A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a blunt-end shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The plurality of drop-off plies are separated from each other by at least one of the plurality of continuous plies.

In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The tips of the plurality of drop-off plies are arranged in a monotonically-inward pattern.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

Systems and methods for pre-flight fabrication and/or assembly of various configurations of aerial vehicles are described. Operations of various configurations of aerial vehicles may be analyzed using models based on various inputs, which inputs may be related to routes, environments, vehicles, components, or other factors. A particular configuration may be selected for a selected route and associated task based at least in part on a desired optimization parameter. Then, the particular configuration of the aerial vehicle may be fabricated and/or assembled to complete the associated task via the selected route.

A folding device is disclosed for a rotary wing aircraft. The foldable device includes a plurality of pivots mounting a plurality of arms supporting driven propellers of the rotary wing aircraft. A projection and a detent resiliently cooperate for securing each of the plurality of arms in desired orientations relative to the rotary wing aircraft and for enabling each of the plurality of arms to rotate about the pivot into a folded position.

Methods and devices of fabricating a stringer for a vehicle. The stringer can be constructed from two charges that are formed together into the stringer. During fabricating, the ends of the charges can be formed in a die cavity. When the ends are misaligned in the die cavity, one of the charges can be moved in the die cavity to align the ends. The device used for fabricating the charges can include a punch with separate punch plates that move the ends of the charges into the die cavity. The punch plates can be separately moved to adjust the position of the charges and align the ends.

Camera calibration may be performed in a mobile environment. One or more cameras can be mounted on a mobile vehicle, such as an unmanned aerial vehicle (UAV) or an automobile. Because of the mobility of the vehicle the one or more cameras may be subjected to inaccuracy in imagery caused by various factors, such as environmental factors (e.g., airflow, wind, etc.), impact by other objects (e.g., debris, vehicles, etc.), vehicle vibrations, and the like. To reduce the inaccuracy in imagery, the mobile vehicle can include a mobile camera calibration system configured to calibrate the one or more cameras while the mobile vehicle is traveling along a path. The mobile camera calibration system can cause the one or more cameras to capture an image of an imaging target while moving, and calibrate the one or more cameras based on a comparison between the image and imaging target data.