EP4153478A1 - Aircraft - Google Patents
AircraftInfo
- Publication number
- EP4153478A1 EP4153478A1 EP21721834.6A EP21721834A EP4153478A1 EP 4153478 A1 EP4153478 A1 EP 4153478A1 EP 21721834 A EP21721834 A EP 21721834A EP 4153478 A1 EP4153478 A1 EP 4153478A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aircraft
- wing
- aircraft according
- ducted propeller
- inlet
- 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.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 7
- 241000446313 Lamella Species 0.000 claims description 17
- 230000007704 transition Effects 0.000 description 10
- 230000008901 benefit Effects 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 241000985905 Candidatus Phytoplasma solani Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009415 formwork Methods 0.000 description 1
- 238000005339 levitation Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L50/00—Electric propulsion with power supplied within the vehicle
- B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
- B60L50/60—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
- B60L50/66—Arrangements of batteries
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/001—Shrouded propellers
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/20—Vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B60L2200/00—Type of vehicles
- B60L2200/10—Air crafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
Definitions
- the present invention relates to an aircraft, in particular a fully electric, vertical take-off and landing (VTOL) aircraft.
- VTOL vertical take-off and landing
- VTOL is any type of aircraft, drone or rocket which is able to take off and touch down essentially vertically and without a runway.
- This collective term is used in a broad sense below, which includes not only fixed-wing aircraft with wings, but also rotary-wing aircraft such as helicopters, gyroscopes, aircraft helicopters and hybrids such as composite helicopters or combination helicopters as well
- Aircraft with the ability to take off and land on particularly short routes (short take-off and landing, STOL), take off on short routes but land vertically (short take-off and vertical landing, STOVL) are also included. or to take off vertically but land horizontally (vertical take-off and horizontal landing, VTHL).
- DE 10 2009 048 201 A1 discloses an aircraft capable of taking off and landing vertically, which has a vertically aligned ducted propeller integrated into the fuselage with thrust vector blades on the outlet side.
- the outlet opening of the lifting propeller in turn, has pivotable slats directed transversely to the longitudinal axis of the aircraft in order to influence the direction of the exiting exhaust gas jet.
- This thrust vector control makes it possible to control movements around the pitch axis.
- WO 2016/066848 A1 relates to a flying car with two stationary impellers and louvre blades that are rolled up between the impeller shafts during flight operations.
- the propulsion force is achieved by adjusting the slats.
- GB 2 146 298 B describes a nozzle channel, the walls of which consist of lamellae articulated to one another, which are guided in guides and moved with cables in order to be able to assume different positions along the guides.
- the invention provides an aircraft, in particular a fully electric aircraft capable of taking off and landing vertically in the above sense, according to independent claim 1.
- the approach according to the invention is based on the insight that a VTOL aircraft intended for lift and cruise flight requires drive units that are able to cope with every flight phase (take-off, transition, cruise and landing).
- a ducted fan integrated into the wing is provided, as is known from aeronautical engineering, for example, from hovercraft or swamp boats.
- the cylindrical housing surrounding the propeller is able to considerably reduce the thrust losses due to turbulence at the blade tips.
- a variant of the invention is also based on the knowledge that a ducted propeller for VTOL aircraft capable of lifting and cruising should not only be closed under cruising conditions, but should also be aerodynamically sealed. Against this background, one possibility of producing an even closing profile during the transition is to cover the ducted propeller with louvers at the inlet and outlet, especially in horizontal flight.
- Another advantage of this solution in addition to the improved performance, is the attractive appearance of the aircraft, since it does not allow a view of the open rotors when cruising.
- On the suction side of the ducted propeller it is particularly important to ensure an optimized air flow and at the same time to create the possibility of opening and closing the integrated blades with a suitable kinematic system.
- An embodiment of the invention therefore opens up the possibility of actuating the integrated inlet lamellae while maintaining the base area of the round flow channel of the ducted propeller, which is essential for its flow guidance and deflection function (into the flow channel).
- webs are used that can be aerodynamically optimized.
- the ducted propeller according to the invention to seal the upper wing surface from the lower wing surface in order to avoid pressure equalization during cruise.
- the advantage of a corresponding embodiment accordingly lies in the sealing of the upper side of the wing from the underside of the wing with minimal impairment of the outer formwork in order to impair the performance of the blade-integrated ducted propeller as little as possible.
- Another embodiment takes into account the fact that such a blade-integrated ducted propeller should be equally suitable for the operating conditions of the hover flight, the transition and the cruise flight.
- the air is deflected twice at an angle of about 90 °: first by 90 ° into the duct that runs through the wing, in order to accelerate the flow with the embedded ducted propeller, which is done through the top Flow guide fins can be supported, and finally 90 ° out of the wing duct to generate forward thrust.
- the ducted propeller in the wing benefits from the compression in the wing channel, which gives the aircraft according to the invention an additional overall lift.
- the possible channel enlargement thus supports the total stroke during the hovering and transition.
- Another embodiment is based on the knowledge that during the acceleration in transitional operation the flow (due to the increasing free jet speed around the aircraft) is not accelerated uniformly along the inlet lip into the channel. Therefore, the flow initially separates at the bow-side edge of the ducted propeller.
- the advantage of a corresponding configuration lies in the improved compression in the ducted propeller during the transition to cruise flight. It also reduces the proportion of turbulent air that is sucked in by the ducted propeller during this transition. Finally, the flow separation at the inlet lip on the bow side is shifted in the stern direction.
- the aircraft can be equipped with angled or even optionally angled wings.
- a corresponding variant increases the wing area effective in level flight, but without expanding the standing area of the aircraft.
- the aircraft may have a battery system that can be charged quickly, which provides the drive energy for vertical take-off and landing as well as level flight and enables the aircraft to be charged at short notice when the vehicle is stationary.
- the granting of manual control to the human pilot comes into consideration, which gives the device according to the invention the greatest possible flexibility in handling.
- Figure 1 shows the cross section of a wing.
- FIG. 2 shows a first detail 15 of the illustration according to FIG. 1.
- FIG. 3 shows a second detail 16 of the illustration according to FIG. 1.
- Figure 4 shows levitation and transition.
- Figure 5 shows the cross section of the wing in a different representation.
- FIG. 6 shows a first detail 22 of the illustration according to FIG. 5.
- Figure 7 shows the cross section of an inlet lamella of the wing.
- FIG. 8 shows a second detail 23 of the illustration according to FIG. 5.
- FIG. 9 shows the cross section of a further wing, the inlet and outlet lamellae of which are in the open position.
- FIG. 10 shows a first detail 25 of the illustration according to FIG. 9.
- FIG. 11 shows a second detail 26 of the illustration according to FIG. 9.
- FIG. 12 shows the cross section of the wing, the inlet and outlet lamellae being in the closed position here.
- FIG. 13 shows a first detail 29 of the illustration according to FIG. 12.
- FIG. 14 shows a second detail 30 of the illustration according to FIG. 12.
- FIG. 15 shows a plan view of the ducted propeller of the wing.
- FIG. 16 illustrates an example of an actuation concept with a rotary drive.
- Figure 1 shows the wing (10) of the aircraft in profile.
- the wing (10) is traversed vertically by a ducted propeller (20), which has inlet lamellas (13) on its upper side, as shown in the illustration, and outlet lamellas (14) for flow guidance on its underside.
- the outlet lamellas (14) can also be used for thrust vector control and thus navigation of the aircraft and are also able to completely close the underside of the ducted propeller (20).
- the inlet lamellas (13) thus serve as flow guide vanes which, in their open position (17), guide the air flow into the ducted propeller (20). (It goes without saying that other locking mechanisms are possible, especially on the inlet side, without departing from the scope of the invention.)
- outlet lamellas (14), which can be seen better in FIG. 3, serve in a corresponding manner as thrust vector blades for controlling the aircraft and as
- FIG. 5 shows an alternative representation of the wing (10) which draws the viewer's attention to two details to be explained below (22 - FIG. 6, 23 - FIG. 7).
- Figure 6 illustrates the seal between the inlet lamellae (13) and the inlet lip of the propeller jacket. This has an inlet lip that at least partially encircles the ducted propeller (20) and has a flexible zone (24) in such a way that the closed inlet lamellas (13) seal the wing (10) by pressing against this zone (24).
- FIGS. 7 and 8 illustrate the seal between the leading or leading edges and trailing or trailing edges of the inlet lamellas (13).
- the latter accordingly have a flexible zone (24) at their trailing edge in such a way that the closed inlet lamellas (13) seal the wing (10) by bending the trailing edge under the leading edge of the inlet lamella (13) following downstream.
- FIG. 9 shows an embodiment of the wing (10), the inlet lip of which surrounds the ducted propeller (20) on the upper side is aerodynamically optimized: As the detailed illustrations in FIGS. 10 and 11 clearly show in comparison, the said inlet lip here has a flat curvature (27) on the bow and a significantly stronger curvature (28) at the rear.
- FIG. 12 shows the same wing (10), the inlet lamellae (13) on the top and the outlet lamellae (14) on the underside now being in the completely closed position.
- pressure equalization between the negative pressure (11) above the wing (10) and the positive pressure (12) below the wing (10) is largely avoided through the ducted propeller (20).
- the inlet lamellas (13) thus serve as flow guide vanes which, in their open position (17), guide the air flow into the ducted propeller (20).
- two webs (21) spanning the ducted propeller in parallel serve as the adjusting mechanism of at least the inlet lamellas (13).
- these webs (21) are driven by a rotary actuator (33) offset by 90 °, which is arranged outside the airfoil channel between the webs (31).
- two planetary gears (35) which act on a continuous shaft of the rotary actuator (33) on both sides are used for translation.
- Each web (21) is assigned a radial lever (34) which converts the rotational movement translated by the gear (35) into a translational movement which - in the present case via an intermediate piece - drives a push rod (32).
- This in turn carries several lamellar levers (31), each of which is assigned one of the lamellas (13).
- both levers (34) are preferably in a self-locking position so that they do not exert any forces on the rotary actuator (33).
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Life Sciences & Earth Sciences (AREA)
- Remote Sensing (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Power Engineering (AREA)
- Transportation (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102020113491.6A DE102020113491A1 (en) | 2020-05-19 | 2020-05-19 | Aircraft |
PCT/EP2021/025148 WO2021233574A1 (en) | 2020-05-19 | 2021-04-21 | Aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4153478A1 true EP4153478A1 (en) | 2023-03-29 |
Family
ID=75690236
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP21721834.6A Pending EP4153478A1 (en) | 2020-05-19 | 2021-04-21 | Aircraft |
Country Status (5)
Country | Link |
---|---|
US (1) | US20230182897A1 (en) |
EP (1) | EP4153478A1 (en) |
CN (1) | CN115605396A (en) |
DE (1) | DE102020113491A1 (en) |
WO (1) | WO2021233574A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11926429B2 (en) * | 2018-07-04 | 2024-03-12 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft having cooling system for distributing heat transfer liquid to different regions of aircraft |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3179353A (en) * | 1958-02-04 | 1965-04-20 | Ryan Aeronautical Co | Jet powered ducted fan convertiplane |
US2988301A (en) | 1958-10-28 | 1961-06-13 | Charles J Fletcher | Ducted fan aircraft |
US3110456A (en) | 1961-08-08 | 1963-11-12 | English Electric Co Ltd | Vertical take-off aircraft |
GB2146298B (en) | 1978-10-02 | 1985-12-18 | Rolls Royce | Apparatus for varying the configuration of the exhaust discharge opening of a gas turbine jet propulsion engine |
US5454531A (en) | 1993-04-19 | 1995-10-03 | Melkuti; Attila | Ducted propeller aircraft (V/STOL) |
US6105901A (en) * | 1996-08-02 | 2000-08-22 | Allison Engine Co., Inc. | Thrust vectoring system |
US6561456B1 (en) * | 2001-12-06 | 2003-05-13 | Michael Thomas Devine | Vertical/short take-off and landing aircraft |
DE102009048201A1 (en) | 2009-10-05 | 2011-04-28 | Eads Deutschland Gmbh | Drive mechanism for e.g. fixed wing aircraft, has lifting drive turbine actuated by exhaust gas stream of radiation jet engine, and device increasing exhaust gas temperature of burners and arranged in section of exhaust gas channel |
US10710713B2 (en) | 2014-07-18 | 2020-07-14 | Pegasus Universal Aerospace (Pty) Ltd. | Vertical take-off and landing aircraft |
DE102014115926A1 (en) | 2014-10-31 | 2016-05-04 | Johann Schwöller | Drive module for a motor vehicle and motor vehicle with such a drive module |
US10246184B2 (en) * | 2015-12-02 | 2019-04-02 | Jon M. Ragland | Aircraft with internally housed propellor units |
GB2555440A (en) | 2016-10-27 | 2018-05-02 | Mono Aerospace Ip Ltd | Vertical take off and landing aircraft |
KR101938459B1 (en) * | 2016-12-15 | 2019-01-14 | 한국항공우주연구원 | Aircraft |
DE102019112132B4 (en) | 2019-05-09 | 2024-05-23 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft |
-
2020
- 2020-05-19 DE DE102020113491.6A patent/DE102020113491A1/en active Pending
-
2021
- 2021-04-21 WO PCT/EP2021/025148 patent/WO2021233574A1/en unknown
- 2021-04-21 US US17/921,381 patent/US20230182897A1/en active Pending
- 2021-04-21 EP EP21721834.6A patent/EP4153478A1/en active Pending
- 2021-04-21 CN CN202180034628.1A patent/CN115605396A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
CN115605396A (en) | 2023-01-13 |
WO2021233574A1 (en) | 2021-11-25 |
DE102020113491A1 (en) | 2021-11-25 |
US20230182897A1 (en) | 2023-06-15 |
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