| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | Life parachute especially for ultra-lightweight aircrafts | US12010479 | 2008-01-25 | US07997535B2 | 2011-08-16 | Milan Babovka |
| 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. The through openings are for the suspension parachute cords. | ||||||
| 2 | Life parachute especially for ultra-lightweight aircrafts | US12010479 | 2008-01-25 | US20080191098A1 | 2008-08-14 | Milan Babovka |
| 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). The slider (9) is, to advantage, in the form of a regular polygon composed of single tetrahedral parts (17) of the netting (11) which are connected one another through the local stiffeners (12) wherein the through openings (13) are for the suspension parachute cords (2). | ||||||
| 3 | Parachute and hang glider safety device | US505937 | 1983-06-20 | US4562981A | 1986-01-07 | David S. Smith; Geoffrey A. Smith |
| A parachute assembly includes a canopy, a harness connected to the canopy by lines, the canopy having an apex and a basal perimeter. Envelopes in the canopy defined by a plurality of generally triangular inflatable gussets extend from adjacent the apex to adjacent the basal perimeter and taper outwardly towards the basal perimeter. The assembly includes a source of pressurized gas and flexible conduits connecting the gas source to the gussets. One or more valves for releasing the gas from the source through the conduits to the inflatable envelopes and manually operable valves to release the pressurized gas into the conduits and envelopes to inflate the gussets. | ||||||
| 4 | PLANEUR DE PENTE | EP02701147.7 | 2002-03-12 | EP1399363A1 | 2004-03-24 | DE KALBERMATTEN, Laurent |
| The invention relates to a hang glider comprising a wing (1), having a lower surface (2) and an upper surface (3), and walls (5) which are provided with openings (6) and which form wing sections. Rigid or semi-rigid bars and tubes (4) are mounted in the wing (1). The wing (1) is inflated, in operating position, by turbines (8) which are installed in the air inlets (7). A pilot (9) is positioned in a harness (10) which is connected to the tubes (4) by straps (11). The pilot can steer the hang glider by moving his/her body weight or by using the controls. | ||||||
| 5 | HANG GLIDER CONTROL DEVICE | US15722088 | 2017-10-02 | US20180093767A1 | 2018-04-05 | Burton James Fenison |
| A hang glider control device may include a cross bar having a first end, a second end, a central region, a first central arm, and a second central arm. The first central arm and the second central arm may be coupled opposingly to the central region. The first end may be formed by a portion of the first central arm distal to the central region, and the second end may be formed by a portion of the second central arm distal to the central region. The first end of the cross bar may be configured to couple the cross bar to the first upright above the base tube, and the second end of the cross bar may be configured to couple the cross bar to the second upright above the base tube so that the crossbar may be generally parallel to the base tube. | ||||||
| 6 | Method and apparatus for deploying a wing | US548771 | 1995-10-26 | US5884863A | 1999-03-23 | Jeffrey A. Fisher; Edward V. Miller; Dennis Van Dam |
| The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air. | ||||||
| 7 | Method and apparatus for landing a wing | US552160 | 1995-11-02 | US5878979A | 1999-03-09 | Jeffrey A. Fisher; Edward V. Miller; Dennis Van Dam |
| The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section and a lower section. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded closed, extracted from an aircraft, deployed in the air and landed with the aid of parachutes. | ||||||
| 8 | Safety apparatus for hang glider | US91403 | 1987-08-31 | US4776530A | 1988-10-11 | Stephen M. Mansfield |
| A safety apparatus for a hang glider that indicates any failure of a pilot to properly hook in a flight harness. The apparatus includes a circuit having a power source, such as a dry cell battery, connected to an alarm through a harness hook in sensor. When the pilot fails to properly hook in the harness, an alarm sounds. The circuit also includes an on/off switch that activates the circuit only in direct response to erection of the hang glider. Thus, the circuit is deactivated when the hang glider is disassembled for transport to or from a launch site and during storage. Consequently, annoying alarm soundings are avoided and battery life is increased. In addition, the circuit includes a deactivation switch that prevents the alarm from sounding when the hang glider is resting on the ground. Finally, a test switch is provided to allow manual testing to confirm proper activation and operation of the circuit. | ||||||
| 9 | Powerchute apparatus | US10669126 | 2003-09-23 | US20050230521A1 | 2005-10-20 | James Medsker; Daniel Richardson; Matt Dautle; Robert Taylor; Shawn Brueshaber; Benjamin Marvin; John Shimer |
| A powerchute comprising a body having an outer shell and an inner reinforcement. The outer shell including a nose, opposing side panels, a roll bar and a powerplant shelf, wherein a plurality of the nose, opposing side panels, roll bar and powerplant shelf define a cavity including a cabin. The outer shell and the inner reinforcement comprise a carbon fiber composite which is of sufficient strength to maintain rigidity and structural integrity without the use of metal support members. | ||||||
| 10 | Safety device for hang glider | US826741 | 1986-02-06 | US4688022A | 1987-08-18 | John R. Gray |
| A safety device to warn the pilot of a hang glider if take-off is attempted without the glider hook-up strap being connected to the pilot's harness includes two sensors arranged in series with an alarm. One of the sensors is arranged to close a circuit when the glider is positioned in a take-off attitude and the other sensor closes a circuit when the free end of the hook-up strap is disconnected from the pilot's harness. The alarm is activated when both circuits are closed. | ||||||
| 11 | Ballistic recovery system | US541787 | 1983-10-13 | US4607814A | 1986-08-26 | Boris Popov |
| A dual system for ballistic deployment of a parachute (40) caused by explosion of a powder charge (54) to propel a projectile (52) away from an air vehicle, pulling the parachute (40) away from the air vehicle and allowing the parachute to inflate free of the air vehicle. The powder charge (54) is exploded alternatively by the pilot pulling a pull handle (12) to send an igniting current to fire cap (55), or by the pilot pulling handle (70) to activate a spring driven firing pin (80) to fire cap (82); the firing of cap (55) or the firing of cap (82) will explode the powder charge (54). | ||||||
| 12 | Aircraft recovery chute | US390513 | 1982-06-21 | US4445654A | 1984-05-01 | James W. Handbury; Dana Handbury |
| An ultralight aircraft and/or pilot recovery system includes a parachute having a canopy connected by means of a plurality of shroud lines to a first elongated cable having a length to position the parachute clear of the aircraft engine and propeller with a second cable for connecting the parachute to the frame of the aircraft and including a harness worn by the pilot which includes a pouch for containing the canopy folded within an inner pouch to permit the pilot to grasp and toss the chute clear of the aircraft for deployment for recovery of the aircraft. An alternate embodiment provides for connecting the parachute to the harness worn by the pilot and securing the harness to the aircraft to thereby give the pilot the option to recover the aircraft or cut loose from the aircraft for pilot recovery only. | ||||||
| 13 | Electronic hang glider hook-up warning system | US953097 | 1978-10-19 | US4272039A | 1981-06-09 | Thomas C. Hollingsworth |
| An electronic warning system that alerts a pilot of light-weight foot-launched aircraft that the required pre-launch physical hook-up of pilot-to-aircraft has not been accomplished. | ||||||
| 14 | Attitude recovery device for hang glider | US24360 | 1979-03-27 | US4247060A | 1981-01-27 | George J. Cory |
| A hang glider attitude recovery device that may be rapidly deployed with a minimum of pilot action comprises a drag element having an effective point of attachment rigidly spaced above the point from which the pilot is suspended, and a mechanism for activating the drag element at a point clear of upper structural members. The separation between the attachment point and suspension point provides a lever arm which is responsible for the operation of the device. When the hang glider is in a position where the lever arm is inclined from the vertical (hang glider out of attitude), activation of the drag element provides an upward force at the upper end of the lever arm, which force produces a moment that tends to bring the suspension point back into a position under the attachment point. In the preferred embodiment, the drag element comprises a small parachute stowed within the tubular king post. The activation mechanism comprises an expulsion device such as a spring loaded position within the king post and a deployment device such as a parachute opening spring. The parachute is attached to the hang glider by a line extending down to the bottom of the king post, but since the line is laterally confined by the small opening at the top of the king post, the effective point of attachment is at the top of the king post. | ||||||
| 15 | Method and apparatus for deploying a wing | EP96307588.2 | 1996-10-18 | EP0770545B1 | 2004-12-29 | Fisher, Jeffrey A.; Miller, Edward V.; Van Dam, Dennis |
| 16 | Method and apparatus for landing a wing | EP96307587.4 | 1996-10-18 | EP0771727A1 | 1997-05-07 | Fisher, Jeffrey A.; Van Dam, Dennis; Miller, Edward V. |
A deployable wing (10) comprising a fabric sail (12), and is provided with a parachute deployment system (40) which can be deployed to land the wing. |
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| 17 | Method and apparatus for deploying a wing | EP96307588.2 | 1996-10-18 | EP0770545A1 | 1997-05-02 | Fisher, Jeffrey A.; Miller, Edward V.; Van Dam, Dennis |
A deployable wing comprises an internal structure having diverging leading edge spars attached to a keel spar (24) and cross spars (22a,22b) to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail (12) having an upper section, a lower section, and fabric ribs (11) disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake (17) at the nose stagnation point. The wing can be folded, extracted from an aircraft and deployed in the air. A payload pod (50) is attached to the keel via a mounting member (42). A detachable extension (45) is removably mounted on said mounting member (42). |
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| 18 | Pneumatic launching device for rescue parachutes for aerodines and aerostats | EP89830150.2 | 1989-04-05 | EP0336910A1 | 1989-10-11 | Comelli, Giordano |
The invention regards a launching device for rescue parachutes for small aircraft capable of launching the parachute with adequate force for correct functioning. The power is supplied by a compressed gas stored in a gas cylinder, which is freed by a rapid release valve: the shove which the parachute receives, throws it into the air, swelling it up and this, once opened, remains connected to the aircraft by a rope. The parachute is held inside a container made up of a base which is fixed to the mobile parts of the device and of a lid which is disposed of during the release. The lid is held fast against the base by set elements whose breakage is caused by the expansion of the gas. The functioning of the device is operated by the traction of a handle which by means of a cable contained inside a sheath, frees a spring: this will push the shutter of the rapid release valve, thus letting out the pressure energy of the gas. A safety-catch is situated on the device, which joins the mobile parts to the fixed parts, thus blocking them: this safety-catch blocks the device even if this is accidently operated. The gas charge can be checked periodically by means of a gauge and the parachute easily inspected. |
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| 19 | Dispositif d'amortissement de chocs pour sellette de parapente | EP10153398.2 | 2010-02-12 | EP2221090A1 | 2010-08-25 | Bouilloux, Pierre |
Sellette (2) de parapente, comportant un dispositif d'amortissement de chocs (1) constitué par une enveloppe souple disposée sous l'assise de la sellette, caractérisé en ce que le dispositif d'amortissement est destiné à être gonflée par le flux d'air crée par le déplacement de la sellette, ladite enveloppe souple comprenant une paroi inférieure (15) qui comprend une ouverture d'entrée d'air (12) permettant l'entrée du flux d'air à l'intérieur de l'enveloppe, tandis qu'afin de faciliter l'entrée d'air et de maintenir l'enveloppe sous sa forme gonflée, il est prévu des moyens pour maintenir ladite enveloppe sensiblement dans la forme qu'elle a en position gonflée, ces moyens étant constitués par un organe raidisseur (14) constitué par une tige souple, rigide voir semi-rigide mise en forme, ledit étrier ayant la forme de U ouvert vers l'avant (A) associé à la paroi inférieure (15) de l'enveloppe souple.
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| 20 | Method and apparatus for landing a wing | EP96307587.4 | 1996-10-18 | EP0771727B1 | 2004-01-07 | Fisher, Jeffrey A.; Van Dam, Dennis; Miller, Edward V. |
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