A container for a flight craft such as a gas balloon is provided. Part of the walls of the container is constituted of three separated plates. The first plate has one or more holes that causes gas to flow in and out of two spaces so that the pressure difference between a first space and a second space separated by the first plate is resolved but does not cause gas convection between those two spaces. As the flight craft ascends, a relationship T1<T2<T3<T4 occurs among the temperatures inside the first to a fourth space. The temperature gradient between the inside and outside of the container becomes less pronounced. Condensation is unlikely to form on any of the three plates. The first plate with the holes buffers the force that the second plate is subjected to due to a pressure difference between the inside and outside of the container.

A container for a flight craft such as a gas balloon is provided. Part of the walls of the container is constituted of three separated plates. The first plate has one or more holes that causes gas to flow in and out of two spaces so that the pressure difference between a first space and a second space separated by the first plate is resolved but does not cause gas convection between those two spaces. As the flight craft ascends, a relationship T1<T2<T3<T4 occurs among the temperatures inside the first to a fourth space. The temperature gradient between the inside and outside of the container becomes less pronounced. Condensation is unlikely to form on any of the three plates. The first plate with the holes buffers the force that the second plate is subjected to due to a pressure difference between the inside and outside of the container.

The system can include: a vehicle 100 and a stabilizer 200. However, the system can additionally or alternatively include any other suitable set of components. The system functions to facilitate vehicular transport (e.g., via a cabin). Additionally, the system can provide impact attenuation and/or mitigate rebound of the vehicle during a water landing. Additionally or alternatively, the system can function to provide aquatic stabilization of the vehicle and/or cabin thereof. However, the system 100 can provide any other suitable functionalities.

A surveillance drone is disclosed. The surveillance drone includes a gas-filled container and propellers for aerial mobility. The surveillance drone also includes an electronic surveillance sensing device positioned below the gas-filled container. The gas-filled container may be filled with a lighter than air gas such as, for example, helium.

A surveillance drone is disclosed. The surveillance drone includes a gas-filled container and propellers for aerial mobility. The surveillance drone also includes an electronic surveillance sensing device positioned below the gas-filled container. The gas-filled container may be filled with a lighter than air gas such as, for example, helium.

Systems and methods for maintaining and stabilizing the position and orientation of a payload attached to a high-altitude balloon are provided. A payload may be attached to a powered gimbal. The powered gimbal may be configured to orient and position the payload in a plurality of directions corresponding to a first, second, and third rotational axis of the balloon-mounted payload system. After the payload is positioned by the powered gimbal, the position and orientation of the payload may be maintained and stabilized by one or more rotational stabilization devices. The stabilization by the one or more rotational stabilization devices can occur along any one, or combination of, the first, second, and third rotational axes.

Systems and methods for maintaining and stabilizing the position and orientation of a payload attached to a high-altitude balloon are provided. A payload may be attached to a powered gimbal. The powered gimbal may be configured to orient and position the payload in a plurality of directions corresponding to a first, second, and third rotational axis of the balloon-mounted payload system. After the payload is positioned by the powered gimbal, the position and orientation of the payload may be maintained and stabilized by one or more rotational stabilization devices. The stabilization by the one or more rotational stabilization devices can occur along any one, or combination of, the first, second, and third rotational axes.

A container for a flight craft such as a gas balloon is provided. Part of the walls of the container is constituted of three separated plates. The first plate has one or more holes that causes gas to flow in and out of two spaces so that the pressure difference between a first space and a second space separated by the first plate is resolved but does not cause gas convection between those two spaces. As the flight craft ascends, a relationship T1<T2<T3<T4 occurs among the temperatures inside the first to a fourth space. The temperature gradient between the inside and outside of the container becomes less pronounced. Condensation is unlikely to form on any of the three plates. The first plate with the holes buffers the force that the second plate is subjected to due to a pressure difference between the inside and outside of the container.

A container for a flight craft such as a gas balloon is provided. Part of the walls of the container is constituted of three separated plates. The first plate has one or more holes that causes gas to flow in and out of two spaces so that the pressure difference between a first space and a second space separated by the first plate is resolved but does not cause gas convection between those two spaces. As the flight craft ascends, a relationship T1<T2<T3<T4 occurs among the temperatures inside the first to a fourth space. The temperature gradient between the inside and outside of the container becomes less pronounced. Condensation is unlikely to form on any of the three plates. The first plate with the holes buffers the force that the second plate is subjected to due to a pressure difference between the inside and outside of the container.

Some embodiments described herein relate to an aircraft that includes a support frame, at least one gas compartment, and multiple propulsion units. The gas compartment(s) can be coupled to the support frame and configured to contain a gas having a gas density less than the density of atmospheric air surrounding the aircraft during operation. Similarly stated, the gas-filled gas compartment(s) can produce a gas lifting force on the support frame. The propulsion units can each be configured to selectively produce a propulsive force with a thrust vector with a non-zero component along a vertical axis of the support frame. The maximum gross weight of the aircraft can be greater than either the gas lifting force of the maximum vertical propulsion force and less than the sum of the gas lifting force and the maximum vertical propulsion force.