Abstract: An exemplary inventive parafoil includes a soft wing and a semi-rigid skeleton. Configured to effect ram-air flight, the soft wing forms adjacent elongate cells directed from leading edge to trailing edge, with respective inflow vents arranged along the leading edge. The semi-rigid skeleton includes one or more cell-compatible support structures, each joined with a cell in furtherance of maintaining the cell's inflated shape and preventing its collapse under adverse aerodynamic circumstances. Each cell-compatible support structure includes a ring-like frame and two parallel rod-like projections attached perpendicular to the ring-like frame at laterally opposite locations. According to each coupling of a cell-compatible support structure with a cell, the ring-like frame is affixed at or near the cell's inflow vent, fitting onto or inside the cell lip; the two rod-like projections extend backward from the ring-like frame along part of the cell length, each integrated with or interiorly contiguous to the cell.

Abstract: Parachutes which have a generally circular skirt or hem, such as semi-hemispherical, extended gore, or any variant of axisymmetric parachutes and cruciform parachutes with arms attached are disclosed with a plurality of vertical slits located in a circumferential band adjacent the skirt or hem of the parachute to prevent canopy inversion. During deployment, when the outer portion of the canopy is exposed to air flow, the slits open up and the drag of the skirt of the canopy is reduced, thus limiting the potential for hem migration. The slits are positioned to allow airflow therethrough in order for the pressure on the outside of the canopy to be transferred through the slit openings and released or transferred to inside of the lower section of the canopy. Instead of slits, elongated narrow openings can be utilized.

Abstract: A multi-staged suspension line length parachute may include a suspension line having a primary length and a secondary length. The primary length may be deployable upon a first deployment of the multi-staged suspension line length parachute. The secondary length may be prevented from deployment until the primary length has fully deployed. An attenuator may attach a first portion of the secondary length to a second portion of the secondary length.

Abstract: A method of loading a bladder into an outer envelope of an inflatable kite involves inserting the bladder through a valve opening in a portion of the outer envelope of the inflatable kite until a valve of the bladder is positioned in the valve opening. The preferred manner of inserting the bladder into position is accomplished by securing a line to a remote end of the bladder and using the line to draw the bladder through the valve opening.

Abstract: A parachute vent reefing system is disclosed. The parachute vent reefing system includes a plurality of attachment members disposed about a vent portion of a parachute canopy and a keeper routed between each attachment member of said plurality of attachment members. The keeper has a diameter less than the diameter of the vent portion and is configured to break at a preselected tensile threshold.

Abstract: Described herein are features for a high altitude lighter-than-air (LTA) system and associated methods. The LTA may include a super-pressure balloon (SPB) and/or a zero-pressure balloon (ZPB). The SPB may include two, three, four or more chambers. There may be more than one SPB. The SPB may use a compressor to provide a variable amount of ballast air by pumping in or expelling out ambient air. The zero-pressure balloon (ZPB) may be attached with the multi-chamber SPB. The ZPB may provide lift for the system. The SPB may include lifting gas and ballast air to provide both lifting and descent functions. The SPB may have an internal barrier separating a lift gas compartment from a variable ballast air compartment.

Abstract: A suspension line assembly for a parachute may comprise a first set of suspension lines bound together to form a first riser, and a second set of suspension lines bound together to form a second riser. A confluence may be formed by the first set of suspension line and the second set of suspension line. The confluence may comprise interior confluence suspension lines and exterior confluence suspension lines that alternate circumferentially along a perimeter of a parachute canopy.

Abstract: A multi-staged suspension line length parachute may include a suspension line having a primary length and a secondary length. The primary length may be deployable upon a first deployment of the multi-staged suspension line length parachute. The secondary length may be prevented from deployment until the primary length has fully deployed. An attenuator may attach a first portion of the secondary length to a second portion of the secondary length.

Abstract: A cinched parachute is disclosed. In various embodiments, a cinched parachute as disclosed herein includes a canopy comprising one or more sections of canopy material, and a device integrated with the canopy that controls dimensions of the canopy material. For example, in some embodiments the device may be used to control the size of an opening atop the parachute.

Abstract: A carrier system for carrying out interception maneuvers of a loadbearing paraglider which has a glider having a trailing edge for carrying out the maneuver with at least one interception line is fixed to said edge includes at least one carried load unit, which is connected to the carrier system via a first, short load carrier belt and a second, longer load carrier belt. A carried load connected to the carried load unit is carried by way of the first, short load carrier belt. The trailing edge is adjusted to carry out the maneuver by the gravitational force of the carried load, in that the first, short load carrier belt is separated and the carried load is carried by way of the longer, second load carrier belt.

Abstract: A coaxial double layer parachute includes an inner inflatable body and an outer canopy which are located along a central axis. Since the inner inflatable body is filled with helium to generate a first buoyance, the inner inflatable body can be obviously lifted to a certain height. When a payload connected to the inner inflatable body and the outer canopy with parachute cords falls, the ambient air flows will enter the inflation space through the annular air inlets to produce a second buoyance, which makes the outer canopy open completely. Hence, a secure descending task from even a very low height can be fulfilled if the coaxial double layer parachute can employed. Apparently, the coaxial double layer parachute can be mainly applied to fire and earthquake rescue actions in the cities when low height deployments, risk-free parachuting, and less complicated manual operation are required.

Abstract: A parachute includes a resistive body which is formed in a bag shape and receives air resistance, and two suspension lines, one end of each of which is connected to the resistive body and the other end of each of which can be connected to an object to be braked. The resistive body includes an opening through which air passes, a bottom part provided at an opposite side of the opening, and a side part provided extending toward a periphery of the opening from the bottom part while expanding. The side part includes a base part having an approximately constant height from the bottom part, and two tapered extension parts, each of which extends from the base part, while reducing a width thereof, to each of two ends as apexes located symmetrically with each other in the periphery of the opening.

Abstract: A system is described to control the flight path of a parafoil. The physical control mechanism is a series of actuators embedded within the parafoil canopy that open a series of meshed venting systems in the upper surface of the parafoil canopy. Opening and closing the meshed venting system changes the forces and moments acting on the parafoil canopy in a consistent manner such that it can be used for flight control. The meshed venting system includes an internal sealing flap and a mesh member.

Abstract: A ram air canopy includes a top skin, a bottom skin, a plurality of ribs between the top skin and the bottom skin forming a plurality of cells. A leading edge of a cell includes an opening to allow air to enter the cell. A glide vent is disposed in the top skin to allow air the exit the cell.

Abstract: Shape memory actuators are utilized to controllably modify the permeability of fabric and fabric based articles. The SMA actuator operates by changing the geometric permeability or by modifying the weave permeability of the fabric based article, or one or more portions thereof. The invention further provides for applications of the controllable permeability fabric, which include by way of example, various parachute, sail, and filter embodiments.

Abstract: Inserts for parachutes, for example modified cruciform parachutes, provide improved structural strength and reduced inflation times. An exemplary insert comprises a high-strength fabric coupled to center panels at a set of discrete points. The insert at least partially blocks airflow between the center panels, allowing the parachute canopy to inflate more rapidly. Via use of an insert, other components of a parachute, such as center panels, may be made of lighter, lower strength, and/or less expensive material without compromising the load-carrying capacity or reliability of the parachute.

Abstract: A system is described to control the flight path of a parafoil. The physical control mechanism is a series of actuators embedded within the parafoil canopy that open a series of holes via slits in the upper surface of the parafoil canopy. Opening and closing the holes changes the forces and moments acting on the parafoil canopy in a consistent manner such that it can be used for flight control. The embedded actuator is attached to a structural cell wall of the parafoil canopy. A control line from the actuator extends through a ring attached to the leading edge of the slit in the upper surface of the parafoil canopy and back down to the lower surface of the parafoil canopy along the opposite side non-structural cell wall.

Abstract: Apparatuses, systems, and methods for securing/releasing material are provided. For example, in one embodiment of the invention a releasable seam system that includes a first textile material. The first textile material includes a plurality of edges. On at least one of these edges is a first plurality of loops. The system also includes at least one at least one other textile material. Each textile material in the at least one other textile material has at least one edge with a plurality of loops thereon. The plurality of loops on the at least one other textile material and the first plurality of loops are paired to form opposing loop pairs. Thereafter, a locking chord is interwoven through the opposing loop pairs to temporarily secure the first textile material to the at least one other textile material.

Abstract: Inserts for parachutes, for example modified cruciform parachutes, provide improved structural strength and reduced inflation times. An exemplary insert comprises a high-strength fabric coupled to center panels at a set of discrete points. The insert at least partially blocks airflow between the center panels, allowing the parachute canopy to inflate more rapidly. Via use of an insert, other components of a parachute, such as center panels, may be made of lighter, lower strength, and/or less expensive material without compromising the load-carrying capacity or reliability of the parachute.

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: 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: The present invention provides poly(ureaurethane)s including a reaction product of components comprising: (a) at least one isocyanate functional ureaurethane prepolymer comprising the reaction product of: (1) at least one isocyanate functional urethane prepolymer comprising the reaction product of: (i) a first amount of at least one polyisocyanate; and (ii) a first amount of at least one branched polyol; and (2) water, to form an isocyanate functional ureaurethane prepolymer; and (b) a second amount of at least one polyisocyanate and a second amount of at least one branched polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A parachute comprising a channel extending from the bottom surface of the parachute to the top surface of the parachute, and configured to allow for the passage of a closing loop mounted to a parachute container.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A modified cruciform parachute is configured to provide improved aerodynamic efficiency and/or reduced construction expense. In an exemplary parachute, a shoulder panel is disposed between a center panel and a side panel to at least partially equalize load path lengths in the cruciform parachute. Components of the parachute may be two-dimensional in construction in order to reduce construction expense. Components of the parachute may also be modular and/or interchangeable. The cruciform parachute may be steerable and/or may be configured to glide via inclusion of venting means on the parachute canopy.

Abstract: A traction kite having a variable geometry leading edge that defines a high projected central propulsive region of increased surface area along the top portion of the kite, and lateral control regions of decreased surfaces area extending on opposite sides of the propulsive region. The leading edge thus defines a concave shape when viewed from the side while in flight. Providing a variable geometry leading edge maximizes propulsive forces due to increased surface area, while enhancing control and turning performance by minimizing the surface area of the control regions, namely those generally vertically disposed regions that begin at the tips and end at the propulsive region.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: Polymerizable liquid compositions of the polyurethane type, consisting of two components (A) and (B), wherein component (A) contains at least one cyclo-aliphatic diisocyanate monomer or a mixture of one cyclo-aliphatic diisocyanate monomer and a pre-polymer obtained by reaction, in the presence of an acid phosphate ester catalyst, between said cyclo-aliphatic diisocyanate monomer and one or more polyols having two or more hydroxy 1 groups per molecule and a molecular weight ranging from 50 to 2,000 g/mole; the second component (B) contains one or more polyols having a molecular weight ranging from 50 to 2,000 g/mole and a functionality between 2 and 5; in the absence of polyalkoxylated tertiary diamines and organometallic catalysts, said components (A) and (B) being present in a weight ratio which varies from 1:1 to 2:1 and the process for the production of organic glass starting from polymerizable liquid compositions of the polyurethane type.

Abstract: The invention relates to an aerodynamic wing, including an upper deck extending in operation in a longitudinal direction and in a transversal direction; wherein the upper deck is shaped and arranged to produce a vertical lifting force which is oriented perpendicular to the longitudinal and the transversal direction when the aerodynamic wing is exposed to a wind flow in a direction oriented parallel to the longitudinal direction; wherein a plurality of ribs are connected to the upper deck, said ribs lying in a plane parallel to the direction of the vertical lifting force and the direction of the wind flow; the aerodynamic wing being coupled to a base platform arranged below the wing in service via a plurality of fastening lines, whereby the fastening lines are secured to the ribs of the wing, at least two fastening lines are secured to one rib at two line attachment points arranged at a distance from each other in the longitudinal direction; wherein the at least two line attachment points are connected to each

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: An inflatable kite has a continuous leading edge tube that is swept forward at its left and right wingtip ends so that bridle lines attaching the canopy to the user are forward of the center of effort of the kite.

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 traction kite having a variable geometry leading edge that defines a high projected central propulsive region of increased surface area along the top portion of the kite, and lateral control regions of decreased surfaces area extending on opposite sides of the propulsive region. The leading edge thus defines a concave shape when viewed from the side while in flight. Providing a variable geometry leading edge maximizes propulsive forces due to increased surface area, while enhancing control and turning performance by minimizing the surface area of the control regions, namely those generally vertically disposed regions that begin at the tips and end at the propulsive region.

Abstract: This invention relates to a composite comprising two polyurethane films, identical or different, that are connected to one another and between which a reinforcement mesh and at least one textile reinforcement thread oriented according to at least one predetermined stress line is inserted. The invention also relates to sails including such a composite.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) at least one polyisocyanate; (b) at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) at least one polyol having one or more bromine atoms, one or more phosphorus atoms or combinations thereof; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A concentric peripheral canopy parachute having a canopy system including a number of peripheral, stacked, concentric, canopies, each superior canopy centered and spaced above the inferior canopy and having its skirt connected to the vent of the inferior canopy for generating an increased low pressure disturbance behind the canopy system for producing higher fluid drag.

Abstract: The present invention provides poly(ureaurethane)s including a reaction product of components comprising: (a) about 1 equivalent of at least one polyisocyanate; (b) about 0.1 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; (c) about 0.1 to about 0.9 equivalents of at least one aliphatic diol having 2 to 18 carbon atoms; and (d) at least one amine curing agent, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

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: 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: The mechanically opening parachute is a parachute that may be opened quickly at low altitudes, such as during an emergency exit from an office building, for example. The mechanically opening parachute includes a telescopic tube having opposed upper and lower ends. A harness adapted for releasably holding the user is secured to the lower end of the telescopic tube. The mechanically opening parachute operates similarly to a conventional umbrella, with the telescopic tube automatically opening upon actuation by the user, and with a conventional umbrella stretcher opening a plurality of ribs secured to a parachute canopy. Preferably, an annular skirt is fixed about the perimeter of the canopy. Suspension cords extend from the annular skirt to the lower end of the telescopic tube.

Abstract: A concentric peripheral canopy parachute having a canopy system including a number of peripheral, stacked, concentric, canopies, each superior canopy centered and spaced above the inferior canopy and having its skirt connected to the vent of the inferior canopy for generating an increased low pressure disturbance behind the canopy system for producing higher fluid drag.

Abstract: The mechanically opening emergency parachute is a parachute that may be opened quickly at low altitudes, such as during an emergency exit from an office building. The parachute includes a tube having opposed upper and lower ends, with an upper end of a suspension cord being secured to the lower end thereof. An upper annular runner is resiliently mounted on the tube. First ends of a plurality of ribs are pivotally attached to the upper end of the tube. An upper stretcher is mounted on the upper annular runner and includes a plurality of supports, with each support extending therefrom to one of the ribs. A lower stretcher is secured to the lower end of the suspension cord and includes a plurality of risers radially extending therefrom. A canopy is secured to the ribs, and a plurality of suspension lines extend between the risers and the canopy.

Abstract: A life parachute for ultra-lightweight aircrafts or for lightweight aircrafts includes a canopy of the parachute fitted with a pole opening and at least some wedge-shaped section of the canopy at the top half of its height is fitted with a discharge valve of air from the inside space of the canopy and a slider is installed at suspension parachute cords. The slider is formed in a ring fitted with a central opening surrounded with netting having, at least in peripheral edges, a local stiffener. Through openings are formed for the suspension parachute cords. The discharge valves are in the width of the single wedge-shaped sections, overlapped with parachute material, with a bottom open end. The discharge valves of the air are formed either with loose vents or at the open end of the parachute material. The slider is, advantageously, in the form of a regular polygon composed of single tetrahedral parts of the netting which are connected to one another through the local stiffeners.

Abstract: A parachute comprising a channel extending from the bottom surface of the parachute to the top surface of the parachute, and configured to allow for the passage of a closing loop mounted to a parachute container.

Abstract: A hybrid parachute, method of deploying a parachute and method of landing a payload. The hybrid parachute utilizes a reefing system that provides for the initial deployment of a deceleration stage that is configured to withstand the stresses of high-speed and/or high altitude openings. The deceleration stage has operating characteristics similar to known high-speed parachutes. After sufficient deceleration has been achieved with the deceleration stage, reefings are released deploying one or more low-speed high drag stages of the device. The high drag stage(s) provide the landing characteristics of a low-speed parachute, including the possibility of controlled descent and landing.

Abstract: The wing (10) having a negative dihedron for towing a load comprises a flexible canopy (12) which is defined between two lateral ends (14A, 14B) which are connected to each other, at the front, by a leading edge and, at the rear, by a trailing. The wing (10) includes rear lines (40A, 40B) which are connected to the suspension members (30A, 30B) which are arranged at the lateral ends (14A, 14B) of the wing, and in that the auxiliary maintenance means of the propulsive central region (16) comprise at least a front line which is connected by one end to the propulsive central region adjacent to the leading edge and which is capable of being connected to the load at the other end.

Abstract: The gift of the solution of the life parachute for ultra-lightweight aircrafts or for lightweight aircrafts consists in that the canopy (1) of the parachute is fitted with the pole opening (4) at least some wedge-shaped section (3) of the canopy (1) are in the top half of its height fitted with a discharge valve (5) of the air situated in the inside space of the canopy (1) and a slider (9) is installed at suspension parachute cords (2). The slider (9) is formed in a ring fitted with a central opening (10) surrounded with netting (11) comprising at least in peripheral edges (23) of a local stiffener (12), wherein through openings (13) are formed for the suspension parachute cords (2). The dischrarge valves (5) are in the width of the single wedge-shaped sections (3) overlapped with parachute material (6) with a bottom open end (7). The discharge valves (5) of the air are formed either with loose vents (8) or the open end (7) of the parachute material (6).

Abstract: The wing (10) having a negative dihedron for towing a load comprises a flexible canopy (12) which is defined between two lateral ends (14A, 14B) which are connected to each other, at the front, by a leading edge (20) and, at the rear, by a trailing edge (22). The canopy (12) has, between those two lateral ends (14A, 14B), a propulsive central region (16) which is bordered at one side and the other by two control regions (18A, 18B). The wing comprises at least a member (30A, 30B) for suspending the load adjacent to each lateral end (14A, 14B) and auxiliary maintenance means (32) which are capable of flattening the propulsive central region (16) adjacent to the leading edge (20) during flight. The trailing edge (22) of the wing is generally concave.

Abstract: A parachute system having a parachute canopy having a skirt, and a plurality of gores spaced about the skirt. The plurality of gores is defined by first and second groups of gores. The parachute system includes a slider having a plurality of through-holes, a line loop attached to the slider, a first reefing line extending through the first group of gores and having a pair of ends attached to the line loop, and a second reefing line extending through the second group of gores and having a pair of ends attached to the line loop. A corresponding group of suspension lines passes through a corresponding through-hole in the slider. Each suspension line in each group of suspension lines is attached to a corresponding gore. A single reefing line cutter is engaged with the line loop and configured to cut the line loop after a predetermined amount of time has elapsed so as to release the reefing lines and allow the slider to slide down the suspension lines.