JETZERO, INC.

An aircraft with an engine dropping mechanism is disclosed. The aircraft includes at least an engine, wherein the at least engine is top mounted to the aircraft; a main body; at least an engine support structure mechanically connecting the at least an engine with the main body; and the well extending from an upper surface of the aircraft toward a lower surface of the aircraft, wherein the well is configured to allow for a vertical displacement of the at least an engine from the at least an engine support structure.

A system for providing favorable environment for propulsion system of a blended wing body aircraft, wherein the system comprises a blended wing body, wherein the blended wing body comprises a main body, wherein the main body comprises a main body shaping comprising an upper aft surface configured to provide a favorable environment for a propulsion system of the blended wing body aircraft, and the propulsion system mounted to the upper aft surface of the main body, wherein the propulsion system comprises one or more prime movers, and a nacelle covering the one or more prime movers.

an aircraft with high transport efficiency, wherein the aircraft include a blended wing body with a downward depressed upper aft surface, configured to operate at a high cruising level within a high cruise altitude range, wherein the blended wing body include a main body configured to accommodate a payload, and at least a wing, wherein the blended wing body include no striking demarcation between the main body and the at least a wing and at least a propulsor attached to the blended wing body and configured to propel the aircraft.

A blended wing body (BWB) aircraft comprising a first composite part comprising, a first dry carbon fiber sheet having a width greater than 3 inches and comprising a first layer comprising dry carbon fibers, a second layer disposed on top of the first layer comprising dry carbon fibers, a stitching extending through the first dry carbon fiber sheet, wherein the stitching is configured to bind the first dry carbon fiber sheet together, and a resin matrix, wherein the stitching and the first dry carbon fiber sheet are embedded within the resin matrix to create a single unified structure. BWB aircraft further comprises a blended wing body, having no clear demarcation along a leading edge of the BWB aircraft from a wing to a nose of the blended wing body, and wherein the first composite part comprises a portion of the blended wing body.

A system for carrying out a Resin Transfer Molding process including a molding tool having an upper mold half and a lower mold half which form a mold cavity configured for placement of a preform, a main control unit, more than one injection units configured to supply a resin mixture into the mold cavity, more than one injection points fluidly connecting the more than one injection units to the molding tool, one or more venting hoses configured to expel an excess of the resin mixture, more than one resin outlets fluidly connecting the one or more venting hoses to the molding tool and one or more flow direction sensors connected to the main control unit, wherein the main control unit is configured to monitor a behavior of the resin mixture from the more than one injection points to the mold cavity using the one or more flow direction sensors.

An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.

An aircraft with carbon fiber material comprising a blended wing body having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, wherein the blended wing body comprises, at least an outer skin surface comprising a carbon fiber material, at least a structural element comprising the carbon fiber material, and at least a portion of the main body comprising the carbon fiber material and configured to contain a pressure vessel and at least a propulsor, the at least a propulsor attached to the blended wing body and configured to propel the aircraft.

Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A non-coupled landing gear for an aircraft includes at least a nose gear and at least a main gear. The at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and the at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are uncoupled from each other.