A solar cell assembly and an aerostat are disclosed. The solar cell assembly includes: a flexible base plate; and a plurality of rigid solar cells that are connected in series by using a conducting wire and that are disposed on a surface of the flexible base plate. According to the solar cell assembly provided in the present invention, the rigid solar cells are disposed on the flexible base plate. Therefore, the entire solar cell assembly can bend freely under specific pressure. The rigid solar cells do not bend as the entire device bends, thereby protecting the rigid solar cells from damage and implementing application of the rigid solar cells on a non-planar structure. A structure is simple, optical-to-electrical conversion efficiency is high, flexibility is achieved, and lamination is strong.

An unmanned aerial vehicle (UAV) includes a UAV body including a first mounting member, a gimbal, and a plurality of stands. The gimbal includes a second mounting member connected to the first mounting member, and a gimbal body connected to the second mounting member. The plurality of stands are fixedly attached to the gimbal body and configured to rotate together with the gimbal body around a yaw axis of the gimbal body.

Systems, methods and device for payload transportation and high altitude atmospheric payload deployment. A gondola includes a frame which is configured to carry a payload, such as a rocket. The gondola includes a control system using a plurality of propellers to provide orientation changes. In the instance of a carried rocket, the system provides timed release such that the rocket is released in desired direction and pitch angle.

A hot air balloon steering system for steering a hot air balloon includes a hot air balloon that includes a basket. A stand unit is movably coupled to the basket. The stand unit abuts a support surface thereby facilitating the basket to be spaced from the support surface when the hot air balloon is not in flight. A sail unit is movably coupled to the basket. The sail unit captures air when the hot air balloon is in flight. Moreover, the sail unit steers the hot air balloon when the hot air balloon is in flight.

The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

A semiconductor device includes a semiconductor substrate, a device layer over the semiconductor substrate, a first color filter in a top surface of the device layer and adjacent to an edge of the device layer, and a second color filter in the top surface of the device layer. The second color filter has substantially the same thickness and the same color as the first color filter.

According to an example aspect of the present invention, there is provided an automated balloon launching system for launching at least one balloon such as a meteorological balloon or a radiosonde. The system comprises a container and a storage arranged in the container for storing at least one box at a defined storage position p=1, 2, . . . , n. The at least one box includes a balloon and a sonde. A release silo is arranged at least partially on top of or above and adjacent to the container for sheltering the balloon during inflation. A x-, y- and z-manipulator is arranged in the container for removing a specific box from one of the defined storage positions p=1, 2, . . . , n, and for subsequent feeding the release silo with the specific box. The present invention also concerns a method for launching at least one balloon such as a meteorological balloon or a radiosonde.

A portable launch rig (PLR) may include a support structure including two side supports defining an interior space for lifting and filling a balloon envelope of a balloon. Wheels on each of the side supports enable the PLR to be moved in various directions in order to prepare the PLR for launching the balloon. The side supports are connected by a lateral support beam having a pair of cranes arranged thereon. Each crane has an arm arranged over the interior space that is connected to a spreader beam. The spreader beam includes a lift assembly configured to lift and inflate the balloon envelope within the interior space. The PLR includes a platform and perch for supporting and moving the balloon envelope. A door assembly of the PLR includes a plurality of hangar doors configured to block wind from a respective direction of each hangar door entering the interior space.

A lighter-than-air craft including an envelope. A mixture of helium and hydrogen disposed within the envelope. The mixture having a ratio of helium to hydrogen such that the mixture is nonflammable during operating conditions for the lighter-than-air craft. The mixture provides buoyancy for the lighter-than-air craft. A hydrogen fuel cell fluidically coupled with the mixture and configured to utilize the mixture to generate electricity. A propulsion system is coupled to the envelope, and the propulsion system is configured to provide propulsion for the lighter-than-air craft. The propulsion system is electrically coupled with the hydrogen fuel cell and receives electricity generated by the hydrogen fuel cell. The propulsion system is configured to utilize the electricity in providing the propulsion to the lighter-than-air craft.