Abstract: Current foot-launched 2-stroke commercial PPG offerings can meet the specified threshold (and in some cases, objective) requirements for flight ceiling, payload capacity and range with little to no modification. We will discuss those in the next section. The APES system enhances the effectiveness and lethality of the PPG-equipped unit by reducing weight of the PPG, increasing reliability and redundancy, reducing pilot workload, and seamlessly integrating with UAV's and UGV's. System improvements in the following areas is assessed: Series hybrid-electric powertrain, Coaxial propellers. Localization, autopilot, and formations, Auto landing and other advanced features, Integration with unmanned systems, and Launch Considerations.

Abstract: An Intermediate Load Attachment Platform (ILAP) for attaching a cargo load to at least one main parachute, the ILAP protects a release mechanism disposed at least partially therein, the release mechanism is coupled to a drogue mechanism, such that the drogue is released from the ILAP when the release mechanism is opened, thus beginning deployment of the main canopy.

Abstract: A neck protection system for a parachute assembly may comprise a head restraint, a first upper strap coupled to a first side of the head restraint, and a second upper strap coupled to a second, opposing side the head restraint. A first lower strap may be coupled to the first side of the head restraint. A second lower strap may be coupled to the second side of the head restraint. A first pull cord may be coupled to the first upper strap. A second pull cord may be coupled to the second upper strap.

Abstract: An aerial payload delivery system uses a cruciform parachute canopy that is connected to base by plurality of suspension lines including an adjustable control line. A control system includes an actuator to selectively adjust the length of the control line. By adjusting the length of the control line, the parachute can be selectively set to glide or descend substantially vertically subject to wind. In an embodiment, the suspension lines also include a short line and a plurality of long lines. The parachute is set to glide by adjusting the control line to be about the same length as the short line and set to vertically descend by adjusting the length of the control line to differ from the short line.

Abstract: The present disclosure provides method and apparatus, an electronic apparatus, and a storage medium for a virtual object control, and relates to the field of computer technologies. In the present disclosure, when a touch operation in a control region is detected, a viewing angle of a virtual scene is determined; an acceleration of a virtual object during a falling process is obtained with reference to the touch operation, the viewing angle, and the gravitational acceleration; and the virtual object is controlled to fall according to the acceleration. In this way, an action of a character can be realistically simulated by determining non-fixed moving directions and speeds.

Abstract: A decelerator for decelerating an attached payload includes a first canopy, a second canopy, and an internal structure for redirecting air entering the decelerator out of the decelerator and in a contraflow direction, which is cognate to the direction of travel. The first canopy defines an interior volume and includes a first opening for receiving a flow of air into the interior volume and a second opening for permitting received air to travel out of the interior volume. The second canopy is then positioned over the second opening, and the internal structure extends at least partially through the interior volume and interconnects the first canopy and the second canopy. Air within the internal structure is directed out of the decelerator in the contraflow direction. The internal structure can be constructed of a plurality of venturi tubes to increase the velocity at which air is emitted from the decelerator.

Abstract: 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.

Abstract: In one possible embodiment, a system capable of a self-propagating data link includes an unmanned vehicle having a data link transceiver and at least one deployable data link transceiver. The unmanned vehicle having a deployment means for deploying the at least one deployable data link transceiver.

Abstract: The invention relates to a method and a device for an intelligent parachute rescue system for manned and unmanned aerial vehicles (14), wherein no pyrotechnic propellants are used, but compressed air (4a) extracted from a pressure bottle (4).

Abstract: 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 ¼?, ??, 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.

Abstract: A redundant clustered parachute apparatus includes a harness and a plurality of lines operatively coupled to the harness. Each line has a length and a plurality of canopies coupled to and along the length. The plurality of canopies, across the plurality of lines, create an aggregated force of air resistance to slow a falling object in the harness. Loss of some of the canopies or some of the lines does not significantly affect the performance of the redundant clustered parachute apparatus to safely deliver the object to the ground.

Abstract: A method for monitoring air pressure in a kite when kite boarding is described. The method involves a first step of connecting an air pressure sensor to one or more bladders of the kite. The method involves a second step of positioning a visual display for the air pressure sensor where it will be visible to a user conducting a visual inspection of the kite to display a pressure reading as sensed by the pressure sensor.

Abstract: A riser release system controllably lands a descending flight vehicle having a parafoil or canopy. The system has control lines and riser lines attached to the parafoil or canopy. The other end of the riser lines are attached to an upper portion of a release structure; a lower portion of the release structure is connected to the payload; and a coupling mechanisms releasably couples the upper and lower portions. When the upper and lower portions are decoupled, a distance control device controls and limits the distance of separation between the two portions, and a rate control device controls the rate of separation. Separation causes the riser lines to increase the distance between the payload and canopy, further causing the canopy to flare and decrease the rate of descent of the flight vehicle.

Abstract: A system for skydiving trajectory and coordination feedback for a user. The system includes a controller coupled to a plurality of sensor inputs. The controller determines a user drag through air based on input data from the plurality of sensor inputs. The controller also receives a user flightpath and determines a projected user trajectory based on the user drag. The controller also determines user drag adjustments to align the projected user trajectory with the received user flightpath. At least one of an aural, haptic, or visual feedback device is coupled to the controller to provide feedback to the user in response to the user drag adjustments.

Abstract: To minimize headspace in a storage container and thereby reduce or eliminate alcohol evaporation, concentrated surfactant solutions stabilized by a diluent of higher volatility than the surfactant, such as alcohol, are stored in a flexible bladder fabricated from fabric including an impermeable or semipermeable membrane, such as polyurethane coated fabric. Because the bladder automatically deflates as the fluid level decreases, minimal head space is maintained and evaporation of the alcohol is thus constrained. A rigid support structure may be employed to hold the flexible bladder. With such a storage system, concentrated surfactant solutions may be manufactured at a convenient location for transport to and storage near an injection well, with considerable time between manufacture and application allowed before the surfactant solution degrades by an unacceptable amount.

Abstract: A pre-deployed parachute includes a double-drag balloon parachute with an inflation canopy and a first drag generating space, a universal joint attached to the double-drag balloon parachute by a universal joint, a pre-deployed canopy with a second drag generating space and attached to the universal joint, a load attached to the pre-deployed canopy. The inflation of the inflation canopy allows the pre-deployed canopy to be deployed without requiring height difference and any dynamic energy. With the buoyancy and the first drag generated by the double-drag balloon parachute and the second drag generated by the pre-deployed canopy, the pre-deployed parachute is capable of producing three drag forces, and therefore, the pre-deployed parachute can be brought to a stable condition within a very short time, which prevents the discomfort feeling of a sudden free fall at the beginning stage of the parachuting.

Abstract: A parachute canopy system includes a canopy having a skirt and a suspension line system, where each suspension line of the suspension line system is attached to the skirt. A pair of first line members is attached to the canopy, the pair of first line members extending in a substantially radial direction away from the skirt towards a center of the canopy. A first end of each line member in the pair of first line members is connected together to the suspension line at the skirt. A first end of the second line member is connected to adjacent second ends of adjacent pairs of first line members that extend towards the center of the canopy.

Abstract: This application generally relates to deformable elastomeric conductors and differential signaling transmission techniques. According to one embodiment, a deformable elastomeric conductor is configured to transmit electrical signals. It comprises: an elastomeric polymer matrix; and conductive filler material uniformly dispersed in the elastomeric polymer matrix sufficient to render the material electrically conductive. The conductive filler material may include substantially non-entangled particles having an aspect ratio sufficiently large to enable the particles to substantially remain in contact and/or in close proximity with adjacent particles so as to maintain conductive pathways in the material when the material is subjected to deformation up to and exceeding 10% strain. Thus, over a transmission distance of an electrical signal through the conductor, the transmission does not suffer greater than about 3 dB of signal attenuation when subjected to the deformation.

Abstract: The present disclosure provides a parachute deployment system. The system may include a deployment spring arranged on a launch platform with a parachute that is foldable and positionable on an opposite side of the deployment spring from the launch platform. The system may also include a bridle line attached to the parachute, and a lanyard line having a first end and a second end. The first end of the lanyard line may be attached to the deployment spring, and the second end of the lanyard line may be attached to the launch platform. The system may also include a trigger system configured to initiate deployment of the parachute. Upon deployment, the deployment spring may be configured to launch the parachute and the bridle line substantially perpendicular to the launch platform. After deployment, the deployment spring and the lanyard line may be configured to hang from the launch platform.

Abstract: A method and apparatus comprising a housing, a processor unit, a display, a navigation module, and a number of modules. The navigation module is configured to guide an airdrop system to a target location. The number of modules is configured to provide functions for use by a number of operators to perform a mission in addition to an airdrop.

Abstract: The present invention relates to the deployment of a plurality of wireless communication devices in order to provide a wireless mesh communications network. According to various embodiments, deployment of the communications devices is made by parachutes suitably adapted for the purpose.

Abstract: An aerial distribution system and method for deploying items is disclosed. The system includes a bulk shipping container comprised of a single piece of corrugated plastic, cut and folded into a closable box, a plurality of deployment boxes within the bulk shipping container, each deployment box containing at least one item, a plurality of tethers, each tether coupling a deployment box to the bulk shipping container, and a freefall retarding device coupled to the bulk shipping container.

Abstract: A recovery system for a disrupter barrel. The recovery system limits the distance the disrupter travels as a result of a force or recoil that occurs upon firing the disrupter.

Abstract: A cost-effective pack adapted to be distributed from an aircraft in the event of a natural, military, political, or other disaster includes an outer package, at least one item in the outer package for aerial delivery, and at least one aerodynamic component formed on the outer package and methods and systems for making the pack.

Abstract: A method of landing a capsule-spacecraft having a crew compartment containing crew, light cargo, and whatever other elements are associated with crew safety and comfort during emergency recovery, such as survival equipment and a service component including any propulsion components, heat shield, heavier structure, or other equipment not directly connected with the crew component. In the event of a propulsion system failure, the crew compartment component is immediately separated from the service component, either by automatic or crew action. One or more parachutes are then deployed by rapid methods, such as rocket extraction, from the crew compartment. Because the space craft is separated into two parts the weight of the parachutes is reduced in proportion as the weight of the crew compartment is to the total capsule-spacecraft.

Abstract: A parachute can be opened automatically without requiring manual operation. In addition, the parachute is capable of staying balanced during the course of landing. The parachute comprises: a spherical canopy, an air guide member and four assistant canopies. The air guide member is a rotation symmetrical structure with respect to the central axis, each of the cylindrical members is also a rotation symmetrical structure with respect to the assistant central axis, and the assistant canopies are also symmetrically arranged with respect to the central axis, so as to maintain the parachute in a stable and balanced state when the parachute is falling.

Abstract: A waist-mounted parachute deployment and retracting system for training runners and other athletes that provides a user a method for selectively deploying and retracting the parachute during training without stopping or breaking stride. The parachute provides drag to increase resistance to improve performance by overloading the muscles. The user selectively deploys the parachute by pressing a button to release and open the parachute. Air flow created by the user's forward motion flows through a pair of ports on the side of a case holding the parachute. The air flow expands the parachute, causing the cords attaching the parachute to the case to extend and wind a recoil mechanism. The user selectively retracts the parachute by pressing a button to close the parachute and the recoil mechanism rewinds the cords, pulling the parachute into the case, ready to be deployed again when desired.

Abstract: Devices, methods, and systems for slowing the descent of an object in flight such as a baseball using a parachute are presented. A parachute assembly includes a canopy attached to a plurality of suspension lines converging downwardly to a corresponding number of attachment points on the surface of a ball. The attachment points are substantially equidistantly spaced apart along a line of substantially equal latitude. In one embodiment, each attachment point defines an opening to an interior channel extending to a central chamber. Each suspension line is inserted into an interior channel, through the central chamber, and out of the ball through a common shaft, where the lines are fastened together in a bundle and then withdrawn until the bundle lies in the central chamber, retaining the lines inside the ball.

Abstract: A cost-effective pack adapted to be distributed from an aircraft in the event of a natural, military, political, or other disaster includes an outer package, at least one item in the outer package for aerial delivery, and at least one aerodynamic component formed on the outer package and methods and systems for making the pack.

Abstract: A method and aircraft system are provided for determining an optimal gliding speed that maximizes gliding distance of the aircraft upon engine failure, and comprises calculating the optimal gliding speed from a speed polar curve, true airspeed, heading, and vertical wind speed. The polar curve may be constructed with consideration of the aircraft center of gravity and weight. The calculated gliding speed, which may be restricted to a threshold, is provided to the pilot and optionally to an autopilot. The method is repeated periodically, or if the wind vertical or horizontal velocities exceed a threshold for a predetermined period of time.

Abstract: An illumination/marker system mounted on a parachute slider is shown for identification, tracking, and collision avoidance in manned and unmanned parachute operations. The system includes a variety of emission/radiation sources (luminaires), and positioned at pre-determined locations on the parachute slider. A battery provides the power source. System activation means are provided automatically upon deployment of a parachute and/or slider, and/or other sensory inputs such as altitude, motion, time, or photometrics, or manual action, on demand, by the parachutist. System deactivation means provide sensory inputs or on demand by the parachutist.

Abstract: Embodiments relate to a drag chute. An exemplary drag chute is comprised of a canopy from flexible material having a perimeter, a first surface, and a second surface. The drag chute is also comprised of a stiffening member coupled to the canopy along a portion of the canopy perimeter. The drag chute is also comprised of a veil attached to the canopy and a leash attached to the veil. The stiffening member may be maintained in a tunnel that extends along at least a portion of the canopy perimeter. In an additional embodiment, the stiffening member may be a foam material. An additional embodiment may include an integrated bag for storing one or more parts of the drag chute when not in use.

Abstract: Devices, methods, and systems for slowing the descent of an object in flight such as a baseball using a parachute are presented. A parachute assembly includes a canopy attached to a plurality of suspension lines converging downwardly to a corresponding number of attachment points on the surface of a ball. The attachment points are substantially equidistantly spaced apart along a line of substantially equal latitude. In one embodiment, each attachment point defines an opening to an interior channel extending to a central chamber. Each suspension line is inserted into an interior channel, through the central chamber, and out of the ball through a common shaft, where the lines are fastened together in a bundle and then withdrawn until the bundle lies in the central chamber, retaining the lines inside the ball.

Abstract: Flare munition for battlefield illumination is provided that includes: (a) at least one electrical flare body; (b) an electrical energy source connectable with the flare body; and (c) an electrical or electronic control device for connecting the electrical flare body with the source of energy during a specified time interval. The flare munition can be fired from a weapon or can be launched as a bomb and allows safe and simple subsequent recovery of the corresponding flare body because no pyrotechnic flare charge is used. Instead, an electrical flare body is used that emits light in the visible and/or infrared wavelength range depending on its intended purpose.

Abstract: A display system for a parachutist is provided based on navigation data and calculations of locations where the parachutist should steer the parachute to increase likelihood of reaching a target. A two-dimensional representation of a navigation funnel is displayed. The display may increase situational awareness by use of color to indicate preferred positions in the navigation funnel.

Abstract: An emergency safety jacket equipped with a rear ejecting parachute to protect an operator against forward accidental impact when riding a motorcycle-type vehicle is herein disclosed. The safety jacket comprises a back-mounted parachute being manually activated and ejected rearward using a propelling device, thereby removing the operator off the rear of the vehicle. The safety jacket also comprises a padded long-sleeve design with an outer shell which provides enhancements to protect the operator from impact, abrasion, and fire. The emergency safety jacket is specifically envisioned for use with motorcycle and scooter type vehicles.

Abstract: The present invention relates to an autonomous stratosphere platform which is preferably intended to be positioned in the stratosphere, is carried by a carrying shield (1) and is controlled by a control and drive unit (3) which can use control elements (301) to control the carrying shield (1) via lines (302). A cable (5) is used to connect the control and drive unit (3) to a capsule (2) which is intended to hold a payload and the requisite electrical and electronic components for operating the autonomous stratosphere platform. A control element (8) having an anchoring shield (6) is fastened to the capsule (2), again on a cable (5). The stratosphere platform experiences uplift as a result of the wind gradient between the wind layer of the anchoring shield (6) and that of the carrying shield (1).

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

Abstract: The invention relates to a steering unit for a wind propulsion system, the steering unit comprising a first fixed attachment means for securing a first end of a tractive cable the second end of which is secured to a device or a vehicle to which a tractive force shall be transferred, a second attachment means for attaching a number of tractive lines, the second end of which being secured to an aerodynamic wing element, a mechanical support frame connecting the first attachment means to the second attachment means for transferring a tractive force. The invention aims at providing such a steering unit with improved design for better maneuverability and stability.

Abstract: An airfoil wing system for releasing air from an airfoil wing for an inflatable airfoil is provided. The airfoil wing is secured to the inflatable airfoil. The airfoil wing system has at least two wing panels connected together and an opening formed between the two wing panels wherein the opening automatically moves from a closed position to an open position to release air from beneath the airfoil wing thereby allowing takedown of the inflatable airfoil.

Abstract: A parachute packing system for facilitating insertion of a parachute canopy into a deployment receptacle or parachute receptacle includes an adjustable spring-like cylindrical sleeve that conforms to a “C”-shaped cross section, the sleeve member having rounded edges to prevent snagging of parachute material, and a gap defining a line passage slot within the cylindrical sleeve for passage of parachute suspension lines and bridle, and a pair of opposing deployment receptacle attachment points or knobs affixed to the outer surface of the cylindrical sleeve. Preferably, at least one of the receptacle attachment points or knobs engages a slotted track for sliding adjustment thereof, and a mechanism for reversibly locking the receptacle attachment point or knob within the slotted track. Optionally, the cylindrical sleeve includes an integral mat attachment hook, which runs across the bottom of the sleeve opening, for attachment to a packing mat made of non-slip rubberized material.

Abstract: A cost-effective pack adapted to be distributed from an aircraft in the event of a natural, military, political, or other disaster includes an outer package, at least one item in the outer package for aerial delivery, and at least one aerodynamic component formed on the outer package and methods and systems for making the pack.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: Disclosed is an attenuated landing system. The landing system includes one or more inflatable structures that are mounted to the underside of a cargo platform. A terrain sensor is likewise mounted to the underside of the cargo platform and is activated upon being air-dropped. Once terrain is detected, pressurized gas vessels are pyrotechnically activated to inflate the structures. Once fully inflated, the structures effectively cushion the landing of the cargo platform and, thereby, protect sensitive on-board equipment.

Abstract: Flare munition for battlefield illumination is provided that includes: (a) at least one electrical flare body; (b) an electrical energy source connectable with the flare body; and (c) an electrical or electronic control device for connecting the electrical flare body with the source of energy during a specified time interval. The flare munition can be fired from a weapon or can be launched as a bomb and allows safe and simple subsequent recovery of the corresponding flare body because no pyrotechnic flare charge is used. Instead, an electrical flare body is used that emits light in the visible and/or infrared wavelength range depending on its intended purpose.

Abstract: A parachute release system is configured to releasably couple a parachute to a payload. A parachute release mechanism is coupled to a suspension strap routed through a strap sleeve. The parachute release mechanism is configured to provide near-simultaneous separation of the suspension straps from the payload via operation of a rotatable hinge pin. The strap sleeve reduces the possibility of the suspension strap becoming entangled with the payload. With this system and method, larger payloads may be supported and/or the mass of the parachute release system may be reduced.

Abstract: A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Abstract: An aerial delivery system is configured to allow delivery of one or more releasable items after the system is extracted from an aircraft. One or more linear guidance devices and releasable securing mechanisms allow the aerial delivery system to deploy one or more releasable items at an appropriate time. The one or more releasable items may be deployed simultaneously, or in a staged or staggered fashion. Through use of drag or lift-producing devices, the system may be recovered and reused. The attitude and/or azimuth orientation of the system may be varied prior to, during, and/or after release of a releasable item.

Abstract: A parachute deployment deceleration assist device for a jumper is disclosed that includes an inverted pocket formed from at least one web of material. The device further includes at least one removable harness attachment means fixed to a peripheral edge of the pocket. Each harness attachment means is selectively attachable to a harness assembly of a parachute between a canopy thereof and the jumper, preferably at a connector link and within easy reach of the jumper when the parachute is fully deployed. In use, before the canopy is inflated the inverted pocket inflates and aids in the deceleration of the jumper, reducing the shock experienced by the jumper upon full inflation of the canopy. Once the canopy is fully inflated and the jumper is falling at a substantially constant speed, the jumper may reach up to remove the device from the harness assembly.