An aerial vehicle (10) has an aerial platform (12) that supports lift elements (11), an engine (14) and a fuel supply (15) and that has a coupling mechanism (16) adapted for coupling to a removable load (17). The lift elements include a soft or flexible wing (11) flexibly coupled to the aerial platform at points of suspension on opposite sides of the aerial platform whose location (A, B) relative to a longitudinal axis of the platform is such that the aerial platform and the attached load has a center of gravity (C.G.) which maintains balance of the aerial platform. An adjustment system (18) is coupled to the points of suspension and is operative for moving the points of suspension relative to the longitudinal axis of the platform when cargo is unloaded from the flying platform to preserve balance.

A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray and a first stop plate secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray and a second stop plate secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

A conventional parachute requires a velocity pressure during descent in order to open the parachute. As a result, a minimum descent distance and time are required from the beginning to the end of the parachute opening operation and use at low altitude has to be restricted. In order to remedy this issue, an airtight tube and a compressed gas device are provided together in a section of the parachute having the largest annular shape when the parachute has been opened. The tube is annularly expanded by the pressure of the gas, and the parachute is forcibly deployed and opened.

A method for controlling an attitude of a payload includes determining an input torque based on an input angle and one or more motion characteristics of the payload, determining an estimated disturbance torque based on one or more motion characteristics of a carrier to which the payload is coupled, and calculating an output torque based on the input torque and the estimated disturbance torque. The output torque is configured to effect movement of the carrier to achieve a desired attitude of the payload.

A method for controlling an attitude of a payload includes determining an input torque based on an input angle and one or more motion characteristics of the payload, determining an estimated disturbance torque based on one or more motion characteristics of a carrier to which the payload is coupled, and calculating an output torque based on the input torque and the estimated disturbance torque. The output torque is configured to effect movement of the carrier to achieve a desired attitude of the payload.

An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

An aerial imaging aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons coupled therebetween. A two-dimensional distributed thrust array is coupled to the airframe. The thrust array includes a plurality of propulsion assemblies each operable for variable speed and omnidirectional thrust vectoring. A payload is coupled to the airframe and includes an aerial imaging module. A flight control system is operable to independently control the speed and thrust vector of each of the propulsion assemblies such that in an inclined flight attitude, the flight control system is operable to maintain the orientation of the aerial imaging module toward a target while translating the aircraft, changing aircraft altitude and/or circling the target.

To provide a flying object in which a working part can be close to an operation target at an appropriate distance the flying object according to the present disclosure includes a flight part including at least a plurality of rotary wings and a motor for driving the rotary wings, a main body elongated in a vertical direction, and a connection part that connects the flight part and the main body in a mutually displaceable manner, wherein a total length of the main body in the vertical direction is at least twice a maximum diameter of the flight part in a horizontal direction. The main body has an upper part that is provided above the connection portion, and a lower portion that is provided below the connection portion, and the length of the upper part is three times or more the length of the lower part.