# US 11,999,509 B2 · Hybrid-electric and all-electric aircraft power systems > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,999,509 B2 - Document ID: US11999509B2 - Status: Granted - Kind: B2 - Application number: 17/322,739 - Filed: 2021-05-17 - Published: 2022-11-17 - Granted: 2024-06-04 - Earliest claimed: 2021-05-17 - Assignees: Pratt & Whitney Canada Corp. - Applicants: Pratt & Whitney Canada Corp. - Inventors: Daniel Mackay - Web page: https://patentgrep.com/patent/US11999509B2 ## CPC - B60L 53/80: Exchanging energy storage elements, e.g. removable batteries - B60L 9/00: Electric propulsion with power supply external to the vehicle (electric propulsion for monorail vehicles, suspension vehicles or rack railways B60L13/00; in combination with batteries or fuel cells within the vehicle B60L50/53) - B60L 50/50: using propulsion power supplied by batteries or fuel cells - B60L 53/16: Connectors, e.g. plugs or sockets, specially adapted for charging electric vehicles - B64F 1/352: {Mobile units} - B64F 5/40: Maintaining or repairing aircraft - B60L 2200/10: Air crafts - B64D 27/33: Hybrid electric aircraft - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A system for an aircraft includes an electric energy module and a connector module operatively connected to the electric energy module. The connector module is: structured to attach the electric energy module to the aircraft when the connector module is in an engaged mode while in use, and operable between the engaged mode and a disengaged mode. The connector module in the disengaged mode while in use disengages the electric energy module from the aircraft. ## Claims ### Claim 1 An on-ground service system, comprising: an aircraft including: an electric energy module; a connector module operatively connected to the electric energy module, the connector module being: structured to attach the electric energy module to the aircraft when the connector module is in an engaged mode while in use; and operable between the engaged mode and a disengaged mode, with the connector module disengaging the electric energy module from the aircraft in the disengage mode; and an electrically-powered system, wherein: the electric energy module is attached to the aircraft via the connector module and is electrically connected to the electrically-powered system; the electric energy module is electrically connected to the electrically-powered system via the connector module; the connector module is structured to electrically disconnect the electric energy module from the electrically-powered system when the connector module is operated from the engaged mode to the disengaged mode; the electric energy module is positioned relative to the aircraft such that when the connector module is in the disengaged mode and the aircraft is stationary on a ground, gravity acts on the electric energy module to move the electric energy module toward the ground; the electric energy module comprises an electrical connector on a side of the electric energy module that faces toward the ground when the aircraft is stationary on the ground; the electrical connector is electrically connected to the electric energy module; and the electrical connector is sized to charge the electric energy module when connected to an electric power source; and a ground vehicle that includes an electrical connector structured to electrically connect to the electrical connector of the electrical energy module when the aircraft is stationary on the ground, wherein: the electrical energy module comprises a support structure that is structured to support a weight of the electrical energy module; and the ground vehicle further comprises a movable structure, the movable structure being structured to move relative to a rest of the ground vehicle to engage the support structure and to remove the electrical energy module from the aircraft while engaged to the support structure. ### Claim 2 (depends on 1) The on-ground service system of claim 1, wherein the electrical connector of the ground vehicle is part of the movable structure of the ground vehicle. ### Claim 3 (depends on 2) The on-ground service system of claim 2, wherein the electrical connector of the electrical energy module is part of the support structure of the electrical energy module and is positioned relative to the support structure such that when the movable structure engages the support structure, the electrical connector of the ground vehicle electrically connects to the electrical connector of the electrical energy module. ### Claim 4 (depends on 2) The on-ground service system of claim 2, further comprising an electrical machine attached to the electrical energy module such that the electrical machine is removable from the aircraft together with the electrical energy module as a unit, and wherein the movable structure of the ground vehicle and the ground vehicle are structured to support a weight of the unit. ### Claim 5 (depends on 1) The on-ground service system of claim 1, wherein: the aircraft is a first aircraft; the on-ground service system further comprises a second aircraft that is of a different model than the first aircraft; and the second aircraft is structured to removably receive the electrical energy module of the first aircraft from the ground vehicle to power at least one system of the second aircraft.