CN208134639U - A kind of aircraft electric drive is to rotary fan propeller - Google Patents
A kind of aircraft electric drive is to rotary fan propeller Download PDFInfo
- Publication number
- CN208134639U CN208134639U CN201820344176.2U CN201820344176U CN208134639U CN 208134639 U CN208134639 U CN 208134639U CN 201820344176 U CN201820344176 U CN 201820344176U CN 208134639 U CN208134639 U CN 208134639U
- Authority
- CN
- China
- Prior art keywords
- fan
- level
- motor
- aircraft
- electric drive
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model discloses a kind of aircraft electric drives to rotary fan propeller, the electric drive is made of rotary fan propeller level-one fan, second level fan, motor, gear assembly, centerbody, by-pass air duct, supporting plate and casing, level-one fan and second level fan rotation direction are on the contrary, motor drives level-one fan and second level fan to rotate by gear assembly.The electric drive uses two-stage to rotary fan propeller and designs rotary fan, can reduce the pressure ratio and revolving speed of fan, and fan is enable preferably to tolerate that inlet flow field distorts, and reduces cycle facigue load suffered by fan under distortion incoming flow, improves fan service life；Meanwhile using to the higher efficiency of rotary fan, the advantage of low weight, the length and weight of propulsion device can be reduced；The motor drive mode of use can make the installation of propulsion device on board the aircraft more flexible, and then realize propeller and body height integrated design.
Description
Technical field
The utility model belongs to Power System of Flight Vehicle field, and in particular to a kind of aircraft pushes away rotary fan with electric drive
Into device.
Background technique
As resource problem, environmental problem, operation cost problem become increasingly conspicuous, section of the civil aviation industry to aircraft
Oil consumption reduction attention rate is higher and higher.In order to meet following growth requirement, aircraft industry is from aero engine technology, aircraft cloth
Office's technology etc. has carried out a large amount of forward position researchs, strives making in 2035 the fuel consumption of aircraft to reduce by 70%.But either
Outstanding blended wing-body aerodynamic arrangement or high efficiency aero-engine is difficult to meet this harsh index request.For
This, USA and Europe country starts to study new technological means, one of them is boundary layer from propulsion/body integration angle
The boundary layer of sucking technology, i.e. propulsion system sucking body.Propulsive efficiency can be improved in boundary layer sucking technology, and then reduces wind
The driving power of fan realizes the purpose of energy resource saving.The liter resistance that After-Body boundary layer sucking technology can also improve aircraft is special
Property, further decrease oil consumption.
U.S. NASA proposes distributed boundary layer sucking propulsion system, which is characterized in that aircraft is blended wing-body cloth
Office devises the electrically driven (operated) distributed propulsion system of a row at fuselage back rear, and propulsion system width is suitable with fuselage width,
The boundary layer at body back can all be sucked.This design can bring the advantage that boundary layer sucks into play, significantly reduce flight
Device oil consumption." the GAS-ELECTRIC PROPULSION SYSTEM FOR AN of U.S. Provisional Patent Application the 62/107196th
AIRCRAFT " and corresponding Chinese patent application " the pneumoelectric propulsion system for aircraft "（Application number 201610042603.7）
Involved in tubulose aircraft tail portion boundary layer suction-type Push Technology.This design can absorb all boundary of tubulose fuselage
Layer, also can significantly reduce oil consumption.Two above promotion program uses single stage fan, quiet comprising an exhaust fan rotor blade and a row
Blades.
Boundary layer sucking will lead to air intake duct and generate stronger pitot loss and flow distortion, after this brings at least two
Fruit.First is that reducing pressure ratio, the efficiency of fan, thrust and oil consumption is caused to increase.Second is that fan turns over Distorted Flow Field with high frequency
When by biggish dynamic stress, cause fan structure to vibrate, in addition occur high cycle fatigue rupture.Therefore, boundary is played
The advantage of layer sucking technology, it is necessary to ensure that fan can tolerate strong inlet distortion, i.e. pressure ratio and efficiency in pneumatic and structure
Loss wants small, can be resistant to high-frequency vibration for a long time.In general, the pressure ratio or efficiency of fan are higher, the ability of distortion is tolerated
It is lower, this is because high load capacity, high efficiency and wide stability margin are often conflicting, and high-loaded fan often vane thickness
It is smaller.Since there are apparent pitot loss for boundary layer suction-type air intake duct, so that fan is generated enough thrust, just must
There must be sufficiently large pressure ratio；Make system oil energy consumption is enough to significantly reduce, just must assure that the enough height of the efficiency of fan.If using
Single stage fan will face a design contradiction：It should ensure that fan has higher pressure ratio and efficiency, ensure that fan can again
Endure strong inlet distortion.This contradiction causes boundary layer sucking technical difficulty higher, it is difficult to carry out commercial introduction.
Summary of the invention
The technical problem to be solved by the utility model is to provide a kind of aircraft electric drives to rotary fan propeller.
The aircraft electric drive of the utility model to rotary fan propeller, its main feature is that, the electric drive is to turning wind
Fanning propeller includes level-one fan, second level fan, motor, gear assembly, centerbody, by-pass air duct, supporting plate and casing；The machine
The shape of casket is annular, and the shape of centerbody is body of revolution, and centerbody is fixed in casing by supporting plate, the inner surface of casing with
Runner between the outer surface of centerbody constitutes by-pass air duct, and the front end face of by-pass air duct is inlet end, and the rear end face of by-pass air duct is row
Gas end；The gear assembly and motor is sequentially arranged at from front to back on the intracorporal central axes in center, the input of gear assembly
End is connected to the shaft of motor；The level-one fan and second level fan is sequentially arranged at the front of centerbody, level-one fan with
First output end of gear assembly is connected, and second level fan is connected with the second output terminal of gear assembly；The centerbody, machine
Casket, level-one fan and second level fan are coaxial, and it is center axis that central axes, which are overlapped,；The level-one fan and second level fan is around center
Axis rotation, rotation direction on the contrary, level-one fan and second level fan without stator blade.
The pressure ratio of the level-one fan is more than or equal to second level fan, and the wheel hub ratio of level-one fan is less than second level fan.
The motor is one of conventional motor or superconducting motor, and the revolving speed of motor is more than or equal to level-one fan, two
Maximum speed in grade fan.
The motor is or cold by introducing from the body of aircraft by the cooling air cooling that is introduced by by-pass air duct
But liquid cooling is but.
The motor is by the generator powered on the battery or jet engine of aircraft.
The inlet end is connected with the air intake duct of aircraft, and exhaust end is connected with the jet pipe of aircraft.
The aircraft of the utility model does not limit rotary fan propeller the type of gear assembly with electric drive, can be
One overall gear case, is also possible to the assembly of gear and transmission shaft.When second level fan and motor speed and direction of rotation phase
Together, then gear assembly will become very simple：Motor direct-drive second level fan, second level fan and level-one fan pass through gear
Transmission.The aircraft of the utility model does not limit rotary fan propeller the form of air intake duct and jet pipe, air inlet with electric drive yet
Road can be the common nacelle inlet of seating plane, be also possible to boundary layer sucking air intake duct, and jet pipe can be seating plane
Common axisymmetric nozzle is also possible to flat jet pipe.The aircraft electric drive of the utility model to rotary fan propeller not
The section shape of casing is limited, casing section shape should match the design of fan and by-pass air duct in practical application, it can be straight line,
It is also possible to curve.The aircraft electric drive of the utility model is to the lubrication of the unlimited fixed tooth wheel assembly of rotary fan propeller, cold
But the rapidoprint of form and fan.
The aircraft electric drive of the utility model uses two-stage to rotary fan in rotary fan propeller, and the pressure ratio of fan obtains
To reduce, and then stability margin can be improved in guaranteed efficiency, be produced after so that fan is preferably tolerated boundary layer sucking
Raw strong Distorted Flow Field.Pressure ratio reduction means rotation speed of the fan reduction, advantageously reduces in the case of distorting incoming flow suffered by fan
Cycle facigue load, improve the service life of fan.Revolving speed reduces, additionally it is possible to reduce fan noise.Fan is using no stator blade
Design can reduce the length and weight of propulsion device in the case where keeping efficient situation.Motor uses high Design of Rotation, facilitates
Improve the efficiency and power density of motor, it is ensured that the motor feels hot less, small in size, and motor drive mode can make propulsion device fly
Installation on device is more flexible, and then realizes propeller and body height integrated design.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the aircraft electric drive to rotary fan propeller of the utility model；
Fig. 2 is the tubulose aircraft schematic diagram using the aircraft electric drive of the utility model to rotary fan propeller；
Fig. 3 is installation of the aircraft electric drive of the utility model to rotary fan propeller after tubulose aircraft on body
Schematic diagram；
Fig. 4 is to illustrate using the aircraft electric drive of the utility model to the blended wing-body aircraft of rotary fan propeller
Figure；
Fig. 5 be the utility model aircraft electric drive to rotary fan propeller in the carry-on installation of blended wing-body
Schematic diagram；
In figure, 110. level-one fan, 120. second level fan, 130. motor, 131. cooling air, 132. coolant liquid, 140. tooth
150. centerbody of wheel assembly 141. first output end, 142. second output terminal, 143. input terminal, 160. by-pass air duct 161. into
200. nacelle of gas end 162. exhaust end, 170. supporting plate, 180. casing, 190. central axis, 100. tubulose aircraft rear fuselage
210. nacelle inlet of formula propulsion system, 220. axisymmetric nozzle, 230. nacelle formula propulsion system outer cover, 250. fuselage support
311. body boundary layer of body, 312. two-dimensional nozzle 313.S after 300. 310. blended wing-body aircraft of distributed propulsion system
The distributed propulsion system outer cover of curved intake port 314..
Specific embodiment
The utility model is described in detail with reference to the accompanying drawings and examples.
The aircraft electric drive of the utility model to rotary fan propeller include level-one fan 110, second level fan 120,
Motor 130, gear assembly 140, centerbody 150, by-pass air duct 160, supporting plate 170 and casing 180；The shape of the casing 180
For annular, the shape of centerbody 150 is body of revolution, and centerbody 150 is fixed in casing 180 by supporting plate 170, casing 180
Runner between inner surface and the outer surface of centerbody 150 constitutes by-pass air duct 160, and the front end face of by-pass air duct 160 is inlet end
161, the rear end face of by-pass air duct 160 is exhaust end 162；The gear assembly 140 and motor 130 is sequentially arranged at from front to back
On central axes in centerbody 150, the input terminal 143 of gear assembly 140 is connected to the shaft of motor 130；The force one wind
Fan 110 and second level fan 120 are sequentially arranged at the front of centerbody 150, and the first of level-one fan 110 and gear assembly 140 is defeated
Outlet 141 is connected, and second level fan 120 is connected with the second output terminal 142 of gear assembly 140；The centerbody 150, casing
180, level-one fan 110 and second level fan 120 are coaxial, and it is center axis 190 that central axes, which are overlapped,；110 He of level-one fan
Second level fan 120 around central axis 190 rotate, rotation direction on the contrary, level-one fan 110 and second level fan 120 without stator leaf
Piece.
The pressure ratio of the level-one fan 110 is more than or equal to second level fan 120, and the wheel hub ratio of level-one fan 110 is less than two
Grade fan 120.
The motor 130 is one of conventional motor or superconducting motor, and the revolving speed of motor 130 is more than or equal to force one wind
Maximum speed in fan 110, second level fan 120.
The motor 130 is cooling by the cooling air 131 introduced by by-pass air duct 160, or passes through the machine from aircraft
The coolant liquid 132 that body introduces is cooling.
The motor 130 is by the generator powered on the battery or jet engine of aircraft.
The inlet end 161 is connected with the air intake duct of aircraft, and exhaust end 162 is connected with the jet pipe of aircraft.
Embodiment 1
As shown in Figure 1, Figure 2 and Figure 3, a nacelle formula is arranged in the tail portion of tubulose aircraft rear fuselage 100 promote system
System 200, the electric drive comprising a utility model is to rotary fan propeller, nacelle inlet 210, axisymmetric nozzle 220, short
Cabin formula propulsion system outer cover 230.Electric drive to rotary fan propeller, including level-one fan 110, second level fan 120, motor 130,
Gear assembly 140, centerbody 150, by-pass air duct 160, supporting plate 170 and casing 180.
The shape of casing 180 is annular, and the shape of centerbody 150 is body of revolution, and centerbody 150 is fixed by supporting plate 170
In casing 180, front end and the tubulose aircraft rear fuselage 100 of centerbody 150 are smoothly connected, and the inner surface of casing 180 is in
Runner between the outer surface of heart body 150 constitutes by-pass air duct 160, and the front end face of by-pass air duct 160 is inlet end 161, by-pass air duct 160
Rear end face be exhaust end 162.Gear assembly 140 and motor 130 are sequentially arranged at the central axes in centerbody 150 from front to back
On, gear assembly 140 uses integrated gear case, and the input terminal 143 of gear assembly 140 is connected to the shaft of motor 130.Level-one
Fan 110 and second level fan 120 are sequentially arranged at the front of centerbody 150, level-one fan 110 and the first of gear assembly 140
Output end 141 is connected, and second level fan 120 is connected with the second output terminal 142 of gear assembly 140.Centerbody 150, casing 180,
Level-one fan 110 and second level fan 120 are coaxial, and it is center axis 190 that central axes, which are overlapped,.Level-one fan 110 and second level fan 120
Around central axis 190 rotate, rotation direction on the contrary, level-one fan 110 and second level fan 120 without stator blade.Casing 170 to
Tubulose aircraft rear fuselage 100 extends, and fuselage support is provided between 170 front end of casing and tubulose aircraft rear fuselage 100
250, for supporting nacelle formula propulsion system 200.Inlet end 161 and nacelle inlet 210 of the electric drive to rotary fan propeller
It is connected, exhaust end 162 is connected with axisymmetric nozzle 220.Nacelle inlet 210 can suck body boundary layer 311.
The pressure ratio of level-one fan 110 and second level fan 120 is respectively 1.180,1.140, overall pressure tatio 1.345, force one wind
Fan 110 and second level fan 120 are respectively 3200rpm, 2800rpm in the revolving speed of design point, level-one fan 110 and second level fan
120 wheel hub is than being respectively 0.28,0.32.Motor 130 is conventional motor, and corresponding level-one fan 110 and second level fan 120 are set
The working speed of enumeration is 8000rpm.Motor 130 pass through second level fan 120 after by-pass air duct 160 introduce cooling air 131 into
Row cooling, cooling air 131 are discharged by the rear-wheel hub of centerbody 150.The storage battery power supply that motor 130 passes through aircraft interior.
Embodiment 2
Embodiment 2 and the embodiment of embodiment 1 are almost the same, the difference is that, the design speed of second level fan 120
For 3200rpm, the working speed of the design point of the corresponding level-one fan 110 of motor 130 and second level fan 120 is 3200rpm.Due to
Level-one fan 110, second level fan 120 are identical with the revolving speed of motor 130, and the structure of gear assembly 140 is simplified, motor 130
Shaft directly drive second level fan 120, be driven between second level fan 120 and level-one fan 110 by gear, so that two
Grade fan 120 and the rotation of level-one fan 110 are reversed.Motor 130 passes through the generator drive on aircraft j et engine.
Embodiment 3
Embodiment 3 and the embodiment of embodiment 1 are almost the same, the difference is that, motor 130 is by aircraft interior
Generator on battery and jet engine drives jointly.
Embodiment 4
As shown in Fig. 1 and Fig. 4, Fig. 5, body 310 is mounted with a distributed propulsion system after blended wing-body aircraft
300, distributed 300 inside of propulsion system is mounted with 10 electric drives to rotary fan propeller altogether.Distributed propulsion system 300 is logical
It crosses partition and separates each electric drive to rotary fan propeller, partition connects body 310 and distribution after blended wing-body aircraft
Propulsion system outer cover 314, one electric drive of installation is to rotary fan propeller between adjacent separator.Electric drive promotes rotary fan
Device, including level-one fan 110, second level fan 120, motor 130, gear assembly 140, centerbody 150, by-pass air duct 160, supporting plate
170 and casing 180.Electric drive is fixed on inside distributed propulsion system 300 rotary fan propeller by casing 180.
The shape of casing 180 is annular, and the shape of centerbody 150 is body of revolution, and centerbody 150 is fixed by supporting plate 170
In casing 180, the runner between the inner surface of casing 180 and the outer surface of centerbody 150 constitutes by-pass air duct 160, by-pass air duct
160 front end face is inlet end 161, and the rear end face of by-pass air duct 160 is exhaust end 162.Gear assembly 140 and motor 130 are in the past
It is sequentially arranged at after on the central axes in centerbody 150, gear assembly 140 uses integrated gear case, gear assembly 140
Input terminal 143 is connected to the shaft of motor 130.Before level-one fan 110 and second level fan 120 are sequentially arranged at centerbody 150
Portion, level-one fan 110 are connected with the first output end 141 of gear assembly 140, and the second of second level fan 120 and gear assembly 140
Output end 142 is connected.Centerbody 150, casing 180, level-one fan 110 and second level fan 120 are coaxial, centered on central axes are overlapped
Axis 190.Level-one fan 110 and second level fan 120 are rotated around central axis 190, and rotation direction is on the contrary, 110 He of level-one fan
Second level fan 120 is without stator blade.Electric drive is connected to the inlet end 161 of rotary fan propeller with S curved intake port 313, row
Gas end 162 is connected with two-dimensional nozzle 312.S curved intake port 313 can suck body boundary layer 311.Two-dimensional nozzle 312 includes that circle turns
Two components of square changeover portion and two-dimensional nozzle section.
The pressure ratio of level-one fan 110 and second level fan 120 is respectively 1.2,1.2, overall pressure tatio 1.44, level-one fan 110
It in the revolving speed of design point is respectively 3200rpm, 3200rpm, the wheel of level-one fan 110 and second level fan 120 with second level fan 120
Hub is than being respectively 0.32,0.35.Motor 130 is superconducting motor, the design point of corresponding level-one fan 110 and second level fan 120
Working speed is 5000rpm, is cooled down by the coolant liquid 132 introduced from body, and coolant liquid 132 is made on aircraft
The refrigerant of cold, the inlet and outlet from bracket 170 of coolant liquid 132.Motor 130 is supplied by the battery of aircraft interior
Electricity.
Embodiment 5
Embodiment 5 and the embodiment of embodiment 4 are almost the same, the difference is that, inside distributed propulsion system 300
It is mounted with the electric drive of 8 the utility model to rotary fan propeller.Motor 130 passes through the power generation on aircraft j et engine
Machine driving.
Embodiment 6
The embodiment of embodiment and embodiment 5 is almost the same, the difference is that, level-one fan 110 and second level fan
120 pressure ratio is respectively 1.22,1.2, overall pressure tatio 1.464, the revolving speed of level-one fan 110 and second level fan 120 in design point
The wheel hub of respectively 3200rpm, 3100rpm, level-one fan 110 and second level fan 120 is than being respectively 0.30,0.33.Motor 130
The working speed of the design point of corresponding level-one fan 110 and second level fan 120 is 3200rpm, and coolant liquid 132 is aircraft j et
The low temp fuel that engine uses（Liquid hydrogen）.
The utility model is not limited to above-mentioned specific embodiment, and person of ordinary skill in the field visualizes from above-mentioned
Hair, without creative labor, made various transformation are all fallen within the protection scope of the utility model.
Claims (6)
1. a kind of aircraft electric drive is to rotary fan propeller, it is characterised in that：The electric drive is to rotary fan propeller
Including level-one fan（110）, second level fan（120）, motor（130）, gear assembly（140）, centerbody（150）, by-pass air duct
（160）, supporting plate（170）And casing（180）；The casing（180）Shape be annular, centerbody（150）Shape be rotation
Adult, centerbody（150）Pass through supporting plate（170）It is fixed on casing（180）It is interior, casing（180）Inner surface and centerbody（150）
Outer surface between runner constitute by-pass air duct（160）, by-pass air duct（160）Front end face be inlet end（161）, by-pass air duct
（160）Rear end face be exhaust end（162）；The gear assembly（140）And motor（130）In being sequentially arranged at from front to back
Heart body（150）On interior central axes, gear assembly（140）Input terminal（143）It is connected to motor（130）Shaft；Described
Level-one fan（110）With second level fan（120）It is sequentially arranged at centerbody（150）Front, level-one fan（110）With gear set
Part（140）The first output end（141）It is connected, second level fan（120）With gear assembly（140）Second output terminal（142）Phase
Even；The centerbody（150）, casing（180）, level-one fan（110）With second level fan（120）Coaxial, central axes, which are overlapped, is
Central axis（190）；The level-one fan（110）With second level fan（120）Around central axis（190）Rotation, rotation direction
On the contrary, level-one fan（110）With second level fan（120）Without stator blade.
2. aircraft electric drive according to claim 1 is to rotary fan propeller, it is characterised in that：The force one wind
Fan（110）Pressure ratio be more than or equal to second level fan（120）, level-one fan（110）Wheel hub ratio be less than second level fan（120）.
3. aircraft electric drive according to claim 1 is to rotary fan propeller, it is characterised in that：The motor
（130）For one of conventional motor or superconducting motor, motor（130）Revolving speed be more than or equal to level-one fan（110）, light breeze
Fan（120）In maximum speed.
4. aircraft electric drive according to claim 1 is to rotary fan propeller, it is characterised in that：The motor
（130）By by by-pass air duct（160）The cooling air of introducing（131）It is cooling, or the cooling by being introduced from the body of aircraft
Liquid（132）It is cooling.
5. aircraft electric drive according to claim 1 is to rotary fan propeller, it is characterised in that：The motor
（130）By the generator powered on the battery or jet engine of aircraft.
6. aircraft electric drive according to claim 1 is to rotary fan propeller, it is characterised in that：The inlet end
（161）It is connected with the air intake duct of aircraft, exhaust end（162）It is connected with the jet pipe of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820344176.2U CN208134639U (en) | 2018-03-14 | 2018-03-14 | A kind of aircraft electric drive is to rotary fan propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820344176.2U CN208134639U (en) | 2018-03-14 | 2018-03-14 | A kind of aircraft electric drive is to rotary fan propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208134639U true CN208134639U (en) | 2018-11-23 |
Family
ID=64289524
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820344176.2U Active CN208134639U (en) | 2018-03-14 | 2018-03-14 | A kind of aircraft electric drive is to rotary fan propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208134639U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108263620A (en) * | 2018-03-14 | 2018-07-10 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of aircraft electric drive is to rotary fan propeller |
| CN111976948A (en) * | 2020-09-02 | 2020-11-24 | 南昌航空大学 | Pneumatic layout of flying wing type unmanned fighting bomber |
| CN113126599A (en) * | 2021-06-18 | 2021-07-16 | 成都康拓兴业科技有限责任公司 | Electrical control test system for air inlet channel |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
-
2018
- 2018-03-14 CN CN201820344176.2U patent/CN208134639U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108263620A (en) * | 2018-03-14 | 2018-07-10 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of aircraft electric drive is to rotary fan propeller |
| CN108263620B (en) * | 2018-03-14 | 2024-06-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Electric drive counter-rotating fan propeller for aircraft |
| CN111976948A (en) * | 2020-09-02 | 2020-11-24 | 南昌航空大学 | Pneumatic layout of flying wing type unmanned fighting bomber |
| CN111976948B (en) * | 2020-09-02 | 2023-07-18 | 南昌航空大学 | Aerodynamic layout of a flying-wing unmanned fighter-bomber |
| CN113126599A (en) * | 2021-06-18 | 2021-07-16 | 成都康拓兴业科技有限责任公司 | Electrical control test system for air inlet channel |
| CN113126599B (en) * | 2021-06-18 | 2021-08-20 | 成都康拓兴业科技有限责任公司 | Electrical control test system for air inlet channel |
| CN113291459A (en) * | 2021-07-27 | 2021-08-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
| CN113291459B (en) * | 2021-07-27 | 2021-11-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108263620A (en) | A kind of aircraft electric drive is to rotary fan propeller | |
| EP3964438B1 (en) | Hybrid aircraft propulsion system | |
| CN208134639U (en) | A kind of aircraft electric drive is to rotary fan propeller | |
| CN109641657B (en) | Tiltrotor propulsion system for aircraft | |
| US8562284B2 (en) | Propulsive fan system | |
| EP2098714B1 (en) | High bypass-ratio turbofan jet engine | |
| CN107696812B (en) | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same | |
| CN118911866A (en) | Unducted thrust producing system architecture | |
| JPH0142879B2 (en) | ||
| CN116745208A (en) | Electric duct fan propeller | |
| CN107284652A (en) | Integrated culvert type propeller | |
| CN111762327A (en) | Energy-Efficient Propulsion System for Blended-Wing Body Aircraft | |
| CN216699737U (en) | Liquid-cold air cooling integrated EVTOL power motor | |
| CN113982782A (en) | Rim-driven turbofan duct jet-propelled shaftless electric permanent magnet aviation propeller and application | |
| CN201864038U (en) | Self-feeding electric air vehicle | |
| CN114313219B (en) | Novel contra-rotating fan propulsion structure | |
| CN113443124B (en) | Boundary layer suction type propeller adopting two-stage large and small blades | |
| CN114476048B (en) | Flange fusion propulsion structure based on rim driving technology | |
| CN1335248A (en) | Helicopter with driving rotary wings | |
| CN114802735A (en) | Rotor duct for vertical take-off and landing aircraft | |
| CN110056429B (en) | Distributed hybrid propulsion system of solid oxide fuel cell gas turbine for aircraft | |
| CN221942567U (en) | Built-in turbine engine | |
| CN117963144B (en) | Propelling transmission device of airplane and application method | |
| CN219840723U (en) | A distributed propulsion variable cycle engine | |
| CN209743063U (en) | Rich fuel gas conveying pipeline |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |