Provided is a circuit abnormality diagnosis device capable of simply and easily diagnosing a circuit abnormality, a current generating device including the circuit abnormality diagnosis device, a deployed object ejection device for a flight object including the current generating device, an airbag device for a flight object including the current generating device, and a cutting device for a flight object including the current generating device.

A circuit abnormality diagnosis device 110 includes a calculation unit 1, an inspection power supply 2, a rectifier element 3, overcurrent preventing resistors 4 and 5, a voltage amplification unit 6, a voltage reading unit 7, and a light emitting unit 8, and performs a circuit abnormality diagnosis at a preset time (including the time of initial mounting) or every predetermined time. The circuit abnormality diagnosis device 110 diagnoses (determines) that a case where a voltage value is within a range of a first voltage value V.sub.1 or more and a second voltage value V.sub.2 or less, which is set in advance as a range of voltage values indicating that a circuit is normal, is a normal state, a case where the voltage value is less than the voltage value V.sub.1 is a short-circuit state in which the circuit is short-circuited, and a case where the voltage value is higher than the voltage value V.sub.2 is a disconnection state in which the circuit is disconnected.

A parachute vent reefing system is disclosed. The parachute vent reefing system includes a plurality of attachment members disposed about a vent portion of a parachute canopy and a keeper routed between each attachment member of said plurality of attachment members. The keeper has a diameter less than the diameter of the vent portion and is configured to break at a preselected tensile threshold.

A parachute vent reefing system is disclosed. The parachute vent reefing system includes a plurality of attachment members disposed about a vent portion of a parachute canopy and a keeper routed between each attachment member of said plurality of attachment members. The keeper has a diameter less than the diameter of the vent portion and is configured to break at a preselected tensile threshold.

In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.

A multi-modal aircraft recovery system is disclosed. In various embodiments, the system includes a first aircraft recovery parachute having a first set of physical attributes optimized for a first set of conditions and a second aircraft recovery parachute having a second set of physical attributes optimized for a second set of conditions different from the first.

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.