CN113753216B - Ship-borne unmanned aerial vehicle platform configuration based on task modularization - Google Patents
Ship-borne unmanned aerial vehicle platform configuration based on task modularization Download PDFInfo
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- CN113753216B CN113753216B CN202111102401.4A CN202111102401A CN113753216B CN 113753216 B CN113753216 B CN 113753216B CN 202111102401 A CN202111102401 A CN 202111102401A CN 113753216 B CN113753216 B CN 113753216B
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- 210000001015 abdomen Anatomy 0.000 claims abstract description 8
- 239000002828 fuel tank Substances 0.000 claims description 8
- 230000007704 transition Effects 0.000 claims description 4
- 239000012780 transparent material Substances 0.000 claims description 3
- 230000008602 contraction Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 18
- 238000005516 engineering process Methods 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 230000009977 dual effect Effects 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000012050 conventional carrier Substances 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The application belongs to the technical field of aircraft structures, and particularly relates to a carrier-borne unmanned aerial vehicle platform configuration based on task modularization. This configuration has the inclined plane in the belly of fuselage in both sides to make the belly of fuselage form from top to bottom contraction structure, the inclined plane has the mount point, mount the externally hung oil tank (12) of the optional mount of point or early warning equipment cabin (13), externally hung oil tank (12) of mount and early warning equipment cabin (13) after mounting to on the inclined plane have with the outer wall surface of inclined plane parallel, carrier-borne unmanned aerial vehicle platform configuration still includes knapsack formula turbofan engine (16), oil tank and equipment cabin. The application adopts stealth, shape-preserving and pressurizing design, improves the pneumatic performance, stealth performance and working efficiency of the carrier-borne unmanned aerial vehicle, and ensures the safety of autonomous carrier landing.
Description
Technical Field
The application belongs to the technical field of aircraft structures, and particularly relates to a carrier-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, so that 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 easy to attack by enemies. The conventional carrier-based early warning machine has small operational radius and is difficult to realize remote early warning. Compared with the conventional carrier-borne unmanned aerial vehicle, the carrier-borne unmanned aerial vehicle has the advantages of low construction and use cost and no casualties. The carrier-based unmanned early warning aircraft and the carrier-based unmanned oiling aircraft can effectively improve the fight efficiency of aircraft carrier formation, but the maintenance of weaponry is difficult due to the multiple carrier-based opportunities.
Disclosure of Invention
In order to solve the technical problems, the application provides a carrier-borne unmanned aerial vehicle platform configuration based on task modularization, which adopts natural laminar flow design, stealth design and distributed conformal early warning radar antenna design technology, can improve the aerodynamic performance, stealth performance and working efficiency of the carrier-borne unmanned aerial vehicle, and ensures the safety of autonomous landing of the carrier-borne unmanned aerial vehicle. Based on the configuration design scheme of the task modularization ship-borne unmanned aerial vehicle platform, the one-type ship-borne unmanned aerial vehicle platform with good pneumatic and stealth performance is used for completing the dual tasks of remote early warning and oiling, and the cost-effectiveness ratio of the ship-borne unmanned aerial vehicle is effectively improved.
The application discloses a task modularization-based carrier-borne unmanned aerial vehicle platform configuration, which comprises a fuselage, wings and a tail wing, wherein inclined planes are arranged on two sides of the belly of the fuselage so that the belly of the fuselage forms a top-down shrinkage structure, the inclined planes are provided with mounting points, the mounting points can selectively mount an externally hung oil tank or an early warning equipment cabin, the externally hung oil tank and the early warning equipment cabin 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 configuration further comprises a backpack turbofan engine, an oil tank and an equipment cabin.
Preferably, the outboard portion of the wing is disposed in a 15 swept rectangular configuration.
Preferably, microstrip conformal phased array antennas are installed at the inner sides of the upper and lower skins and the front beam of the outer side part of the wing.
Preferably, a spiral conformal phased array antenna is mounted on the outer surface of the early warning equipment cabin.
Preferably, the tail fin is arranged as a V-shaped tail fin, the V-shaped tail fin comprises two fins, the inclination angle between the two fins is adjustable, and the inclination angle is 40-50 degrees.
Preferably, the tail fin is made of wave-transparent materials and is arranged on two sides of the rear end of a nozzle of the engine.
Preferably, the wing and the fuselage are designed in a smooth transition manner, and a natural laminar flow airfoil design is adopted.
Preferably, the wing comprises an inner wing and an outer wing, the inner wing and the outer wing are connected through a wing folding hinge, the outer wing can be folded upwards and backwards relative to the inner wing, the end part of the outer wing is further provided with a telescopic wing, and the telescopic wing is arranged to extend out or retract into an inner cavity of the outer wing along the wing span.
Preferably, when the mounting point mounts the external hanging oil tank, the carrier-borne unmanned aerial vehicle platform configuration has a first wing load and a first thrust-weight ratio, when the mounting point mounts the pre-warning device cabin, the carrier-borne 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-borne unmanned aerial vehicle platform configuration to carry out 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-borne unmanned aerial vehicle platform configuration to carry out 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 carrier-based unmanned platform provided by the application is based on the task modularization design thought, adopts the carrier-based unmanned platform, the early warning equipment cabin capable of being quickly assembled, disassembled and replaced and the externally hung oil tank, completes the dual tasks of remote early warning and oiling, and effectively improves the cost-effectiveness ratio of the carrier-based aircraft. According to the application, the pneumatic performance, stealth performance and working efficiency of the carrier-based unmanned aerial vehicle can be improved by adopting the natural laminar flow design, stealth design and distributed conformal early warning radar antenna design technology, and the safety of autonomous carrier landing of the carrier-based unmanned aerial vehicle is ensured.
Drawings
FIG. 1 is a schematic structural view of a preferred embodiment of the task-based modular unmanned aerial vehicle platform configuration of the present application.
Fig. 2 is a left side view of the embodiment of the application shown in fig. 1.
Wherein, 1-inner measuring wing; 2-outboard wings; 3-telescoping wings; 4-high lift flaps; 5-flap aileron; 6-ailerons; 7-wing folding hinges; 8-a front equipment bay of the fuselage; 9-a rear equipment compartment of the fuselage; 10-a fuselage tank; 11-wing oil tanks; 12-an externally hung oil tank; 13-an early warning equipment cabin; 14-tail wing; 15-tail control surface; 16-backpack turbofan engine; 17-wing.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail 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 application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, based on the embodiments of the application, which are apparent to those of ordinary skill in the art without inventive faculty, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application aims to provide a pneumatic layout design scheme of a carrier-borne unmanned aerial vehicle platform, and provides technical support for such aircraft design.
The application provides a task modularization-based carrier-borne unmanned aerial vehicle platform configuration, which mainly comprises a machine body, wings 17 and tail wings 14, wherein the two sides of the belly of the machine body are provided with inclined planes, so that the belly of the machine body forms a top-down shrinkage structure, the inclined planes are provided with mounting points, the mounting points can selectively mount an externally hung oil tank 12 or an early warning equipment cabin 13, the externally hung oil 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 configuration further comprises a knapsack turbofan engine 16, an oil tank and an 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 inclined angle, such as the external oil tank or the early warning equipment cabin which is inclined inwards and downwards in fig. 2, so that the mirror reflection effect of radar waves is reduced. By adopting the conformal design of the externally hung oil tank and the early warning equipment cabin, the interference resistance of the mission pod and the platform is reduced.
In some alternative embodiments, the outboard portion of the wing 17 is configured in a 15 ° swept rectangular configuration, with parallel wing leading and trailing edges effective to reduce the RCS area.
In some alternative embodiments, microstrip conformal phased array antennas are mounted on the inner sides of the upper and lower skins and at the front spar of the outer portion of the wing 17.
In some alternative embodiments, the external surface of the pre-warning device compartment 13 is fitted with a helical conformal phased array antenna.
The application adopts a conformal antenna design technology, the antenna is conformal with the platform structure, the resistance increment generated by the backpack type large-scale early warning antenna is reduced, for example, the antenna is conformal with the wing, the antenna is designed on the upper surface and the lower surface of the wing, and the antenna and the task system are designed together.
In some alternative embodiments, the tail 14 is configured as a V-shaped tail, the V-shaped tail includes two fins, and the inclination angle between the two fins is adjustable, and the inclination angle is 40 ° to 50 °, so that the RCS of the platform can be effectively reduced. In addition, the inclination angle adjustable V-shaped tail wing can ensure the longitudinal stability and pitching operation efficiency of platforms at different gravity centers and accurately control the landing track of the platforms.
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 jet of the engine. In the present application, the engine 16 is installed above the rear body of the front body, which can prevent the radar wave from being irradiated to the engine compressor; the nozzle of the engine is blocked by the two V-shaped tail wings at the rear side face, so that the infrared stealth performance can be improved.
In some alternative embodiments, the wing 17 and the fuselage are designed in a smooth transition mode, a natural laminar flow wing profile design is adopted, a wing laminar flow area is enlarged, friction resistance is reduced, and 2) a wing body fusion design technology (smooth transition) is adopted, so that wing body interference resistance is reduced.
In some alternative embodiments, the wing 17 includes 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 outer wing end is further provided with a telescopic wing 3, and the telescopic wing 3 is configured to extend or retract into an inner cavity of the outer wing 2 along the machine span.
In the application, the outer section of the folding wing adopts a sectional and telescopic configuration design, the aspect ratio of the cruising configuration is increased, the induced resistance is reduced, for example, the wingspan of the landing configuration can be controlled below 22m, and the safety threat caused by the deviation of the landing track of the platform is reduced. On the other hand, the application adopts the design of the winglet carrier, reduces the landing speed of the platform carrier, reduces the impact load of the platform carrier, and can obtain the expected winglet carrier by optimizing the area of the wing.
In some optional embodiments, when the mounting point mounts the external hanging oil tank 12, the carrier-borne unmanned aerial vehicle platform configuration has a first wing load and a first thrust-weight ratio, when the mounting point mounts the pre-warning equipment cabin 13, the carrier-borne 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-borne unmanned aerial vehicle platform configuration to carry out 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-borne unmanned aerial vehicle platform configuration to carry out platform design.
The key technology of the configuration design of the application comprises a task system modularized design and a platform overall parameter design part besides the aspects of stealth design, pneumatic efficiency improvement and landing safety design. In the modularized design process of the mission system, the oiling mission management system is integrated in the fuel management system of the platform, the oiling pump, the oiling hose and other related equipment are positioned in the equipment cabin at the rear section of the fuselage, the two sides of the fuselage are respectively provided with a conformal oil tank, in addition, the pre-warning mission equipment cabin adopts stealth, conformal and supercharging design, and is hung on the two sides of the fuselage through a quick-dismounting interface.
In the aspect of overall parameter design of a platform, the wing load of the platform takes the minimum value of the wing load required by two task configurations (a carrier-based oiling machine and a carrier-based early warning machine), the thrust-weight ratio takes the maximum value of the thrust-weight ratio required by the two task configurations, the loading capacity of the fuel oil of the platform is 1.08 times of that of the task fuel oil required by the early warning configuration, and the variation range of the gravity center is not more than 10 percent of MAC (average aerodynamic chord length of the wing);
b) Besides the conventional aircraft design constraint, the platform configuration design also considers design requirements such as the safety of autonomous landing, the suitability of the aircraft, the compatibility of stealth performance and mission performance and the like.
In some alternative embodiments, the fuel tanks include a fuselage fuel tank 10 and a wing fuel tank 11, and the equipment tanks include a front fuselage equipment tank 8 at the front of the fuselage and a rear fuselage equipment tank 9 at the rear of the fuselage.
According to the scheme provided by the application, the dual-task carrier-borne unmanned aerial vehicle platform is designed, the pneumatic layout is shown in fig. 1 and 2, and the design data are as follows:
1) Performance index:
the early warning and refueling radius is not less than 950km, the minimum flat flying speed is not more than 0.44Ma, the maximum flat flying speed is not less than 0.62Ma, the landing approach speed is not more than 200km/h, and the rising limit is not less than 15000m. The blank time of the early warning task mode is not less than 12h, and the available refueling of the refueling task mode is not less than 7t. The wingspan of the ship landing configuration is not more than 22m, and the takeoff weight is not more than 20t.
2) Platform overall parameters:
the landing weight of the platform is 16t, the aircraft weight is 8t, the standby fuel weight is 500kg, and the maximum landing weight is 10t. The take-off weight of the early warning task mode is 16.8t, and the take-off weight of the oiling task mode is 19.8t. The wing area of the extended state of the inner wing is 55m2, and the wing area of the retracted state is 50m2.
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 internal wing in the extending state is 26.2m, and the aspect ratio is 12.5; the wing span of the inner wing in the retracted state is 20.6m, and the aspect ratio is 8.5; the sweepback angle of the front edge of the inner side wing is 28 degrees, the sweepback angle of the rear edge is 11 degrees, the root ratio is 0.5, the half-span length is 3.5m, a supercritical wing shape is adopted, the thickness is 0.18, and the joint of the inner side wing and the outer side wing is a wing folding hinge; the sweepback angle of the front edge and the rear edge of the outer wing is 15 degrees, the slight root ratio is 1, the half span length is 6.9m, the chord length of the wing is 2.3m, and the thickness is 0.15 by adopting NACA64 laminar flow wing profile; the sweepback angle and the root ratio of the telescopic wing are equal to those of the wing profile at the outer side, the half span of the extending section is 2.8m, the chord length of the wing is 0.95m, and the thickness is 0.11.
4) Fuselage parameters and wing control surface configuration:
the fuselage was 15.5m long, 1.5m wide and 1.38m high. The deflection angle of the flap and the flap aileron in the take-off configuration is 22 degrees, the deflection angle of the flap and the flap aileron in the landing configuration is 33 degrees, and the deflection angle of the flap and the flap aileron in the oiling stage is adjusted between 0 and 15 degrees according to the different required flat flight speeds;
5) Power system parameters:
a turbofan engine has a bypass ratio of 5, a maximum thrust of 53.8KN,12000m, and a fuel consumption of 0.6MA of 0.66kg/kgf.h.
6) Tail configuration parameters:
the tail airfoil product is 18m2, the front edge is swept back by 16 degrees, the rear edge is swept forward by 10 degrees, the root ratio is slightly 0.38, the thickness is 0.1, and the NACA64 laminar flow airfoil is adopted. The inclination angle of the tail wing can be adjusted between 40 degrees and 50 degrees.
7) Early warning equipment cabin parameters:
the equipment cabins are 6.6m long, 0.35m wide and 1.2m high, and the weight of the two early warning equipment cabins is 800kg.
8) Conformal early warning antenna parameters:
microstrip conformal phased array radar antenna that outside wing was installed, upper and lower skin inboard antenna length 6.6m, wide 1.1m, thickness 38mm, leading edge antenna length 6.2m, high 30cm, thickness 33mm. And spiral conformal phased array radar antennas installed on two sides of the machine body are 6.2m long, 1m high and 60mm thick.
9) Conformal external tank parameters:
the length of the fuel tank is 7.6m, the width is 0.5m, the height is 1m, the weight of two conformal fuel tanks is 200kg, and the fuel can be loaded for 3.6t.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
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 to make the belly of fuselage form the shrink structure from top to bottom, the inclined plane has the mount point, mount the externally hung oil tank (12) or early warning equipment compartment (13) of the optional of mount point, mount externally hung oil tank (12) and early warning equipment compartment (13) after mounting on the inclined plane, have with the outer wall surface of inclined plane parallel, carrier-borne unmanned aerial vehicle platform configuration still includes knapsack formula turbofan engine (16), oil tank and equipment compartment;
when the mounting point mounting externally hung oil tank (12) is mounted, the carrier-borne unmanned aerial vehicle platform configuration is provided with a first wing load and a first thrust-weight ratio, when the mounting point mounting pre-warning equipment cabin (13) is mounted, the carrier-borne unmanned aerial vehicle platform configuration is provided with 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 to serve as a wing load constraint parameter of the carrier-borne unmanned aerial vehicle platform configuration to carry out platform design, and a larger thrust-weight ratio of the first thrust-weight ratio and the second thrust-weight ratio is selected to serve as a thrust-weight ratio constraint parameter of the carrier-borne unmanned aerial vehicle platform configuration to carry out platform design.
2. Mission-modularization-based unmanned aerial vehicle platform configuration according to claim 1, wherein the outer part of the wing (17) is arranged in a 15 ° swept rectangular configuration.
3. The task modularization-based carrier-borne unmanned aerial vehicle platform configuration according to claim 1, wherein microstrip conformal phased array antennas are installed at the inner sides of upper and lower skins and front beams of the outer side portion of the wing (17).
4. The task modularization-based carrier-borne unmanned aerial vehicle platform configuration according to claim 1, wherein the external surface of the pre-warning equipment compartment (13) is provided with a spiral conformal phased array antenna.
5. The task modularization-based carrier-borne unmanned aerial vehicle platform configuration as claimed in claim 4, wherein the tail wing (14) is configured as a V-shaped tail wing, the V-shaped tail wing comprises two wings, and an inclination angle between the two wings is adjustable, and the inclination angle is 40-50 °.
6. The task modularization-based unmanned ship-based unmanned aerial vehicle platform configuration according to claim 5, wherein the tail fin (14) is made of a wave-transparent material and is installed at both sides of the rear end of the nozzle of the engine.
7. The task modularization-based carrier-borne unmanned aerial vehicle platform configuration according to claim 1, wherein the wing (17) and the fuselage are designed in a smooth transition manner by adopting a natural laminar flow airfoil design.
8. The mission-modularization-based unmanned aerial vehicle platform configuration according to claim 1, wherein the wing (17) comprises 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) is foldable upwards and backwards relative to the inner wing (1), the outer wing end is further provided with a telescopic wing (3), and the telescopic wing (3) is arranged to extend or retract into an inner cavity of the outer wing (2) along the wing span.
9. The mission-modularity-based unmanned aerial vehicle platform configuration of claim 1, wherein the fuel tanks comprise a fuselage fuel tank (10) and a wing fuel tank (11), and the equipment compartment comprises a fore-fuselage equipment compartment (8) at the front of the fuselage and a aft-fuselage equipment compartment (9) at the rear of the fuselage.
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| CN202111102401.4A CN113753216B (en) | 2021-09-19 | 2021-09-19 | Ship-borne unmanned aerial vehicle platform configuration based on task modularization |
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| CN202111102401.4A CN113753216B (en) | 2021-09-19 | 2021-09-19 | Ship-borne unmanned aerial vehicle platform configuration based on task modularization |
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