A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.

A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.

An apparatus for air dropping equipment and supplies from an aircraft is disclosed herein. The apparatus includes a canister having a rotor system configured to slow the descent at a predetermined altitude to a desired landing speed via auto-rotation and/or with motor assist. The rotor system is configured to prevent the container from spinning about its longitudinal axis during the descent.

The present invention provides a method for decelerating and redirecting an airborne platform, comprising the steps of retaining a flexible airfoil in non-deployed form in controllably releasable secured relation with each corresponding rotor arm of a multi-rotor drone; and upon detecting rate of descent of said drone in a first direction to be greater than a predetermined value, triggering release of one or more of said retained airfoils from said corresponding rotor arm and causing each of said released airfoils to be circumferentially displaced from a first rotor arm to a second rotor arm of said drone to occlude an adjacent inter-arm region, wherein each of said circumferentially displaced airfoils generates a sufficient value of localized lift that causes said descending drone to change its direction of descent from said first direction to a second direction.

The present invention provides a method for decelerating and redirecting an airborne platform, comprising the steps of retaining a flexible airfoil in non-deployed form in controllably releasable secured relation with each corresponding rotor arm of a multi-rotor drone; and upon detecting rate of descent of said drone in a first direction to be greater than a predetermined value, triggering release of one or more of said retained airfoils from said corresponding rotor arm and causing each of said released airfoils to be circumferentially displaced from a first rotor arm to a second rotor arm of said drone to occlude an adjacent inter-arm region, wherein each of said circumferentially displaced airfoils generates a sufficient value of localized lift that causes said descending drone to change its direction of descent from said first direction to a second direction.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

Provided is a non-motorized flying unit. The non-motorized flying unit includes a body part having a head part and a tail part having an accommodation space and a through hole, an image capturing unit installed in the through hole and configured to obtain an image information, a protective window installed in the through hole, a plurality of shock absorbing devices installed at the end portion of the tail part, a weight installed at the end portion of the tail part, and a lighting device installed at an end portion of the plurality of shock absorbing devices. A propulsion unit which is detachably coupled to the tail part storing a propellant which, upon combustion, forms pressure in the propulsion unit to provide thrust to the body part.