Systems and methods are disclosed for providing a controlled temperature in a control volume. Such systems include a main chamber (defining the control volume), a mixing chamber and a gasflow source. The mixing chamber is in selective fluid communication with the main chamber, and has at least one mixing chamber inlet, and a ram air inlet for allowing ram airflow at a first temperature to be channeled into the mixing chamber. The gasflow source provides a source gasflow at a greater, second temperature to the mixing chamber. The mixing chamber provides the mixing chamber outflow at a third temperature by selectively allowing the ram airflow and the source gasflow in the mixing chamber to mix therein, or, by selectively allowing the ram airflow in the mixing chamber to flow to the main chamber (in absence of source gasflow). A controller is operative to provide a desired level for the third temperature.

A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

An unmanned aerial vehicle includes at least one rotor motor configured to drive at least one propeller to rotate; and a micro hybrid generator system configured to provide power to the at least one rotor motor. The micro hybrid generator system includes a rechargeable battery configured to provide power to the at least one rotor motor; a small engine configured to generate mechanical power; and a generator motor coupled to the small engine and configured to generate electrical power from the mechanical power generated by the small engine. The unmanned aerial vehicle also includes a cooling system configured to couple to the micro hybrid generator system. The cooling system includes one or more plates; and a plurality of fins extending from each of the one or more plates. The cooling system is configured to dissipate heat from the micro hybrid generator system.

An unmanned aerial vehicle includes an atmospheric sensor configured to measure an atmospheric condition. The unmanned aerial vehicle includes a rotor motor configured to drive rotation of a propeller of the unmanned aerial vehicle. The unmanned aerial vehicle includes a hybrid energy generation system including a rechargeable battery configured to provide electrical energy to the rotor motor; an engine configured to generate mechanical energy; and a generator coupled to the engine and configured to generate electrical energy from the mechanical energy generated by the engine, the electrical energy generated by the generator being provided to at least one of the rechargeable battery and the rotor motor.

In one or more aspects of the present disclosure, an aerospace vehicle includes a frame, an actuable multifunctional cellular structure connected to the frame, the actuable multifunctional cellular structure including a first face member and a second face member, and a shape memory alloy core coupled to the first face member and the second face member, and wherein, at least one of the first face member and the second face member is a graded thermal structure configured so that heat transferred through the graded thermal structure in a predetermined thermal pattern to the shape memory alloy core effects a predetermined change in a shape of the shape memory alloy core and effects a change in shape of the actuable multifunctional cellular structure.

An innovative passive cooling solution with sealed UAV enclosure system allows heat from a semiconductor chip to be dissipated to the ambient environment through evaporation/condensation phase-change cooling and air cooling a heat sink such as a fin without any additional power consumption to operate cooling solution. One example of such a solution may include a pipe with a fin and a fluid. The pipe may include a wick structure along an inner surface of the pipe configured to allow the fluid to travel within the wick structure and to allow a vapor form of the fluid to exit the wick structure towards a center of the pipe.

A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

A heat sink is disclosed comprising a metallic pin extending between a proximal end and a distal end. A lower pin stud is positioned adjacent to the proximal end. An upper pin stud is positioned adjacent to the distal end. A base flange is interposed between the lower pin stud and the upper pin stud and defines a lower base surface and an upper base surface. The lower pin stud engages a source aperture and the lower base surface engages a source surface. A composite pitch fiber encapsulates the upper pin stud and the upper base surface. The metallic pin and the composite pitch fiber transfer the thermal energy from the lower pin stud and the lower base surface, through the upper pin stud and through the composite pitch fiber for dissipating the thermal energy from the source.

Battery modules for unmanned and human piloted electric aircraft comprise two planar substrates with electrochemical cells secured between to form load-bearing structural components from which aircraft with greater endurance can be constructed. The cells can be oriented perpendicular or parallel to the substrates, and in the latter case the substrates can include slots that the cells fit into. The cells can be secured to the substrates by adhesives, welding, soldering and the like, as well as by mechanical tensioners. Battery modules can be formed to the shapes of aircraft parts such as wings. Multirotor aircraft are disclosed in which the arms and other parts of the aircraft are constructed from such battery modules.

In some embodiments, systems and methods are provided that limit the change in temperature and/or control a temperature of a product during delivery. Some embodiments provide systems comprising an unmanned delivery vehicle (UDV) comprising: a body comprising a nanotechnology insulation material, wherein the nanotechnology insulation material comprises material having been manipulated at a molecular level during the macroscale fabrication of the nanotechnology insulation material to enhance insulation effectiveness; at least one propulsion system; a control circuit coupled with the at least one propulsion system to control the operation of the at least one propulsion system and control a direction of travel of the UDV, wherein the body physically supports the propulsion system and the control circuit; and a product cavity defined within the body and configured to receive at least one product while the at least one product is transported by the UDV to a delivery location.