Abstract: Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.

Abstract: A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.

Abstract: A landing gear system for an aircraft includes a drag brace, a lateral brace, and a support assembly, the support assembly coupled to: a lateral side of the fuselage via the lateral brace, an upper portion of the fuselage via a hinge, and a forward portion of the fuselage via the drag brace. The support assembly can rotate about the hinge connection about a forward-aft axis, with the lateral brace resisting rotation of the support assembly about the forward-aft axis, and the drag brace resisting rotation of the support assembly about a vertical axis. The system includes inboard and outboard landing gear separately coupled to the support assembly to support weight of the aircraft. The hinge transfers vertical forces to the fuselage, moments about the hinge are reacted by forces on the lateral brace, and drag forces are transferred to the fuselage by the drag brace.

Abstract: Systems, methods, and vehicles for loading and unloading cargo from a long-distance transport vehicle, such as an aircraft, are described. The systems and methods include operating a plurality of vehicles to unload large cargo from the aircraft and transporting the large cargo to an installation site. In some instances, the vehicles hold the payload the entire time, including while loading aircraft, during flight, unloading the aircraft, and moving the payload to the installation site. Alternatively, the vehicles can drive on the plane to load the payload to a designated area, and equivalent vehicles can drive on the plane after the payload has been flown to unload the payload and moving the payload to the installation site. Various vehicles and systems, and components thereof, along with methods of operating the same, are also provided.

Abstract: Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

Abstract: A fixture for supporting a payload including first and second carriages, first and second cantilevered supports, and a support beam is disclosed. The first and second carriages each have a longitudinal axis that is parallel with the other. Each cantilevered support is coupled to a respective carriage and extends at an oblique angle with respect to the longitudinal axis of the carriage. The first and second cantilevered supports extend substantially parallel to each other. The support beam extends between the cantilevered supports such that a first end of the support beam is coupled to the first support structure and a second end of the support beam is coupled to the second support structure. The cantilevered supports enable the payload to extend into otherwise unusable cargo bay storage space within the nose or tailcones of an aircraft.

Abstract: Systems and methods for loading a cargo aircraft are described. The system includes at least one rail disposed in an interior cargo bay of a cargo aircraft that extends at an angle relative to an interior bottom contact surface of a forward portion of the interior cargo bay, through a kinked portion and an aft portion of the interior cargo bay. Payload-receiving fixtures are described that can be used in conjunction with the rail system, allowing for large cargo, such as wind turbine blades, to be transported by aircraft. Methods of loading a cargo aircraft can include advancing the large payload into the interior cargo bay of the aircraft such that at least one of the payload-receiving fixtures rises relative to a plane defined by the interior bottom contact surface of the forward portion of the interior cargo bay. Various systems, methods, components, and related tooling are also provided.

Abstract: Methods of determining a final space reservation for a new aircraft are disclosed. The methods include using parametric definitions of potential payloads to generate a population of representative payloads for use in creating an initial space reservation. The methods include accounting for and applying a variety of margins on each potential payload and taking the union of potential payloads. Alternatively, the union can be taken first and then the margins applied. A homogenous space reservation can be determined based upon a variety of differently shaped or sized payloads, including a margin build-up to mitigate risk of unknowns associated with future changes in specific payload shapes and sizes, build tolerances, environmental conditions, and/or loading and unloading motions and clearances. Once this space reservation is known, it is possible to design an external shape of a carrying vehicle by staying outside of this space reservation.

Abstract: During landing and rejected-takeoff flight phases, aircraft drag is a useful force to supplement braking and reduce stopping distance. During descents, aircraft drag is a useful force in steepening flight path angle and achieving higher rates of vertical descent speed at a trimmed forward flight speed in unaccelerated flight. A flight control system is detailed herein that deflects opposing flight control components in a symmetric fashion to increase aircraft drag, while maintaining controllability.

Abstract: Methods and systems for efficiently loading cargo transports, such as cargo aircraft, are described. The methods and systems rely upon payload profiles for various payloads where the payloads include repeatable payloads that have the same characteristics. Based on the payload profile, the payload is positioned at a designated location in an interior cargo bay of the cargo transport. The designated location is denoted by one or more pre-formed markings in the interior cargo bay that establish where a payload having the respective payload profile should be positioned in the bay. The payload can then be secured in the bay. Because the designated location accounts for centers of gravity, the payload can be loaded and secured in the bay without having to run various calculations each time a payload is loaded. Systems and methods related to how the payloads are packaged in an efficient, expeditious manner are also provided.

Abstract: Systems, methods, and vehicles for loading and unloading cargo into or out of a large transport vehicle, such as an aircraft, utilizing a curved path are described. The systems and methods include one or more support structures disposed, either permanently or removably, within a cargo bay of the transport vehicle to form a curved path extending into an aft portion of the cargo bay. During loading, the payload can move in the aft direction while concurrently rotating about a center point of an arc. In some embodiments, the cargo bay can include a kinked portion disposed between a proximal and aft portions of the cargo bay, with the curved path extending at least through the kinked portion and into the aft portion. Methods, systems, and components thereof for assembling a cargo, unloading cargo from a large transport vehicle, and disassembling a cargo are also provided.

Abstract: Methods and systems for efficiently loading cargo transports, such as cargo aircraft, are described. The methods and systems rely upon payload profiles for various payloads where the payloads include repeatable payloads that have the same characteristics. Based on the payload profile, the payload is positioned at a designated location in an interior cargo bay of the cargo transport. The designated location is denoted by one or more pre-formed markings in the interior cargo bay that establish where a payload having the respective payload profile should be positioned in the bay. The payload can then be secured in the bay. Because the designated location accounts for centers of gravity, the payload can be loaded and secured in the bay without having to run various calculations each time a payload is loaded. Systems and methods related to how the payloads are packaged in an efficient, expeditious manner are also provided.

Abstract: A cargo aircraft configured to carry a portion of its payload in a cargo bay volume enclosed by a moveable nose door and supported by a structural extension of the fuselage that extends forward into the moveable nose door is disclosed. Examples include an aircraft with a continuous cargo bay extending from an aft end of a fixed portion into forward portion inside a nose door, where the portion of the cargo bay in the nose door is supported by a cantilevered support structure extending forward a length from a cargo opening into the fixed portion and such that the support structure extends into the nose door when the door is closed. The length of the support structure defines a supported cargo volume of at least about 15% of the overall volume of the fuselage forward of an aft end of the support structure.

Abstract: Methods of determining a final space reservation for a new aircraft are disclosed. The methods include using parametric definitions of potential payloads to generate a population of representative payloads for use in creating an initial space reservation. The methods include accounting for and applying a variety of margins on each potential payload and taking the union of potential payloads. Alternatively, the union can be taken first and then the margins applied. A homogenous space reservation can be determined based upon a variety of differently shaped or sized payloads, including a margin build-up to mitigate risk of unknowns associated with future changes in specific payload shapes and sizes, build tolerances, environmental conditions, and/or loading and unloading motions and clearances. Once this space reservation is known, it is possible to design an external shape of a carrying vehicle by staying outside of this space reservation.

Abstract: Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.

Abstract: Systems, methods, and vehicles for loading and unloading cargo from a long-distance transport vehicle, such as an aircraft, are described. The systems and methods include operating a plurality of vehicles to unload large cargo from the aircraft and transporting the large cargo to an installation site. In some instances, the vehicles hold the payload the entire time, including while loading aircraft, during flight, unloading the aircraft, and moving the payload to the installation site. Alternatively, the vehicles can drive on the plane to load the payload to a designated area, and equivalent vehicles can drive on the plane after the payload has been flown to unload the payload and moving the payload to the installation site. Various vehicles and systems, and components thereof, along with methods of operating the same, are also provided.

Abstract: Systems, methods, and vehicles for loading and unloading cargo into or out of a large transport vehicle, such as an aircraft, utilizing a curved path are described. The systems and methods include one or more support structures disposed, either permanently or removably, within a cargo bay of the transport vehicle to form a curved path extending into an aft portion of the cargo bay. During loading, the payload can move in the aft direction while concurrently rotating about a center point of an arc. In some embodiments, the cargo bay can include a kinked portion disposed between a proximal and aft portions of the cargo bay, with the curved path extending at least through the kinked portion and into the aft portion. Methods, systems, and components thereof for assembling a cargo, unloading cargo from a large transport vehicle, and disassembling a cargo are also provided.

Abstract: Systems, methods, and vehicles for loading and unloading cargo into or out of a large transport vehicle, such as an aircraft, utilizing a curved path are described. The systems and methods include one or more support structures disposed, either permanently or removably, within a cargo bay of the transport vehicle to form a curved path extending into an aft portion of the cargo bay. During loading, the payload can move in the aft direction while concurrently rotating about a center point of an arc. In some embodiments, the cargo bay can include a kinked portion disposed between a proximal and aft portions of the cargo bay, with the curved path extending at least through the kinked portion and into the aft portion. Methods, systems, and components thereof for assembling a cargo, unloading cargo from a large transport vehicle, and disassembling a cargo are also provided.

Abstract: Methods of determining a final space reservation for a new aircraft are disclosed. The methods include using parametric definitions of potential payloads to generate a population of representative payloads for use in creating an initial space reservation. The methods include accounting for and applying a variety of margins on each potential payload and taking the union of potential payloads. Alternatively, the union can be taken first and then the margins applied. A homogenous space reservation can be determined based upon a variety of differently shaped or sized payloads, including a margin build-up to mitigate risk of unknowns associated with future changes in specific payload shapes and sizes, build tolerances, environmental conditions, and/or loading and unloading motions and clearances. Once this space reservation is known, it is possible to design an external shape of a carrying vehicle by staying outside of this space reservation.

Abstract: Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.