US3508727A - Apparatus for saving of the passengers of a crash landing,ditching or diving and in danger to be diving,respectively,airplane - Google Patents

Apparatus for saving of the passengers of a crash landing,ditching or diving and in danger to be diving,respectively,airplane Download PDF

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US3508727A
US3508727A US709560A US3508727DA US3508727A US 3508727 A US3508727 A US 3508727A US 709560 A US709560 A US 709560A US 3508727D A US3508727D A US 3508727DA US 3508727 A US3508727 A US 3508727A
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saving
airplane
saving cell
passengers
diving
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Peter Willems
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B64D25/08—Ejecting or escaping means
    • B64D25/12—Ejectable capsules
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes

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  • the present invention relates to a method of and apparatus for saving of passengers of a crash-landing, ditching or diving and in danger to be diving, respectively, airplane.
  • the inventor of the present invention who is a pilot himself and the victim of several divings and crash landings, has occupied himself for years to find means and ways, in order to control this catastrophic development which increases in volume from year to year.
  • the air pressure In case of an emergency ditching, the air pressure must be controlled such, that no water can penetrate the inside of the device.
  • the present invention is further also concerned with the prevention of fright or shock which, knowingly, lead to a sudden or later death.
  • the present invention also includes the possibility of performing all measures which are conventional with an airplane and permitting the emission of any kind of of signals or SOS calls, release of optical signals as light beacons, rockets and the like, and also acoustical supersonic and other known emergency calls.
  • a closed capsule (saving cell) receiving the passenger or passengers of the airplane is spontaneously released from the portion of the airplane carrying the capsule by operation of at least one releasing device.
  • connections having a sufliciently high safety coefiicient which connections are releasable suddenly and simultaneously by manual operation of at least one of the releasing members.
  • FIGURE 1 is a. perspective side view of the device for performing the saving method in accordance with the present invention required for the performance of the saving method;
  • FIG. 2 is a fragmentary section through the airplane, as set forth in FIG. 1, the section taken being disposed just in front of the wings;
  • FIG. 3 is a side elevation of a saving cell of the airplane as set forth in FIG. 1, released from the parts of the airplane carrying the saving cell and being lowered to the ground on parachutes;
  • FIG. 4 is a fragmentary view showing a plurality of superposed parachutes
  • FIG. 5 is a sectional view for sudden and simultaneous release of the connections between the saving cell and the parts of the airplane carrying the latter;
  • FIG. 6 is a variation of the device indicated in FIG. 5;
  • FIG. 7 is a circuit diagram of a control circuit and a working circuit for electro-mechanical release of the connections
  • FIG. 8 is a longitudinal section through a parachute designed as a balloon
  • FIG. 9 is a perspective view of a second embodiment of the device for performing the saving method of the present invention.
  • FIG. 10 is a section through a plane shown in FIG. 9 immediately in front of the wings;
  • FIG. 11 is an axial section of one embodiment of the safety coupling for a tube conduit
  • FIG. 12 is a side elevation of a saving cell of the airplane according to FIG. 9, released from the carrying part of the airplane on two parachutes and a balloon;
  • FIG. 13 is a section of an embodiment of a keel with falling shaft and sword keel
  • FIG. 14 is a longitudinal section of another embodiment of the showing in FIG. 13.
  • FIG. 15 is a schematic showing of an electric circuit diagram together with some elements operated thereby.
  • FIG. 1 which is shown as a monoplane, has on the wing roots of the supporting wings I and at the end of the fuselage 2 a plurality of connections 3 built with a sufliciently high safety coefficient, which connections 3 normally connect rigidly the fuselage 2 with the remaining parts of the airplane.
  • the connections 3 are suddenly and simultaneously releasable, so that the portion of the airplane comprising the cockpit 2a, the passenger space 2b and the luggage space 2c, which part of the airplane constitutes here the saving cell, falls out downwardly.
  • the cross-section of the passenger and luggage space 2b and 2c is enlarged in this embodiment by a cover pail 20!, mounted on the upper side of the passenger space 2b, to form an egg-like cross-section.
  • a hollow space of sickel-shaped cross-section in which, divided over the length of the fuselage 2, two carefully folded parachutes 4 are provided.
  • the latter are secured by means of elastic carrying cords 5 to the saving cell and by means of a releasing cord 6 of corresponding strength secured to the cover pail 2d.
  • the cover pail 2d is, as will be Set forth below, secured to the upper side of the passenger space 2b such, that it is imultaneously therewith or directly after the release of the connections 3 lifted by the travel wind and, thereby, folds out the parachutes 4, which then open and as shown in FIG. 3, brings the saving cell with the passengers safely to the groundandwater surface, respectively.
  • the suspension of the saving cell on the elastic carrying cords 5 is statically designed such, that the normal position of the passenger or passengers remains as much as possible unchanged.
  • the carrying cords as indicated at the right parachute in FIG. 3 by pointed lines, is spread out downwardly and secured at different points on the saving cell. It would, however, be also possible, as indicated at the left parachute in FIG. 3 by pointed lines, to provide particular stabilizing lines 40 secured to the carrying ropes 5.
  • the securing of the cover pail 2d can, for instance, take place in accordance with the same system as the connection of the saving cell with the airplane fuselage.
  • Each of the parachutes 4 carrie in its center advantageously an upwardly extending, vertical funnel 7 which exerts the function of a control nozzle.
  • the elastic carrying ropes 5 are prefer ably formed as respective diagonally woven and knitted hoses of heavily carrying spinnings (for instance, nylon, rayon, polyester or the like) which surround a core of highly elastic rubber cord.
  • heavily carrying spinnings for instance, nylon, rayon, polyester or the like
  • still additional expansion means are provided, for instance, in form of strong springs (if necessary, with inserted rubber lines), or in form of hydraulic and pneumatic, respectively, damping members responding to pull.
  • suitable corresponding protecting device are provided, for instance, winding drums subjected to pull.
  • a towing line 5b from a small parachute 4a of noninflammable or difficult inflammable material, which carries one or a plurality of lighting sets 39 ignited by a pull ignition, through which the optical location of the safety cell by other vehicles in the air, on the ground and on the sea, particularly at night, is made possible and is simplified, respectively.
  • connections 3 already mentioned before can be lockings of any type for instance, in form of bolts or hooks, which are mounted in forked members and which are removable or which can be run out or swing out mechanically, pneumatically, hydraulically or electromagnetically.
  • the bolts can also be hollow bolts and may be filled with an explosion load, which can be electrically ignited for a sudden release of the connection.
  • an embodiment is disclosed with two connection such, that bolts and 11 are mounted in forked members 8 and 9, which bolts 10 and 11 are formed at one end as gear racks and can simultaneously run out by an electro-motorically driven pinion 12 from the forked members 8 and 9.
  • the structural material of the bolts 10 and 11 must be a very high rigid one, for instance, hard metal (as titan, wolframe or the like), in order to prevent a cut-in of edges into the surface of the bolts 10 and 11.
  • FIG. 6 of the drawings A second embodiment, in which more than two bolts 10a are simultaneously run out, is disclosed partly in FIG. 6 of the drawings.
  • screw spindles with one or a plurality of electromotorically driven spindle nuts can be used, whereby by means of synchronization of the motors driving the spindle nuts, by corresponding selection of the thread pitch and by mutual adjustment of the screw spindles, the data of the releasing process is variable within certain limits and is settable with greatest precision, for instance, of one hundredth of a second exact.
  • two or more motors are applied for the drive, so that upon inoperativeness of one motor, the release of the saving cell is assured.
  • FIG. 7 An embodiment of a control device for releasing of the previously mentioned connections 3 is shown in FIG. 7.
  • the circuit comprises a battery 13 (or a power net connection) to which battery 13 a pressure knob 14 is provided for the member leading the saving action (for instance, the flight captain), a pressure knob 15 for the pilot and a pressure knob 16 for the co-pilot, Which pressure knobs are disposed in series relative to each other.
  • this control circuit is disposed the device designed in forming of a switching relay 17 for starting of the electro-motor 18 driving the pinions 12 (FIGS. 5 and 6) running out the bolts 10 and 11 as well as under circumstances, additional parallel switched motors.
  • the motor circuit is switched to the circuit of the battery 13 (or the net) by means of the contact points 19 and 20 and 21, respectively. It could also, however, be fed by an independent current source.
  • an electro-magnetic or hydraulic device releasing the connections 3 can be provided, the control of which takes place by the control circuit with the pressure knobs 14, 15 and 16 and the switching relay 17.
  • the switching relay 17 is operated only then by the control current of the battery 14 (and of the net, respectively) when all three pressure knobs 14, 15 and 16 are simultaneously operated.
  • a device in operative connection with the control current circuit and the working current circuit, respectively, according to FIG. 7, or with the released wings I in operative connection, for instance, a pulling line the throw-off of the cover pail 2d is caused, which, for instance in accordance with the same system can be secured to the saving cell, as the latter to the parts of the airplane carrying the latter.
  • the cover pail 2d lifted upwardly by the travel wind tears off through the unfolding line 6 of the parachutes 4, whereupon the latter open up.
  • This system constitutes a simple example. It is to be understood, that the system can be extended to double, in case of simple airplanes, even to one person, or in large airplanes to a plurality of persons, whereby also one or a plurality of passengers can be called upon for the performance of the saving procedure.
  • the parachutes can be formed as balloons filled with a supporting gas.
  • a centrically arranged filling hose 23 is provided, which is made preferably rubberizing to gas-tight textile material made of natural or synthetic threads, for instance, parachute silk, and leads to one or a plurality of pressure gas bottles provided in the saving cell.
  • the filling hose can be increased by means of an inserted wire spiral. How the filling of the balloonlike parachutes takes place with the carrying gas will be explained below in connection with the description of the carrying balloon, the filling of which with the carrying gas takes place in the same manner.
  • the path of the carrying gas during the filling of the balloon-like parachute is indicated in dotted arrows in FIG. 8, while the full arrows show how a part of air accumulated below the parachute reaches by means of openings 24 into the shaft 7 operating as a nozzle.
  • a still stronger upward force than the just described balloon-like parachutes are produced by actual balloons, as they are described in combination with the following embodiment of an overseas airplane in accordance with the present invention.
  • the airplane disclosed in FIG. 9 comprises, as the crosssection according to FIG. 10 indicates, two parts, namely a hollow carrying body 25 open at the bottom and consisting of a longitudinal carrier (back) with wings, fuel tanks and the motor carrying portion and railroad car-like saving cell 26 and inserted into the carrying body 25 from below and suspended in the latter by means of the connections 3.
  • the saving cell 26 is in known manner designed as an over-pressure cabin and, according to the present invention, its lower side is equipped with a keel 27.
  • the space surrounded by the saving cell 26 is divided such that the passenger space is disposed on the top, in the center is the luggage space and below is a keel space receiving the pressure gas bottles 28.
  • the latter is disposed in the space surrounded by the cover of the saving cell 26 and the cover of the carrying body 25 and having sickle-shaped cross-section.
  • In the same space are disposed also carefully folded parachutes 4, which in a manner already described above are secured by means of elastic carrying cords on the saving cell and by means of unfolding cords (for tearing open the parachutes) on the cover of the carrying body 25.
  • Over the entire length of the saving cell 26 can, depending upon its weight, be provided a plurality of folded parachutes 4 and/or folded balloons 31.
  • the balloons can be formed for the obtaining of a lift volume as body expanding upwardly with circular, oval, rectangular or square crosssection, depending upon the formation of the space for receiving the same, whereby the balloon covers prior to the filling are folded in similar manner as a lampion prior to tearing the same apart.
  • the wire spiral which fortifies the filling hose, can favor in such balloon the maintenance of the form, which balloon extends perpendicularly upwardly over the ejected saving cell. For this reason, preferably it is inserted with the diameter of the balloon cover between a double wall.
  • the cockpit projecting upwardly through an opening in the vicinity of the bend of the carrying body 25 makes possible for the flight captain during the floatig of the saving cell after an emergency ditching for a good view and even then when the largest part of the saving cell is disposed below the water surface.
  • the surface available for the flight captain and the pilot for the view from the cockpit can, without of course interference with the safety of the control of the aircraft be divided by spokes into individual smaller surfaces or slots.
  • the saving cell 26 is equipped in the manner of a U-boat with all necessary devices and auxiliary means, including telescope, so that it is in the position to perform a longer voyage, if necessary even under water.
  • the cover of the cockpit is designed such, that it can be opened and be ejected so that the flight captain during setting of the saving cell can abandon the same as the first one and take, if necessary measures, outside of the latter.
  • the saving cell In order to avoid that during the non-sealing of the saving cell standing under pressure above atmospheric pressure biological damages of the occupants occur, for instance, the bursting of the lungs or other circulatory vessels, the saving cell must be equipped with safety devices known from U-boats for obtaining an eventual pressure equalization.
  • the members of the crew for instance, the captain, the pilot and the co-pilot (which can be substituted for instance also by the chief steward) which are charged with the performance of the safety measures, must be clear who are charged with the performance of the safety measures, about the question whether the safety measures have to be instituted immediately or not. If this question is answered positively unanimous, the chief steward causes that in the passenger space a lighted plate lights up with the inscription SOS or a similar writing pointing to the danger situation.
  • the captain describes over the loudspeaker system at first in a few short, precise, easily understood and calming words the basic process of the not bound, rather in view of the position of the aircraft intended and completely controlled slow descent to the ground surface and water surface, respectively, and reminds the passengers in short words to the individual points of an instruction sheet (safety measures in emergency).
  • This instruction sheet printed on a very tearfast paper in a wide red frame and printed in easily legible script in several languages, is pasted to the menu at the back of the seat disposed in front of the passenger.
  • This complex measures constitutes one of the most important in the total saving action in accordance with the present invention and can be assigned only to such crew members for performance, which are particularly suitable therefor psychologically.
  • the captain pushes the button 14 coordinated to him (FIG. 7).
  • the electro-magnets 15a and 16a receive current from the battery 13 (or the net) and pull the anchors 15b and 161) formed as locking members.
  • the anchors 15b and 16b release the spring covers and of the housings 15d and 16d, so that now the push buttons 15 and 16, specially spaced apart from each other and disposed in the housings 15d and 16d and assigned to the pilot and the co-pilot are accessible.
  • the switching relay 17 responds and closes the Working circuit of the electro-motor 18. The latter starts and releases, for instance, in the manner shown in FIG. 5, the connections 3 (FIG.
  • the tube conduit is interrupted, so that there the two tubes 32 and 33 abut each other obtusely with their end faces.
  • a preferably synthetic, fuel-resistant (non-soluble), not glueable and not after-polymerizable high pressure hose 34 is slit.
  • peripheral ribs 35 are provided within the range of both ends, which peripheral ribs 35 snap into corresponding peripheral grooves of the tubes 32 and 33, if the latter are pressed together by hand or by means of a device after the introduction into the high pressure hose 34.
  • the tearing coupling is measured corresponding to its tear and shear resistance such, that it yields upon removal of the hose 34 from the tube ends by the widening of the hose forced thereon upon exit from the grooves or in an extreme case, the ribs 35 are torn 011', if necessary, on the inner hose walls.
  • the tube ends can be equipped outwardly or the hoses at the inner wall with waves.
  • the tubes are secured on a base during their mounting when their ends abut each other exactly, in this joint position by corresponding resistance members or tube clamps, as long as the operation runs without any disturbance.
  • the pipe clamp is expanded axially over the general conventional and the inner edge is gripped at an acute angle conically at the ends of the pipe clamps or members.
  • a separating of the two tube ends is prevented in normal operation basically already by proper roughness of the members as well as, if necessary, of the two tube ends, or also the base, which can be, for instance, a lead or the wall of the body.
  • the safety couplings include an automatic losing valve provided at the tube and coordinated to the saving cell 26, which closing valve closes, after the separation of the connection, the tube end remaining on the saving cell 26 with safety automatically, for instance, against the surrounding atmosphere of, above all, against the space surrounding the tube and with a possible pressure difference, thus also against pressure below atmospheric pressure, so that the pressure prevailing inside (under circumstances also a pressure below atmospheric pressure prevailing within an apparatus) cannot be balanced.
  • An advantageous and safety solution of the problem of such double function is a valve body provided within two springs effective with corresponding tension, which valve body has the shape of a ball or any other suitable form and depending upon requirements, closes towards the one or the other side.
  • an absolutely oxidation-free metal and metal alloy respectively, as for instance Cr-Nisteel or pure nickel, and as material for the seat disposed in each end position of both sides of the valve body in the form of a non-variable ring, preferably a like-wise fuel-resistant (not soluble), not glueable and not after-polymerizable synthetic material.
  • the saving cell 26 is equipped with a fully automatically operable emergency device, to which the feeding and control conduits, can be switched, under circumstances, automatically, if the latter are separated.
  • valves 29 are quickly opened on the pressure gas bottles by means of a working circuit switched by a control current circuit according to FIG. 7.
  • This opening can, however, also forcibly be performed by other means, for instance by tear strings secured on the one hand on the carrying body 25 and on the other hand on a valve 29 each.
  • the balloon cover 31 By the carrying gas flowing from the pressure gas bottles 28 over the valves 29 and the gas tube 30 into the balloon cover 31, the latter is filled within a few seconds and by the lift created thereby, the falling speed of the saving cell 26 removed from the aircraft, already reduced by the parachutes 4, is still further reduced, so that the saving cell 26 carrying the passengers eventually arrives smoothly on the ground and, in case the flight disturbance has taken place over the sea, arrives on the water surface (see FIG. 12).
  • a plurality of balloons 31 can be provided operating on the saving cell 26. The number and distribution of the balloons 31 and/ or of the parachutes 4 depends upon the size and the weight of the saving cell 26.
  • signals In case of an emergency landing over the sea, passengers and crew cannot abandon the saving cell 26, if not by accident a vessel or ship in the immediate neighborhood. For this reason, signals must be given at first, which call the attention of air and water vehicles disposed in the neighborhood of the place of the saving cell 26 to the latter driving in water. Simultaneously, signals, in particular light signals, indicate the location of the saving cell 26. In addition to light signals SOS, which can be beamed out by means of a normal aircraft signal device or of a sender fed from the emergency current device, also optical signals can be given. For this purpose, the saving cell 26 has a telescope tube movable upwardly for firing of magnesium light balls. Also, an acetylene cannon can be provided, with the help of which water-tight CA-carbide filled cartridges can be shot.
  • acoustical signals can be given, for instance, by means of a siren, Or in fog, by means of a fog horn.
  • a bearing device disposed in the saving cell 26, and in particular in the cockpit which bearing device is, if necessary, fed with current by means of an emergency current device, a ship passing at larger or smaller distance or a sending station located at the coast in the vicinity and at an isle, respectively, is a ship screw operable by an electro-motor is moved out from the saving cell 26 and is put into operation.
  • the electro-motor is likewise driven from the emergency current device.
  • the ship screw 42 under circumstances, with electro-motor, is swingably arranged or a particular control radar is provided which can be operated from the cockpit. It would, however, also be possible to provide two ship screws, disposed adjacent each other, whereby the number of revolutions of each screw is endlessly controllable independently from the number of revolutions of the other screw. In this manner by setting of different numbers of revolutions, the saving cell 26 can be controlled without resorting to a rudder.
  • each of the ship screws is surrounded by a frame on which cutting edges cooperate in a shearing manner with the surrounding screw in order to cut through the growths (tangs, algae, etc.) winding about the screw.
  • ship screws also equivalent devices can be used, for instance, tube pumps (Venturi nozzles).
  • the saving cell 26 contains, furthermore, an oxygen bottle, or, advantageously, two thereof, in order to secure the oxygen necessary for the breathing of the passengers after the release at greater heights with the maintenance of the pressure above atmospheric pressure inside of the saving cell 26.
  • an O -producing device arranged for this special case, which even beyond the time of emptying of the oxygen bottles delivers the oxygen required for the breathing.
  • a sufiicient storage of food in form of cans for several days in addition, a drink water storage, as well as medicaments, particularly tablets against seasickness (which are suitably glued to the menu) furthermore, fortifying vitamins, tracer elements, calming and geriatric means, particularly the latter for older passengers.
  • a drink water storage as well as medicaments, particularly tablets against seasickness (which are suitably glued to the menu) furthermore, fortifying vitamins, tracer elements, calming and geriatric means, particularly the latter for older passengers.
  • a sliding weight can be provided in the keel space, which sliding weight can be displaced parallel to the longitudinal axis of the saving cell 26 by remote control from the cockpit or by some automatic means.
  • the already mentioned oxygen bottle or bottles or another steel bottle can be designed and serve as displaceable sliding weight. Since in case of a heavier sea, the keel 27 of the saving cell 26 does not suffice for the stabilization of the position of the latter in the water, it is suitable, as indicated in FIG. 13 quite clearly, to arrange a vertical falling shaft 36 in the keel space in which the pressure gas bottles 28 are received, in which falling shaft 36 at least a keel sword 37 is mounted and movable vertically downwardly.
  • This sword 37 could, however, be swingably mounted, also in accordance with FIG. 14, within the range of a lower edge by a link 38 horizontally projecting through the falling shaft 36, so that after the swinging in the direction of the arrow y, it assumes the position indicated in dotted lines in the direction of the arrow y and in which the swinging movement of the saving cell 26 is extensively dampened and suppressed, respectively.
  • the saving cell can receive only a few passenger seats, whereby, corresponding with the number of passengers, under circumstances, a plurality of saving cells (also such for the crew) must be provided.
  • Such smaller savings cells can, of course, be equipped only with the most necessary. They are used, therefore, only for medium size or smaller air craft, which do not fly transcontinental lanes.
  • the releasing device is put at first into function readiness and the release itself is performed by a pressure button pushed by the captain.
  • the function of the remaining members of the saving crew is limited thus to introductory measures, while the function of the head of the saving crew, who was already engaged with the starting measures, includes the actual release of the saving cell such that the head by the last commando, namely by operation of a corresponding device, gives this last step for release of the saving cell.
  • the member of the crew functioning as the head of the safety crew has the possibility, prior to the issue of the last commando, as much as the danger still permits, to.
  • the lit warning lamp 57 shows the captain that the saving cell 26 is ready for ejection from the carrying body 25 of the aircraft.
  • the captain under circumstances, by a control walk, has convinced himself personally that all necessary measures have been taken care of properly, he hits with a small hammer a disc 59 of the box 58 made of glass or transparent synthetic material and operates the switch 61, so that the latter connects the contact points 54- and 56 together.
  • the current flows in the following manner:
  • the switching relay 17 passed by electric current pulls up the anchor and closes thereby the two contact pairs 43 and 44.
  • the electric motor 18 is fed with current in the following manner:
  • the device reducing the free fall speed of the saving cell 2 6 can also consist of a rocket or a set of rockets, which after the ignition exercises a return pushing force directed oppositely to the falling movement of the saving cell.
  • said saving cell including a cockpit, a passenger cabin and a baggage compartment,
  • At least one emergency current source disposed in said saving cell
  • said circuit means comprising a current source and a plurality of in series disposed manually operated switching means for closing said circuit means.
  • said saving cell comprises a hollow body suspended in the fuselage of said airplane,
  • said saving cell complementing said open area of said airplane fuselage.
  • the apparatus as set forth in claim 1, which includes:
  • conduit means leading from said pressure gas bottle to an upwardly directed gas tube
  • said gas tube is connected by means of a filling hose with said ballon.
  • said fast closing valves are operatively connected with automatically operating means
  • said driving means for movement in water comprises at least one ship screw.
  • said driving means for movement in water comprises at least one tubular pump.
  • said circuit means includes a single manually operated means for controlling and rendering operative and circuit means.
US709560A 1967-08-08 1968-03-01 Apparatus for saving of the passengers of a crash landing,ditching or diving and in danger to be diving,respectively,airplane Expired - Lifetime US3508727A (en)

Applications Claiming Priority (1)

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CH1124867A CH497315A (de) 1967-08-08 1967-08-08 Einrichtung zur Rettung der Insassen eines notlandenden, notwassernden oder abstürzenden bzw. absturzgefährdeten Flugzeuges

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US3508727A true US3508727A (en) 1970-04-28

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US709560A Expired - Lifetime US3508727A (en) 1967-08-08 1968-03-01 Apparatus for saving of the passengers of a crash landing,ditching or diving and in danger to be diving,respectively,airplane

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US (1) US3508727A (de)
CH (1) CH497315A (de)
DE (2) DE1992863U (de)
FR (1) FR1603439A (de)
GB (1) GB1236283A (de)
NL (1) NL6811183A (de)

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US3622108A (en) * 1970-02-27 1971-11-23 George A Mathewson Safety device for disabled airplanes
JPS52170500U (de) * 1976-06-18 1977-12-24
WO1990013479A1 (en) * 1989-05-04 1990-11-15 Mashinostroitelny Zavod Im P.O.Sukhogo Aircraft
US5568903A (en) * 1995-01-18 1996-10-29 Pena; Jesus S. Plane saddle for a safety airplane
US5673875A (en) * 1995-01-30 1997-10-07 Martin; Joseph R. Stabilizing inflight parachute system
US5921504A (en) * 1997-08-17 1999-07-13 Elizondo; Joey P. Aircraft passenger extraction system
US6382563B1 (en) * 1999-12-20 2002-05-07 Chui-Wen Chiu Aircraft with severable body and independent passenger cabins
US6595466B2 (en) 2000-11-28 2003-07-22 Airbus France Boarding device for aircraft and flying wings equipped with such a device
US6761334B1 (en) * 2003-05-28 2004-07-13 Costica Nutu Aircraft passenger safety module
US7234667B1 (en) * 2003-12-11 2007-06-26 Talmage Jr Robert N Modular aerospace plane
US8643850B1 (en) * 2010-03-02 2014-02-04 Richard L. Hartman Automated system for load acquisition and engagement
US20150203200A1 (en) * 2011-12-21 2015-07-23 George Bye Unmanned Aerial Systems
US20180155038A1 (en) * 2016-12-02 2018-06-07 Joseph Miller Aircraft Parachute System
US10005559B2 (en) * 2015-09-01 2018-06-26 Guoxin WEI Crash-resistant aircraft and crash-resistant control method
US11286052B2 (en) 2020-08-03 2022-03-29 Ami Industries, Inc. Drogue parachute assemblies with elastomeric insert sleeves
US11299281B2 (en) 2020-08-03 2022-04-12 Ami Industries, Inc. Parachute assemblies with elastomeric inserts
RU2799956C1 (ru) * 2022-07-18 2023-07-14 Михаил Сергеевич Беллавин Самолет

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CH587106A5 (de) * 1973-10-12 1977-04-29 Granger Maurice
DE3010833A1 (de) * 1980-03-21 1982-11-25 Eric 5000 Köln Neubeck Luftnotrettungssystem fuer grossraumpassagierflugzeuge
GB2200877B (en) * 1987-02-10 1990-10-10 Zinovi Levin Device for overcoming the problem of crew safety during a spacecraft launch and improve the joints connecting the segments of the solid rocket booster
DE9416639U1 (de) * 1994-10-15 1994-12-08 Hoechst Ag Vorrichtung zum Aufschneiden von Folienrollen
DE19507069C2 (de) * 1995-03-01 1999-07-01 Schubert Werner Vorrichtungen gegen Luftfahrzeugabstürze
DE19847546A1 (de) * 1998-10-15 2000-01-05 Mellmann Gerhard Flugzeug-Airbag-Sicherheitssystem FAS
GB2355965B (en) * 1999-11-06 2001-12-12 Andrew Thomas Pike Passenger aircraft escape system
DE10222712A1 (de) * 2002-05-23 2003-12-11 Gerhard Mellmann Luftfahrzeug mit einer Rettungseinrichtung
HRPK20020783B3 (en) * 2002-11-11 2005-12-31 Donas Don Aircraft structure reinforcement
TR200703725A2 (tr) * 2007-05-31 2007-12-24 Gülteki̇n Bülent Hayat kurtaran uçak sistemleri.
CN107672816A (zh) * 2017-09-22 2018-02-09 国网河南省电力公司新乡供电公司 无人机放线导引绳自动切断保护装置
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US3622108A (en) * 1970-02-27 1971-11-23 George A Mathewson Safety device for disabled airplanes
JPS52170500U (de) * 1976-06-18 1977-12-24
JPS568800Y2 (de) * 1976-06-18 1981-02-25
WO1990013479A1 (en) * 1989-05-04 1990-11-15 Mashinostroitelny Zavod Im P.O.Sukhogo Aircraft
US5568903A (en) * 1995-01-18 1996-10-29 Pena; Jesus S. Plane saddle for a safety airplane
US5673875A (en) * 1995-01-30 1997-10-07 Martin; Joseph R. Stabilizing inflight parachute system
US5921504A (en) * 1997-08-17 1999-07-13 Elizondo; Joey P. Aircraft passenger extraction system
US6382563B1 (en) * 1999-12-20 2002-05-07 Chui-Wen Chiu Aircraft with severable body and independent passenger cabins
US6595466B2 (en) 2000-11-28 2003-07-22 Airbus France Boarding device for aircraft and flying wings equipped with such a device
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US7234667B1 (en) * 2003-12-11 2007-06-26 Talmage Jr Robert N Modular aerospace plane
US8643850B1 (en) * 2010-03-02 2014-02-04 Richard L. Hartman Automated system for load acquisition and engagement
US20150203200A1 (en) * 2011-12-21 2015-07-23 George Bye Unmanned Aerial Systems
US10005559B2 (en) * 2015-09-01 2018-06-26 Guoxin WEI Crash-resistant aircraft and crash-resistant control method
US20180155038A1 (en) * 2016-12-02 2018-06-07 Joseph Miller Aircraft Parachute System
US11286052B2 (en) 2020-08-03 2022-03-29 Ami Industries, Inc. Drogue parachute assemblies with elastomeric insert sleeves
US11299281B2 (en) 2020-08-03 2022-04-12 Ami Industries, Inc. Parachute assemblies with elastomeric inserts
RU2799956C1 (ru) * 2022-07-18 2023-07-14 Михаил Сергеевич Беллавин Самолет

Also Published As

Publication number Publication date
CH497315A (de) 1970-10-15
DE1992863U (de) 1968-08-29
FR1603439A (de) 1971-04-19
DE1756581A1 (de) 1970-04-30
NL6811183A (de) 1969-02-11
GB1236283A (en) 1971-06-23

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