Patent Grant
12006048
This invention relates to electric powered flight, namely a power system for electric motors used on aircrafts.
The following description of the preferred embodiments of the invention is not intended to limit the invention to these preferred embodiments, but rather to enable any person skilled in the art to make and use this invention.
The power system can include: a plurality of batteries, a plurality of electric propulsion units, flight computers, and power connections. The propulsion assemblies can include a motor, a propeller, and one or more inverters. The power system can optionally include a plurality of flight actuators. However, the power system can include any other suitable set of components. The power system functions to provide aircraft propulsion and/or aircraft control authority during flight.
In variants, the power system can be implemented in conjunction with the redundant power architecture and/or tiltrotor aircraft power configuration described in U.S. application Ser. No. 16/428,794, filed 31 May 2019, which is incorporated in its entirety by this reference.
In variants, the power system can be implemented in conjunction with the electric aircraft configuration described in U.S. application Ser. No. 16/409,653, filed 10 May 2019, which is incorporated in its entirety by this reference.
Motors of the power system can be integrated into a propeller and/or include an integrated inverter, or can be otherwise suitably connected to an inverter and/or propeller. Accordingly, the term “electric propulsion unit” (EPU) as referenced herein can refer to any suitable motor, propeller, and/or inverter system.
The term “rotor” as utilized herein, in relation to portions of the power system 100 or otherwise, can refer to a rotor, a propeller, and/or any other suitable rotary aerodynamic actuator. While a rotor can refer to a rotary aerodynamic actuator that makes use of an articulated or semi-rigid hub (e.g., wherein the connection of the blades to the hub can be articulated, flexible, rigid, and/or otherwise connected), and a propeller can refer to a rotary aerodynamic actuator that makes use of a rigid hub (e.g., wherein the connection of the blades to the hub can be articulated, flexible, rigid, and/or otherwise connected), no such distinction is explicit or implied when used herein, and the usage of “rotor” can refer to either configuration, and any other suitable configuration of articulated or rigid blades, and/or any other suitable configuration of blade connections to a central member or hub. Likewise, the usage of “propeller” can refer to either configuration, and any other suitable configuration of articulated or rigid blades, and/or any other suitable configuration of blade connections to a central member or hub. Accordingly, the tiltrotor aircraft can be referred to as a tilt-propeller aircraft, a tilt-prop aircraft, and/or otherwise suitably referred to or described.
The term “battery” as utilized herein, in relation to portions of the power architecture or otherwise, can refer to any suitable set or combination of battery cells, battery bricks, battery modules, battery packs, and/or other suitable portions of an energy system. Battery “cell” preferably refers to a unitary battery element, but can be otherwise defined. A battery “brick” can refer to a plurality of battery cells connected in parallel (e.g., with a common bus), but can be otherwise defined. A battery module can refer to a plurality of battery cells and/or bricks arranged in series, but can be otherwise defined. A battery pack can refer to any suitable combination or permutation of battery cells, bricks, and/or modules arranged in series and/or parallel; a set of battery cells, bricks, and/or modules enclosed within a common housing; and/or otherwise defined. One or more battery packs can collectively form an energy system, which can supply power to various aircraft endpoints.
Variations of the technology can afford several benefits and/or advantages.
First, variations of the power system can prevent marginal power and/or actuator failures from escalating into a serious failure (e.g., loss of aircraft command and control ability, etc.) by utilizing multiple layers of power and/or actuator redundancy. In variations, the power system can retain control authority with a loss of any two batteries, motors (and propellers mounted thereto), flight control surfaces (or flight actuators driving said flight control surfaces), power connections, and/or any other suitable components. In an example, the power system can rely upon dual-wound motors to provide an additional degree of power redundancy (e.g., for control surface actuators) and/or electrical redundancy. In such variants, the power system can reliably enhance power system architecture for electric motors adapted for use in an aircraft. Individual batteries may be used to power a subset of two or more motors in power systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. Each motor may have two or more sets of windings, with each winding powered by a different battery. With a failed winding, failed battery, or failed motor in a forward flight or a vertical take-off and landing mode, power routing may be automatically altered to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.
However, the power system can include any other suitable redundancies.
Second, variations of the power system can make the aircraft robust to unplanned external damage sources (e.g., electrical or mechanical inputs). For example, components of the power system can be arranged such that flight-critical hardware (e.g., flight computers, batteries, PoE switches, etc.) are physically separated from one another (while connected via the power architecture and/or data transfer network) outside of a predetermined radius (e.g., predetermined based on a predicted, estimated, and/or historical damage radius resulting from explosive component failure, decompression, fire damage, etc.).
Third, variations of the power system can provide continuous power availability by load balancing various batteries of the aircraft. In such variants, the flight computers can command different proportions of power to various motors, motor windings, and/or flight actuators within the power architecture to shift power/current draw to batteries with the greatest remaining charger (e.g., highest SOC). However, the power architecture can otherwise ensure continuous power availability on the aircraft.
However, variations of the technology can additionally or alternatively provide any other suitable benefits and/or advantages.
The power system 100 can include: a plurality of batteries, a plurality of electric propulsion units, flight computers, and power connections (e.g., forming a power distribution architecture). The electric propulsion units (EPUs) can include a motor, a propeller, and one or more inverters. The power system can optionally include a plurality of flight actuators. However, the power system can include any other suitable set of components. The power system functions to provide aircraft propulsion and/or aircraft control authority during flight.
The power system 100 can include a plurality of batteries which function to store electrochemical energy in a rechargeable manner. The system can include any suitable number of batteries (e.g., battery packs), such as 1, 2, 3, 4, 5, 6, more than 6, a range bounded by the aforementioned values, and/or any other suitable number of battery packs as a part of a complete energy system. Battery packs can be arranged and/or distributed about the aircraft in any suitable manner. Preferably, battery packs are arranged proximal to a vertical lateral plane of the aircraft, but can be otherwise suitably arranged. Battery packs can be arranged within wings (e.g., inside of an airfoil cavity), inside nacelles, and/or in any other suitable location on the aircraft. In a specific example, the system includes a first battery pack within an inboard portion of a left wing and a second battery pack within an inboard portion of a right wing. In a second specific example, the system includes a first battery pack within an inboard nacelle of a left wing and a second battery pack within an inboard nacelle of a right wing. In a third example, one or more battery packs include a plurality of battery modules. The battery pack can include or exclude the battery pack housing/enclosures (e.g., closeouts), can be assembled into the aircraft separately from the battery pack housing/enclosures, and/or can be otherwise suitably configured. The battery pack can include any suitable cells of any suitable type, chemistry, voltage, maximum C-rate, capacity, and/or other characteristics. Battery cells can be the same or different across various battery modules/packs, or within the same battery module/pack. Battery cell types (e.g., geometries) can include cylindrical, button, prismatic, pouch, and/or any other suitable cell geometries.
The electric propulsion units (EPUs) function to rotate an airfoil to generate thrust and/or aerodynamic lift, propelling the aircraft. The EPUs (hereinafter interchangeably referenced as “propulsion assemblies”) can include a motor, a propeller, and one or more inverters. However, the EPUs can include any other suitably components. The aircraft preferably includes 6 EPUs, but can additionally or alternatively include 3 EPUs, 8 EPUs, and/or any other suitable number of EPUs. The EPUs are preferably distributed symmetrically about a sagittal midplane of the aircraft, and most preferably substantially equidistant from a center of gravity of the aircraft, but can be otherwise suitably implemented.
The motor functions to generate a torque about and/or rotate about a motor axis. In variants, the motor can be connected to a propeller of an aircraft and/or integrated into the hub of a propeller. The motor can be an in-runner motor, outrunner motor, and/or any other suitable type of motor. Preferably, the motor is a large diameter motor and/or a motor designed for high-torque, low-speed operation. The motor can include a diameter of: 100 mm, 200 mm, 250 mm, 300 mm, 320 mm, 350 mm, 380 mm, 400 mm, 420 mm, 450 mm, 500 mm, greater than 500 mm, any range bounded by the aforementioned values, and/or any other suitable diameter. However, the motor can have any other suitable dimensions. The motor can have any suitable power capabilities and/or requirements. Preferably, the motor is a 3-phase motor, and more preferably is a dual-wound 3-phase motor (e.g., two sets of redundant 3-phase windings). However, the motor can include any other suitable number of phases or be otherwise constructed. The motor can have a power threshold (e.g., peak power, maximum continuous power, nominal power, max power of individual set of windings of dual-wound motor, etc.) of: less than 80 kW, 80 kW, 120 kW, 150 kW, 200 kW, 220 kW, 230 kW, 240 kW, 250 kW, 300 kW, 450 kW, 460 kW, 480 kW, 500 kW, greater than 500 kW, any range bounded by the aforementioned values, and/or any other suitable power characteristics. Accordingly, the torque/speed characteristics of the motor can be designed/selected to correspond to the aerodynamic properties of the propeller (and/or aircraft). In a specific example, the motor can be operate the rotor at a top speed of: less than 100 RPM, 100 RPM, 300 RPM, 500 RPM, 800 RPM, 1000 RPM, 1200 RPM, 1300 RPM, 1500 RPM, 1800 RPM, 2000 RPM, 2200 RPM, 2500 RPM, 3000 RPM, 5000 RPM, greater than 5000 RPM, any range bounded by the aforementioned values, and/or any appropriate speed, and can operate with a maximum torque of: less than 10 N-m, 50 N-m, 100 N-m, 500 N-m, 800 N-m, 1000 N-m, 1200 N-m, 1500 N-m, 1800 N-m, 2000 N-m, 2200 N-m, 2500 N-m, 3000 N-m, 5000 N-m, greater than 5000 N-m, any range bounded by the aforementioned values, and/or any appropriate maximum torque. However, the motor can have any suitable torque/speed characteristics, and the propeller can likewise be operated in any suitable regime of the torque-speed curve of the motor.
In a first variant of the motor (‘dual wound motor variant’), electrical bussing within the motor subdivides the field coils into a first and second set of windings (e.g., 2 sets of 3 phase windings) which can be separately powered and/or separately drive rotation of the motor. Preferably, adjacent field coils are in opposing sets of windings, however the field coils can be otherwise suitably distributed to enable independent and/or separate actuation via each set of windings. Accordingly, each set of windings can be powered by a separate inverter and/or can be powered by the same inverter. The dual wound variant can provide an additional layer of redundancy, since a single point of electrical failure (either within the motor and/or at the inverter) can compromise only a single set of windings. In variants, each set of windings and/or each inverter can be powered by a separate set of power sources (e.g., separate sets of battery packs), which can similarly allow the motor to continue operating even with the loss of one or more power sources. In a specific example, the bussing divides the full electromagnetic motor circuit into equal partial motors dividing stator and windings (e.g., like ‘pie slices’) which are controlled by two independent phase control schemes. The electrical bussing is preferably arranged on a rear portion of the motor and/or inboard portion of the motor, but can additionally or alternately be formed on the front side, radially inward of the stator body, and/or otherwise suitably configured. The electrical bussing can include a set of motor terminals (e.g., one terminal associated with each pole of the motor for each set of windings) which connect the motor to the inverter and a set of power connections connecting the field coil terminals. However, the motor can alternatively include only a single set of windings (e.g., one set of three phase windings), include more than two sets of windings, and/or be otherwise suitably configured.
However, the EPUs can include any other suitable motor.
The inverters function to supply conditioned power to the motor and/or control the rotation of the motor based on the commands from the flight computer(s). there is preferably one inverter associated with each set of motor windings of the motors. In a specific example, each EPU can include a first and second inverter respectively associated with the first and second sets of windings of a dual-wound motor. However, the EPU can include additional inverters, which can power a motor cooling pump, cooling fan, blade pitch mechanism, and/or tilt linkage of the propulsion assembly. The inverter can be integrated into the motor, mounted to an inboard portion of the motor, separate from the motor (e.g., arranged within a nacelle, remote, etc.) and connected to the motor within the power system. However, the EPUs can include any other suitable inverters.
The propellers function to generate aerodynamic lift when driven by the rotation of the motor about the motor axis, thereby propelling the aircraft. The propellers can be mounted to the motor in a fixed and/or pivotable manner (e.g., by a blade pitch mechanism), and are configured to rotate about the motor axis. However, the propulsion assemblies can include any suitable propellers.
The propulsion assemblies can optionally include a tilt mechanism which functions to pivot and/or translate the motor (and the propeller mounted thereto). In a specific example, the tilt mechanism can be configured to transform the motor and propeller between a forward configuration, wherein the motor/propeller axis is substantially parallel with the longitudinal/roll axis of the aircraft, and a hover configuration, wherein the motor/propeller axis is substantially parallel to the vertical/yaw axis of the aircraft (e.g., and/or a gravity vector). The tilt mechanism can connect to the rear/inboard portion of the motor (and/or an inverter mounted thereto) and mount the motor to the airframe of the aircraft. In a first example, the tilt mechanism can include the linkage and/or nacelle/boom pivot described in U.S. application Ser. No. 16/409,653, filed 10 May 2019, which is incorporated herein in its entirety by this reference. In a second example, the tilt mechanism can include the linkage described in U.S. application Ser. No. 14/660,838, filed 17 Mar. 2015, which is incorporated herein in its entirety by this reference.
However, the propulsion assembly can include any other suitable tilt mechanism, and/or exclude a tilt mechanism.
The propulsion assemblies can optionally include a blade pitching mechanism which functions to change an angle of attack of the blades of an aircraft propeller (e.g., relative to a disc plane). The blade pitching mechanism can allow independent articulation of each blade, collective articulation of the blade pitch (e.g., simultaneous), cyclic articulation of the blade pitch, and/or otherwise suitably allow articulation. The blade pitching mechanism can include a rotary plate mechanism (e.g., swashplate) and/or linkage which extends through an interior of the motor. In a specific example, the blade pitching mechanism extends through an interior of a motor bearing and/or is mounted at a radial position inward of the bearing. However, the blade pitching mechanism can extend through the motor (e.g., along the motor's rotational axis, through the motor center), extend around the motor, or be otherwise arranged. The blade pitching mechanism can connect to the tilt mechanism directly and/or indirectly (e.g., mounted to the inverter housing and/or stator of the motor).
However, the set of actuators can include any other suitable blade pitching mechanism, and/or exclude a blade pitching mechanism.
The flight computer functions to generate commands that can be transmitted to and interpreted by EPU inverters and/or flight actuators to control aircraft flight. In variations including a plurality of flight computers, each of the plurality of flight computers can be a substantially identical instance of the same computer architecture and components, but can additionally or alternatively be instances of distinct computer architectures and components (e.g., generalized processors manufactured by different manufacturers). The flight computers can include: CPUs, GPUs, TPUs, ASICs, microprocessors, and/or any other suitable set of processing systems. In variations, each of the flight computers performs substantially identical operations (e.g., processing of data, issuing of commands, etc.) in parallel, and is connected (e.g., via the distribution network) to the same set of flight components. In such variations, the output of each flight computer is provided to the EPUs and/or flight actuators by way of a data distribution network (e.g., as described in U.S. application Ser. No. 16/573,837, filed 17 Sep. 2019, which is incorporated herein in its entirety by this reference).
However, the power system can be used with any suitable propulsion assemblies.
The power connections function to distribute power between the batteries and the EPUs, and can additionally or alternatively function to provide power to a (e.g., low voltage) data transfer network and/or flight actuators. Power connections can be configured in any suitable architectures. Examples of power connection architectures are shown in
The power connections can group the batteries into battery sets, where batteries within a battery set are connected to each component within a component set (e.g., wherein components of the same type can be divided into component sets). Examples of component sets include: battery sets, flight actuator sets, EPU sets, and/or sets of other components. Component sets preferably do not overlap with other sets of the same component type, but can alternatively overlap with other sets of the same component type. Component sets connected to a given battery set are preferably connected to each other and/or are not connected to other component sets that are connected to other battery sets, but the component sets powered by a different battery sets can alternatively overlap. The power connections between the battery set and each component set can be: a shared wire, a shared bus, different connections (e.g., wires, busses, etc.) for each battery-component connection, and/or be otherwise configured.
The power connections can group the batteries into various ‘pairs’, where paired batteries are connected to the respective windings of one or more dual wound motors and/or are connected to two different inverters of an EPU (associated in a pairwise manner with the dual windings of the motor within the EPU). Accordingly, each battery can be paired with exactly one other battery and/or can form a portion of exactly one battery pair (e.g., doublet variant, an example is shown in
Paired and/or unpaired batteries can be distributed about the aircraft based on: a threshold spatial offset (e.g., for impact survivability), fire vent paths, distance from passenger seats, electrically isolation (e.g., between switch sets and/or actuator sets, as described in U.S. application Ser. No. 16/428,794, filed 31 May 2019, which is incorporated in its entirety by this reference), and/or otherwise suitably distributed.
However, power connections can interconnect batteries with the EPUs and/or other components of the power system in any suitably manner.
However, the power system can include any other suitable components.
In some aspects, an aircraft may use bladed propellers powered by electric motors to provide thrust during take-off. The propeller/motor units may be referred to as propulsion assemblies. In some aspects, the wings of the aircraft may rotate, with the leading edges facing upwards, such that the propellers provide vertical thrust for takeoff and landing. In some aspects, the motor driven propeller units on the wings may themselves rotate relative to a fixed wing, such that the propellers provide vertical thrust for take-off and landing. The rotation of the motor driven propeller units may allow for directional change of thrust by rotating both the propeller and the electric motor, thus not requiring any gimbaling, or other method, of torque drive around or through a rotating joint.
In some aspects, aircrafts according to embodiments of the present invention take off from the ground with vertical thrust from rotor assemblies that have deployed into a vertical configuration. As the aircraft begins to gain altitude, the rotor assemblies may begin to be tilted forward in order to begin forward acceleration. As the aircraft gains forward speed, airflow over the wings results in lift, such that the rotors become less important and then unnecessary for maintaining altitude using vertical thrust. Once the aircraft has reached sufficient forward speed, some or all of the blades used for providing vertical thrust during take-off may be stowed along their nacelles. In some aspects, all propulsion assemblies used for vertical take-off and landing are also used during forward flight. The nacelle supporting the propulsion assemblies may have recesses such that the blades may nest into the recesses, greatly reducing the drag of the disengaged rotor assemblies.
After take-off, the aircraft will begin a transition to forward flight by articulating the propellers from a vertical thrust orientation to a position which includes a horizontal thrust element. As the aircraft begins to move forward with speed, lift will be generated by the wings, thus requiring less vertical thrust from the rotors. As the propellers are articulated further towards the forward flight, horizontal thrust, configuration, the aircraft gains more speed.
In a first vertical configuration according to some embodiments of the present invention, as seen in a vertical take-off configuration in
The aircraft body 201 extends rearward is also attached to raised rear stabilizers 204. The rear stabilizers have rear propulsion assemblies 205 attached thereto. The motor driven rotor assemblies 207 at the tips of the rear stabilizers may deploy from a forward flight configuration to a vertical take-off and landing configuration along a pivot axis wherein the nacelle and the electric motor and propeller deploy in unison.
As seen in top view in
The aircraft 200 is seen with two passenger seats side by side, as well as landing gear under the body 201. Although two passenger seats are illustrated, other numbers of passengers may be accommodated in differing embodiments of the present invention.
In some aspects, all or a portion of the wing mounted propulsion assemblies may be adapted to be used in a forward flight configuration, while other wing mounted propellers may be adapted to be fully stowed during regular, forward, flight. The aircraft 200 may have two propulsion assemblies on the right wing 203 and two propulsion assemblies on the left wing 202. The inboard propulsion assemblies on each wing may have wing mounted rotors 206 that are adapted to flip up into a deployed position for vertical take-off and landing, to be moved back towards a stowed position during transition to forward flight, and then to have their blades stowed, and nested, during forward flight. The outboard propulsion assembly 207 may pivot in unison from a horizontal to a vertical thrust configuration.
Similarly, the each rear stabilizer 204 may have propulsion assemblies mounted to it, both of which are adapted to be used during vertical take-off and landing, and transition, modes. In some aspects, all of the propulsion assemblies designs are the same, with a subset used with their main blades for forward flight. In some aspects, all of the propulsion assemblies designs are the same, with all propellers used for forward flight. In some aspects, there may be a different number of propulsion assemblies units mounted to the rear stabilizer 204.
The aircraft can include any suitable set of flight actuators, which functions to transform aerodynamic forces/moments of the aircraft to affect aircraft control. Flight actuators can include control surface actuators (configured to drive control surfaces), tilt linkages (e.g., which function to transform the aircraft and/or propulsion assemblies thereon between a forward and a hover configuration), variable blade pitch actuators (e.g., for variable blade pitch rotors), and/or any other suitable actuators. Control surfaces can include flaps, elevators, ailerons, rudders, ruddervators, spoilers, slats, air brakes, and/or any other suitable control surfaces. In variants, control surfaces can include the high-lift mechanism as described in U.S. application Ser. No. 17/033,178, filed 25 Sep. 2020, which is incorporated in its entirety by this reference.
The aircraft can additionally or alternatively include landing gear (e.g., retractable landing gear, fixed landing gear), which functions to structurally support the aircraft when it is in contact with the ground and/or maneuver the aircraft during taxi.
However, the power architecture can be integrated into and/or implemented in conjunction with any suitable aircraft.
The motors driving the wing mounted propulsion assemblies 206, 207 and/or the motors driving the rear stabilizer mounted propulsion assemblies may each have two sets of windings. In some aspects, both winding sets are powered during flight. In some aspects, each winding of the motor is powered by a different battery circuit. In some aspects, each motor may have more than two sets of windings. In variants, each motor can be configured to be separately and/or cooperatively powered via a plurality of inverters. In a specific example, each electric propulsion unit (EPU) can include two inverters (e.g., quad inverters), each powered by a separate battery (e.g., of a doublet pair, etc.), an example of which is shown in
In some embodiments, the electric motors of the aircraft are powered by rechargeable batteries. The use of multiple batteries driving one or more power busses enhances reliability, in the case of a single battery failure. In some embodiments, the batteries reside within the vehicle body on a rack with adjustable position such that the vehicle balance may be adjusted depending upon the weight of the pilot.
In some embodiments, as seen in
In an exemplary six motor six battery embodiment 10, the first motor 11 is coupled to the sixth battery 26 and the first battery 21. The second motor 12 is coupled to the first battery 21 and the second battery 22. The third motor 13 is coupled to the second battery 22 and the third battery 23. The fourth motor 14 is coupled to the third battery 23 and the fourth battery 24. The fifth motor 15 is coupled to the fourth battery 24 and the fifth battery 25. The sixth motor 16 is coupled to the fifth battery 25 and the sixth battery 26. In a nominal operating scenario, each battery splits its power distribution evenly between the two motors to which it is coupled, and each motor receives an equal amount of power from each battery to which it is coupled.
The fault tolerant aspect of the power system architecture according to embodiments of the present invention is adapted to withstand, and respond to, at least the following failures: the failure of a battery; the failure of a motor; or the failure of a motor inverter.
As seen in
As seen in
In some embodiments, the vertical take-off and landing aircraft has an autonomous attitude control system adapted to withstand a power link failure, or complete motor failure, in a multi-battery system by load sharing to better equate battery discharge levels. In some aspects, each motor is driven on multiple complementary winding sets, with each winding set using a different load link and being driven by a different battery.
A flight computer 205 monitors the current from each of the twelve motor inverters 202 which are supplying power to the twelve winding sets in the six motors 203. The flight computer 205 may also control the motor current supplied to each of the 12 sets of windings of the six motors. In some embodiments, the batteries 201 also supply power to the blade pitch motors and position encoders of the variable pitch propellers 206. The batteries also supply power to control surface actuators 207 used to position various control surfaces on the airplane. The blade pitch motors and the control surface actuators 207 may receive power run through a DC-DC converter 208, stepping the voltage down from 600V to 160V, for example. A suite of avionics 209 may also be coupled to the flight computer. A battery charger 210 may be used to recharge the batteries 201, and the battery charger may be external to the aircraft and ground based. In variants, the flight computer can be implemented and communicatively connected within the power architecture as described in U.S. application Ser. No. 16/573,837, filed 17 Sep. 2019, which is incorporated in its entirety by this reference. In a specific example, a first set of batteries (e.g., doublet pair) can power a first switch set, and a second set of batteries (e.g., separate and distinct from the first set, remainder of the batteries, second doublet pair, etc.) can power a second switch set, the switch sets communicatively connecting the flight computers to the flight actuators (e.g., an example is shown in
In the case of a failure, such as the failure of a motor, or of a power link to a motor, the compensations to power distribution to the various motors from the various batteries, as described above, may be done autonomously and onboard the aircraft. The compensations may be done without needing input from the pilot, for example.
In another failure scenario, a single winding on a motor may fail. In such a scenario, the opposing motor may be powered down somewhat while the motor with a sole remaining winding may be powered up somewhat. The power supplied by the batteries may be moderated to even out the discharge of the various batteries. In yet another failure scenario, a battery may fail. In that case the cross motor may be reduced 10-20%, with the sole battery remaining on the motor with the failed battery/inverter providing extra power, and differential power along the ring used to spread the battery discharge. In the case of a completely failed battery in the ring architecture, which would result in two motors each having one winding set go unpowered, the remaining winding set in each of the adjacent motors would take increased power from that winding set's battery, and there would be differentially adjusted power around the ring in order to best equalize the battery discharge rates. The cross motor would be partially powered down to maintain appropriate discharge rates.
In an exemplary embodiment, the maximum gross take-off weight (MGTOW) may be 4200 pounds. The discharge rates are out of ground effect (OGE), with a total energy storage of all batteries of 150 kWh. In the case of an emergency landing in the emergency hover mode 231, the anticipated time using the high discharge rate at the emergency hover discharge rate 237 is approximately 1 minute.
In some embodiments of the present invention, other battery and motor architectures may be used which further enhance the fault tolerance of the system. In some aspects, as seen in
However, the power architecture can be integrated into and/or implemented in conjunction with an aircraft including any suitable number and/or arrangement of EPUs, motors, propulsion assemblies. Likewise, the aircraft can include any suitable number and/or arrangement of batteries (packs, cells, modules, etc.).
Flight actuators and/or landing gear can include redundancies which functions to preserve control authority in the event of a failure (e.g., mechanical, electrical, thermal, communication, etc.). Flight actuator and/or landing gear redundancy can include: duplicative redundancy (e.g., multiple instances of a control surface and/or actuator on the same side of a sagittal midplane of the aircraft), multiplicative communication channels (e.g., to distinct switch sets, an example is shown in
Preferably, each flight actuator can be supplied with power from a single battery (e.g., by a single power connection; an example is shown in
Flight actuators can be subdivided into sets/pairs if they are redundant (e.g., can interchangeably/cooperatively affect the same generic aircraft control authority) and are separately powered by paired batteries. Flight actuator pairs are preferably located on the same side of the sagittal midplane of the aircraft and/or adjacent to one another (e.g., along a rear portion of the main wing, along a rear portion of the rear stabilizer, etc.), but can be otherwise suitably arranged/distributed. However, flight actuators can alternatively be construed to define any other suitable redundant and/or non-redundant sets/groups.
However, flight actuators can be otherwise suitably powered and/or operated in conjunction with various load balancing schemes.
Redundant flight actuators (and/or control surfaces driven thereby) and/or landing gear can be associated with (e.g., powered by) paired batteries and/or unpaired batteries. In a first example, the aircraft can include two wing flaps on each side of the sagittal midplane of the aircraft (e.g., 4 wing flaps: 2 left and 2 right). The two left wing flaps (mounted to the main wing) are preferably associated with (e.g., driven by actuators powered by) the first and second batteries of a first battery pair, respectively. The two right wing flaps are preferably associated with (e.g., powered by) the first and second batteries of a second battery pair (e.g., where the intersection of the first and second battery pairs is null), respectively. However, the first example can likewise hold for ailerons in place of flaps, and/or any other suitable control surfaces on the main wing or rear stabilizer. In a second example, the aircraft can include a three ruddervators (e.g., mounted to the rear stabilizer 204) on each side of the sagittal midplane of the aircraft (e.g., 6 ruddervators: 3 left and 3 right). The three left ruddervators are preferably associated with the first battery of a first battery pair, the second battery of a first battery pair, and the first battery of a second battery pair (e.g., unpaired with either the first or second batteries of the first battery pair), respectively. However, the second example can likewise hold for elevators, rudders, ailerons, and/or any other suitable control surfaces in place of ruddervators (e.g., on either the main wing or rear stabilizer). In a third example, landing gear actuators can be dual would and powered by paired batteries. In a fourth example, landing gear actuators can be dual wound and redundantly powered by unpaired batteries. In a fifth example, each of a plurality of dual wound landing gear actuators (e.g., 4) is powered by a different combination of batteries (an example is shown in
In one or more embodiments, an electric aircraft comprising: a battery pair comprising a first and second battery; a first propulsion assembly comprising: a dual-wound electric motor comprising a first and second set of windings connected to the first and second batteries, respectively; and a propeller coupled to the dual-wound electric motor; a pair of control surfaces arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface; and a first and a second flight actuator electrically connected to the first and second batteries, respectively, wherein the first and second flight actuators are mechanically connected to the first and second control surfaces, respectively.
In one or more embodiments, first flight actuator is not redundantly powered by the second battery.
In one or more embodiments, the aircraft is configured to equilibrate a state of charge (SoC) of the first and second batteries based on a weighted power distribution of the first and second sets of windings.
In one or more embodiments, the aircraft further comprising a second and third propulsion assembly, each comprising a respective dual-wound electric motor and a respective propeller, the first and second batteries connected to a respective set of windings of the dual-wound electric motor of each of the second and third propulsion assemblies.
In one or more embodiments, the electric aircraft further comprising: a first motor inverter electrically coupled to the first set of windings and the first control surface; and a second motor inverter electrically coupled to the second set of windings, wherein the second battery is selectively connected to the first flight actuator in a propulsive mode of the second motor inverter and a regenerative mode of the first motor inverter.
In one or more embodiments, each battery of the battery pair is sized to be capable of independently powering the first propulsion assembly above a power threshold of the motor.
In one or more embodiments, the first battery is arranged on the first side of the midsagittal plane and the second battery is arranged on a second side of the midsagittal plane, opposite the first side.
In one or more embodiments, the first battery is arranged within an inboard portion of a wing of the aircraft, wherein the second battery is arranged within an outboard portion of the wing relative to the inboard portion.
In one or more embodiments, the electric aircraft further comprising: a second battery pair comprising a third and fourth battery; a second propulsion assembly comprising: a second dual-wound electric motor comprising a third and fourth set of windings connected to the third and fourth batteries, respectively; and a propeller coupled to the dual-wound electric motor; a second pair of control surfaces comprising a third and a fourth control surface symmetrically opposing the first and second control surfaces across the midsagittal plane, respectively; and a third and a fourth flight actuator electrically connected to the third and fourth batteries and mechanically connected to the third and fourth control surfaces, respectively.
In one or more embodiments, during a failed state of the third actuator: the third control surface is in a deployed position, and the first actuator is configured to actuate the first control surface to mirror the deployed position of the third control surface.
In one or more embodiments, the electric aircraft comprising a plurality of propulsion assemblies comprising the first and second propulsion assemblies, wherein the electric aircraft is further configured to accommodate a failure state of the first propulsion assembly by: reducing a first power provision to the second propulsion assembly; and increasing a respective power provision to each of a remainder of the plurality of propulsion assemblies.
In one or more embodiments, the electric aircraft further comprising: a fifth control surface adjacent to the first and second control surfaces and arranged on a first side of the mid-sagittal plane; and a fifth flight actuator electrically connected to the third battery and mechanically connected to the fifth control surface.
In one or more embodiments, the first, second, and third control surfaces are ruddervators.
In one or more embodiments, the third battery is larger than the fourth battery and the third battery symmetrically opposes the first battery across the midsagittal plane.
In one or more embodiments, the first and second control surfaces are duplicative.
In one or more embodiments, a method comprising: determining a flight command for an electric aircraft, the electric aircraft comprising: a battery pair comprising a first and a second battery; and a propulsion assembly comprising a propeller coupled to a dual-wound motor, the dual wound motor having a first and a second set of windings connected to the first and second batteries of the battery pair, respectively; determining a battery state for each battery of the battery pair; determining a weighted power distribution relative to the battery states of the first and second batteries, the weighted power distribution comprising a first weight associated with the first battery and a second weight associated with the second battery; based on the flight command and the first weight, supplying power from the first battery to the first set of windings of a propulsion assembly of the plurality; while supplying power to the first set of windings, regeneratively harvesting power from the propeller at the second set of windings based on the second weight; and supplying the regeneratively harvested power to a first flight actuator.
In one or more embodiments, the first and second batteries are arranged on opposing sides of a midsagittal plane of the electric aircraft and are asymmetric about the midsagittal plane.
In one or more embodiments, the electric aircraft further comprises: a second flight actuator, wherein the second and first flight actuators are electrically connected to the first and second batteries, respectively; and a duplicative pair of control surfaces arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface, wherein the first and second flight actuators are mechanically connected to the first and second control surfaces, respectively.
In one or more embodiments, the method further comprising cooperatively actuating the duplicative pair of actuators based on a flight command.
In one or more embodiments, a method comprising: determining a flight command for an electric aircraft, the electric aircraft comprising: a battery pair comprising a first and a second battery; and a plurality of propulsion assemblies, each comprising a propeller coupled to a dual-wound motor, the dual wound motor having a first and a second set of windings connected to the first and second batteries of the battery pair, respectively; a pair of control surfaces arranged on a first side of the mid-sagittal plane of the aircraft, the pair comprising a first and a second control surface; and a first and a second flight actuator electrically connected to the first and second batteries, respectively, the first and second flight actuators mechanically connected to the first and second control surfaces, respectively; determining a battery state for each battery of the battery pair; based on the battery state, load balancing the battery pair, comprising: determining a weighted power distribution relative to the battery states of the first and second batteries, the weighted power distribution comprising a first weight associated with the first battery and a second weight associated with the second battery; and based on the flight command, supplying power to a propulsion assembly of the plurality based on the first and second weights.
In one or more embodiments, supplying power to the propulsion assembly comprises: based on the first weight, supplying power from the first battery to the first set of windings of a propulsion assembly of the plurality; while supplying power to the first set of windings, regeneratively harvesting power from the propeller at the second set of windings based on the second weight; and supplying the regeneratively harvested power to the second battery.
As evident from the above description, a wide variety of embodiments may be configured from the description given herein and additional advantages and modifications will readily occur to those skilled in the art. The invention in its broader aspects is, therefore, not limited to the specific details and illustrative examples shown and described. The embodiments described herein may include physical structures, as well as methods of use. Accordingly, departures from such details may be made without departing from the spirit or scope of the applicant's general invention.
Alternative embodiments implement the above methods and/or processing modules in non-transitory computer-readable media, storing computer-readable instructions. The instructions can be executed by computer-executable components integrated with the computer-readable medium and/or processing system. The computer-readable medium may include any suitable computer readable media such as RAMs, ROMs, flash memory, EEPROMs, optical devices (CD or DVD), hard drives, floppy drives, non-transitory computer readable media, or any suitable device. The computer-executable component can include a computing system and/or processing system (e.g., including one or more collocated or distributed, remote or local processors) connected to the non-transitory computer-readable medium, such as CPUs, GPUs, TPUS, microprocessors, or ASICs, but the instructions can alternatively or additionally be executed by any suitable dedicated hardware device.
Embodiments of the system and/or method can include every combination and permutation of the various system components and the various method processes, wherein one or more instances of the method and/or processes described herein can be performed asynchronously (e.g., sequentially), concurrently (e.g., in parallel), or in any other suitable order by and/or using one or more instances of the systems, elements, and/or entities described herein.
As a person skilled in the art will recognize from the previous detailed description and from the figures and claims, modifications and changes can be made to the preferred embodiments of the invention without departing from the scope of this invention defined in the following claims.
This application is a continuation in part of U.S. application Ser. No. 16/428,794, filed on 31 May 2019, which claims priority to U.S. Provisional Patent Application No. 62/678,275, filed 31 May 2018, each of which is incorporated herein in its entirety by this reference. This application claims benefit to U.S. Provisional Patent Application No. 63/135,387, filed 8 Jan. 2021, and U.S. Provisional Patent Application No. 63/118,504, filed 25 Nov. 2020, each of which is incorporated herein in its entirety by this reference.
| Number | Name | Date | Kind |
|---|---|---|---|
| 1386713 | Leinweber et al. | Aug 1921 | A |
| 1496723 | Albert | Jun 1924 | A |
| 1634167 | Wilson | Jun 1927 | A |
| 1794202 | Pickard | Feb 1931 | A |
| D171509 | Lightborn et al. | Feb 1954 | S |
| 2868476 | Schlieben | Jan 1959 | A |
| 2969935 | Price | Jan 1961 | A |
| 2981339 | Kaplan | Apr 1961 | A |
| 3002712 | Beckwith | Oct 1961 | A |
| 3035789 | Young | May 1962 | A |
| 3059876 | Platt | Oct 1962 | A |
| 3081964 | Quenzler | Mar 1963 | A |
| 3082977 | Melvin | Mar 1963 | A |
| 3089666 | Quenzler | May 1963 | A |
| 3136499 | Kessler | Jun 1964 | A |
| 3141633 | Mackay | Jul 1964 | A |
| 3159361 | Weiland | Dec 1964 | A |
| 3181810 | Olson | May 1965 | A |
| 3231221 | Platt | Jan 1966 | A |
| 3259343 | Roppel | Jul 1966 | A |
| 3350035 | Schlieben | Oct 1967 | A |
| 3360217 | Trotter | Dec 1967 | A |
| 3404852 | Sambell et al. | Oct 1968 | A |
| 3592412 | Glatfelter | Jul 1971 | A |
| 3618875 | Kappus | Nov 1971 | A |
| 3693910 | Aldi | Sep 1972 | A |
| 3795372 | Feldman | Mar 1974 | A |
| 3834654 | Miranda | Sep 1974 | A |
| 3856238 | Malvestuto | Dec 1974 | A |
| 4022405 | Peterson | May 1977 | A |
| 4047840 | Ravenhall et al. | Sep 1977 | A |
| 4053125 | Ratony | Oct 1977 | A |
| 4146199 | Wenzel | Mar 1979 | A |
| 4356546 | Whiteside et al. | Oct 1982 | A |
| 4387866 | Eickmann | Jun 1983 | A |
| 4434389 | Langley et al. | Feb 1984 | A |
| 4519746 | Wainauski et al. | May 1985 | A |
| 4784351 | Fickmann | Nov 1988 | A |
| 4799629 | Mori | Jan 1989 | A |
| 4914657 | Walter et al. | Apr 1990 | A |
| 4925131 | Eickmann | May 1990 | A |
| 4979698 | Ederman | Dec 1990 | A |
| 4982914 | Fickmann | Jan 1991 | A |
| 5031858 | Schellhase et al. | Jul 1991 | A |
| 5082079 | Lissaman et al. | Jan 1992 | A |
| 5085315 | Sambell | Feb 1992 | A |
| 5141176 | Kress et al. | Aug 1992 | A |
| 5184304 | Huddle | Feb 1993 | A |
| 5374010 | Stone et al. | Dec 1994 | A |
| 5405105 | Kress | Apr 1995 | A |
| 5419514 | Duncan | May 1995 | A |
| 5515282 | Jackson | May 1996 | A |
| 5715162 | Daigle | Feb 1998 | A |
| 5806805 | Elbert et al. | Sep 1998 | A |
| 5823468 | Bothe | Oct 1998 | A |
| 5839691 | Lariviere | Nov 1998 | A |
| 5842667 | Jones | Dec 1998 | A |
| 5868351 | Stamps et al. | Feb 1999 | A |
| 6098923 | Peters, Jr. | Aug 2000 | A |
| 6254032 | Bucher | Jul 2001 | B1 |
| 6260796 | Klingensmith | Jul 2001 | B1 |
| 6276633 | Balayn et al. | Aug 2001 | B1 |
| 6286783 | Kuenkler | Sep 2001 | B1 |
| 6293491 | Wobben | Sep 2001 | B1 |
| 6343127 | Billoud | Jan 2002 | B1 |
| 6402088 | Syrovy et al. | Jun 2002 | B1 |
| 6474604 | Carlow | Nov 2002 | B1 |
| 6561455 | Capanna | May 2003 | B2 |
| 6625033 | Steinman | Sep 2003 | B1 |
| 6655631 | Austen-Brown | Dec 2003 | B2 |
| 6719244 | Gress | Apr 2004 | B1 |
| 6745977 | Long et al. | Jun 2004 | B1 |
| 6883748 | Yoeli | Apr 2005 | B2 |
| 6892980 | Kawai | May 2005 | B2 |
| 7048505 | Segota et al. | May 2006 | B2 |
| 7118066 | Allen | Oct 2006 | B2 |
| 7147182 | Flanigan | Dec 2006 | B1 |
| 7159817 | Vandermey et al. | Jan 2007 | B2 |
| 7193391 | Moore | Mar 2007 | B2 |
| 7219013 | Young et al. | May 2007 | B1 |
| 7263630 | Sailer | Aug 2007 | B2 |
| 7310573 | Stickling | Dec 2007 | B2 |
| 7318565 | Page | Jan 2008 | B2 |
| 7376088 | Gambardella et al. | May 2008 | B2 |
| 7802754 | Karem | Sep 2010 | B2 |
| 7822516 | Yanaka et al. | Oct 2010 | B2 |
| 7857253 | Yoeli | Dec 2010 | B2 |
| 7857254 | Parks | Dec 2010 | B2 |
| 7874513 | Smith | Jan 2011 | B1 |
| 8016226 | Wood | Sep 2011 | B1 |
| 8056866 | De | Nov 2011 | B2 |
| 8152096 | Smith | Apr 2012 | B2 |
| 8275494 | Roth | Sep 2012 | B1 |
| 8376264 | Hong et al. | Feb 2013 | B1 |
| 8469306 | Kuhn, Jr. | Jun 2013 | B2 |
| 8485464 | Kroo | Jul 2013 | B2 |
| 8527233 | Mcintyre | Sep 2013 | B2 |
| 8602347 | Isaac et al. | Dec 2013 | B2 |
| 8708273 | Oliver | Apr 2014 | B2 |
| 8733690 | Bevirt et al. | May 2014 | B2 |
| 8800912 | Oliver | Aug 2014 | B2 |
| 8849479 | Walter | Sep 2014 | B2 |
| 8998125 | Hollimon et al. | Apr 2015 | B2 |
| 9102401 | Collins et al. | Aug 2015 | B2 |
| 9128109 | Oneill | Sep 2015 | B1 |
| 9415870 | Beckman et al. | Aug 2016 | B1 |
| 9435661 | Brenner et al. | Sep 2016 | B2 |
| 9694911 | Bevirt et al. | Jul 2017 | B2 |
| 9786961 | Dyer et al. | Oct 2017 | B2 |
| 9944386 | Reichert et al. | Apr 2018 | B1 |
| 9963228 | Mccullough et al. | May 2018 | B2 |
| 10046855 | Bevirt et al. | Aug 2018 | B2 |
| 10144503 | Vander Lind et al. | Dec 2018 | B1 |
| 10183746 | Mccullough et al. | Jan 2019 | B2 |
| 10246184 | Ragland | Apr 2019 | B2 |
| 10287011 | Wolff et al. | May 2019 | B2 |
| 10364036 | Tighe et al. | Jul 2019 | B2 |
| 10497996 | Muniz et al. | Dec 2019 | B1 |
| 10513334 | Groninga et al. | Dec 2019 | B2 |
| 11065979 | Demont et al. | Jul 2021 | B1 |
| 11312256 | Vinson | Apr 2022 | B2 |
| 11588431 | Bachmann | Feb 2023 | B2 |
| 11715948 | Perkinson | Aug 2023 | B2 |
| 11724600 | Culpin | Aug 2023 | B2 |
| 11827347 | Bevirt et al. | Nov 2023 | B2 |
| 20030038213 | Yoeli | Feb 2003 | A1 |
| 20030062443 | Wagner et al. | Apr 2003 | A1 |
| 20030080242 | Kawai | May 2003 | A1 |
| 20030085319 | Wagner et al. | May 2003 | A1 |
| 20030094537 | Austen-Brown | May 2003 | A1 |
| 20030106959 | Fukuyama | Jun 2003 | A1 |
| 20040126241 | Zha et al. | Jul 2004 | A1 |
| 20040195460 | Sailer | Oct 2004 | A1 |
| 20040245376 | Muren | Dec 2004 | A1 |
| 20050178879 | Mao | Aug 2005 | A1 |
| 20050230524 | Ishiba | Oct 2005 | A1 |
| 20060016930 | Pak | Jan 2006 | A1 |
| 20060097103 | Atmur | May 2006 | A1 |
| 20060113426 | Yoeli | Jun 2006 | A1 |
| 20060226281 | Walton | Oct 2006 | A1 |
| 20070221779 | Ikeda | Sep 2007 | A1 |
| 20080048065 | Kuntz | Feb 2008 | A1 |
| 20080205416 | Dechiara | Aug 2008 | A1 |
| 20080283673 | Yoeli | Nov 2008 | A1 |
| 20090008499 | Shaw | Jan 2009 | A1 |
| 20090084907 | Yoeli | Apr 2009 | A1 |
| 20090140102 | Yoeli | Jun 2009 | A1 |
| 20090159757 | Yoeli | Jun 2009 | A1 |
| 20090200431 | Konings et al. | Aug 2009 | A1 |
| 20090224095 | Cox et al. | Sep 2009 | A1 |
| 20090283629 | Kroetsch et al. | Nov 2009 | A1 |
| 20100072325 | Sambell | Mar 2010 | A1 |
| 20100076625 | Yoeli | Mar 2010 | A1 |
| 20100100260 | Mcintyre et al. | Apr 2010 | A1 |
| 20100193644 | Karem | Aug 2010 | A1 |
| 20100264257 | Brunken, Jr. | Oct 2010 | A1 |
| 20100270419 | Yoeli | Oct 2010 | A1 |
| 20100270435 | Karem | Oct 2010 | A1 |
| 20110001020 | Forgac | Jan 2011 | A1 |
| 20110042508 | Bevirt | Feb 2011 | A1 |
| 20110042509 | Bevirt et al. | Feb 2011 | A1 |
| 20110042510 | Bevirt et al. | Feb 2011 | A1 |
| 20110049306 | Yoeli | Mar 2011 | A1 |
| 20110049307 | Yoeli | Mar 2011 | A1 |
| 20110139923 | Papanikolopoulos et al. | Jun 2011 | A1 |
| 20110139939 | Martin et al. | Jun 2011 | A1 |
| 20110147533 | Goossen et al. | Jun 2011 | A1 |
| 20110315809 | Oliver | Dec 2011 | A1 |
| 20120025016 | Methven et al. | Feb 2012 | A1 |
| 20120061526 | Brunken, Jr. | Mar 2012 | A1 |
| 20120091257 | Wolff et al. | Apr 2012 | A1 |
| 20120234968 | Smith | Sep 2012 | A1 |
| 20130132548 | Cabos | May 2013 | A1 |
| 20130201316 | Binder et al. | Aug 2013 | A1 |
| 20130204544 | Thomas | Aug 2013 | A1 |
| 20140299708 | Green et al. | Oct 2014 | A1 |
| 20140333127 | Edwards | Nov 2014 | A1 |
| 20140358333 | White et al. | Dec 2014 | A1 |
| 20150012154 | Senkel et al. | Jan 2015 | A1 |
| 20150056058 | Grissom et al. | Feb 2015 | A1 |
| 20150102659 | Liffring et al. | Apr 2015 | A1 |
| 20150136897 | Seibel et al. | May 2015 | A1 |
| 20150147181 | Henze et al. | May 2015 | A1 |
| 20150232178 | Reiter | Aug 2015 | A1 |
| 20150266571 | Bevirt et al. | Sep 2015 | A1 |
| 20150360794 | Certain et al. | Dec 2015 | A1 |
| 20160031555 | Bevirt et al. | Feb 2016 | A1 |
| 20160031556 | Bevirt et al. | Feb 2016 | A1 |
| 20160083073 | Beckman | Mar 2016 | A1 |
| 20160094143 | Huang et al. | Mar 2016 | A1 |
| 20160112151 | Chedas et al. | Apr 2016 | A1 |
| 20160144957 | Claridge et al. | May 2016 | A1 |
| 20160236790 | Knapp et al. | Aug 2016 | A1 |
| 20160272312 | Mallard | Sep 2016 | A1 |
| 20160294882 | Michaels | Oct 2016 | A1 |
| 20160304194 | Bevirt et al. | Oct 2016 | A1 |
| 20160304214 | Himmelmann et al. | Oct 2016 | A1 |
| 20160340051 | Edwards et al. | Nov 2016 | A1 |
| 20170057650 | Walter-Robinson | Mar 2017 | A1 |
| 20170066531 | Mcadoo | Mar 2017 | A1 |
| 20170101176 | Alber et al. | Apr 2017 | A1 |
| 20170104385 | Salamon et al. | Apr 2017 | A1 |
| 20170253344 | Wangemann et al. | Sep 2017 | A1 |
| 20170274983 | Beckman et al. | Sep 2017 | A1 |
| 20170277152 | Liu et al. | Sep 2017 | A1 |
| 20170297431 | Epstein et al. | Oct 2017 | A1 |
| 20170331323 | Ehrmantraut | Nov 2017 | A1 |
| 20180002016 | Mccullough et al. | Jan 2018 | A1 |
| 20180105279 | Tighe et al. | Apr 2018 | A1 |
| 20180118356 | Armstrong et al. | May 2018 | A1 |
| 20180141428 | Toyota et al. | May 2018 | A1 |
| 20180237148 | Hehn et al. | Aug 2018 | A1 |
| 20180244370 | Lombard | Aug 2018 | A1 |
| 20180251226 | Fenny et al. | Sep 2018 | A1 |
| 20180290736 | Mikic et al. | Oct 2018 | A1 |
| 20180319491 | Kearney-Fischer | Nov 2018 | A1 |
| 20180354615 | Groninga et al. | Dec 2018 | A1 |
| 20180356439 | Luo et al. | Dec 2018 | A1 |
| 20190013679 | Radun | Jan 2019 | A1 |
| 20190044451 | Huang et al. | Feb 2019 | A1 |
| 20190210740 | Luo | Jul 2019 | A1 |
| 20190214161 | Chen et al. | Jul 2019 | A1 |
| 20190288533 | Stroppiana | Sep 2019 | A1 |
| 20190393809 | Lacaux et al. | Dec 2019 | A1 |
| 20200010187 | Bevirt et al. | Jan 2020 | A1 |
| 20200290742 | Kumar et al. | Sep 2020 | A1 |
| 20210309392 | Wiegman | Oct 2021 | A1 |
| 20220009643 | Datta et al. | Jan 2022 | A1 |
| Number | Date | Country |
|---|---|---|
| 103363993 | Apr 2016 | CN |
| 107042884 | Aug 2017 | CN |
| 112368208 | Feb 2021 | CN |
| 102012104783 | Dec 2013 | DE |
| 0945841 | Sep 1999 | EP |
| 3090951 | Nov 2016 | EP |
| 3184425 | Jun 2017 | EP |
| 3366583 | Aug 2018 | EP |
| 3802322 | Apr 2021 | EP |
| 1271102 | Apr 1972 | GB |
| 2017527059 | Sep 2017 | JP |
| 2017184504 | Oct 2017 | JP |
| 2021525673 | Sep 2021 | JP |
| 2023134581 | Sep 2023 | JP |
| 20210006972 | Jan 2021 | KR |
| 2724940 | Jun 2020 | RU |
| 03074924 | Sep 2003 | WO |
| 03086857 | Oct 2003 | WO |
| 2017009037 | Jan 2017 | WO |
| 2017108634 | Jun 2017 | WO |
| 2017200609 | Nov 2017 | WO |
| 2018084261 | May 2018 | WO |
| 2019001203 | Jan 2019 | WO |
| 2019056053 | Mar 2019 | WO |
| 2019232472 | Dec 2019 | WO |
| Entry |
|---|
| “Japanese Application Serial No. 2020-566669, Examiners Decision of Final Refusal dated Mar. 7, 2023”, w English Translation, 8 pgs. |
| “International Application Serial No. PCT US2019 039247, International Search Report dated Sep. 13, 2019”, 2 pgs. |
| “International Application Serial No. PCT US2019 039247, Written Opinion dated Sep. 13, 2019”, 6 pgs. |
| “International Application Serial No. PCT US2019 035236, International Search Report dated Aug. 20, 2019”, 2 pgs. |
| “International Application Serial No. PCT US2019 035236, Written Opinion dated Aug. 20, 2019”, 5 pgs. |
| “International Application Serial No. PCT US2019 031863, International Search Report dated Jul. 24, 2019”, 2 pgs. |
| “International Application Serial No. PCT US2019 031863, Written Opinion dated Jul. 24, 2019”, 8 pgs. |
| “Inclined Flat Plate”, Aerodynamics of the airplane, (Feb. 13, 2016), 9 pgs. |
| “International Application Serial No. PCT US2019 051565, International Search Report dated Dec. 4, 2019”, 2 pgs. |
| “International Application Serial No. PCT US2019 051565, Written Opinion dated Dec. 4, 2019”, 4 pgs. |
| “International Application Serial No. PCT US2019 035044, International Search Report dated Sep. 20, 2019”, 2 pgs. |
| “International Application Serial No. PCT US2019 035044, Written Opinion dated Sep. 20, 2019”, 6 pgs. |
| “International Application Serial No. PCT US2019 035044, International Preliminary Report on Patentability dated Dec. 10, 2020”, 8 pgs. |
| “European Application Serial No. 19812608.8, Response to Communication pursuant to Rules 161(1) and 162 EPC filed Feb. 24, 2021”, 10 pgs. |
| “European Application Serial No. 15765064.9, Extended European Search Report dated Oct. 16, 2017”, 10 pgs. |
| “International Application Serial No. PCT US2010 046500, International Search Report dated Apr. 13, 2011”, 2 pgs. |
| “International Application Serial No. PCT US2010 046500, Written Opinion dated Apr. 13, 2011”, 8 pgs. |
| “International Application Serial No. PCT US2015 021344, International Search Report dated Sep. 11, 2015”, 4 pgs. |
| “International Application Serial No. PCT US2015 021344, Written Opinion dated Sep. 11, 2015”, 7 pgs. |
| “International Application Serial No. PCT US2015 021350, International Search Report dated Sep. 15, 2015”, 5 pgs. |
| “International Application Serial No. PCT US2015 021350, Written Opinion dated Sep. 15, 2015”, 13 pgs. |
| “International Application Serial No. PCT US2017 059809, International Search Report dated Jul. 31, 2018”, 2 pgs. |
| “International Application Serial No. PCT US2017 059809, Written Opinion dated Jul. 31, 2018”, 5 pgs. |
| “Curtiss-Wright X-19”, [Online]. Retrieved from the Internet: https: en.wikipedia.org wiki Curtiss-Wright_X-19, 4 pgs. |
| “U.S. Appl. No. 16/428,794, Non Final Office Action dated Jan. 21, 2022”, 5 pgs. |
| “European Application Serial No. 19812608.8, Extended European Search Report dated Jan. 21, 2022”, 7 pgs. |
| Carson, Biz, “First Look: Uber Unveils New Design for Uber Eats Delivery Drone”, [Online]. Retrieved from the Internet: https:www.forbes.com sites bizcarson 2019 10 28 first-look-uber-unveils-new-design-for -uber -eats-delivery-drone #1703f8d77812. |
| Denham Jr., James W, “Converging on a Precision Hover Control Strategy for the F35B Stovl Aircraft”, AIAA Guidance, Navigation and Control Conference and Exhibit 18, Honolulu, Hawaii, Abstract only, (Aug. 21, 2006). |
| Dubois, Arthur, “Design of an Electric Propulsion System for SCEPTOR”, Aviation Technology, Integration, and Operations Conference, Washington, DC, (Jun. 13, 2016), 1-30. |
| Falco, Gianluca, “Loose and Tight GNSS INS Integrations: Comparison of Performance Assessed in Real Urban Scenarios”, Sensors (Basel) 17(2): 225, [Online] Retrieved from the internet:https: www.ncbi.nlm.nih.gov pmc articles PMC5335985 , (Feb. 2017). |
| Gold, Phillip J, “Design and Pilot Evaluation of the RAH-66 Comanche Selectable Control Modes”, https: ntrs.nasa.gov search.jsp?, N94-13322, (Jul. 1, 1993), 419-431. |
| Heliciel, Mecaftux, “Airfolds Blade Profile”, Propeller and Wing, [Online] Retrieved from the internet:https: www.heliciel.com en aerodynamique-hydrodynamique profils%20aile%20profil%20pale.htm. |
| Kim, Tae, “Reduction of Tonal Propeller Noise by Means of Uneven Blade Spacing”, University of California, Irvine, Thesis, (2016). |
| NASA, “Sceptor Critical Design Review”, Day 1 Package, [Online] Retrieved from the Internet:https: www.nasa.govaeroresearch X-57 technical index.html, (Nov. 15, 2016), 1-242. |
| Saraf, A, “Study of Flow Separation on Airfoil with Bump”, International Journal of Applied, Engineering Research ISSN 09773-4562, vol. 13, No. 16, (2018), 128686-12872. |
| Sullivan, Brenda M, “A Subject Test of Modulated Blade Spacing for Helicopter Main Rotors”, Presented at the American Helicopter Society 58th Annual Forum, Montreal, Canada, (Jun. 11-13, 2002). |
| Yeh, Y C (Bob), “Triple-Triple Redundant 777 Primary Flight Computer”, IEEE, (1996), 293-307. |
| Young, Larry, “Conceptual Design Aspects of Three General Sub-Classes of Multi-Rotor Configurations: Distributed, Modular, and Hetergenerous”, NASA Ames Research Center, Moffett Field Computer Science, (2015). |
| “Japanese Application Serial No. 2020-566669, Response Filed Dec. 23, 2022 to Notification of Reasons for Refusal dated Sep. 27, 2022”, W English Claims, 10 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Response Filed Dec. 26, 2022 to Notice of Preliminary Rejection dated Oct. 27, 2022”, W English Claims, 17 pgs. |
| “U.S. Appl. No. 16/428,794, Non Final Office Action dated Feb. 9, 2023”, 7 pgs. |
| “European Application Serial No. 19812608.8, Communication pursuant to Rule 114(2) EPC dated Feb. 17, 2023”, 6 pgs. |
| “Scalable Convergent Electric Propulsion Technology and Operations Research (SCEPTOR)”, Critical Design Review, Day 1 Package, (Nov. 15, 2016), 36 pgs. |
| “U.S. Appl. No. 16/428,794, Restriction Requirement dated Sep. 2, 2022”, 5 pgs. |
| “Japanese Application Serial No. 2020-566669, Notification of Reasons for Refusal dated Sep. 27, 2022”, With English translation, 11 pgs. |
| “U.S. Appl. No. 16/428,794, Response filed Nov. 1, 2022 to Restriction Requirement dated Sep. 2, 2022”, 6 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Notice of Preliminary Rejection dated Oct. 27, 2022”, With English translation, 9 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Response Filed May 25, 2022 to Notice of Preliminary Rejection dated Mar. 27, 2022”, With English machine translation, 29 pgs. |
| “European Application Serial No. 19812608.8, Response Filed Jul. 28, 2022 to Extended European Search Report dated Jan. 21, 2022”, 7 pgs. |
| “Japanese Application Serial No. 2020-566669, Notification of Reasons for Refusal dated Feb. 22, 2022”, w English Translation, 9 pgs. |
| “International Application Serial No. PCT US2021 042205, International Search Report dated Mar. 21, 2022”, 6 pgs. |
| “International Application Serial No. PCT US2021 042205, Written Opinion dated Mar. 21, 2022”, 6 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Notice of Preliminary Rejection dated Mar. 27, 2022”, w English translation, 8 pgs. |
| “U.S. Appl. No. 16/428,794, Examiner Interview Summary dated Apr. 26, 2022”, 2 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Final Office Action dated Apr. 25, 2023”, w English Translation, 6 pgs. |
| “International Application Serial No. PCT US2021 042205, International Preliminary Report on Patentability dated Jun. 8, 2023”, 8 pgs. |
| “U.S. Appl. No. 16/428,794, Response filed Jun. 9, 2023 to Non Final Office Action dated Feb. 9, 2023”, 12 pgs. |
| “European Application Serial No. 19812608.8, Communication Pursuant to Article 94(3) EPC dated Jun. 28, 2023”, 4 pgs. |
| “U.S. Appl. No. 16/428,794, Notice of Allowance dated Jul. 6, 2023”, 5 pgs. |
| “U.S. Appl. No. 16/428,794, 312 Amendment filed Oct. 5, 2023”, 4 pgs. |
| “U.S. Appl. No. 16/428,794, PTO Response to Rule 312 Communication dated Oct. 24, 2023”, 2 pgs. |
| “U.S. Appl. No. 16/428,794, Supplemental Notice of Allowability dated Jul. 20, 2023”, 2 pgs. |
| “European Application Serial No. 19812608.8, Response Filed Oct. 6, 2023 to Communication Pursuant to Article 94(3) EPC dated Jun. 28, 2023”, 9 pgs. |
| “Japanese Application Serial No. 2023-111506, Voluntary Amendment filed Jul. 27, 2023”, W/ English Claims, 46 pgs. |
| “Korean Application Serial No. 10-2020-7035350, Response Filed Jul. 11, 2023 to Final Office Action dated Apr. 25, 2023”, W/ English Claims, 24 pgs. |
| U.S. Appl. No. 16/428,794, filed May 31, 2019, Electric Power System Architecture and Fault Tolerant VTOL Aircraft Using Same. |
| Number | Date | Country | |
|---|---|---|---|
| 20210339881 A1 | Nov 2021 | US |
| Number | Date | Country | |
|---|---|---|---|
| 63135387 | Jan 2021 | US | |
| 63118504 | Nov 2020 | US | |
| 62678275 | May 2018 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 16428794 | May 2019 | US |
| Child | 17379464 | US |
