The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition.

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 variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising. in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.

An embodiment of the present invention discloses a repair system for a planetary exploration parachute. The repair system includes a folding piece and a fuse, the fuse is provided in the folding piece, a sensing signal for reflecting an impact force of dust is received by the fuse, fusing is generated in the fuse when the sensing signal is greater than a preset threshold, and the folding piece is changed from a folded state to an unfolded state after the fusing is generated in the fuse, so as to automatically repair a damaged part of the parachute.

An embodiment of the present invention discloses a repair system for a planetary exploration parachute. The repair system includes a folding piece and a fuse, the fuse is provided in the folding piece, a sensing signal for reflecting an impact force of dust is received by the fuse, fusing is generated in the fuse when the sensing signal is greater than a preset threshold, and the folding piece is changed from a folded state to an unfolded state after the fusing is generated in the fuse, so as to automatically repair a damaged part of the parachute.

A rotary wing aircraft has a nacelle, at least one rotor provided with at least one blade, a braking device to stop the rotation of the rotor, an emergency parachute provided with a canopy and with a rope, a rocket to start the extraction of the canopy from the nacelle, two operating devices to operate the braking device and the rocket, respectively, and a single actuator device to operate both the operating devices.

A rotary wing aircraft has a nacelle, at least one rotor provided with at least one blade, a braking device to stop the rotation of the rotor, an emergency parachute provided with a canopy and with a rope, a rocket to start the extraction of the canopy from the nacelle, two operating devices to operate the braking device and the rocket, respectively, and a single actuator device to operate both the operating devices.

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 variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising. in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.