Gimbaled thruster configuration for use with unmanned aerial vehicle
AssigneeFlightwave Aerospace Systems
InventorsTrent Lukaczyk, Michael Colonno
Life of this patent
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Abstract
A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.
Claims18
A vectored thrust control module for an aircraft having an aircraft structure comprising:
- a servo system that includes a tilt motor and an output shaft, wherein the output shaft of the servo system is coupled to the aircraft structure at a connection point such that the servo system is supported by the output shaft and the servo system rotates with respect to the aircraft structure;
- a bladed component configured to rotate and provide thrust;
- and
- a thrust motor assembly that includes a thrust motor configured to rotate the bladed component to provide the thrust,
- wherein the thrust motor assembly is connected to and fully supported by the servo system;
- wherein the thrust motor assembly and the servo system are configured to be rigidly connected together and are further configured to rotate together with respect to the aircraft structure;
- wherein the bladed component and the thrust motor assembly are configured to generate a line of thrust;
- and
- wherein a center of the line of thrust extends through the connection point that rigidly connects the output shaft of the servo system to the aircraft structure.
A vectored thrust control module for an aircraft having an aircraft structure comprising:
- a servo system that includes a tilt motor and an output shaft, wherein the output shaft of the servo system is coupled to the aircraft structure at a connection point such that the servo system is supported by the output shaft and the servo system rotates with respect to the aircraft structure and further wherein the servo system is encased by a servo housing;
- a bladed component configured to rotate and provide thrust;
- a thrust motor assembly that includes a thrust motor configured to rotate the bladed component to provide the thrust;
- and
- an adapter plate directly coupled with the thrust motor assembly and the servo system is configured to be directly coupled to the adapter plate;
- wherein the thrust motor assembly is connected to and fully supported by the servo system;
- wherein the thrust motor assembly and the servo system are configured to be rigidly connected together and are further configured to rotate together with respect to the aircraft structure and further configured to generate a line of thrust;
- and
- wherein a center of the line of thrust extends through the connection point that rigidly connects the output shaft of the servo system to the aircraft structure.
A vectored thrust control module for an aircraft having an aircraft structure comprising:
- a servo system that includes a tilt motor and an output shaft, wherein the output shaft of the servo system is coupled to the aircraft structure at a connection point such that the servo system is supported by the output shaft and the servo system rotates with respect to the aircraft structure;
- a bladed component configured to rotate and provide thrust;
- a thrust motor assembly that includes a thrust motor configured to rotate the bladed component to provide the thrust,
- wherein the thrust motor assembly is connected to and fully supported by the servo system;
- wherein the thrust motor assembly and the servo system are configured to be rigidly connected together and are further configured to rotate together with respect to the aircraft structure and further configured to generate a line of thrust;
- and
- wherein a center of the line of thrust extends through the connection point of the servo system to the aircraft structure.
Dependencies are inferred from the claim text.