The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

The present invention relates to a method for controlling land surface temperature using stratospheric airships and a reflector. In the method for controlling land surface temperature using stratospheric airships and a reflector, four corners are connected to a lower end of support lines coupled to be disposed vertically downward from a plurality of airships, and sunlight is reflected by a reflector unfolded into a tetragonal shape in the air, wherein the reflecting surface of the reflector plate is maintained at an angle to remain perpendicular to an incident angle of sunlight to shield, or redirect, the land surface from incident sunlight.

The present invention relates to a method for controlling land surface temperature using stratospheric airships and a reflector. In the method for controlling land surface temperature using stratospheric airships and a reflector, four corners are connected to a lower end of support lines coupled to be disposed vertically downward from a plurality of airships, and sunlight is reflected by a reflector unfolded into a tetragonal shape in the air, wherein the reflecting surface of the reflector plate is maintained at an angle to remain perpendicular to an incident angle of sunlight to shield, or redirect, the land surface from incident sunlight.

An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship.

An airship is provided. The airship includes a hull configured to contain a gas, at least one propulsion assembly coupled to the hull and including a propulsion device, and at least one aerodynamic component including a plurality of fairing structures including one or more slats, wherein the at least one aerodynamic component is associated with the hull and is configured to direct airflow around the airship.

A method for balloon launching may include loading a pre-packaged balloon and payload into a shell structure. The pre-packaged balloon may be pulled out of its packaging in a vertical direction, for instance using a gantry crane. The gantry crane may be configured to inflate the balloon from the top of the envelope. The balloon may be inflated while substantially within the shell structure, which may provide protection from wind gusts. A vehicle, such as a heavy forklift, may provide mobility and support for the balloon and shell. Once the balloon is inflated, the vehicle may move the balloon/shell combination at a rate and direction substantially matching the current wind direction/speed. Furthermore, after reaching a zero-velocity condition relative to the wind, the vehicle may assist and/or initiate the opening of the shell. A tether connecting the balloon to the shell structure may be disconnected, allowing the balloon to launch.

A lift and drive unit for an aircraft or submarine vehicle may include a hydrogen based drive component for providing a forward drive force to move the aircraft or vehicle over ground, and a hydrogen-based lift component for providing an upward drive force to move the aircraft or vehicle upward. An onboard hydrogen generating apparatus is connectable to both the drive component and the lift component, for providing the drive and lift components with hydrogen.

The technology relates to health and lifetime estimation for a lighter-than-air (LTA) vehicle. An LTA vehicle health and lifetime estimation system may include a processor and a memory storing instructions executable by the processor to cause the processor to implement an estimation service for determining a remaining lifetime output and a simulator for simulating a terminal event based on the remaining lifetime output. The estimation service may include a thermal model configured to determine a gas temperature, a gas and air estimator configured to estimate a gas amount and an air amount remaining in a balloon of the LTA vehicle, a leak rate estimator configured to estimate a leak rate, and a zero pressure estimator configured to determine the remaining lifetime output based on the leak rate. The system also may include an air flow estimator configured to determine an air mass flow rate based on the air amount.

The technology relates to health and lifetime estimation for a lighter-than-air (LTA) vehicle. An LTA vehicle health and lifetime estimation system may include a processor and a memory storing instructions executable by the processor to cause the processor to implement an estimation service for determining a remaining lifetime output and a simulator for simulating a terminal event based on the remaining lifetime output. The estimation service may include a thermal model configured to determine a gas temperature, a gas and air estimator configured to estimate a gas amount and an air amount remaining in a balloon of the LTA vehicle, a leak rate estimator configured to estimate a leak rate, and a zero pressure estimator configured to determine the remaining lifetime output based on the leak rate. The system also may include an air flow estimator configured to determine an air mass flow rate based on the air amount.