A method for collecting acoustic data from an industrial machine is disclosed. The method may include: providing an unmanned aerial vehicle (UAV) having an acoustic receiver attached thereto; and positioning the unmanned aerial vehicle at a specific location so that the acoustic receiver collects acoustic data from the industrial machine at the specific location. An acoustic receiver is attached to the UAV for collecting acoustic data from the industrial machine. An acoustic filter is attached to the acoustic receiver and the UAV for filtering unwanted sound from the acoustic data. Acoustic data can be used by a flight control system to identify a specific location relative to the industrial machine that is a source a specific acoustic signature emanating from the industrial machine.

In some embodiments, apparatuses and methods are provided herein useful to transport unmanned aircraft systems to delivery products. In some embodiments, gas-filled aerial transport and launch system, comprises: a transport aircraft comprising: a gas chamber; and a carrier compartment where the gas chamber induces a lifting force on the carrier compartment; at least one propulsion system; and a navigation control system that controls the direction of travel of the transport aircraft; wherein the carrier compartment comprises: an unmanned aircraft system (UAS) storage area configured to receive multiple UASs; and an UAS launching bay that enables the UAS to be launched while the transport aircraft is in flight and while the UAS is carrying a package to be delivered.

In some embodiments, apparatuses and methods are provided herein useful to transport unmanned aircraft systems to delivery products. In some embodiments, gas-filled aerial transport and launch system, comprises: a transport aircraft comprising: a gas chamber; and a carrier compartment where the gas chamber induces a lifting force on the carrier compartment; at least one propulsion system; and a navigation control system that controls the direction of travel of the transport aircraft; wherein the carrier compartment comprises: an unmanned aircraft system (UAS) storage area configured to receive multiple UASs; and an UAS launching bay that enables the UAS to be launched while the transport aircraft is in flight and while the UAS is carrying a package to be delivered.

The present invention relates a wind power generation system using an airship, which can generate wind power using strong wind of a jet stream by using the airship, convert the wind power into a laser beam and transmit the laser beam to the ground so that power can be produced on the ground by converting the laser beam into electricity. The present invention provides efficiency and convenience in collecting power of the airship on the ground by implementing a wind power generation system using an airship to include: an airship for producing power through wind power generation while floating in the air and transmitting the produced power as a laser beam; and a ground receiving unit for receiving the laser beam transmitted. from the airship and converting the laser beam into electricity.

The present invention relates a wind power generation system using an airship, which can generate wind power using strong wind of a jet stream by using the airship, convert the wind power into a laser beam and transmit the laser beam to the ground so that power can be produced on the ground by converting the laser beam into electricity. The present invention provides efficiency and convenience in collecting power of the airship on the ground by implementing a wind power generation system using an airship to include: an airship for producing power through wind power generation while floating in the air and transmitting the produced power as a laser beam; and a ground receiving unit for receiving the laser beam transmitted. from the airship and converting the laser beam into electricity.

An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; a balloon that laterally covers the plurality of rotor units, across a height of the plurality of rotor units in an up-and-down direction; and a drive unit configured to change the external shape of the balloon at a predetermined timing.

An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; a balloon that laterally covers the plurality of rotor units, across a height of the plurality of rotor units in an up-and-down direction; and a drive unit configured to change the external shape of the balloon at a predetermined timing.

A system for numerical simulation and test verification of icing characteristics of an aerostat includes an aerostat icing characteristic calculation model and an aerostat icing characteristic test system. The aerostat icing characteristic calculation model is configured to obtain icing data of the aerostat through numerical simulation, and the aerostat icing characteristic test system is configured to obtain icing characteristic data of the aerostat through a physical simulation test. The calculation result obtained through the numerical simulation and the test result obtained through the physical simulation test are mutually verified and improved, so as to facilitate the in-depth research and accurate analysis of the icing characteristics of the aerostat.

Aspects of the technology relate to lighter-than-air (LTA) high altitude platforms configured to operate in the stratosphere. Such platforms can generate solar power from solar panels, enabling long-term operation for weeks, months or longer. Shaped envelope LTA platforms may have solar panels arranged along an upper section of the envelope, which can be particularly helpful when the envelope is made of a fabric that is not transparent or translucent. To address possible thermal effects, aerodynamics and other issues with the solar panels, one or more external air bladders are disposed between the such components and the shaped envelope. One or more perimeter chamber of the air bladder configuration can be employed to create more aerodynamically efficient leading and trailing edges to blend the envelope surface with the surface(s) of the solar panel components. The insulative air bladder(s) may also provide structural support during fill of a shaped envelope at launch.

Aspects of the technology relate to lighter-than-air (LTA) high altitude platforms configured to operate in the stratosphere. Such platforms can generate solar power from solar panels, enabling long-term operation for weeks, months or longer. Shaped envelope LTA platforms may have solar panels arranged along an upper section of the envelope, which can be particularly helpful when the envelope is made of a fabric that is not transparent or translucent. To address possible thermal effects, aerodynamics and other issues with the solar panels, one or more external air bladders are disposed between the such components and the shaped envelope. One or more perimeter chamber of the air bladder configuration can be employed to create more aerodynamically efficient leading and trailing edges to blend the envelope surface with the surface(s) of the solar panel components. The insulative air bladder(s) may also provide structural support during fill of a shaped envelope at launch.