The embodiments of the Parachute Landing Assistant are comprised of a battery pack, a power switch, an LED indicator light; an audio jack; a microcontroller; and a ground proximity sensor. The LED indicator light informs the parachutist as to whether operation is enabled or disabled and indicates when the unit is charging. The microcontroller controls the components of the Parachute Landing Assistant. The ground proximity sensor senses the distance from the ground of the parachutist. The ambient pressure sensor allows the unit to determine its height. During a jump the ambient pressure gauge will sense the pressure change and turn on the Parachute Landing Assistant. It will also be used to send a warning to advise the parachutist of upcoming flare tones established by the ground proximity sensor and microcontroller.

A package delivery mechanism (PDM) of an unmanned aerial vehicle (UAV) is described. The PDM includes a gravity activated locking mechanism to lock and unlock a package attached to the UAV based on the weight of the package. When the package is attached to a suspension member of the UAV, the locking mechanism automatically engages with the package and keeps the package locked to the suspension member, due to the weight of the package. When the package is lowered and reaches the ground, the weight of the package is offloaded from the suspension member, which enables the locking mechanism to be disengaged, thereby releasing the package.

An ejection launcher is an apparatus that effectively ejects a payload while maintaining a compact structure. The apparatus includes an elongated enclosure, a cover, a trigger mechanism, a spring-loaded piston, and a payload. The elongated enclosure positions and connects the trigger mechanism with the spring-loaded piston. The elongated enclosure also houses the spring-loaded piston and the payload. The trigger mechanism releases the spring-loaded piston which forces the payload from within the elongated enclosure. The payload is a desired delivered item and is preferably a parachute. The trigger mechanism and the spring-loaded piston translates horizontal force into vertical force which releases the payload and reduces the release resistance. The trigger mechanism preferably utilizes and includes a servo motor with a output arm. The output arm pushes against a catch plate of the trigger mechanism and releases a catch pin of the spring-loaded piston.

A method of constructing a reduced drag wing, including: providing a top wing surface panel; coupling a top surface external leading-edge panel to the external surface of the top wing surface panel, wherein the top surface external leading-edge panel extends forward from the top wing surface panel and extends rearward covering at least partially the top surface external leading-edge panel; coupling internal rib elements to the interior surface of the top wing surface panel; coupling the top surface external leading-edge panel to a sleeve element; coupling the rear sleeve element to a bottom wing surface panel; coupling the internal rib elements to the interior surface of the bottom wing surface panel; and coupling the top surface external leading-edge panel and the sleeve element to a releasable mechanical mechanism. A reduced drag wing for a wingsuit. A wingsuit including a reduced drag wing.

A flight phase stability indicator system and method for generating and presenting stability indicator(s) are disclosed. A processor receives flight phase data representative of an identification of a current operational flight phase; receives navigation data comprised of aircraft position, a planned flight trajectory, and runway data if runway data is needed for the current operational flight phase; determines stability data representative of a stability of the current operational flight phase based upon at least the navigation data; generates presentation data responsive to the determination and representative of the flight phase stability indicator and/or presentation(s) of flight phase stability; and presents the indicator represented in the presentation data on or through a presentation unit comprised of a visual display, aural advisory unit, and/or tactile advisory unit.

A flight phase stability indicator system and method for generating and presenting stability indicator(s) are disclosed. A processor receives flight phase data representative of an identification of a current operational flight phase; receives navigation data comprised of aircraft position, a planned flight trajectory, and runway data if runway data is needed for the current operational flight phase; determines stability data representative of a stability of the current operational flight phase based upon at least the navigation data; generates presentation data responsive to the determination and representative of the flight phase stability indicator and/or presentation(s) of flight phase stability; and presents the indicator represented in the presentation data on or through a presentation unit comprised of a visual display, aural advisory unit, and/or tactile advisory unit.

An unmanned aerial vehicle may include a fuselage and an anchor structure coupled to the fuselage and including a wing retention structure and a power module retention structure. The unmanned aerial vehicle may also include a wing releasably coupled to the wing retention structure, thereby coupling the wing to the fuselage, and a power module releasably coupled to the power module retention structure, thereby coupling the power module to the fuselage.

An unmanned aerial vehicle may include a fuselage and an anchor structure coupled to the fuselage and including a wing retention structure and a power module retention structure. The unmanned aerial vehicle may also include a wing releasably coupled to the wing retention structure, thereby coupling the wing to the fuselage, and a power module releasably coupled to the power module retention structure, thereby coupling the power module to the fuselage.

The embodiments of the Parachute Landing Assistant are comprised of a battery pack, a power switch, an LED indicator light; an audio jack; a microcontroller; and a ground proximity sensor. The battery pack is comprised of a power storage means such as alkaline, lithium ion, or other types of battery system. The power switch allows the parachutist to enable or disable the operation of Parachute Landing Assistant. The LED indicator light is comprised of an LED that informs the parachutist as to whether the Parachute Landing Assistant operation is enabled or disabled. The audio jack is comprised of a standard , , or 3/32 mono audio or stereo audio receptacle that accepts the analogous audio plug. The microcontroller controls all the other components of the Parachute Landing Assistant. The ground proximity sensor senses the distance from the ground of the parachutist.

The embodiments of the Parachute Landing Assistant are comprised of a battery pack, a power switch, an LED indicator light; an audio jack; a microcontroller; and a ground proximity sensor. The battery pack is comprised of a power storage means such as alkaline, lithium ion, or other types of battery system. The power switch allows the parachutist to enable or disable the operation of Parachute Landing Assistant. The LED indicator light is comprised of an LED that informs the parachutist as to whether the Parachute Landing Assistant operation is enabled or disabled. The audio jack is comprised of a standard , , or 3/32 mono audio or stereo audio receptacle that accepts the analogous audio plug. The microcontroller controls all the other components of the Parachute Landing Assistant. The ground proximity sensor senses the distance from the ground of the parachutist.