Multifunctional patrol flying device

Abstract

The invention relates to the technical field of patrol flight devices, in particular to a multifunctional patrol flight device which comprises a projectile body, the head of the projectile body is a rotating body, a generatrix of the head of the projectile body comprises an arc and a power exponent curve which are sequentially distributed from front to back, and the arc and the power exponent curve are in tangent transition. The method can have good aerodynamic characteristics matched with task attributes in different flight stages, and is suitable for various combat environments and application scenes.

Description

Technical Field

[0001] The present invention relates to the technical field of cruise vehicles, and specifically to a multi-functional cruise vehicle. Background Art

[0002] The common features of new unmanned cruise vehicles include low cost, convenient carrying, remote control, low-speed cruising, integrated surveillance and strike, and swarm attack. However, due to task attributes and structural design, several current representative cruise vehicles only focus on one aspect of characteristics and cannot meet the multi-task attribute usage scenarios. Summary of the Invention

[0003] The present invention aims to provide a multi-functional cruise vehicle that can have good aerodynamic characteristics matching the task attributes in different flight stages and is applicable to various combat environments and application scenarios.

[0004] To solve the above technical problems, the specific solution adopted by the present invention is as follows: A multi-functional cruise vehicle includes a fuselage. The head of the fuselage is a body of revolution. The generatrix of the head of the fuselage includes an arc and a power-exponential curve that are sequentially distributed from front to back, and the arc and the power-exponential curve are tangent and transition.

[0005] Preferably, the radius of the arc is 70 - 80 mm, the circumferential length of the power-exponential curve is 380 - 420 mm, and the maximum radius is 120 - 130 mm.

[0006] Preferably, a cruise wing is provided on the fuselage. The cruise wing is an asymmetric convex wing with a thickness of 11.5 - 13 mm, the position of the maximum thickness is 36 - 39 mm from the leading edge to the trailing edge direction, the camber is 9.6 - 10.4 mm, the position of the maximum camber is 59 - 64 mm from the leading edge to the trailing edge direction, the leading edge radius is 2.3 - 2.9 mm, the trailing edge angle is 28.6° - 31.4°, the span is 2750 - 2850 mm, and the chord length is 160 - 170 mm.

[0007] Preferably, a wing box for connecting the cruise wing is provided on the fuselage, and the front part and both sides of the wing box are transitionally connected to the fuselage through a streamline-shaped curved surface.

[0008] Preferably, the base of the cruise wing is connected to the wing box through an explosive device, and the explosive device can blast the cruise wing off the wing box.

[0009] Preferably, the fuselage includes a front cabin and a tail cabin that are both bodies of revolution. The front cabin and the tail cabin are transitionally connected through a smooth inclined plane. The length of the front cabin is 1300 - 1400 mm, the diameter is 380 - 420 mm, the length of the tail cabin is 1100 - 1200 mm, and the diameter is 230 - 250.

[0010] Preferably, a propeller is provided at the tail end of the fuselage.

[0011] Preferably, the rear part of the projectile body is successively provided with fins and control surfaces from front to back; the fins and control surfaces are distributed in an X shape with respect to the central axis of the projectile body.

[0012] Preferably, the fin is a flat plate airfoil in the shape of a right trapezoid, with the chord length of the upper bottom surface being 610 - 620 mm, the chord length of the lower bottom surface being 745 - 755 mm, the span being 420 - 430 mm, and the thickness being 4 - 6 mm.

[0013] Preferably, the control surface is a flat plate airfoil in the shape of a rectangle, with the chord length being 210 - 220 mm.

[0014] The present invention can be divided into two structural states according to different flight missions. In the loitering state, the loitering wings, fins, and control surfaces are fully deployed. A pair of loitering wings are distributed on both sides of the projectile body in a "one - character" shape, and the fins and control surfaces are circumferentially evenly distributed at the tail of the projectile body in an "X - shape". The flight power is provided by the tail propeller. This state has a high lift - to - drag ratio and static stability, and can meet the mission requirements of long endurance and long range. By carrying different tactical modules, it can perform tasks such as firepower reconnaissance, air defense early warning, signal relay, and camouflage tactical targets. In the attack state, the two - side loitering wings are cut off, and the projectile body, fins, and control surfaces form a tailless aerodynamic configuration. At this time, it has low resistance and high normal overload characteristics, enabling high - maneuverability and flexibility at the end of the attack, and can perform precision guided ground attacks or "suicide" bomb missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 is the front view structural schematic diagram of a multi - functional loitering vehicle of the present invention;

[0016] Figure 2 is Figure 1 the right view of

[0017] Figure 3 is the state schematic diagram of a multi - functional loitering vehicle of the present invention in the loitering state;

[0018] Figure 4 is the state schematic diagram of a multi - functional loitering vehicle of the present invention in the attack state;

[0019] Figure 5 is the power - index curve graph of the head of a multi - functional loitering vehicle of the present invention;

[0020] Figure 6 is the zero - lift drag comparison graph of the head bus of a multi - functional loitering vehicle of the present invention with two other head buses;

[0021] Figure 7 is the sectional view structural schematic diagram of the loitering wing of a multi - functional loitering vehicle of the present invention;

[0022] Figure 8Lift comparison diagram of the cruise wing of a multi-functional cruise vehicle of the present invention and two other cruise wings;

[0023] Figure 9 Drag-lift ratio comparison diagram of the cruise wing of a multi-functional cruise vehicle of the present invention and two other cruise wings;

[0024] Figure 10 Normal overload comparison diagram of the attack section balance method of a multi-functional cruise vehicle of the present invention;

[0025] Markings in the figure: 1. Head of the arc section, 2. Head of the power exponent curve, 3. Front cabin, 4. Wing box, 5. Tail cabin, 6. Tail wing, 7. Rudder surface, 8. Propeller, 9. Cruise wing; Detailed implementation manners

[0026] As Figure 1-2 shown, the designed outer shape of a multi-functional cruise vehicle of the present invention is divided into two structural states according to different flight missions. As Figure 3 shown, in the cruise state, the cruise wing 9, the tail wing 6 and the rudder surface 7 are fully deployed. A pair of cruise wings 9 are distributed on both sides of the cruise vehicle in a "one-word" shape. The tail wing 6 and the rudder surface 7 are circumferentially evenly distributed in the form of "X" in the tail cabin 5 of the projectile body. The flight power is provided by the tail propeller 8. This state has a high drag-lift ratio and static stability, and can meet the mission requirements of long endurance and long range. By carrying different tactical modules, it can perform tasks such as firepower reconnaissance, air defense early warning, signal relay, and camouflage tactical targets. As Figure 4 shown, in the attack state, the two-sided cruise wings 9 are cut off by the root detonating lock or other explosive devices, and the projectile body, the tail wing 6 and the rudder surface 7 form a tailless aerodynamic shape. At this time, it has the characteristics of low resistance and large normal overload, so that the attack end has high maneuverability and flexibility, and can perform ground precision guided attack or "suicide" bomb mission.

[0027] The above-mentioned projectile body is a spin body, mainly including a front cabin 3 and a tail cabin 5. The length of the front cabin 3 is 1300 - 1400 mm, the diameter is 380 - 420 mm, the length of the tail cabin 5 is 1100 - 1200 mm, the diameter is 230 - 250 mm, and the front cabin 3 and the tail cabin 5 are transitioned through a smooth inclined plane.

[0028] The head bus of the front cabin is formed by the tangential transition combination of two curves to form the head of the arc section 1 and the head of the power exponent curve 2: The main part of the bus is a power exponent curve with an axial length of 380 - 420 mm and a maximum radius of 120 - 130 mm. To ensure head drag reduction and a large space, a section of arc with a radius of 70 - 80 mm is added at the front end of the power exponent curve to be tangent to it for transition, ensuring the smooth connection of the head bus. The above-mentioned power exponent curve equation is:

[0029]

[0030] In the formula, L represents the total length of the power exponential curve, D represents the projectile diameter, n represents the exponent, the X value represents the horizontal coordinate point of the power exponential curve, the Y value represents the vertical coordinate point of the power exponential curve, and the final series of (X, Y) coordinate points are the values of the power exponential curve in the two-dimensional coordinate axis.

[0031] In the present invention, according to the optimal drag reduction design of the loitering munition, the length-to-diameter ratio of its head is 1:(1.6 - 1.8), the value range of D is 230 - 250 mm, the value range of L is D*(1.6 - 1.8)=380 - 420 mm, the value range of n is 2.3 - 2.6. After determining the front part size of the power exponential curve, the head arc diameter is 70 - 80 mm, the length is 40 - 50 mm, and finally the curve profile of the loitering device is determined.

[0032] Compared with the commonly used arc head and "arc + conic line" head schemes, the present invention has lower zero-lift drag at the typical cruising state altitude of 1 Km, speed of 0.3 Ma, and rudder deflection angle 、angle of attack when the sizes are the same, and the comparison is as Figure 6 shown.

[0033] The zero-lift drag can be divided into two parts: frictional drag and pressure drag. When the loitering device is flying at a low speed, the drag is related to the viscosity of the air and the flow of the boundary layer, that is, the frictional drag accounts for the main proportion. The zero-lift drag is related to the relative thickness , and its calculation formula is as follows:

[0034]

[0035] In the formula, D is the zero-lift drag, is the air density, V is the flight speed, S is the characteristic area, is the zero-lift drag coefficient.

[0036] The above-mentioned front cabin 3 is provided with a wing box 4. The wing box 4 adopts the upper single-wing installation method. The front part and both sides of the wing box 4 are transitioned with the shell of the front cabin 3 through a streamline surface. Considering the shell strength and stress concentration in the actual assembly process, the rear part extends to the end of the front cabin 3 without interfering with the transition section between the front cabin 3 and the tail cabin 5. The inside of the wing box 4 provides sufficient space for the folding and assembly mechanism of the loitering wing 9.

[0037] As Figure 7 shown, the loitering wing 9 of the present invention adopts an asymmetric convex airfoil, which has a high lift-to-drag ratio. Due to the size limitation after the loitering wing 9 is folded, through the calculation of the projectile diameter and projectile length dimensions, the maximum dimension of its span is 2900 mm, and the maximum dimension of the chord length is 200 mm. At the same time, in order to meet the lift requirement, the designed dimensions of the loitering wing 9 are determined to be a span of 2750 - 2850 mm and a chord length of 160 - 170 mm.

[0038] The design dimensions of the loitering wing 9 refer to Figure 7 As shown, the thickness c is 11.5 - 13 mm, the position of the maximum thickness Xc is 36 - 39 mm, the camber f is 9.6 - 10.4 mm, the position of the maximum camber Xf is 59 - 64 mm, the leading edge radius is 2.3 - 2.9 mm, the trailing edge angle is 28.6° - 31.4°. In the typical cruise state, the lift-drag ratio is increased by 30.3% compared with the flat wing and symmetric airfoil of the same size. The comparison of its lift and lift-drag ratio is as Figure 8 and Figure 9 As shown, the comparison of the balanced normal overload in the attack section is as Figure 10 shown.

[0039] When the loitering aircraft is flying, the air flows through the upper and lower surfaces of the wing. Since the loitering wing 9 is an airfoil with camber, the air flow velocities through the upper and lower wing surfaces are different, generating a pressure difference on the upper and lower surfaces of the wing. The force that lifts the wing upward is the lift, and its calculation formula is as follows:

[0040]

[0041] In the formula, L is the lift, Lift coefficient.

[0042] Each component of the loitering aircraft will generate lift and drag. To better describe the relationship between the lift and drag of the aircraft, the lift-drag ratio is generally used for description. The lift-drag ratio formula is as follows:

[0043]

[0044] Normal overload refers to the resultant force of all forces acting on the aircraft except gravity. The force perpendicular to the velocity direction is called normal overload. The greater the normal overload, the greater the normal acceleration that the aircraft can generate. At the same speed, the greater the ability of the aircraft to change its flight direction, that is, the aircraft can perform a more curved ballistic flight.

[0045] The above-mentioned tail fin 6 adopts a right-angled trapezoidal wing surface with a flat airfoil type, and is circumferentially distributed around the outside of the tail compartment 5 in an "X" shape. The chord length of the upper bottom surface is 610 - 620 mm, the chord length of the lower bottom surface is 745 - 755 mm, the span of the tail fin 6 is 420 - 430 mm, and the thickness is 4 - 6 mm. Chamfering and drag reduction treatments are carried out at the leading edge and the upper bottom surface of the tail fin 6. The four tail fins 6 provide 31.6% and 43.5% of the total missile lift respectively in the loitering section and the attack section.

[0046] The above-mentioned control surface 7 adopts a rectangular shape with a flat airfoil type, and is also circumferentially distributed around the outside of the tail compartment 5 in an "X" shape. The chord length of the control surface 7 is 210 - 220 mm. The thickness and span of the control surface 7 are the same as those of the tail fin 6, and only chamfering and drag reduction treatment are carried out at the top.

[0047] Based on the above technical solutions, the technical advantages of the present invention are as follows:

[0048] 1. Multi-task attribute design

[0049] The present invention belongs to the design of medium-sized cruise vehicles. The overall design mass of the whole missile is about (150-200) kg, and it has a modular inner cabin. By carrying different mission modules such as power batteries, reconnaissance equipment, relay navigation, and high-explosive warheads, it can complete single or combined tasks such as intelligence reconnaissance, firepower guidance, signal relay, and "suicide" bomb attacks.

[0050] 2. Large lift surface design

[0051] In the present invention, multiple groups of lift surfaces are adopted, including two cruise wings 9, four tail fins 6, and four control surfaces 7. Among them, the cruise wings 9 adopt an asymmetric convex airfoil with a large aspect ratio, which has an extremely high lift-drag ratio at typical cruise speeds. The four "X-shaped" arranged tail fins 6 ensure the flight stability of the missile body during the cruise phase while providing a large lift. The design of the rectangular control surface 7 ensures the efficiency of the servo and guarantees sufficient overload capacity during maneuvers.

[0052] 3. Multiple drag reduction designs

[0053] In the present invention, multiple drag reduction designs are adopted, including the "arc + power exponent" curve design at the head, the streamlined drag reduction design of the wing box 4, the smooth transition section design of the front cabin 3 and the tail cabin 5, and the chamfer design of the tail fin surface 6 and the control surface 7. By reducing the drag coefficient, the overall lift-drag ratio of the cruise vehicle is improved.

[0054] 4. Long endurance and long range design

[0055] Through the drag reduction and large lift design, the present invention increases the hovering time of the cruise vehicle by 43% compared with the same type, has a longer range, reduces the single-use cost, and improves the mission cost-effectiveness ratio of combat.

Claims

1. A multifunctional patrol aircraft, comprising a body, characterized in that: The head of the projectile body is a spiral body, and the generatrix of the head of the projectile body includes circular arcs and power exponential curves distributed in sequence from front to back, and the circular arcs and the power exponential curves are tangently transitioned.

2. A multifunctional patrol aircraft as claimed in claim 1, characterized in that: The radius of the arc is 70-80 mm, the axial length of the power exponential curve is 380-420 mm, and the maximum radius is 120-130 mm.

3. The multifunctional patrol aircraft according to claim 1, characterized in that: The missile body is provided with a patrol wing (9), which is an asymmetric convex wing with a thickness of 11.5-13 mm, a maximum thickness position at 36-39 mm from the leading edge to the trailing edge, a curvature of 9.6-10.4 mm, a maximum curvature position at 59-64 mm from the leading edge to the trailing edge, a leading edge radius of 2.3-2.9 mm, a trailing edge angle of 28.6°-31.4°, a span of 2750-2850 mm, and a chord length of 160-170 mm.

4. A multifunctional patrol aircraft as claimed in claim 3, characterized in that: The body of the missile is provided with a wing box (4) for connecting the cruising wing (9), and the front part and both sides of the wing box (4) are transitionally connected to the body of the missile through streamlined curved surfaces.

5. A multifunctional patrol aircraft as claimed in claim 4, characterized in that: The base of the cruising wing (9) is connected to the wing box (4) via an explosive device, and the explosive device can blow the cruising wing (9) off the wing box (4).

6. The multifunctional patrol aircraft according to claim 1, characterized in that: The projectile body comprises a front cabin (3) and a tail cabin (5) both of which are screw-in bodies. The front cabin (3) and the tail cabin (5) are connected by a smooth inclined transition. The length of the front cabin (3) is 1300-1400 mm and the diameter is 380-420 mm. The length of the tail cabin (5) is 1100-1200 mm and the diameter is 230-250 mm.

7. The multifunctional patrol aircraft according to claim 1, characterized in that: A propeller (8) is provided at the rear end of the projectile body.

8. The multifunctional patrol aircraft according to claim 1, characterized in that: The rear part of the projectile is provided with a tail wing (6) and a rudder surface (7) in sequence from front to rear; the tail wing (6) and the rudder surface (7) are respectively distributed in an X shape with respect to the central axis of the projectile body.

9. A multifunctional patrol aircraft as claimed in claim 8, characterized in that: The tail wing (6) is a right-angled trapezoidal flat airfoil, with an upper bottom surface chord length of 610-620 mm, a lower bottom surface chord length of 745-755 mm, a span of 420-430 mm, and a thickness of 4-6 mm.

10. The multifunctional patrol aircraft according to claim 8, characterized in that: The rudder surface (7) is a rectangular flat airfoil with a chord length of 210-220 mm.

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