An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

This disclosure relates to a system and method for an inflatable motorcycle outfit. The system comprises an inflatable trouser, an inflatable jacket, a pair of inflatable boots, one or more inflatable canopies. The system is flat when worn by the rider, resembling ordinary clothing and inflates in the event of a motorcycle accident. The system reduces the speed of a rider when the inflatable canopies are deployed by inflation, thus reducing the overall impact force the rider is facing in an accident situation. The system offers impact reducing protection for the rider by having a barrier of inflatable air tunnel structures inside or outside the outfit that absorbs impact energy in an accident situation when inflated. The air tunnel shells and the outfit are made from material with abrasion resistant, heat resistant, and/or stretchable properties.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

A paradrone includes a canopy having a parafoil, a transverse canopy frame coupled to the parafoil to support the parafoil, a longitudinal canopy frame that is coupled to the parafoil while having a bent structure such that the parafoil generates a lift, and at least one parafoil connecting portion for connecting at least one canopy frame among the transverse canopy frame and the longitudinal canopy frame to the parafoil. The paradrone also includes a servomotor portion having a servomotor body and a servomotor arm for coupling and fixing intersecting parts of the transverse canopy frame and the longitudinal canopy frame. The servomotor arm is connected to a servomotor body and rotated in a predetermined direction by driving of the servomotor body to change the angle between the travelling direction of the paradrone fuselage and the transverse and longitudinal canopy frames, thereby changing the angle of attack.

A decelerator for decelerating an attached payload includes a first canopy, a second canopy, and an internal structure for redirecting air entering the decelerator out of the decelerator and in a contraflow direction, which is cognate to the direction of travel. The first canopy defines an interior volume and includes a first opening for receiving a flow of air into the interior volume and a second opening for permitting received air to travel out of the interior volume. The second canopy is then positioned over the second opening, and the internal structure extends at least partially through the interior volume and interconnects the first canopy and the second canopy. Air within the internal structure is directed out of the decelerator in the contraflow direction. The internal structure can be constructed of a plurality of venturi tubes to increase the velocity at which air is emitted from the decelerator.

A decelerator for decelerating an attached payload includes a first canopy, a second canopy, and an internal structure for redirecting air entering the decelerator out of the decelerator and in a contraflow direction, which is cognate to the direction of travel. The first canopy defines an interior volume and includes a first opening for receiving a flow of air into the interior volume and a second opening for permitting received air to travel out of the interior volume. The second canopy is then positioned over the second opening, and the internal structure extends at least partially through the interior volume and interconnects the first canopy and the second canopy. Air within the internal structure is directed out of the decelerator in the contraflow direction. The internal structure can be constructed of a plurality of venturi tubes to increase the velocity at which air is emitted from the decelerator.

A preferred break point is provided in the airframe, where there is a ballistic parachute system which includes a rocket which sits in a rocket canister and a canopy which sits in a canopy canister. The airframe includes a composite material and covers the ballistic parachute system. The preferred break point is located in the airframe over the opening of the rocket canister. A preferred break path is provided in the airframe located at least partially over the opening of the rocket canister and at least partially over the opening of the canopy canister.