A drogue parachute system for a spacecraft includes a first parachute, a first set of connection lines, an extension device, a second set of connection lines, a second parachute and a third set of connection lines. Each connection line of the first set of connection lines includes two opposite ends respectively connected to the first parachute and the spacecraft. Each connection line of the second set of connection lines includes two opposite ends respectively connected to the extension device and the first parachute. Each connection line of the third set of connection lines includes two opposite ends respectively connected to the second parachute and the extension device.

A drogue parachute system for a spacecraft includes a first parachute, a first set of connection lines, an extension device, a second set of connection lines, a second parachute and a third set of connection lines. Each connection line of the first set of connection lines includes two opposite ends respectively connected to the first parachute and the spacecraft. Each connection line of the second set of connection lines includes two opposite ends respectively connected to the extension device and the first parachute. Each connection line of the third set of connection lines includes two opposite ends respectively connected to the second parachute and the extension device.

An enhanced automatic activation device (EAAD) is provided. The EAAD includes a housing; a plurality of environmental sensors disposed within the housing; a connection to a reserve canopy deployment mechanism, the connection being disposed at least partially within the housing; and a processor coupled to the plurality of environmental sensors and the connection. The processor is configured to execute a machine learning process. The machine learning process is configured to classify environmental data from the plurality of environmental sensors into either a first group associated with nominal deployment of a main canopy of a parachute rig or a second group associated with failed deployment of the main canopy of the parachute rig. The processor is also configured to transmit a signal to the reserve canopy deployment mechanism where the machine learning process classifies the environmental data within the second group.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

An aircraft safety lifesaving system, disclosing an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. A safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first.

An aircraft safety lifesaving system, disclosing an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body. A safety cabin is provided at the top of the aircraft body, and a deceleration device in the safety cabin is ejected in an emergency to assist the aircraft body to decelerate; the damping and buffering mechanism extends below the wheel body, and the damping and buffering mechanism contacts with the ground first.

An aircraft safety lifesaving system, which includes an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body.

An aircraft safety lifesaving system, which includes an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body.

The invention provides an inexpensive means of transporting people and objects to altitudes of 10,000 meters or more. Flying System 1 has Balloon 11, Suspension Lines 12 hanging downwards from Balloon 11, and Cabin 13 attached to the lower ends of Suspension Lines 12. The main body of Cabin 13 consists of laminated walls that include a fiber-reinforced plastic layer that keeps Cabin 13 watertight and airtight and also serves to maintain the shape of Cabin 13, an ultra-violet-rays blocking layer that reduces the amount of ultra-violet-rays transmitted into Cabin 13, an insulation layer that reduces the amount of heat conducted from the inside to the outside of Cabin 13, and an adhesive layer that enters and seals a crack or hole in the fiber-reinforced plastic layer when the crack or hole appears. The side walls of the main body of Cabin 13 have two hatches located opposite each other.