Granted Patent B2

US 12,570,407 · App. 18/223,210 · Granted Mar 10, 2026

Inventors: Kyle B. Clark (South Burlington, VT); Herman Wiegman (South Burlington, VT)

Assignee: BETA AIR LLC

B64D37/04B64D27/31B64D27/34B64D31/18B64D35/04B64C29/0008B64D27/026

Abstract

Claims (28)

1 . A hybrid electric aircraft comprising:

a flight component configured to propel the hybrid electric aircraft;

a battery configured to selectively power the flight component;

a flight controller configured to control operation of the hybrid electric aircraft; and

a fuel pod comprising:

a housing;

a fuel tank contained within the housing, wherein the fuel tank is configured to hold a fuel therein;

a generator contained within the housing and connected to the fuel tank, wherein the generator is configured to power one or more of the battery and the flight component, wherein the generator is configured to recharge the battery during operation; and

a connection mechanism at the housing, wherein the connection mechanism is configured to releasably attach the fuel pod to a surface of the hybrid electric aircraft, wherein the connection mechanism comprises:

an electrical interface configured to electrically link the fuel pod to the flight component.

2 . The hybrid electric aircraft of claim 1 , wherein the hybrid electric aircraft comprises an electric vertical takeoff and landing aircraft.

3 . The hybrid electric aircraft of claim 1 , wherein the fuel pod is attached to a wing of the hybrid electric aircraft.

4 . The hybrid electric aircraft of claim 1 , wherein the fuel pod is attached to a boom of the hybrid electric aircraft.

5 . The hybrid electric aircraft of claim 1 , wherein the battery is mounted within a fuselage of the hybrid electric aircraft.

6 . The hybrid electric aircraft of claim 1 , wherein the fuel pod further comprises a sensor, wherein the sensor is communicatively connected to the flight controller.

7 . The hybrid electric aircraft of claim 6 , wherein the sensor is configured to detect characteristics associated with the battery.

8 . The hybrid electric aircraft of claim 6 , wherein the sensor is configured to detect an electric current emanating from the generator.

9 . The hybrid electric aircraft of claim 6 , wherein the sensor is configured to detect a flight mode of the hybrid electric aircraft.

10 . The hybrid electric aircraft of claim 1 , wherein the flight component comprises a propulsor component.

11 . The hybrid electric aircraft of claim 10 , wherein the propulsor component comprises an electric motor.

12 . The hybrid electric aircraft of claim 10 , wherein the propulsor component comprises at least a lift component.

13 . The hybrid electric aircraft of claim 10 , wherein the propulsor component comprises a pusher component.

14 . The hybrid electric aircraft of claim 1 , wherein the flight controller is configured to selectively engage at least one of the battery and the generator to power the flight component as a function of a flight mode of the hybrid electric aircraft.

15 . The hybrid electric aircraft of claim 14 , wherein the flight mode comprises fixed-wing based flight.

16 . The hybrid electric aircraft of claim 14 , wherein the flight mode comprises rotor-based flight.

17 . The hybrid electric aircraft of claim 1 , wherein the flight controller is configured to selectively engage at least one of the battery and the generator to power the flight component as a function of a state of charge of the battery.

18 . The hybrid electric aircraft of claim 1 , wherein the battery and the generator are configured to power the flight component simultaneously.

19 . The hybrid electric aircraft of claim 1 , wherein the connection mechanism further comprises an aircraft port of the hybrid electric aircraft.

Assignments (1)

Continuity (2)

References Cited (23)