To improve safety during a fall of a flying apparatus, a flying apparatus (1) according to a representative embodiment of the present application includes a body unit (2), a lift-force generating part (3) that is connected to the body unit and generates a lift force, a flight control part (14) that controls the lift-force generating part, an abnormality detecting part (15) that detects an abnormality during flight, a parachute device (4) including a parachute (41, 41A) and a parachute accommodating part (42) that accommodates the parachute, and a fall control part (16) that ejects the parachute from the parachute accommodating part according to the detection of the abnormality by the abnormality detecting part.

An apparatus an unmanned aerial vehicle recovery system is provided. The apparatus includes a base to mount to an unmanned aerial vehicle. The apparatus further includes a housing to engage the base. In addition, the apparatus includes a parachute disposed within the housing. Also, the apparatus includes a deployment mechanism to deploy the parachute. The deployment mechanism is to eject the housing away from the base upon a triggering event.

To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

Methods, systems and apparatus for the deploying of buoyancy and impact reduction measures during operation of a UAV in the event of a failure, malfunction or collision. One or more airbags or bladders may be inflated to reduce the force transferred to the UAV as a result of a crash or collision. The bladders may both be used in the impact reduction as well as being used as a floatation device in the event a water landing/crash. The airbags may be configured to keep the UAV afloat so as to allow for the recovery of the UAV.

An electronic parachute deployment system includes an electronic actuator, a control module, a deployment actuator, and a release mechanism. A parachute is positioned on a payload device, such as a racecar, to slow or stop the payload upon receipt of an electronic deployment activation signal. The electronic deployment signal is verified, including determining proper voltage and source. The deployment system includes multiple redundancies including mechanical deployment redundancy, remote deployment redundancy, and power supply redundancy. The control module responsible for monitoring deployment includes indicators and sensors to indicate a status, operation, or mode relative to the operability of the payload device, relative to components of the release mechanism, and relative to the parachute deployment.

A movable object for detecting an obstacle includes a first passive infrared sensor having a first detection range and a first field of view, and one or more second passive infrared sensors each having a second detection range and a second field of view. The second detection range is longer than the first detection range and the second field of view is smaller than the first field of view. The movable object further includes one or more processors configured to calculate a distance from the movable object to the obstacle based on data from at least one of the first passive infrared sensor or the one or more second passive infrared sensors, and determine whether to effect a collision avoidance maneuver for the movable object to avoid the obstacle based on the distance.

To provide a safety device that can control a landing point of a flight vehicle in the event of a crash. The safety device provided with a flight vehicle includes a first parachute configured to reduce a falling velocity and control an attitude of the flight vehicle during falling, a second parachute configured to be opened later than the first parachute and to reduce an impact when the flight vehicle lands, a sensor portion configured to detect a fall of the flight vehicle, and a control unit configured to control opening of the first parachute and the second parachute. In addition, the control unit opens the first parachute at a first timing after the sensor portion detects the fall and opens the second parachute at a second timing after the first timing and when a predetermined condition is satisfied.

To provide a safety device that can control a landing point of a flight vehicle in the event of a crash. The safety device provided with a flight vehicle includes a first parachute configured to reduce a falling velocity and control an attitude of the flight vehicle during falling, a second parachute configured to be opened later than the first parachute and to reduce an impact when the flight vehicle lands, a sensor portion configured to detect a fall of the flight vehicle, and a control unit configured to control opening of the first parachute and the second parachute. In addition, the control unit opens the first parachute at a first timing after the sensor portion detects the fall and opens the second parachute at a second timing after the first timing and when a predetermined condition is satisfied.

Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.

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.