How are parachutes folded for reuse

WO2007062440A1 - Foldable space shuttle - Google Patents

Foldable space shuttle Download PDF

info

Publication number
WO2007062440A1
WO2007062440A1PCT / AT2006 / 000486AT2006000486WWO2007062440A1WO 2007062440 A1WO2007062440 A1WO 2007062440A1AT 2006000486 WAT2006000486 WAT 2006000486WWO 2007062440 A1WO2007062440 A1WO 2007
Authority
WHERE
WIPO (PCT)
Prior art keywords
foldable
collapsible
airship
flight
aircraft
Prior art date
Application number
PCT / AT2006 / 000486
Other languages
English (en)
French (fr)
Other versions
WO2007062440A8 (de
Inventor
Issam Sharif
Original assignee
Issam Sharif
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to AT19222005 priority Critical
Priority to ATA1922 / 2005priority
Application filed by Issam ShariffiledCriticalIssam Sharif
Publication of WO2007062440A1publicationCriticalpatent / WO2007062440A1 / de
Publication of WO2007062440A8publicationCriticalpatent / WO2007062440A8 / de

Left

  • 239000007789gasSubstances0.000claimsabstractdescription25
  • 239000001307heliumSubstances0.000claimsabstractdescription17
  • 229910052734heliumInorganic materials0.000claimsabstractdescription17
  • SWQJXJOGLNCZEY-UHFFFAOYSA-Nhelium (0) Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N0.000claimsabstractdescription17
  • 239000001257 hydrogenSubstances0.000claimsabstractdescription16
  • UFHFLCQGNIYNRP-UHFFFAOYSA-NhydrogenChemical compound [H] [H] UFHFLCQGNIYNRP-UHFFFAOYSA-N0.000claimsabstractdescription16
  • 229910052739 hydrogenInorganic materials0.000claimsabstractdescription16
  • 239000000446fuelSubstances0.000claimsdescription10
  • 239000001301oxygenSubstances0.000claimsdescription5
  • 229910052760oxygenInorganic materials0.000claimsdescription5
  • MYMOFIZGZYHOMD-UHFFFAOYSA-NoxygenChemical compoundO = OMYMOFIZGZYHOMD-UHFFFAOYSA-N0.000claimsdescription5
  • 210000004279OrbitAnatomy0.000description8
  • 230000003068staticEffects0.000description8
  • 238000005086 pumpingMethods0.000description5
  • 230000033001locomotionEffects0.000description4
  • 230000000694effectsEffects0.000description3
  • 239000000969carrierSubstances0.000description2
  • 230000005611electricityEffects0.000description2
  • 150000002431 hydrogenChemical class0.000description2
  • 241000283899GazellaSpecies0.000description1
  • 230000001133accelerationEffects0.000description1
  • 238000002485combustion reactionMethods0.000description1
  • 238000005265energy consumptionMethods0.000description1
  • 238000005516 engineering processMethods0.000description1
  • 239000003517fumeSubstances0.000description1
  • 239000000463materialSubstances0.000description1
  • 239000003566 sealing materialSubstances0.000description1
  • 239000000725suspensionSubstances0.000description1
  • XLYOFNOQVPJJNP-UHFFFAOYSA-NwaterSubstancesOXLYOFNOQVPJJNP-UHFFFAOYSA-N0.000description1

Classifications

    • B — PERFORMING OPERATIONS; TRANSPORTING
    • B64-AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G-COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1 / 00 — Cosmonautic vehicles
    • B64G1 / 14 — Space shuttles
    • B — PERFORMING OPERATIONS; TRANSPORTING
    • B64-AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B — LIGHTER-THAN AIR AIRCRAFT
    • B64B1 / 00 — Lighter-than-air aircraft
    • B64B1 / 06-Rigid airships; Semi-rigid airships
    • B — PERFORMING OPERATIONS; TRANSPORTING
    • B64-AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G-COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1 / 00 — Cosmonautic vehicles
    • B64G1 / 002 — Launch systems
    • B — PERFORMING OPERATIONS; TRANSPORTING
    • B64-AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B — LIGHTER-THAN AIR AIRCRAFT
    • B64B2201 / 00 — Hybrid airships, i.e. airships where lift is generated aerodynamically and statically

Abstract

Description

The invention relates to an airship that can be opened and collapsed automatically on the ground and during flight, which can be used as an aircraft or as a reusable space shuttle, with a combined collapsible gas cell, a shaping grid, an aircraft body consisting of a cockpit, a Storage room, an engine room and foldable wheels, component for aircraft navigation control, two rotatable rocket motors, a foldable rudder wing and a mechanism for operating the foldable rudder wing.
A hybrid airship, which flies heavier than air, with a static and a dynamic lift force is known from US Pat. No. 4,838,501 A1. The object of this invention is that the take-off of the aircraft is carried out by means of a static and a dynamic lift. The static buoyancy is generated by means of a gas cell which is filled with heated gas. The dynamic lift is generated by two swiveling engines. The locomotion is generated by means of the two engines mentioned. The aircraft is also equipped with two control surfaces. These are necessary to generate additional buoyancy while moving. This reduces the drag force when moving compared to traditional airships, which fly lighter than air. The disadvantage of this airship is the fact that the lift during take-off cannot be generated entirely by means of the static lift. Furthermore, despite the use of guide surfaces, the losses of thrust caused by the drag force are relatively very high compared to aircraft.
An airship with variable geometry is known from US Pat. No. 5,005,783 A1. The object of this invention is that the shape of the airship, which flies lighter than air, is changed in flight to the shape of an airplane, which flies heavier than air. The change in shape during flight takes place on the basis of the generation of pressure in the flexible hull of the airship. The necessary additional lift force during the movement is generated by means of two wing-like extended parts. This reduces the drag force when moving compared to traditional airships, which fly lighter than air. As with the hybrid flying ship mentioned above, the effect of drag force remains very high compared to aircraft. Furthermore, because of the dependence of the lift on the light gas, the two aircraft are only suitable for flight in the earth's atmosphere and can therefore not be used for a flight into space. A large number of types of aircraft are known in the art. A disadvantage of all types of aircraft, including jackscrews, is the enormous fuel consumption during take-off due to the complete dependence on dynamic lift. A number of re-used spacecraft destined for less than one orbit of the earth are known in the state of the art. Disadvantages of such space shuttles are the high fixed costs and fuel consumption as well as some technical inconvenience, such as the dependence on special airports or on ramps during take-off and parachutes during landing, as well as other disadvantages during take-off, such as noise and environmental pollution from exhaust gases.
In contrast, the object of the present invention is to form an airship that can be opened and collapsed automatically on the ground and during flight, which airship can be used as an aircraft or as a reusable space shuttle. Such an airship must be able to take off in the earth's atmosphere completely by means of static lift, must also take off completely by means of dynamic lift if necessary, must be able to fully carry its own weight during horizontal flight in the earth's atmosphere to overcome the generation of lift force by the wings in order to minimize the loss of thrust due to the drag force. Such an airship in the form of a reusable space travel for less than one orbit of the earth must also be able to fly further into space by means of the dynamic lift.
The invention solves the problem in that the combined collapsible gas cell consists of a collapsible shell and a non-collapsible housing, the non-collapsible housing is attached to the inner walls and the floor of the storage room, the combined collapsible gas cell in the opened state with helium or Filled with hydrogen and completely teaching when folded, the foldable shell is captured by the form-giving grid in the unfolded state and lies in the inner area of ​​the non-foldable housing when folded.
An airship that can be opened and collapsed automatically on the ground and during flight, which is used as an aircraft or as a reusable space shuttle for less than one orbit around the earth, will take off in the unfolded state. It is only folded up when the necessary flight altitude in the earth's atmosphere has been reached. When folded, the aircraft takes the form of an airplane. As a result, the take-off will be carried out by means of the static buoyancy, thus saving enormous amounts of energy. On the other hand, when moving, the effect of drag force will be just as minimal as with traditional aircraft. Therefore, such an aircraft has the take-off and landing capabilities of an airship and the locomotion of an aircraft.
The take-off by means of static buoyancy has other advantages for a reusable space shuttle for shorter than one orbit. As is well known, the biggest problem that space technology is confronted with is the enormous amounts of fuel required to get a space device to its intended destination in space. Attempts are therefore made to circumvent this problem in various ways, such as dividing the flight of shorter than one orbit around the earth into two stages and dividing the aircraft into two aircraft. Namely a carrying device and a carried device. When detached from the carrying device, the carried device will only carry the necessary amount of fuel for the second flight stage. A space shuttle shorter than an orbit around the earth with the take-off and landing capacity of an airship will replace a carrier device and a worn device as a result of the saving in fuel and thus save enormous amounts of fixed and variable costs.
A space shuttle shorter than an orbit around the earth with the take-off and landing capacity of an airship will be able to perform a safe, quiet vertical take-off when unfolded without a ramp or special airports. Landing in the unfolded state also ensures a soft and safe landing. This eliminates the need for special airports or parachutes
The subject of the invention is shown in the drawing, for example. Show it:
1 shows a schematic side view of an airship that can be automatically opened and collapsed during flight in the opened state;
2 shows a schematic partial side view of the aircraft body;
3 shows a schematic partial side view of the combined gas cell during collapse;
4 shows a schematic view of an airship that can be automatically opened and collapsed in the collapsed state from above;
5 shows a schematic side view of an automatically foldable and openable
Airship in the folded state on the ground;
6 shows a schematic side view of an automatically foldable and openable
Airship, in the folded state during flight;
7 shows a schematic side view of an automatically foldable and openable
Airship when unfolding or collapsing on the ground; 8 shows a schematic side view of an automatically foldable and openable
Airship when unfolding or collapsing during flight;
9 shows a schematic side view of an airship which can be automatically opened and collapsed and which flies more easily than air with the aid of the vacuum, the airship being in the unfolded state;
10 shows a schematic partial side view of the aircraft body, with the necessary
Components for creating a vacuum;
11 shows the flight route of an airship which can be automatically opened and collapsed in the form of a reusable space shuttle for shorter than one orbit around the earth;
12 shows the flight route of an airship in the form of an airplane that can be automatically opened and collapsed.
According to FIGS. 1 and 2, an airship that can be opened and collapsed automatically on the ground and during flight, which can be used as an aircraft or as a reusable space shuttle, consists of the following main components: a combined collapsible gas cell 400, an aircraft body 200 , Component for aircraft navigation control 300, two rotatable rocket motors 500L and 500R, a folding rudder wing 700 and a mechanism for operating the folding rudder wing 100.
The aircraft body consists of a cockpit 210, a storage room 220, an engine room 230 and rattle wheels 240. The combined collapsible gas cell 400 consists of a foldable envelope 402 and a non-foldable housing 401. The non-foldable housing 401 is on the inner walls and the Floor of the storage room 220 attached.
The folding or unfolding of the airship takes place automatically on the ground or during the flight in the same way. According to FIG. 7, the folding and unfolding of the airship takes place on the ground. Folding it on the ground is necessary so that little space is used for stationing the airship. According to FIG. 8, the folding and unfolding of the airship takes place during flight.
When the aircraft is opened, the helium or hydrogen is drawn into the combined gas cell 400 from the pressure tank for helium 233 or from the pressure tank for hydrogen 235 by means of the inlet valve 233.1 or inlet valve 235.1. Both pressure tanks 233 and 235 are located in engine room 230. After the combined gazelle has been filled with helium or hydrogen, the unfolded airship will fly lighter than air. In this state, the foldable envelope 402 is captured by the forming grid 600. The latter is attached to the points 601 on the foldable cover 402 from above and to the storage room 220 from below.
The rudder wing 700 is equipped with two brackets 701L and 701R and operated by means of the mechanism for operating the foldable rudder wing 100. The latter consists of an electric motor 101, a service brake 106, two electric motors 102L and 102R, three support pieces 103, 104L and 104R and a rotating coast 105. The supporting piece 103 is fastened from both ends to the rotating coast 105 from the inside. The rotating coast 105 itself is stored in the engine room 230. The electric motors 102L and 102R are mounted on the support piece 103 and see the shafts supported on the rotating coast 105. The electric motor 101 is fastened on the support piece 103 on the shaft side and fastened together with the service brake 106 on the floor of the machine room 230. The support piece 104L or 104R is attached to the shaft of the electric motor 102L or 102R.
The rudder wing 700 is used as an airship rudder when unfolded. In this state, it is in the vertical position and controlled by the electric motors 102L and 102R.
Referring to Fig. 6, the rotatable rocket motors 500L and 500R provide propulsion in the horizontal position. According to FIG. 7, they provide dynamic lift in the vertical position. The rotatable rocket motors 500L and 500R are mounted on the missile 200 and operate based on the combustion of liquefied hydrogen with liquefied oxygen. The liquefied hydrogen is obtained from the pressure tank for hydrogen 235 and the liquefied oxygen from the pressure tank for oxygen 234. The latter is also located in engine room 230.
The in-flight unfolding and folding is based on the generation of the necessary dynamic lift by means of the rotatable rocket motors 500L and 500R. This is necessary so that the air device can stay in suspension. The collapsing of the air device during flight begins with the creation of an absolute vacuum in the combined collapsible gas cell 400. The pumping out of helium or hydrogen is carried out by means of the vacuum pump 237, which is equipped with the outlet valve 237.1. The pump-out begins in the higher thinner layers in flight to avoid excessive pressure in the combined collapsible gas cell 400. If helium is used, the vacuum pump 237 is connected to the liquefaction system 231 so that the pumped-out helium is liquefied and stored in the pressure tank for helium 233. The fuel cells 232 are activated so that electricity for the liquefaction of the helium is generated by means of the liquefaction system 231. The fuel cells 232 consume hydrogen and oxygen and generate electricity and water.The latter is thrown from the ship. The liquefaction plant 231, the vacuum pump 237 and the fuel cells 232 are located in the machine room 230.
If hydrogen is used, the pumped-out hydrogen will be used directly in the actuation of the fuel cells 232 or rocket motors 500L and 500R by means of the vacuum pump 237.
According to FIG. 3, as a result of the helium or hydrogen being pumped out into the non-foldable housing 401, the foldable casing 402 is pulled under the effect of the vacuum. The shaping grid 600 is also drawn into the non-foldable housing 401 by means of the foldable cover 402. Finally, under the effect of the absolute vacuum, the foldable envelope 402 together with the grid 600 is pressed together in the tightest space in the non-foldable housing 401.
The foldable rudder wing 700 is then folded up. The folding of the folding rudder wing 700 begins with the rotation of the coast 105 about its vertical axes by 90 °. This is done by means of the electric motor 101 after its shaft has been freed from the action of the service brake 106. As a result, the hinged rudder wing 700 will be in the horizontal position. The rudder blade 700 is then placed on the storage room 220 by means of the electric motors 102L and 102R. So that the rudder wing 700 is folded tightly directly onto the storage room 220, the latter is equipped with a sealing material 221 from above. The rudder wing 700 is clamped firmly from several points on the storage room 220 by means of a mechanism (not shown).
So that the airship can perform the function of an aircraft in the folded state, it is equipped by means of the component for aircraft navigation control 300. The latter consist of two rudders 302L and 302R, two tail fins 301L and 301R and two tail units 303L and 303R. Each tail unit 303L or 303R is equipped with an elevator 303.1L or 303.1R and attached to the engine room 230. The tail fin 301L or 301R is attached to the tail unit 303L or 303R. The rudder 302R or 302L is mounted on the tail fin 301L or 30 IR.
According to FIG. 12, the flight route of an airship in the form of an airplane that can be automatically opened and collapsed consists of 5 phases. The first phase begins with the vertical start. The take-off to the necessary flight altitude during the first phase is carried out by means of static lift. During the second phase, the aircraft is collapsed. The third phase begins with the flight in the form of an airplane. During the fourth phase, the aircraft is unfolded. The fifth phase begins with the flight in the form of an airship
Direction of the landing site.
According to FIG. 11, the flight route of an airship that can be automatically opened and collapsed in the form of a reusable space travel vehicle for shorter than one orbit around the earth also consists of 5
Phases. The first two phases are the same as in the case of the airplane. At the beginning of the third
In the form of a space shuttle, the aircraft takes a vertical course to the targeted phase
Altitude in space. This phase ends after the return flight without thrust. The fourth phase begins with the opening of the air device when entering the earth's atmosphere. During this
During the phase, the aircraft is unfolded. The fifth phase begins with the flight in the form of a
Direction of the airship to the landing site.
According to FIGS. 9 and 10, the combined collapsible gas cell 400 * consists of a foldable one
Case 402, a foldable inner cover 405, a non-foldable housing 401 and a foldable one
Air envelope 406. The foldable envelope 402 and the foldable inner envelope 405 are attached to each other by means of the
Binding elements 404 bound.
The closed space between the foldable cover 402 and the foldable inner cover 405 becomes with
Air or filled with a light gas. For the sake of simplicity, let's assume that the space with
Air is filled. The outlet valve 408 and the inlet valve 409 were provided for this purpose. The
Exhaust valve 408 is attached to the foldable envelope 402 from the outside. The inlet valve 409 is attached to the foldable inner cover 405 from the inside.
The air pump 211 is located in the cockpit 210 and is connected to the
Inlet valve 409 connected. By generating a necessary pressure in the space between the foldable outer shell 402 and the foldable inner shell 405, the desired aerodynamic outer shape of the foldable shell 402 is created and at the same time a vacuum is created in the
Inside the combined gas cell 400 generated.
An airship which flies lighter than air with the help of the vacuum is known from GB 1345288.
The application of this principle for the airship that can be folded up and folded automatically on the ground as well as during flight is very suitable because of the acceleration of the up and down
Since the shading of an absolute vacuum in the combined foldable gas cell 400 * could lead to excessive material expenditure, small amounts of helium or
Hydrogen fed inside to generate a certain counter pressure from inside.
The unfolding of the airship begins with the pumping of air into the space between the foldable shell 402 and the foldable inner shell 405. At the same time, the combined collapsible gas cell 400 * is filled with the necessary amount of helium or hydrogen. The collapse begins with the opening of the outlet valve 408 and pumping out helium or hydrogen from the combined collapsible gas cell 400 *. In order to enable a landing for the air device in the form of an airship, the air envelope 406 was provided. This is equipped with a vacuum pump 212 and an inlet valve 410. With the opening of the inlet valve 410, the outside air will flow into the air envelope 406 and the airship will fly heavier than the air. This air can be pumped out again with the vacuum pump 212 so that the airship can again fly lighter than the air. The vacuum pump 211 is located in the cockpit 210.

Claims

PCT / AT2006 / 0004862005-11-292006-11-27 Foldable space shuttle WO2007062440A1 (de)

Priority Applications (2)

Application NumberPriority DateFiling dateTitle
AT192220052005-11-29
ATA1922 / 20052005-11-29

Applications Claiming Priority (4)

Publications (2)

ID = 37781980

Family Applications (1)

Application NumberTitlePriority DateFiling date
PCT / AT2006 / 000486WO2007062440A1 (de) 2005-11-292006-11-27Foldable space shuttle

Country Status (5)

Cited By (2)

Publication numberPriority datePublication dateAssigneeTitle
CN104590539A (zh) *2014-08-192015-05-06中国 特种 飞行器 研究所用于 伞 张 式 飞艇 气囊 超 压 及 变形 控制 装置
CN111086656A (zh) *2019-12-092020-05-01北京 宇航 系统工程 研究所一种 组合 可调 式 栅格 舵 展开 锁定 机构

Families Citing this family (2)

Publication numberPriority datePublication dateAssigneeTitle
FR2981055B1 (fr) *2011-10-052016-06-03Voliris METHOD AND SYSTEM FOR TRANSPORTING CONTAINERS BY MODULAR AIRCRAFT
US9725192B2 (en) *2015-03-242017-08-08Kevin Arash PeymanAirship powered aerospace vehicle

Citations (6)

Publication numberPriority datePublication dateAssigneeTitle
US3120932A (en) *1960-11-141964-02-11Stahmer BernhardtJet-balloon aircraft
GB1345288A (en) 1972-10-101974-01-30Pedrick A PAerial ships supported by vacuum balls or other forms of evacuated vessels
FR2320229A1 (fr) *1975-08-041977-03-04ZodiacPerfectionnements apportes aux aerostats, notamment aux dirigeables, et a leur procede de mise en oeuvre
US4838501A (en) 1986-04-031989-06-13Judson Edward GBalopod (hybrid flying machine)
US5005783A (en) 1990-01-181991-04-09The United States Of America As Represented By The Secretary Of The Air ForceVariable geometry airship
US6357700B1 (en) *2000-10-022002-03-19Anthony Italo ProvitolaElectrically powered spacecraft / airship

Family Cites Families (12)

Publication numberPriority datePublication dateAssigneeTitle
US2010743A (en) *1933-04-261935-08-06Abram A. AndersonAircraft
US2272643A (en) *1941-01-111942-02-10Peters HarryToy convertible automobile-plane
US2751169A (en) *1950-05-241956-06-19Honeywell Regulator CoAutomatic steering apparatus
US3204892A (en) *1963-08-011965-09-07Lockheed Aircraft Corp.Aerospace vehicle
US3371886A (en) *1966-01-141968-03-05Robert O. SchertzAircraft adapted for highway usage
US3801044A (en) *1972-01-131974-04-02A moorsBallooned, stol aircraft
FR2287784B1 (de) *1974-10-091979-02-09Inst Francais Du Petrole
USD331893S (en) *1991-06-211992-12-22Szakacs Joseph J.Combined aircraft and road vehicle
US6648272B1 (en) *2001-06-282003-11-18Keith L. KothmannAirship
US6565037B1 (en) *2002-06-042003-05-20Tonkovich Gregory PHybrid aircraft and methods of flying