An airborne computational facility uses an energy collection system to provide energy for operation. An airborne balloon is provided with a photovoltaic collector array, and uses energy generated by the photovoltaic collector array to power an on-board computational facility. Data for computation is received by a communication module and computational results are transmitted by the communication module.

An airborne computational facility uses an energy collection system to provide energy for operation. An airborne balloon is provided with a photovoltaic collector array, and uses energy generated by the photovoltaic collector array to power an on-board computational facility. Data for computation is received by a communication module and computational results are transmitted by the communication module.

An aircraft includes: a plurality of rotor units each including a propeller and a motor that drives the propeller; a plurality of shock absorbers including a first shock absorber and a second shock absorber different from the first shock absorber, the first shock absorber defining a first gas chamber containing a first gas that is less dense than air; and a release unit that is disposed on the first shock absorber and configured to release the first gas contained in the first gas chamber at a predetermined timing.

The disclosed invention describes a method for determining a current state of a gas cell in an airship, particularly the lift. A computing device receives depth measurements of the interior of the gas cell using a lidar sensor positioned outside the cell and uses these depth measurements to create a mesh, segment a space within the mesh into geometric shapes, calculate the volume of the shapes, and use the calculated volume to estimate the total volume of the space within the mesh, representing the volume of gas within the gas cell. The computing device then uses the estimated volume to calculate the lift of the gas cell and sends the calculated lift to a control module of the airship.

The disclosed invention describes a method for determining a current state of a gas cell in an airship, particularly the lift. A computing device receives depth measurements of the interior of the gas cell using a lidar sensor positioned outside the cell and uses these depth measurements to create a mesh, segment a space within the mesh into geometric shapes, calculate the volume of the shapes, and use the calculated volume to estimate the total volume of the space within the mesh, representing the volume of gas within the gas cell. The computing device then uses the estimated volume to calculate the lift of the gas cell and sends the calculated lift to a control module of the airship.

An aircraft apparatus may include an outer membrane and an inner flexible bladder. The flexible bladder may include a lighter-than-air lifting gas therein, and an interstitial space between the outer membrane and the inner flexible bladder may include air. Various techniques are disclosed for preventing or reducing physical contact between the outer membrane and the inner flexible bladder, reducing an amount of leakage of the lighter-than-air lifting gas.

An aircraft apparatus may include an outer membrane and an inner flexible bladder. The flexible bladder may include a lighter-than-air lifting gas therein, and an interstitial space between the outer membrane and the inner flexible bladder may include air. Various techniques are disclosed for preventing or reducing physical contact between the outer membrane and the inner flexible bladder, reducing an amount of leakage of the lighter-than-air lifting gas.

A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability. A vehicle comprising a first lift device capable of providing hydrostatic lift; a second lift device capable of providing dynamic lift through movement; and a system structured to generate thrust coupled to the second lift device, the second lift device and the thrust generation system capable of rotating together about an axis that is lateral to a longitudinal axis of the vehicle at angles at least in the range of 90 degrees to and including 180 degrees.

A hybrid VTOL vehicle having an envelope configured to provide hydrostatic buoyancy, a fuselage attached to the envelope and having at least one pair of wings extending from opposing sides thereof to produce dynamic lift through movement, and a thrust generation device on each wing and configured to rotate with each wing about an axis that is lateral to a longitudinal axis of the envelope to provide vertical takeoff or landing capabilities. Ideally, the envelope provides negative hydrostatic lift to enhance low-speed and on-the-ground stability. A vehicle comprising a first lift device capable of providing hydrostatic lift; a second lift device capable of providing dynamic lift through movement; and a system structured to generate thrust coupled to the second lift device, the second lift device and the thrust generation system capable of rotating together about an axis that is lateral to a longitudinal axis of the vehicle at angles at least in the range of 90 degrees to and including 180 degrees.

A fail-safe aerostat system is discussed, for structural support and network interconnection, applicable to many systems based on lighter-than-air lift. The invention describes a system with reinforced structure and optimized connection and an integration structure (reinforcement and integration structure), reinforcing a hydrogen cell or cells with a fail-safe design. The theorized structure is strong enough to withstand explosive forces, avoiding propagation of shock wave damage and fire, and a hydrogen cell or cells automatically self-controlled, operating independently to obtain lift strength and multi-parameter control.