Abstract: A fuel pod for a hybrid electric aircraft. The fuel pod includes a housing, a fuel tank, a generator and a connection mechanism. The fuel tank is contained within the housing and is configured to hold a fuel therein. The generator is contained within the housing and is connected to the fuel tank. The generator is configured to power at least one of a plurality of flight components of a hybrid electric aircraft. The connection mechanism is at the housing and is configured to removably attach the fuel pod to the hybrid electric aircraft. The connection mechanism includes an electrical interface configured to electrically link to at least one of the plurality of flight components of the hybrid electric aircraft, and a communication interface configured to communicatively link to a flight controller communicatively connected to the hybrid electric aircraft.

Abstract: A system collects a plurality of drill cuttings from a subsurface of a geothermal borehole while drilling the borehole. The system obtains a plurality of thermal conductivity values for the plurality of drill cuttings. The system determines, using the plurality of thermal conductivity values, thermal performance data of the geothermal borehole. In accordance with a determination that the thermal performance data of the geothermal borehole meets or exceeds a threshold value, the system updates, according to the thermal performance data, one or more drilling parameters to one or more updated drilling parameters and controls the drilling of the geothermal borehole according to the one or more updated drilling parameters.

Abstract: The various embodiments described herein include systems and methods for installing geothermal loops using coiled tubing. In one aspect, a system for installing geothermal loops includes a geothermal loop spooled on a geothermal loop reel that is mounted on a first axle. The system includes a coiled tubing string configured for inserting the geothermal loop into a borehole. The coiled tubing string is spooled on a coiled tubing reel that is mounted on a second axle. As the geothermal loop is inserted into the borehole, the geothermal loop is configured to unspool from the geothermal loop reel, the coiled tubing string is configured to unspool from the coiled tubing reel, and the geothermal loop and the coiled tubing string are configured to move at substantially similar speeds.

Abstract: In some embodiments, an electric aircraft may include a plurality of flight components including a plurality of control surfaces; a plurality of lift propulsors; at least a thrust propulsor; and a plurality of electric motors configured to power the plurality of propulsors; a flight controller, communicatively connected to a pilot input and flight components. In some embodiments, a flight controller may be configured to receive control datum from a pilot input; and generate an output datum as a function of the control datum.

Abstract: The various embodiments described herein include systems and methods for constructing geothermal fields. In one aspect, a system for constructing a geothermal field comprises a coiled tubing. The coiled tubing is configured for drilling one or more boreholes of the geothermal field. The coiled tubing is configured for inserting one or more geothermal loops into the one or more boreholes. The coiled tubing is also configured for grouting the one or more geothermal loop.

Abstract: A system for constructing geothermal fields includes a coiled tubing (CT) string, a power source, and an electrically activated bottomhole assembly (BHA) coupled to the CT string. The electrically activated BHA includes an electric motor and a drill bit. The system includes one or more processors and memory. The memory stores instructions that, when executed by the one or more processors, cause the system to deploy the CT string from a surface into a subsurface for drilling a geothermal borehole, and cause the system to, during the drilling, (i) transfer power from the power source to the electric motor via at least a first portion of the CT string and (ii) transfer electrical current from the electric motor to the electric power source via an electrical conductor that is different from the at least the first portion of the CT string.

Abstract: A system collects a plurality of drill cuttings from a subsurface of a geothermal borehole while drilling the borehole. The system obtains a plurality of thermal conductivity values for the plurality of drill cuttings. The system determines, using the plurality of thermal conductivity values, thermal performance data of the geothermal borehole. In accordance with a determination that the thermal performance data of the geothermal borehole meets or exceeds a threshold value, the system updates, according to the thermal performance data, one or more drilling parameters to one or more updated drilling parameters and controls the drilling of the geothermal borehole according to the one or more updated drilling parameters.

Abstract: In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Abstract: A hybrid electric vertical takeoff and landing (VTOL) aircraft. The hybrid electric VTOL aircraft generally includes a fuselage, a pair of wings, a pair of booms, a plurality of flight components and a power system. The wings are connected to the fuselage and extend generally laterally therefrom with each wing on either side of the fuselage. Each boom is connected to a respective one of the wings and extends generally longitudinally and parallel to the fuselage. The plurality of flight components is configured to provide thrust to the hybrid electric VTOL aircraft. The power system is configured to power the plurality of flight components and includes at least a fuel tank and a generator, and at least a battery. The at least a fuel tank is mounted to at least one of the booms. The at least a battery configured to power the plurality of flight components.

Abstract: A system and method for a recharging station including a landing pad, a rechargeable component coupled to the landing pad, a power delivery unit configured to deliver power from a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the landing pad.

Abstract: A system of vibration mitigation for a propulsor and a boom in an electric aircraft is disclosed. The system may include at least a propulsor, wherein the at least a propulsor is configured to propel an electric aircraft through a fluid medium and the at least a propulsor comprises a driving frequency from 0 to its maximum driving frequency that is generated as a function of a rotational speed of the at least a propulsor when the at least a propulsor propels the electric aircraft through the fluid medium. The system may include at least a boom, wherein the at least a boom comprises the at least a propulsor mounted on the at least a boom and a natural frequency of the at least a boom, wherein the natural frequency is a fraction of the maximum driving frequency of the at least a propulsor.

Abstract: In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Abstract: A system and method for a recharging station including a landing pad, a rechargeable component coupled to the landing pad, a power delivery unit configured to deliver powerfrom a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the landing pad.

Abstract: In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Abstract: The present disclosure is generally related to a system and method for a recharging station for an electric aircraft. The system may include a landing pad and a recharging component coupled to the landing pad. Further, the system may include a power delivery unit configured to deliver stored power from a power supply unit to the recharging component and wherein the floating platform is in direct contact with a body of water.

Abstract: A system and method for a recharging station including an elevated landing pad, a rechargeable component coupled to the elevated landing pad, a power delivery unit configured to deliver power from a power supply unit or power storage unit to the recharging component, and a support component coupled to the bottom of the elevated landing pad.

Abstract: In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Abstract: A system for reducing rotor acoustics of an aircraft. The system includes a structural feature of an aircraft and a propulsor configured for fixed-wing flight mounted on the structural feature. The system further includes a plurality of rotors mounted on the structural feature. The plurality of rotors are configured to include a first rotor, a first motor mechanically coupled to the first rotor, a second rotor, and a second motor mechanically coupled to the second rotor. The system further includes an aircraft controller communicating with the first motor, second motor, and the propulsor. The system includes an alignment module configured to place the second rotor in alignment with the first rotor. The system further includes a rotational control module configured to initiate rotation of the plurality of rotors. Initiating rotation of the plurality of rotors further includes initiating rotation of the first rotor and the second rotor.

Abstract: This disclosure relates to methods and systems for selling products across sales channels in a single swipe transaction. In one aspect a method for purchasing products is disclosed. The method includes identifying a first product to be purchased from a first sales channel, determining whether the first product is available from the first sales channel, in response to determining that the first product is not available from the first sales channel, determining whether the first product is available from a second sales channel, in response to determining that the first product is available from the second sales channel, adding the first product from the second sales channel to the transaction, and selling the first product from the second sales channel, wherein the transaction is completed with a single tender.