CN113753216A - Carrier-borne unmanned aerial vehicle platform configuration based on task modularization - Google Patents
Carrier-borne unmanned aerial vehicle platform configuration based on task modularization Download PDFInfo
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- CN113753216A CN113753216A CN202111102401.4A CN202111102401A CN113753216A CN 113753216 A CN113753216 A CN 113753216A CN 202111102401 A CN202111102401 A CN 202111102401A CN 113753216 A CN113753216 A CN 113753216A
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- 210000001015 abdomen Anatomy 0.000 claims abstract description 9
- 239000002828 fuel tank Substances 0.000 claims abstract description 9
- 230000008602 contraction Effects 0.000 claims abstract description 4
- 230000007704 transition Effects 0.000 claims description 4
- 239000012780 transparent material Substances 0.000 claims description 2
- 238000004321 preservation Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 21
- 238000005516 engineering process Methods 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 4
- 239000012050 conventional carrier Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/04—Arrangement thereof in or on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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Abstract
The application belongs to the technical field of aircraft structures, and particularly relates to a ship-borne unmanned aerial vehicle platform configuration based on task modularization. The abdomen of the fuselage is provided with inclined planes on two sides of the abdomen of the fuselage, so that the abdomen of the fuselage forms a self-to-down contraction structure, each inclined plane is provided with a mounting point, the mounting points can selectively mount an external fuel tank (12) or an early warning equipment cabin (13), the external fuel tank (12) and the early warning equipment cabin (13) are provided with outer wall surfaces parallel to the inclined planes after being mounted on the inclined planes, and the carrier-borne unmanned aerial vehicle platform further comprises a backpack turbofan engine (16), a fuel tank and an equipment cabin. The design of stealth, shape preservation and pressurization is adopted, the pneumatic performance, stealth performance and working efficiency of the carrier-borne unmanned aerial vehicle are improved, and the safety of autonomous carrier landing is guaranteed.
Description
Technical Field
The application belongs to the technical field of aircraft structures, and particularly relates to a ship-borne unmanned aerial vehicle platform configuration based on task modularization.
Background
The current military unmanned aerial vehicle has low flying speed and poor stealth performance, and the battlefield damage rate is higher. The conventional ship-based oiling machine and the ship-based early warning machine have the same problems and are easily attacked by enemies. The conventional carrier-based early warning aircraft has small combat radius and is difficult to realize remote early warning. Compared with the conventional carrier-based unmanned aerial vehicle, the carrier-based unmanned aerial vehicle has the advantages of low construction and use cost and no casualties. The shipborne unmanned early warning aircraft and the shipborne unmanned oiling machine can effectively improve the combat efficiency of aircraft carrier formation, but the weapon equipment is difficult to maintain due to various shipborne opportunities.
Disclosure of Invention
In order to solve the technical problems, the application provides a ship-borne unmanned aerial vehicle platform configuration based on task modularization, and a natural laminar flow design, stealth design and distributed conformal early warning radar antenna design technology is adopted, so that the pneumatic performance, stealth performance and working efficiency of the ship-borne unmanned aerial vehicle can be improved, and the safety of autonomous carrier landing is ensured. Based on a configuration design scheme of a ship-borne unmanned aerial vehicle platform with task modularization, a ship-borne unmanned aerial vehicle platform with good pneumatic and stealth performances is used for completing double tasks of remote early warning and refueling, and the cost-effectiveness ratio of the use of the ship-borne aircraft is effectively improved.
This application is based on task modularization's carrier-borne unmanned aerial vehicle platform configuration, including fuselage, wing and fin, the belly of fuselage has the inclined plane in both sides, so that the belly of fuselage forms from last contraction structure extremely down, the inclined plane has the carry point, the optional external oil tank of carry point or early warning equipment cabin, the external oil tank of carry and early warning equipment cabin are in the carry arrive after on the inclined plane, have with the parallel outer wall of inclined plane, carrier-borne unmanned aerial vehicle platform configuration still includes backpack turbofan engine, oil tank and equipment cabin.
Preferably, the outboard portion of the wing is provided in a swept 15 rectangular configuration.
Preferably, microstrip conformal phased-array antennas are mounted on the inner sides of the upper skin and the lower skin of the outer part of the wing and at the front beam.
Preferably, a helical conformal phased array antenna is mounted on the outer surface of the early warning equipment cabin.
Preferably, the tail wing is a V-shaped tail wing, the V-shaped tail wing comprises two wing pieces, an inclination angle between the two wing pieces is adjustable, and the inclination angle is 40-50 °.
Preferably, the tail fin is made of a wave-transmitting material and is installed at both sides of a rear end of a nozzle of the engine.
Preferably, the wings and the fuselage are in smooth transition design, and a natural laminar flow wing type design is adopted.
Preferably, the wings comprise an inner wing and an outer wing, the inner wing and the outer wing are connected through wing folding hinges, the outer wing can be folded upwards and backwards relative to the inner wing, telescopic wings are further arranged at the end portions of the outer wing, and the telescopic wings are arranged to extend out of or retract into an inner cavity of the outer wing along the wingspan direction of the aircraft.
Preferably, when the mounting point mounts the external fuel tank, the carrier-based unmanned aerial vehicle platform configuration has a first wing load and a first thrust ratio, when the mounting point mounts the warning equipment cabin, the carrier-based unmanned aerial vehicle platform configuration has a second wing load and a second thrust ratio, a smaller load of the first wing load and the second wing load is selected as a wing load constraint parameter of the carrier-based unmanned aerial vehicle platform configuration for platform design, and a larger thrust ratio of the first thrust ratio and the second thrust ratio is selected as a thrust ratio constraint parameter of the carrier-based unmanned aerial vehicle platform configuration for platform design.
Preferably, the oil tank comprises a fuselage oil tank and a wing oil tank, and the equipment cabin comprises a front fuselage equipment cabin positioned at the front part of the fuselage and a rear fuselage equipment cabin positioned at the rear part of the fuselage.
The pneumatic layout design scheme of the shipborne unmanned platform is based on the task modular design idea, and the shipborne unmanned platform, the early warning equipment cabin capable of being quickly disassembled and replaced and the externally-hung oil tank are adopted, so that double tasks of remote early warning and oiling are completed, and the cost-to-efficiency ratio of a shipborne aircraft is effectively improved. The design technology of the natural laminar flow design, the stealth design and the distributed conformal early warning radar antenna is adopted, the pneumatic performance, the stealth performance and the working efficiency of the carrier-borne unmanned aerial vehicle can be improved, and the safety of autonomous carrier landing is guaranteed.
Drawings
Fig. 1 is a schematic structural diagram of a preferred embodiment of the configuration of the ship-based unmanned aerial vehicle platform based on task modularization.
Fig. 2 is a left side view of the embodiment of fig. 1 of the present application.
Wherein, 1-inner side wing; 2-outboard airfoils; 3-telescopic wing; 4-high lift flaps; 5-flaperon; 6-ailerons; 7-wing folding hinges; 8-fuselage forward equipment bay; 9-fuselage rear equipment cabin; 10-fuselage fuel tanks; 11-wing tank; 12-externally hanging an oil tank; 13-early warning equipment cabin; 14-tail fin; 15-tail rudder surface; 16-backpack turbofan engine; 17-wing.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The utility model provides a pneumatic overall arrangement design of carrier-borne unmanned aerial vehicle platform provides technical support for this type of aircraft design.
The application provides a carrier-borne unmanned aerial vehicle platform configuration based on task modularization, as shown in fig. 1 and fig. 2, mainly include fuselage, wing 17 and fin 14, the belly of fuselage has the inclined plane in both sides, so that the belly of fuselage forms from last contraction structure extremely down, the inclined plane has the carry point, carry the external oil tank of the optional carry 12 or early warning equipment cabin 13 of point, carry the external oil tank of carry 12 and early warning equipment cabin 13 and arrive at carry after on the inclined plane, have with the parallel outer wall of inclined plane, carrier-borne unmanned aerial vehicle platform configuration still includes backpack turbofan engine 16, oil tank and equipment cabin.
The side surface of the platform body, the external oil tank or the early warning equipment cabin adopts a plane design with an inclination angle, such as the external oil tank or the early warning equipment cabin which is inclined inwards and downwards in the figure 2, so that the mirror reflection effect of radar waves is reduced. By adopting the shape-preserving design of the externally-hung oil tank and the early warning equipment cabin, the interference resistance between the task nacelle and the platform is reduced.
In some alternative embodiments, where the outboard portion of the wing 17 is configured in a 15 ° swept rectangular configuration, the parallel leading and trailing edges of the wing may be effective to reduce the RCS area.
In some alternative embodiments, microstrip conformal phased array antennas are mounted inside the upper and lower skins of the outboard portion of the wing 17 and at the front spar.
In some alternative embodiments, the outer surface of the pre-warning equipment compartment 13 is equipped with a helical conformal phased array antenna.
The application adopts a conformal antenna design technology, the antenna is conformal with the platform structure, and the resistance increment generated by the backpack large-scale early warning antenna is reduced, for example, the antenna is conformal with the wings, and is designed on the upper surface and the lower surface of the wings, and then the antenna and a task system are designed together like the conformal design of the antenna and a nacelle.
In some alternative embodiments, the tail 14 is a V-shaped tail, and the V-shaped tail includes two wings, and the inclination angle between the two wings is adjustable, and the inclination angle is 40-50 °, which can effectively reduce the RCS of the platform. In addition, the V-shaped empennage with the adjustable inclination angle can ensure the longitudinal stability and the pitching operation efficiency of the platform at different gravity centers and accurately control the landing flight path of the platform.
In some alternative embodiments, the tail fin 14 is made of a wave-transparent material and is mounted on both sides of the rear end of the nozzle of the engine. In the present application, the engine 16 is mounted above the rear body of the fuselage, the front fuselage preventing radar waves from impinging on the engine compressor; the nozzle of the engine is shielded by the two V-shaped empennages at the rear side surface, so that the infrared stealth performance can be improved.
In some optional embodiments, the wing 17 and the fuselage are designed to be in smooth transition, and a natural laminar flow airfoil design is adopted to enlarge a laminar flow area of the wing and reduce frictional resistance, and 2) a wing body fusion design technology (smooth transition) is adopted to reduce interference resistance of the wing body.
In some alternative embodiments, the wings 17 include an inner wing 1 and an outer wing 2, the inner wing 1 and the outer wing 2 are connected by a wing folding hinge 7, the outer wing 2 can be folded upwards and backwards relative to the inner wing 1, the end of the outer wing is further provided with a telescopic wing 3, and the telescopic wing 3 is arranged to extend out of or retract into an inner cavity of the outer wing 2 along the wingspan direction of the aircraft.
In the application, the outer section of the folding wing adopts a segmented and telescopic configuration design, the aspect ratio of a cruise configuration is increased, the induced resistance is reduced, for example, the wingspan of a landing configuration can be controlled below 22m, and the safety threat generated by the landing flight path deviation of a platform is reduced. On the other hand, the design of winglet loading is adopted, the landing approach speed of the platform is reduced, the impact load of landing the platform is reduced, and the design of winglet loading can obtain the expected winglet loading by optimizing the wing area.
In some optional embodiments, when the mounting point mounts the external fuel tank 12, the ship-based unmanned aerial vehicle platform configuration has a first wing load and a first thrust ratio, when the mounting point mounts the warning device cabin 13, the ship-based unmanned aerial vehicle platform configuration has a second wing load and a second thrust ratio, a smaller load of the first wing load and the second wing load is selected as a wing load constraint parameter of the ship-based unmanned aerial vehicle platform configuration for platform design, and a larger thrust ratio of the first thrust ratio and the second thrust ratio is selected as a thrust ratio constraint parameter of the ship-based unmanned aerial vehicle platform configuration for platform design.
The key technology of the configuration design of the application not only comprises the aspects of stealth design, pneumatic efficiency improvement and landing safety design, but also comprises a task system modular design part and a platform overall parameter design part. In the process of task system modular design, a refueling task management system is integrated in a fuel management system of a platform, a refueling pump, a refueling hose and other related equipment are positioned in an equipment cabin at the rear section of a machine body, a shape-preserving oil tank is respectively mounted on two sides of the machine body, in addition, the early warning task equipment cabin adopts a stealth, shape-preserving and pressurization design and is mounted on two sides of the machine body through a quick disassembly and assembly interface.
In the aspect of platform overall parameter design, the wing load of a platform is the minimum value of the wing load required by two task configurations (a ship-based oiling machine and a ship-based early warning machine), the thrust-weight ratio is the maximum value of the thrust-weight ratio required by the two task configurations, the platform fuel oil loading capacity is 1.08 times of the task fuel oil required by the early warning configuration, and the gravity center change range is not more than 10% of MAC (mean aerodynamic chord length of wings);
b) besides the design constraint of the conventional airplane, the design requirements of safety of autonomous carrier landing, adaptability of the airplane, stealth performance, compatibility of task performance and the like are also considered in the design of the platform configuration.
In some alternative embodiments, the oil tanks include fuselage oil tanks 10 and wing oil tanks 11, and the equipment bays include a front fuselage equipment bay 8 at the front of the fuselage and a rear fuselage equipment bay 9 at the rear of the fuselage.
According to the scheme provided by the invention, a dual-task carrier-borne unmanned aerial vehicle platform is designed, the pneumatic layout is shown in the figure 1 and the figure 2, and the design data is as follows:
1) performance indexes are as follows:
the radius of the early warning and refueling is not less than 950km, the minimum level flight speed is not more than 0.44Ma, the maximum level flight speed is not less than 0.62Ma, the landing approach speed is not more than 200km/h, and the lifting limit is not less than 15000 m. The air-leaving time of the early warning task mode is not less than 12h, and the available refueling time of the refueling task mode is not less than 7 t. The span of the landing configuration is not more than 22m, and the takeoff weight is not more than 20 t.
2) Overall platform parameters:
the takeoff weight of the platform is 16t, the weight of an empty aircraft is 8t, the weight of backup fuel oil is 500kg, and the maximum landing weight is 10 t. The takeoff weight of the early warning task mode is 16.8t, and the takeoff weight of the refueling task mode is 19.8 t. The wing area in the extended state of the inner wing is 55m2 and the wing area in the retracted state is 50m 2.
3) Wing configuration parameters:
the wing is composed of an inner side, an outer side and a telescopic wing 3 section. The wing span of the inner wing in a protruding state is 26.2m, and the aspect ratio is 12.5; the wing span of the inner wing in a retraction state is 20.6m, and the aspect ratio is 8.5; the sweep angle of the front edge of the inner side wing is 28 degrees, the sweep angle of the rear edge is 11 degrees, the root ratio is 0.5, the half span length is 3.5m, a supercritical wing type is adopted, the thickness is 0.18, and the connection part of the inner side wing and the outer side wing is a wing folding hinge; the sweep angle of the front edge and the rear edge of the outer wing is 15 degrees, the root-to-root ratio is 1, the half span length is 6.9m, the wing chord length is 2.3m, and the thickness is 0.15 by adopting an NACA64 laminar flow airfoil profile; the sweepback angle and the root ratio of the telescopic wing are the same as those of an airfoil and an outer wing, the semi-span of the extending section is 2.8m, the chord length of the wing is 0.95m, and the thickness of the wing is 0.11.
4) Fuselage parameters and wing control surface configuration:
the length of the fuselage is 15.5m, the width is 1.5m, and the height is 1.38 m. The drift angle of the flap with take-off configuration and the flaperon is 22 degrees, the drift angle of the flap with landing configuration and the flaperon is 33 degrees, and the drift angle of the flap with refueling stage is adjusted between 0 degree and 15 degrees according to the difference of required flat flight speeds;
5) parameters of a power system:
the turbofan engine has a bypass ratio of 5, a maximum thrust of 53.8KN and 12000m, and the fuel consumption of 0.6MA is 0.66 kg/kgf.h.
6) And (3) tail configuration parameters:
the area of the tail wing is 18m2, the front edge is swept backward by 16 degrees, the rear edge is swept forward by 10 degrees, the root ratio is 0.38, the thickness is 0.1, and a NACA64 laminar flow wing profile is adopted. The inclination angle of the tail wing can be adjusted between 40 degrees and 50 degrees.
7) Early warning equipment compartment parameters:
the length of the equipment cabin is 6.6m, the width is 0.35m, the height is 1.2m, and the weight of the two early warning equipment cabins is 800 kg.
8) Conformal early warning antenna parameters:
the antenna on the inner side of the upper skin and the inner side of the lower skin of the microstrip conformal phased array radar antenna installed on the outer wing is 6.6m long, 1.1m wide and 38mm thick, and the leading edge antenna is 6.2m long, 30cm high and 33mm thick. The conformal phased array radar antenna of spiral of fuselage both sides installation, long 6.2m, high 1m, thickness 60 mm.
9) The parameters of the conformal external oil tank are as follows:
the length of the oil tank is 7.6m, the width is 0.5m, the height is 1m, the two conformal oil tanks weigh 200kg, and 3.6t of fuel oil can be loaded.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a carrier-borne unmanned aerial vehicle platform configuration based on task modularization, includes fuselage, wing (17) and fin (14), its characterized in that, the belly of fuselage has the inclined plane in both sides, so that the belly of fuselage forms from last contraction structure to down, the inclined plane has the carry point, carry the optional carry external fuel tank (12) of point or early warning equipment cabin (13), carry external fuel tank (12) and early warning equipment cabin (13) after the carry arrives on the inclined plane, have with the outer wall surface that the inclined plane is parallel, carrier-borne unmanned aerial vehicle platform configuration still includes backpack turbofan engine (16), oil tank and equipment cabin.
2. The mission-based modular shipboard drone platform configuration according to claim 1, characterized in that the outer part of the wings (17) is arranged in a rectangular configuration with a sweep of 15 °.
3. The task-based modular ship-based unmanned aerial vehicle platform configuration of claim 1, wherein microstrip conformal phased array antennas are installed at the inner sides of the upper and lower skins of the outer part of the wing (17) and the front beam.
4. The task-based modular shipboard unmanned aerial vehicle platform configuration of claim 1, wherein an outer surface of the early warning equipment bay (13) is mounted with a helical conformal phased array antenna.
5. The mission-based modular shipboard unmanned aerial vehicle platform configuration of claim 4, wherein the tail wing (14) is provided as a V-shaped tail wing, the V-shaped tail wing comprises two wing panels, the inclination angle between the two wing panels is adjustable, and the inclination angle is 40-50 degrees.
6. The mission-based modular shipboard unmanned aerial vehicle platform configuration of claim 5, wherein the empennage (14) is made of wave-transparent material and is installed on both sides of the rear end of the nozzle of the engine.
7. The task-based modular shipboard unmanned aerial vehicle platform configuration of claim 1, wherein the wings (17) and the fuselage are designed in smooth transition and adopt a natural laminar flow airfoil design.
8. The mission-based modular shipboard unmanned aerial vehicle platform configuration of claim 1, wherein the wings (17) comprise an inner wing (1) and an outer wing (2), the inner wing (1) and the outer wing (2) are connected through wing folding hinges (7), the outer wing (2) can be folded upwards and backwards relative to the inner wing (1), and a telescopic wing (3) is further arranged at the end of the outer wing, and the telescopic wing (3) is arranged to extend out of or retract into an inner cavity of the outer wing (2) along the wingspan direction.
9. The task modularization-based carrier-based unmanned aerial vehicle platform configuration of claim 1, wherein when the mounting point mounts the external fuel tank (12), the carrier-based unmanned aerial vehicle platform configuration has a first wing load and a first thrust-weight ratio, when the mounting point mounts the early warning equipment cabin (13), the carrier-based unmanned aerial vehicle platform configuration has a second wing load and a second thrust-weight ratio, a smaller load of the first wing load and the second wing load is selected as a wing load constraint parameter of the carrier-based unmanned aerial vehicle platform configuration for platform design, and a larger thrust-weight ratio of the first thrust-weight ratio and the second thrust-weight ratio is selected as a thrust-weight ratio constraint parameter of the carrier-based unmanned aerial vehicle platform configuration for platform design.
10. The task-based modular shipboard unmanned aerial vehicle platform configuration of claim 1, wherein the oil tanks comprise fuselage oil tanks (10) and wing oil tanks (11), and the equipment bay comprises a front fuselage equipment bay (8) at the front part of the fuselage and a rear fuselage equipment bay (9) at the rear part of the fuselage.
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