure the flight stability and controllability; the rear fuselage is a converging fairing shape, effectively reducing the tail resistance and at the same time helping to improve the flight speed and maneuverability; the overall design of the fuselage greatly reduces the resistance and realizes high-speed flight.

[0036] The wing 2 adopts a swept-back upper wing to reduce the resistance during high-speed flight; the wing 2 has a dihedral angle to avoid the problem of excessive lateral stability caused by the swept-back and high-mounted wing; the wing 2 can be disassembled and assembled as a whole, with good operability and convenience; it adopts a supercritical airfoil, with a wing root setting angle of 1.5°, a leading edge sweep angle of 33°, a dihedral angle of 4°, and a spanwise negative twist of 2°.

[0037] The horizontal tail 3 adopts a fully movable inverted V layout. The fully movable horizontal tail has a higher control efficiency, and the inverted V tail design can improve the course stability at a large angle of attack; the horizontal tail 3 can be used as both a rudder and an elevator at the same time. When the left and right wing surfaces deflect in the same direction, it is an elevator, and when the wing surfaces deflect in the opposite direction, it is a rudder; it adopts a symmetric airfoil, with a wing root setting angle of -1.5°, a leading edge sweep angle of 35°, and a dihedral angle of 30°.

[0038] The vertical tail 4 adopts a design without control surfaces, which can increase the course stability, ensure the matching of the lateral and directional stability, and has a light structural weight and small flight resistance; it adopts a symmetric airfoil, with a leading edge sweep angle of 40°.

[0039] The air intake 5 adopts a dorsal separated-channel air intake, which can avoid the landing damage of the air intake 5 during parachute recovery, and at the same time takes into account requirements such as high total pressure recovery, low intake distortion, and radar stealth.

[0040] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present utility model and not to limit them. Although the present utility model has been described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that the technical solutions of the present utility model can be modified or equivalently replaced without departing from the spirit and scope of the technical solutions of the present utility model, and they should all be covered within the scope of the claims of the present utility model.

Claims

1. A high-speed and highly maneuverable target drone, comprising a fuselage (1), wings (2), horizontal tails (3), vertical tails (4), and an air inlet duct (5), characterized in that: The wing (2) is located in the middle of the fuselage (1), the horizontal tail (3) and vertical tail (4) are located at the rear of the fuselage (1), and the air inlet (5) is located in the mid-rear part of the fuselage (1).

2. The high-speed and highly maneuverable target drone according to claim 1, characterized in that: The fuselage (1) is divided into three parts: the front fuselage, the middle fuselage and the rear fuselage. The front fuselage is spherical and arc-shaped, the cross-section of the middle fuselage is trapezoidal, with a smooth longitudinal transition, and the rear fuselage is a convergent fairing shape.

3. A high-speed and highly maneuverable target drone according to claim 1, characterized in that: The wing (2) is a swept-back high wing, adopting a supercritical airfoil, with a wing root setting angle of 1.5°, a leading edge sweep angle of 33°, a dihedral angle of 4°, a spanwise negative twist of 2°, and the wing (2) is an integral wing.

4. A high-speed and highly maneuverable target drone according to claim 1, characterized in that: The horizontal tail (3) adopts a fully movable inverted V layout and can be used as a rudder and elevator at the same time. When the left and right wing surfaces deflect in the same direction, it is an elevator, and when they deflect in the opposite direction, it is a rudder; it adopts a symmetric airfoil, with a wing root setting angle of -1.5°, a leading edge sweep angle of 35°, and a dihedral angle of 30°.

5. A high-speed and highly maneuverable target drone according to claim 1, characterized in that: The vertical tail (4) adopts a symmetric airfoil and a design without control surfaces, with a leading edge sweep angle of 40°.

6. The high-speed and highly maneuverable target drone according to claim 1, wherein: The air inlet (5) adopts a back-mounted separated air inlet.

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