An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft, wherein the plurality of load attenuators are configured to mechanically deform in a progressive failure fashion from a first effective length to a second effective length greater than the first length in response to an applied tensile load on the load attenuators coupled to the plurality of girts and the aircraft airframe, wherein the load attenuators are selected to reduce the force with a total length that minimizes buoyancy depth of the aircraft.

A warning method for an aircraft includes receiving a first parameter indicative of an aircraft's flight path, calculating a stable approach value based on the first parameter, receiving a second parameter indicative of the aircraft's turbulence, calculating a turbulence factor based on the second parameter, calculating a safe landing value based on the stable approach value and the turbulence factor, comparing the safe landing value to a threshold value, and providing an aircraft warning when the safe landing value fails to meet the threshold value.

Falling drone warning apparatuses and methods are disclosed. The apparatus may be attached to a drone and may measure acceleration during the drone's operation in order to ascertain whether the drone is free falling. If the apparatus detects that the drone is free falling, the apparatus may activate an audible alarm to warn people on the ground of the potential danger and to afford them the opportunity to take action to avoid the drone's impact or minimize its effect.

A ballistic parachute associated with an aircraft is deployed where the aircraft includes a first part and a second part, the two parts are detachably coupled to each other when the ballistic parachute is deployed, and the ballistic parachute is coupled to the first part of the aircraft. A landing zone associated with the second part of the aircraft is determined and it is decided whether to decouple the two parts, including by deciding whether the landing zone associated with the second part of the aircraft is inhabited. If it is decided to decouple the two parts from each other, they are decoupled from each other.

An on-board emergency response system for a vehicle include a drone being integrated with a vehicle to become separated only when the vehicle is in trouble or experiencing difficulties. Activation of the drone may be from inside the vehicle or remotely via a communication link. The drone is automatically ejected or activated when abnormal conditions inside or outside the vehicle are detected. The drone may provide a backup communication when needed. Once the drone is ejected from the plane, it then follows the vehicle from above at a predetermined distance. It also sends its location, video and images taken inside and outside the vehicle to the command center. If a disaster is inevitable, the drone then tracks the vehicle all the way to its destination. Since the vehicle's actual location is immediately known to the central command, the rescue team can take off in no time, skipping the search altogether.

A hard landing indicator assembly is disclosed herein. The hard landing indicator assembly includes a pressure relief valve, a hydraulic tube having a first end and a second end, the first end coupled to the pressure relief valve, and a plunger having a top portion and a shaft, the plunger disposed in the hydraulic tube, wherein a portion of the shaft is a hard landing indicator that extends outward from the hydraulic tube in response to a hard landing event.

An unmanned aerial vehicle (UAV) damage mitigation system includes a drone housing, a processor, a memory, an inertial measurement unit (IMU), and associated electronics configured to determine if the drone is experiencing a failure event or is in danger of crashing. If such a failure is indicated, then the drone includes a parachute, alarm, and programming intended to mitigate or minimize damage to people and property on the ground. The UAV damage mitigation system also includes a mobile software application that is notified if the drone is experiencing a catastrophic event, and is notified of all other aerial vehicles in a proximity to the drone housing.

A hard landing indicator assembly is disclosed herein. The hard landing indicator assembly includes a pressure relief valve, a hydraulic tube having a first end and a second end, the first end coupled to the pressure relief valve, and a plunger having a top portion and a shaft, the plunger disposed in the hydraulic tube, wherein a portion of the shaft is a hard landing indicator that extends outward from the hydraulic tube in response to a hard landing event.

A method for monitoring an aircraft landing gear. The method includes using information from at least one accelerometer firmly secured to a landing gear wheel mounted to rotate on a landing gear axle to estimate an angle of deflection ? of the axle at least when the wheel is in contact with the ground.

An emergency landing procedure that includes a sequence of control settings is continuously generated. An aircraft is landed, including by using the sequence of control settings and a set of one or more inertial sensors to control an actuator.