CN109866919A - A kind of carrier-borne heat power electricity drive tiltrotor aircraft - Google Patents
A kind of carrier-borne heat power electricity drive tiltrotor aircraft Download PDFInfo
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- CN109866919A CN109866919A CN201910222426.4A CN201910222426A CN109866919A CN 109866919 A CN109866919 A CN 109866919A CN 201910222426 A CN201910222426 A CN 201910222426A CN 109866919 A CN109866919 A CN 109866919A
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Abstract
The invention discloses a kind of carrier-borne heat power electricity to drive tiltrotor aircraft, including tilting rotor system, modularization airframe structure, boxlike bilayer wing, the double-deck boxlike flying tail, vertical fin, power assembly and energy management integral system, flight control system, tilting rotor system includes the rotor and propeller hub that boxlike bilayer wing end is arranged in, boxlike bilayer wing is symmetricly set on the two sides of modularization airframe structure, power assembly and energy management integral system include that heat power directly drives electricity generation system, generator and motor, heat power is directly driven electricity generation system and is connect with generator, the electric energy that generator issues is divided into two-way, enter double redundancy 1100V Energy Management System all the way, another way enters double redundancy 270V Energy Management System, modularization airframe structure of the present invention, boxlike bilayer wing, the double-deck boxlike flying tail Pneumatic efficiency can be improved in structure design, and is convenient to carry out rotor folding, realizes short distance VTOL, is particularly suited for carrier-borne use.
Description
Technical field
The invention belongs to aircraft technical fields, and specifically a kind of carrier-borne heat power electricity drives tiltrotor aircraft.
Background technique
Conventional configuration carrier-based helicopter delivers that efficiency is higher, better economy, adaptable, but is executing sea assault fortune
When defeated, Quick rescue, extensive search task, speed is slow, voyage is short, battlefield viability is low, it is complicated to ensure, tactics efficiency is not
Height is highly detrimental to the expansion of amphibious tactical mission, denounces for naval always.Develop the carrier-borne vertically taking off and landing flyer of high-speed type at
For a kind of certainty.
From the nineties in last century, on the basis of XV-15 principle prototype, under the insistent subsidy of USN, wave
A kind of novel tiltrotor aircraft of sound development of company, i.e., famous MV-22 osprey tiltrotor aircraft.The type arrives
It equips in small batches starting in 2007, is developed to B-stage at present.Hawkeye has also equipped 69 framves without human-like.Practical application proves, the configuration
It is strong that aircraft quickly assaults transport capacity, 1 times of comprehensive task enhancing efficiency, has that outstanding warship face is vertical, sliding runs landing ability.
Tiltrotor aircraft greatly extends task envelope curve, covers substantially whole the requiring of naval's assault transport task.
The tiltrotor aircraft of above-mentioned configuration is all made of traditional mechanical actuation device driving rotor and leans forward, needs to lead
Retarder, lubricating oil, heat dissipation, transmission shaft mechanical transmission mechanism, it is hydraulic turn the big weight, high complexity driving member such as driving mechanism,
System construction is complicated, and maintenance work is cumbersome, high failure rate, and there are serious compatibility to ask with naval vessel when carrying out carrier-borne flight
Topic.
Summary of the invention
It is an object of the invention to overcome defect of the existing technology, above-mentioned technical problem is solved, is proposed a kind of carrier-borne
Heat power electricity drives tiltrotor aircraft design scheme.
To achieve the goals above, The technical solution adopted by the invention is as follows:
A kind of carrier-borne heat power electricity drive tiltrotor aircraft, including tilting rotor system, modularization airframe structure, boxlike
The double-deck wing, the double-deck boxlike flying tail, vertical fin, power assembly and energy management integral system, flight control system, it is described
Tilting rotor system includes the rotor and propeller hub that boxlike bilayer wing end is arranged in, and the boxlike bilayer wing is symmetricly set on
The two sides of modularization airframe structure, the power assembly and energy management integral system include heat power directly drive electricity generation system,
Generator and motor, the heat power are directly driven electricity generation system and are connect with generator, and the electric energy that the generator issues is divided into two
Road enters double redundancy 1100V Energy Management System all the way, and another way enters double redundancy 270V Energy Management System, into double remaining
The electric energy for spending 1100V Energy Management System, respectively drives left-handed wing turn drive motor and dextrorotation wing turn drive motor, into double redundancy
The electric energy of 270V Energy Management System, a part enter basic battery storage, and another part is to airborne sensor system, rotor
Handling controller, rotor vert controller, rotor rotational speed governor and airborne TU task unit power supply.
Further, the tilting rotor system is that double redundancy permanent magnetic brushless turns bilateral reversion rotor, has 1 grade
Slow down, rotor verts using 270V electric servomechanism, and rotor can realize that warship face folds.
Further, the modularization airframe structure includes modularization forebody and modularization rear body, the modularization
Forebody, which can accommodate 1-2 occupants or double centner task equipment, the modularization rear body, can accommodate 150 kilograms of tasks
The upper case unit of equipment, the modularization airframe structure is engine flat, and the engine flat includes air intake duct and tail
Spout module, engine block, the modularization airframe structure are connected with main landing gear, boxlike bilayer wing, the modularization
Fuel system and emergency power supply system are accommodated in airframe structure, the rear body configuration of the modularization airframe structure increases journey fuel tank.
Further, the boxlike bilayer wing includes top wing and lower wing, and the top wing has a wing flap, it is described on
Upper surface of the airfoil is equipped with vortex generator, and the boxlike bilayer wing tip installs tilting rotor.
Further, the double-deck boxlike flying tail includes upper and lower tail surface, and the vertical fin, which is that folding V-type is double, to hang down
Tail.
Further, the generator is 650kW generator, and motor is 320kW motor, the power assembly and energy
It further includes 660kW secondary power supply, Energy Management System that buret, which manages integral system, and it includes whirlpool that the heat power, which directly drives electricity generation system,
The output shaft of shaft generator, the turboshaft engine connects shaft by retarder, and the shaft is generator amature, directly drives
Dynamic generator, the 650kW generator are sine wave magneto alternator, and wherein stator is permanent magnet, using neodymium iron boron material
Material, rotor coil use copper coil, and slot wedge is element made of permeability magnetic material, and the 320kW motor is that sine wave permanent magnet is same
Motor is walked, the motor controller includes two channels, controls left-handed wing turn drive motor respectively and the dextrorotation wing turns
Motor, the 660kW secondary power supply use modular parallel structure, and the modular parallel inside configuration design uses three-level function
Rate transformation: three-phase does not control full-bridge rectification, three level BUCK converters and high frequency LLC resonance DC-DC converter, the energy management
System includes 1 set of 1100V power-supply system and 1 set of 270V DC power system, and the 1100V power-supply system is supplied to rotor motor
Electricity, the 270V DC power system charge to battery pack, are powered by battery pack to airborne equipment.
Further, the flight control system includes triplex redundance flight-control computer and double redundancy control steering engine, institute
Stating double redundancy control steering engine includes that the flap/aileron electric steering engine 2, lifting steering engine 1, nacelle vert and control electric steering engine 2.
Compared with prior art, the present invention its remarkable advantage is:
(1) carrier-borne heat power electricity of the invention drives tiltrotor aircraft, solves traditional heat power tilting rotor completely
The problem of Flight Vehicle Structure complexity, high failure rate, use and maintenance efficiency can be improved；
(2) carrier-borne heat power electricity of the invention drives tiltrotor aircraft, solves traditional heat power tilting rotor completely
The problem of aircraft is serious to deck thermal shock effect in landing on warship, machine warship poor compatibility, traditional tiltrotor aircraft
Rotor is directly driven by engine, when warship face is parked, engine tail nozzle is pointing directly at deck, and away from deck apart from close, height
The tail gaseous blast of fast high temperature directly impacts deck, and deck ablation is caused to damage, and heat power electricity drives the hair of tiltrotor aircraft
Motivation is fixed on fuselage, and nozzle is fixed to be leaned forward using motor driven rotor backward, and there is no the high temperature and high speeds on impact deck
Tail gaseous blast improves the applicability used on warship；
(3) carrier-borne heat power electricity of the invention drives tiltrotor aircraft, and the foldover design of tilting rotor system solves
Storage problem of the aircraft on warship, in conjunction with its new configurations, which is particularly suited for carrier-borne use；
(4) carrier-borne heat power electricity of the invention drives tiltrotor aircraft, and the real-time generation technology of the heat power of use solves
Traditional electric power storage Electric aircraft cruise duration and the problem that course continuation mileage is short, battery weight is excessive, extend aircraft
Task radius can be used for executing various tasks；
(5) carrier-borne heat power electricity of the invention drives tiltrotor aircraft, uses boxlike bilayer wing, the double-deck horizontal tail folding
Folded V-type twin vertical fin and the design of modularization fuselage, improve the pneumatic efficiency of aircraft, and are convenient for task loading.
Detailed description of the invention
Fig. 1 is the main view that the carrier-borne heat power electricity of the present invention drives tiltrotor aircraft.
Fig. 2 is the front view that the carrier-borne heat power electricity of the present invention drives tiltrotor aircraft.
Fig. 3 is the top view that the carrier-borne heat power electricity of the present invention drives tiltrotor aircraft.
Fig. 4 is the perspective view that the carrier-borne heat power electricity of the present invention drives tiltrotor aircraft.
Fig. 5 is the folding picture that the carrier-borne heat power electricity of the present invention drives tiltrotor aircraft.
Fig. 6 is Energy Management System schematic diagram of the present invention.
Fig. 7 is -8 Engine Series structural schematic diagram of whirlpool axis.
Fig. 8 is that axis -8 Engine Series in whirlpool of the present invention and engine direct drive power generation transformation schematic diagram.
Fig. 9 is generator engineering sample schematic diagram of the present invention.
Figure 10 is motor principle block diagram of the present invention.
Figure 11 is motor engineering sample figure of the present invention.
Figure 12 is secondary power supply module map of the invention.
Figure 13 is tiltrotor aircraft navigation and control law architecture design schematic diagram of the invention.
Specific embodiment
With reference to the accompanying drawings of the specification, the present invention is further illustrated.
Fig. 1-4 is that carrier-borne heat power electricity of the invention drives tiltrotor aircraft total arrangement schematic diagram.The present invention proposes
A kind of carrier-borne heat power electricity drive tiltrotor aircraft, including tilting rotor system, modularization airframe structure 3, boxlike are double-deck
Wing 4, the double-deck boxlike flying tail 6, vertical fin 8, power assembly and energy management integral system, flight control system.It verts
Rotor system is for generating hovering lift and preceding winged pulling force, and modularization airframe structure is for installing aircraft all parts and task
Equipment, ascend to heaven before the generation of boxlike bilayer wing power, and the supporting element as tilting type rotor, before the double-deck boxlike flying tail is used for
Pitch control is carried out when winged, power assembly and energy management integral system are produced electricl energy using engine driven generators, and
Electric energy is allocated, provides electric energy, flight control system control using motor drive rotor wing rotation, and for other airborne equipments
The conversion of aircraft flight mode processed is, it can be achieved that autonomous flight.
Fig. 5 is folding scheme schematic diagram of the invention, and rear body, wing and tilting rotor component have manual fast folding
Ability.Meanwhile to promote shipping-direction stability, reducing radar target signature, folding V-type twin vertical fin aerodynamic arrangement is used.
Current method for folding is all made of manual folding.Folding includes the following steps:
Step 1: rotor and motor nacelle entirety automatic horizontal are placed；
Step 2: the sagging folding of rotor blade and fixation；
Step 3: using hoist cable traction mechanism, will be folded up and fix in the middle part of wing；
Step 4: vertical tail is laid flat；
Step 5: undercarriage is squatted down 30cm.
Fig. 6 is Energy Management System schematic diagram of the invention.As a kind of preferred embodiment, turboshaft engine works,
According to the instruction of optimum condition controller, 650kW electrical power generators are driven；Generator generate electric energy be divided into two-way, all the way into
Entering double redundancy 1100V Energy Management System, (Energy Management System uses the control strategy based on optimization, by battery pack SOC and is somebody's turn to do
For power needed for aircraft as input quantity, power needed for engine formulates energy management criterion as output quantity.), enter all the way
Double redundancy 270V Energy Management System (double redundancy)；Into the electric energy of double redundancy 1100V Energy Management System, respectively drive left-handed
Wing turn drive motor and dextrorotation wing turn drive motor；Into the electric energy of double redundancy 270V Energy Management System, a part enters basis and stores
Battery storage, another part to airborne sensor system, rotor control controller, rotor vert controller, rotor revolving speed control
Device and the power supply of airborne TU task unit.
Fig. 7-8 is that-8 Engine Series of whirlpool axis and engine direct of the invention drive power generation transformation schematic diagram.In the figure, it is marked as
Air intake duct 9, compressor 10, combustion chamber 11, gas turbine 12, power turbine 13, output shaft 14, retarder 15, generator 16, should
Np revolving speed is 41850rpm under h type engine h rated condition.Cancelling the revolving speed in figure is 6000rpm main shaft, retains the first order
High-speed shaft of speed reducer holds system and shaft, which is restructured as generator amature direct drive generator group, the efficient hair of realization
Electricity.Engine control system revolving speed is needed according to total energy consumption of motor, the on-demand optimal power generation of dynamic implement.
Fig. 9 is novel electricity generator engineering sample schematic diagram of the invention, this generator uses the sine wave of high mature forever
Magnetic-synchro generator, wherein stator is permanent magnet, and using NdFeB material, rotor coil uses copper coil, and slot wedge is magnetic conduction material
Element made of expecting, rotor section are directly made using the output shaft extension after engine primary speed-down, generator and hair
Motivation drives transmission connection mode using straight, and 17 be nut in figure, and 18 be installation fixture nut, and 19 be high-intensitive, high heat-conducting ceramic
Material base, 20 be high conducting magnet core.
Figure 10 is motor principle block diagram of the invention, and structural member uses novel high-strength material, further decreases totality
Quality.Figure 11 is motor engineering sample figure of the invention, using the sine wave permanent magnet synchronous motor of high mature, output shaft
Optimization design is 8000rpm, and electric machine controller includes two channels, and each channel controls a turn drive motor, revolving speed control letter
Number come from flight-control computer, wherein 21 be stator, 22 be connecting component, and 23 be permanent-magnet material, and 24 be Inside coil.
Figure 12 is secondary power supply module map of the invention.Using modular parallel structure.Individual module is according to can select
Power topology and the selected optimization of device module rated power.Inside modules design proposed adoption three-level power conversion: 1. three-phases
Do not control full-bridge rectification；2. three level BUCK converters；3. high frequency LLC resonance DC-DC converter.Power module proposed adoption is digital
Control, externally provides digital communication interface.
Figure 13 is tiltrotor aircraft navigation of the invention and control law architecture design schematic diagram, according to navigation spots, pre-
It programs, make a return voyage, image guidance, the conditions such as anticollision carry out model selection.Aircraft realizes navigation feature and flight control mould with this
Formula executes autonomous warship face VTOL task in 5 grades of sea situations freely, using advanced cruise mode carry out target search and with
Track etc..
The carrier-borne heat power electricity of the present invention drives tiltrotor aircraft work and includes the following steps:
Step 1: turboshaft engine work drives 650kW electrical power generators according to the instruction of optimum condition controller；
Step 2: generator generate electric energy be divided into two-way, all the way enter double redundancy 1100V Energy Management System, all the way into
Enter double redundancy 270V Energy Management System；
Step 3: into the electric energy of double redundancy 1100V Energy Management System, respectively driving left-handed wing turn drive motor and dextrorotation
Wing turn drive motor；
Step 4: into the electric energy of double redundancy 270V Energy Management System, a part enters basic battery storage, another
It verts controller, rotor rotational speed governor and airborne job order to airborne sensor system, rotor control controller, rotor part
Member power supply.
The present invention is that machine warship dynamic fit process has built a set of l-G simulation test environment, by using Modern Modeling means,
The complete electric tiltrotor aircraft of board design, establishing includes tiltrotor aircraft flight dynamics mathematical model, heat power
It is straight to drive electricity generation system simulation model, flight control system simulation model, Naval equipment and warship stern flow field Real-Time Model, it opens
Vision emulation system is sent out, the tasks envelope curve subjects such as simulation warship face landing, cruise carry out Simulation Test.
Basic principles and main features and advantage of the invention have been shown and described above.The technical staff of the industry should
Understand, the present invention is not limited to the above embodiments, and the above embodiments and description only describe originals of the invention
Reason, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes and improvements
It all fall within the protetion scope of the claimed invention.The claimed scope of the invention is by appended claims and its equivalent circle
It is fixed.
Claims (7)
1. a kind of carrier-borne heat power electricity drives tiltrotor aircraft, which is characterized in that including tilting rotor system, modularization fuselage
Structure (3), boxlike bilayer wing (4), the double-deck boxlike flying tail (6), vertical fin (8), power assembly and energy management integration
System, flight control system, the tilting rotor system include rotor (1) and paddle of the setting in boxlike bilayer wing (4) end
Hub (2), the boxlike bilayer wing (4) are symmetricly set on the two sides of modularization airframe structure (3), the power assembly and energy
Management integration system includes that heat power directly drives electricity generation system, generator and motor, the heat power directly drive electricity generation system with
Generator connection, the electric energy that the generator issues are divided into two-way, enter double redundancy 1100V Energy Management System all the way, another
Road enters double redundancy 270V Energy Management System, into the electric energy of double redundancy 1100V Energy Management System, respectively drives the left-handed wing
Turn drive motor and dextrorotation wing turn drive motor, into the electric energy of double redundancy 270V Energy Management System, a part enters basic electric power storage
Pond storage, another part vert controller, rotor rotational speed governor to airborne sensor system, rotor control controller, rotor
It powers with airborne TU task unit.
2. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the tilting rotor
System is that double redundancy permanent magnetic brushless turns bilateral reversion rotor, and with 1 grade of deceleration, rotor verts using 270V electrical servo
Mechanism, rotor can realize that warship face folds.
3. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the modularization machine
Body structure includes modularization forebody and modularization rear body, and the modularization forebody can accommodate 1-2 occupants or 100,000
Gram task equipment, the modularization rear body can accommodate 150 kilograms of tasks equipments, the upper fuselage of the modularization airframe structure
Unit is engine flat, and the engine flat includes air intake duct and nozzle module, engine block, the modularization machine
Body structure is connected with main landing gear (5), boxlike bilayer wing (4), and fuel system is accommodated in the modularization airframe structure and is answered
The rear body configuration of anxious power supply system, the modularization airframe structure increases journey fuel tank.
4. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the boxlike is double-deck
Wing (4) includes top wing (4-1) and lower wing (4-2), and the top wing (4-1) has a wing flap, on the top wing (4-1)
Surface is equipped with vortex generator, and boxlike bilayer wing (4) wing tip installs tilting rotor.
5. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the bilayer boxlike
Flying tail (6) includes upper and lower tail surface, and the vertical fin (8) is folding V-type twin vertical fin.
6. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the generator is
650kW generator, motor are 320kW motor, and the power assembly and energy management integral system further include 660kW bis-
Secondary source, Energy Management System, it includes turboshaft engine that the heat power, which directly drives electricity generation system, the output of the turboshaft engine
Axis connects shaft by retarder, and the shaft is generator amature, and direct drive generator, the 650kW generator is positive
String wave magneto alternator, wherein stator is permanent magnet, and using NdFeB material, rotor coil uses copper coil, and slot wedge is
Element made of permeability magnetic material, the 320kW motor are sine wave permasyn morot, the motor controller
Comprising two channels, left-handed wing turn drive motor and dextrorotation wing turn drive motor are controlled respectively, and the 660kW secondary power supply uses module
Change parallel-connection structure, the modular parallel inside configuration design uses three-level power conversion: three-phase does not control full-bridge rectification, three level
BUCK converter and high frequency LLC resonance DC-DC converter, the Energy Management System include 1 set of 1100V power-supply system and 1 set
270V DC power system, the 1100V power-supply system are powered to rotor motor, and the 270V DC power system is to battery pack
Charging is powered by battery pack to airborne equipment.
7. carrier-borne heat power electricity according to claim 1 drives tiltrotor aircraft, which is characterized in that the flight control
System includes triplex redundance flight-control computer and double redundancy control steering engine, and the double redundancy control steering engine includes the flap/aileron electricity
Dynamic steering engine 2, lifting steering engine 1, nacelle vert and control electric steering engine 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222426.4A CN109866919B (en) | 2019-03-22 | 2019-03-22 | Ship-borne thermal power electric-driven tilting rotor aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910222426.4A CN109866919B (en) | 2019-03-22 | 2019-03-22 | Ship-borne thermal power electric-driven tilting rotor aircraft |
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| Publication Number | Publication Date |
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| CN109866919A true CN109866919A (en) | 2019-06-11 |
| CN109866919B CN109866919B (en) | 2020-12-29 |
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| CN201910222426.4A Active CN109866919B (en) | 2019-03-22 | 2019-03-22 | Ship-borne thermal power electric-driven tilting rotor aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110572028A (en) * | 2019-09-26 | 2019-12-13 | 哈尔滨工业大学 | DC/DC converter based on switch capacitor and resonance SEPIC circuit |
| CN112389639A (en) * | 2020-11-10 | 2021-02-23 | 中国船舶重工集团公司第七一六研究所 | 270V dual-redundancy high-power electric steering engine |
| EP3932805A1 (en) * | 2020-06-29 | 2022-01-05 | Bell Textron Inc. | Hybrid propulsion system for convertible aircraft |
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| WO2018099856A1 (en) * | 2016-11-29 | 2018-06-07 | Pfammatter Thomas | Electrical vertical take-off and landing aircraft |
| WO2018163171A1 (en) * | 2017-03-09 | 2018-09-13 | Shafir Yehuda | Vertical takeoff and landing light aircraft |
| CN108528734A (en) * | 2017-03-02 | 2018-09-14 | 贝尔直升机德事隆公司 | Hybrid propulsion drivetrain system for tiltrotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9248908B1 (en) * | 2013-06-12 | 2016-02-02 | The Boeing Company | Hybrid electric power helicopter |
| WO2018099856A1 (en) * | 2016-11-29 | 2018-06-07 | Pfammatter Thomas | Electrical vertical take-off and landing aircraft |
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| CN110572028A (en) * | 2019-09-26 | 2019-12-13 | 哈尔滨工业大学 | DC/DC converter based on switch capacitor and resonance SEPIC circuit |
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| CN112389639A (en) * | 2020-11-10 | 2021-02-23 | 中国船舶重工集团公司第七一六研究所 | 270V dual-redundancy high-power electric steering engine |
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| Publication number | Publication date |
|---|---|
| CN109866919B (en) | 2020-12-29 |
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