Implementations of an unmanned aerial vehicle (UAV) fuselage are provided. In some implementations, the fuselage comprises a frame having a shell removably secured thereto. The frame of the fuselage is made of printed circuit board (PCB) material that includes conductive tracks configured to conductively connect electrical components of the UAV. Due to the inherent rigidity of PCB material, the transfer of vibration loads to electrical components secured to the frame of the fuselage is minimized. While the shell is secured to the frame, an enclosure for any electrical components on the topside of the frame is formed. In this way, the encased electrical components may be protected from the environment (e.g., rain) and direct impact during a crash. In some implementations, the frame of the UAV fuselage may include a plurality of stiffening inserts that are positioned and configured to increase the rigidity of the frame.

An aircraft structural component that is adapted for absorbing and transmitting forces in an aircraft, the aircraft structural component comprising at least one panel element and at least one reinforcing structure. The at least one reinforcing structure is rigidly attached to the at least one panel element such that at least one cavity is defined between the at least one panel element and the at least one reinforcing structure, the at least one cavity being adapted for distributing forces that are absorbed by the aircraft structural component in operation.

A pressure bulkhead for a pressurized cabin of an aerospace craft includes: a pressure wall and a frame for connecting the pressure wall to the aerospace craft; wherein the frame is connected to the pressure wall; wherein the pressure wall has: a core layer; and a first covering layer and a second covering layer; wherein the core layer is arranged between the first covering layer and the second covering layer; and wherein the core layer comprises an auxetic foam. Such a pressure bulkhead has increased stiffness, thus ensuring that smaller bending deformations and lower stresses occur. Hence costs can be saved, and the volume of the pressurized cabin which can be made available to the crew and passengers is maximized.

A nosecone of an aircraft sensor probe may include a first portion defining a tip of the nosecone that is formed from a first material. The nosecone further includes a second portion aft of the first portion and formed from a second material. The second portion may define an internal volume. The second material may have a greater porosity than the first material. The nosecone may further include a third portion aft of the second portion. The third portion may be configured to arrange a microphone assembly relative to the internal volume. The nosecone may a component or subassembly or a sensor probe for the aircraft. For example, the sensor probe may include the nosecone and the microphone assembly. The nosecone may be configured to block the audio signals at the tip and reduce turbulent noise of the audio signals associated with non-parallel local flow angles of the airflow.

An unmanned aerial vehicle includes a body and a heat source disposed in the body. The heat source includes at least one of an electronic controller system and a motor. The unmanned aerial vehicle further includes a plurality of rotor blades. At least a portion of the body is constructed of crystalline carbon fibers.

An aircraft assembly is disclosed having a first structural component and a second structural component. A fastener fastens the first component to the second component. The first structural component includes a body and an insert in the body. The insert has a machined hole through which the fastener extends. The material hardness of the insert is lower than the material hardness of the body.

A dissolvable composition is disclosed. The composition includes a first material (e.g., an anode), a second material (e.g., a cathode), and a third material (electrolytic material). The third material is reactive with water to form an electrolyte. The first material and the second material are electrochemically different such that the first material and the second material are capable of galvanic reaction in the presence of water and electrolytes. Also disclosed are tools or other apparatus made from the composition, as well as processes, systems, and apparatus for making and using such compositions, tools, and other apparatus.

An apparatus includes a foam layer, a coating layer and an elastomer. The foam layer includes a first surface for coupling the apparatus to a surface exposed to weather, a second surface opposite the first surface, and a plurality of pores within the foam layer. The coating layer is deposited on the second surface of the foam layer. The elastomer is deposited within the plurality of pores within the foam layer.

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.

An aircraft protective component for an aircraft module, the aircraft protective component includes: a plurality of cells connected together to form a lattice, each cell having a chiral structure, wherein the lattice of the cells is configured to at least partially surround the aircraft module to provide an energy absorption barrier for the aircraft module. The aircraft protective component enables the energy generated by an impact to the aircraft to be dissipated throughout the lattice of the protective component. The protective component thus acts as a crumple zone to minimize the transfer of such impact energy to the aircraft module.