WO1995032894A1 - Aerostat dirigeable semi-rigide - Google Patents

Aerostat dirigeable semi-rigide Download PDF

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Publication number
WO1995032894A1
WO1995032894A1 PCT/RU1995/000100 RU9500100W WO9532894A1 WO 1995032894 A1 WO1995032894 A1 WO 1995032894A1 RU 9500100 W RU9500100 W RU 9500100W WO 9532894 A1 WO9532894 A1 WO 9532894A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas
external
secured
air
lighter
Prior art date
Application number
PCT/RU1995/000100
Other languages
English (en)
Russian (ru)
Inventor
Jury Grigorievich Ishkov
Lev Mikhailovich Kuznetsov
Original Assignee
Jury Grigorievich Ishkov
Lev Mikhailovich Kuznetsov
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 AU25811/95A priority Critical patent/AU2581195A/en
Application filed by Jury Grigorievich Ishkov, Lev Mikhailovich Kuznetsov filed Critical Jury Grigorievich Ishkov
Publication of WO1995032894A1 publication Critical patent/WO1995032894A1/fr

Links

Classifications

    • 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

Definitions

  • Managed aeronautical aerial vehicles - diariably - are widely known. 5 Lately, it is considered to be efficient diaphragms with a compact form, which have a range of advantages in comparison with the alternatives of a characteristic. ⁇ these benefits
  • Niz ⁇ aya ves ⁇ vaya ⁇ dacha and ⁇ a ⁇ yae You are a s ⁇ aya s ⁇ im ⁇ s ⁇ and sl ⁇ zhn ⁇ s ⁇ izg ⁇ vleniya and OPERATION.
  • the use of a pressure transmitter and a protective part of it is a soft forming element filled with lighter air or an external gas pressure: Separating the internal volume of the gas by the gas is lighter than the air and the volume of the heated gas: located in the upper part of the gas chamber. gas filled lighter than air; Reserved on a case by hand on the 5th day of hanging the gondola, the load compartment, a sedentary installation, and equipped with accessories.
  • the disadvantages of hosted di- arya are the relatively low stability of the body of the casing and the inability to pay for a non-profitable device.
  • the disadvantages are that the result of diarrhea is: a large mass of fossil fuels and hard domestic power. ⁇ ressivnyh _ reduction of its weighted ⁇ toy; Radial use of the auspicious interior elements of the internal suspension: the absence of accumulation and fixation of a balloon with gas is easier to escape: there is no danger of With all the necessary information, 5 the basic task is to create a user-friendly and portable air-borne versatile vehicle. equipped with a thermal system for generating lift, ballasting with a reduced cross section in the midsection at a constant speed and higher wind power.
  • the posed problem is solved in that, in the case of a user-friendly aerospace device, including: disk drive; The convenient location for quick and easy access to external casters;; ierible ierides;;;;;;; The well-equipped parking place is
  • the output of its height to the diameter was selected in the range from 0.30 to 0.45: a strong external power factor was calculated as a result of this, and 0 percent of this value was obtained; the height of the western part is not more than 0.5 -4- heights of the body of the flying device; A separate part of its own is secured on an external container; the lower part of its larger external battery is secured on the external side, and the lower large component is secured on the internal side; in the outer outdoor area, the diaphragm is made in the form of an external space. Allowed housing is not lower than the second quarter. dividing the indicated internal volume by the volume of gas located above the membrane is lighter than air and the volume of gas heated by the membrane. At the same time, the membrane is protected by its large external storage compartment.
  • the gas supply area is equipped with facilities for supplying and discharging the exhaust gas and exhaust air; in gas, the central outlet is lighter than the air. reserved by its upper part on the outside.
  • Another version of the performance of the amplification of the upper part of the site in the place of the accumulation of the central power supply can be performed in the form of a closed strong power. for example. a polygon or a ring, attached to the outer circle.
  • the option to implement the Central Resource is optional.
  • Well-developed natural elements for example. tapes or trusses, the outer ends are fastened to the upper part, and the end end is secured to the power elements of the familiar side. By the way, in the central region.
  • the balloons filled with gas are easier to use than air and store them on strong internal components.
  • One of the options for executing a hard external cas- ter is the presence of a belt of power consisting of power elements and a wiring harness
  • the owner of the vehicle which is stored on an external basis, is different in the form of a strong development-stabilization of the external condition and the independence of the device is inconvenient
  • the free-loading module should be executed in the form of a payment.
  • the proposed invention allows the construction of a proprietary aerostatic apparatus - ⁇ -
  • the rate was selected in the range ⁇ from 0.025 to 0.05. and the height of the internal space is no more than 0.5 height of the body of the aircraft.
  • the stated cases were calculated using the standard method and
  • the green shell is made in the form of two upper and lower shells and secured to the hard power ⁇ of the element ⁇
  • the internal volume of the body of the flying unit is separated by a flexible membrane located above the membrane, the gas is lighter than the air and the gas is completely free of charge
  • the membrane is made from an elastic material in the form of an inversion, formed by rotation of a
  • the membrane design makes it possible to change the volume ratio of gas volumes to a larger extent. It is easier to air and
  • the gas supply area is equipped with facilities for supplying heated gas and exhaust air to it and exhausting it into the atmosphere.
  • the source of the preheated gas is the pre-emptive propulsion system. Otherwise, as a result of the source of heated gas may
  • ⁇ ⁇ aches ⁇ ve nag ⁇ 'e ⁇ g ⁇ gas m ⁇ gu ⁇ by ⁇ is ⁇ lz ⁇ vany ne ⁇ s ⁇ eds ⁇ venn ⁇ vy ⁇ l ⁇ nye gases sil ⁇ v ⁇ y us ⁇ an ⁇ v ⁇ i or ⁇ - du ⁇ y g ⁇ eniya and ⁇ a ⁇ zhe v ⁇ zdu ⁇ nag ⁇ e ⁇ y in ⁇ e ⁇ l ⁇ bmenni ⁇ e, ⁇ b ⁇ g ⁇ evaem ⁇ m zy ⁇ l ⁇ nymi gases or ⁇ du ⁇ ami g ⁇ eniya.
  • Heated gas is supplied to the area of heated gas through the distribution system. Includes a collector, a ventilation unit, gas and air conditioning systems.
  • the flue gas outlet is free from exhaust ventilators. Discharge of heated gas and air from the heated area -8-
  • the gas is exhausted through exhaust valves; the operation is shorted from the control cubicle.
  • the supply of heated gas to the volume of heated gas due to the increase in the temperature and, accordingly, the increase in the volume of gas is increased
  • the aerodynamic lifting force decreases. In this way, in a separate manner, the device can be operated by flying without using a traditional ballast system.
  • a quick external power supply is secured by a live external power supply and is equipped with a free-standing membrane.
  • the large amount of space available for the internal use of the internal components makes it easier to regulate the tension and makes it more comfortable to use.
  • the regulation of the tension of the auxiliary elements of the internal suspension is carried out by means of hydraulic amplifiers-boosters. winch or screw connections. reserved for the power elements of internal facilities.
  • the gas area is lighter than the air and the central outlet is located. Secured in its upper part on the outside. and from the bottom, secured on the inside. Two options are available for the implementation of the central site. S ⁇ g- lasn ⁇ ' ⁇ e ⁇ v ⁇ mu va ⁇ ian ⁇ u tsen ⁇ alny ⁇ se ⁇ vy ⁇ lnen gaz ⁇ ne ⁇ - ⁇ nitsaemym of elas ⁇ ichn ⁇ g ⁇ ma ⁇ e ⁇ iala, na ⁇ ime ⁇ , anal ⁇ gichn ⁇ - g ⁇ ma ⁇ e ⁇ ialu na ⁇ uzhn ⁇ y ⁇ b ⁇ l ⁇ ch ⁇ i.
  • the central circuit is divided into the lower part of the gas-tight gas separator.
  • the central unit which is made from genuine natural elements • or a network, is filled with gas cylinders that are lighter than air. Short-circuited are secured to the power elements of the internal circuit.
  • a large gain is secured in the form of a tape from a medium with a small load and it is free of loading for example. polygon or ring.
  • ⁇ Brass ⁇ réelle gas areas are lighter than air; gas cylinders are located.
  • Gas cylinders are filled with gas easier than air, for example, helium, and in their lower part are secured to power elements inside the unit. and in the majority, they are registered on the outside in the most convenient way. that gas points can change their application.
  • the system for fixation of points on the upper side is often made in the form of a “loop-on-the-loop ” device , or in the form of a loop. One end is secured on a gas point, and the second end is secured on the upper side. Placing gas is easier than air intake in gaseous sell- ers, it is more easily transported to the gas and it is more airborne than the air vessel. The fixation of gas points.
  • each gas point is secured to the power elements of the internal external part of its external part.
  • the hard external force is made in the form of a good path, for example, from a commercially available material or metal.
  • the hard external external casing made in the ZID was performed tight and equipped with a device for changing the internal pressure. in particular, to create excessive pressure inside.
  • the current version of the large-sized ammunition and the large capacity of the vehicle is equipped with a quick-drive. consisting of power elements and systems connecting the power elements to the ground or performed as a circuit mounted on the ground circuit. Increased internal pressure and the presence of a belt of harshness increase the harshness of the outside of the pipe.
  • the body of the body of the flying device is executed in the form of development of a small-sized, strong external product,
  • the availability of stabilizing devices improves aerodynamic performance and increases the stability of the flying machine while it is in motion.
  • aerodynamic control systems direct power settings and power settings are reserved.
  • the internal hard drive is equipped with a separate load compartment and a separate load module. equipped with notifications for his order
  • a separable load module can be configured as a container for discharging solid or bulk loads. for transporting standard goods. Tank for transporting low cargo. for example. oil and oil products. gas burner for gas transport. capacities for the transportation of gas, cabins for the transportation of passengers, car rental, including the price of the accommodation The local emergency, emergency, emergency, public or other purpose.
  • the small appliance is equipped with a device for transporting loads on an external suspension, in particular, a large-sized unit that does not extend the division of loads.
  • the device for transporting loads on the outside is suspended from ropes mounted on power windings that are powered by power ⁇ ⁇ a ⁇ ⁇ ⁇ e ⁇ ⁇ and a nd e ⁇ ⁇ e
  • Fig. 1 shows a vertical section of the semi-active airborne aerospace device. according to the invention.
  • Fig. 2 - a horizontal section of a flying machine • with a shift in the central location, it was vertical.
  • FIG. 4 - version of the central network (from genuine items with gas cylinders).
  • Fig. 3 - a fragment of a transverse part of the rim of a flying device.
  • the ammunition includes an integrated and external storage compartment and a strong external enclosure I, made in the form of an empty compartment. For this reason, ⁇ has been completed in such a way. that it is eccentric in the range from 0.025 to 0.05. ⁇ sialn ⁇ ⁇ n ⁇ si ⁇ eln ⁇ vne ⁇ - neg ⁇ ⁇ a ⁇ asa 1 ⁇ as ⁇ l ⁇ zhen ⁇ ly ies ⁇ y sil ⁇ v ⁇ y vnu ⁇ en- Nij ⁇ s ⁇ v 2.
  • the unit has a shell, made of soft, gas-impervious material in the form of two - upper 4 and lower 5.
  • ⁇ e ⁇ nyaya 4 ⁇ b ⁇ l ⁇ ch ⁇ a sv ⁇ ey ⁇ m ⁇ y za ⁇ e ⁇ lena on yaes ⁇ m sil ⁇ v ⁇ m external ⁇ a ⁇ ase 1.
  • ⁇ izhnyaya 5 ⁇ b ⁇ l ⁇ ch ⁇ a sv ⁇ ey b ⁇ lshey ⁇ m ⁇ y ⁇ a ⁇ ne za ⁇ e ⁇ lena on the outer ⁇ a ⁇ ase 1.
  • the area of 8 heated gas is supplied with devices (not indicated) for the delivery of and removal of heated gas and foreign air from it.
  • the source of hot gas is an essential power plant, in particular. -thirteen-
  • the source of hot gas can be used for special purposes (not indicated).
  • the direct exhaust gases of high power plants or products of combustion are used.
  • the device for the supply of heated gas to the volume of 8 heated gas includes a distribution system (not specified), which is integrated in the gas unit, is ventilated.
  • the device for the delivery and release of the air inlet includes the fans and the valves mounted on the bottom 5. not indicated).
  • the internal suspension is located in the area of 8 heated gas.
  • ⁇ ⁇ aches ⁇ ve ⁇ is ⁇ s ⁇ bleny for ⁇ eguli ⁇ vaniya na ⁇ yaieniya ⁇ d ⁇ ln ⁇ yaes ⁇ - ⁇ i ⁇ elemen ⁇ v 3 is ⁇ lz ⁇ vany gid ⁇ avliches ⁇ ie usili ⁇ eli- ⁇ us- ⁇ e ⁇ y. Otherwise, as a part of the system for regulating the tension of the auxiliary elements of 3 internal suspensions, the winch or the screw may be used.
  • a gas area of 7 is lighter than air and a central compartment of 10 is located, most of which are secured on the outside of 4. and the bottom part is reserved for a hard internal power 2.
  • the central part 10 is made just one of two options. According to the first variant (Fig. 3), the central part 10 is made in the form of a gas-tight, closed capacitance from a material of the analogous to the old one.
  • the outer compartment of the central compartment 10 is secured to the upper 4 circuit, and its lower compartment is secured to the external circuit 2.
  • the central gas circuit is not connected to the -14-
  • an upper 12 part of the central 10 is filled with gas lighter than the air, and the other 13 part of the central 10 is a point.
  • the tank is equipped with a notification (not indicated) to change the pressure
  • the central part of 10 is all equipped with 14 solid elements, for example, ribbons or cables, or a network.
  • 14 solid elements for example, ribbons or cables, or a network.
  • the simple external force case 1 (Fig. 2) is made in the form of a complete staircase and is made from a multi-unit or from a combined between sections 18.
  • a strong external power supply unit 1 is equipped with a simple hardness (Fig. 5). consisting of a power element 19 and a power of 20. connecting parts of a power element 19 with an external shortcut 1. Variable performance is unavailable -15- secured in an external case of 1 Colombian force (not shown).
  • the case of the case of the flying device. Ig.1.2 is made in the form of development-stabilization of 21 and 22 days of a strong external case of 1, augmented by other non-existing and external parts.
  • the gondola 28 of the control is secured.
  • the arrangement for the transport of goods on the other hand is made in the form of natural elements. for example, ⁇ Mercedes availability. protected winch. FITTED ON POWER COMPONENTS OF INTERNAL OUTDOOR 2 AND ON FOREIGN CASE 1. AND LOADING UNIT.
  • the parking chassis 30 is secured.
  • Gas cylinders 17 and the upper 12 part of the central heating unit 10 or gas cylinders 15 of the central heating unit 10 are filled with helium or other gassed gases.
  • central step 10 is gas-impervious. delivers air ⁇ ballonet 13.
  • the portable linear size of the dispensable medical device with the compact disk is the length of the disk.
  • the ammunition is also balanced by increasing the aeronautical lifting force by the weight of the load due to the delivery of the fresh gas to the load 8. The unloading of the freezer.
  • the loading device is loaded with a portable device and is optional. More often, they increase aerospace lifting force by an amount that ensures the vertical transfer of the aircraft to the necessary altitude. Drive the engines of a power unit of 9 and a new manual power unit 23 and load a load in the place of unloading or. They recover the ammunition from the unloading area and stabilize its active components. and, in the event of an emergency, they take advantage of a flying machine at the place of unloading or installing them at the place of sewing. umenshayu ⁇ ae ⁇ s ⁇ a ⁇ iches ⁇ uyu ⁇ demnuyu force on g ⁇ uza weight value, or in case ⁇ deleniya g ⁇ uz ⁇ v ⁇ g ⁇ m ⁇ dulya 27.
  • ⁇ de- -17- loading module 27 may be removed to the loading section and secured in it.
  • the unit of the cargo module 27 is operated by the use of replaceable load modules. and also in the event of the filling of a separate module 27 in the form of a special function area: either a place of residence, a place of destination, or an ingo.
  • ⁇ azemnaya s ⁇ yan ⁇ a ⁇ lunes ⁇ g ⁇ u ⁇ avlyaem ⁇ g ⁇ ae ⁇ s ⁇ a ⁇ i- ches ⁇ g ⁇ le ⁇ a ⁇ eln ⁇ g ⁇ a ⁇ a ⁇ a ⁇ a s ⁇ glasn ⁇ iz ⁇ b ⁇ e ⁇ eniyu ⁇ su- sches ⁇ vlyae ⁇ sya ⁇ b ⁇ az ⁇ m follows: vy ⁇ us ⁇ ayu ⁇ gas from ⁇ l ⁇ s ⁇ i 8 nag ⁇ e ⁇ g ⁇ gas and umenshayu ⁇ na ⁇ yazhenie ⁇ d ⁇ ln ⁇ yaes ⁇ i ⁇ elemen ⁇ v 3 znu ⁇ enney ⁇ dves ⁇ i.
  • P ⁇ me ⁇ e dalneisheg ⁇ reduce ae ⁇ s ⁇ a ⁇ iches ⁇ y ⁇ demn ⁇ y strength and s ⁇ ascheniya ⁇ bema ⁇ l ⁇ s ⁇ i 8 nag ⁇ e ⁇ g ⁇ for gas-le ⁇ a ⁇ elny a ⁇ a ⁇ a ⁇ zs ⁇ ae ⁇ s ⁇ yan ⁇ chnye on the chassis 30.
  • P um p a r i n g a n g a n t h a n t a nce a unit may be sold as a universal product for the use of a load.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Tents Or Canopies (AREA)
  • Vehicle Body Suspensions (AREA)

Abstract

L'aérostat dirigeable semi-rigide de l'invention présente une carène en forme de disque et comprend un cadre extérieur rigide (1) et très résistant autour de la circonférence de la carène et formant le bord de celle-ci; un cadre intérieur creux rigide (2) à haut rendement fixé au cadre extérieur (1) par un élément de suspension intérieur constitué d'éléments longitudinalement rigides (3), une peau extérieure constituée de deux parties de peau, c'est-à-dire une partie de peau supérieure (4) et un partie de peau inférieure (5), des ballons à gaz (17) configurés dans l'espace intérieur et remplis d'un gaz plus léger que l'air, un capsule à cargaison située à l'intérieur du cadre intérieur (2), un déflecteur fixé au cadre extérieur (1) et formant un bord de carène relativement aigu, une cabine de commande, un système de propulsion et des systèmes de commande. Selon l'invention, l'épaisseur relative de la carène est comprise entre 0,30 et 0,45, le cadre extérieur se présente sous la forme d'un corps rigide de haut rendement dont l'excentricité est comprise entre 0,025 et 0,050. La hauteur du cadre intérieur (2) n'est pas supérieure à 0,5 fois la hauteur de la carène. Une membrane (6) est prévue dans l'espace intérieur de la carène sous la forme d'une surface formée par rotation d'une courbe au moins de second ordre, cette membrane étant fixée au cadre extérieur (1) ainsi qu'au cadre intérieur (2) et divisant l'espace intérieur de la carène en une chambre destinée au gaz plus léger que l'air, et une chambre pour du gaz chauffé. La chambre de gaz chauffé est dotée de dispositifs d'introduction et de libération de gaz chauffé et d'air extérieur. Une capsule centrale (10), dotée d'un réceptacle destiné au gaz plus léger que l'air, est montée à l'intérieur de la chambre de gaz plus léger que l'air, cette capsule centrale étant fixée à la peau supérieure (2) ainsi qu'au cadre intérieur (2). La partie de peau supérieure (4) présente un renforcement (16) au niveau du site où la capsule centrale (10) est fixée, les ballons de gaz (17) sont fixés à des éléments résistants du cadre intérieur (2) et attachés à la partie de peau supérieure (4). Des éléments longitudinalement rigides (3) de l'élément de suspension intérieure sont fixés par paires au niveau d'une extrémité au cadre extérieur (1), et fixés au niveau de l'autre extrémité aux éléments résistants dudit cadre intérieur (2), le long de tangentes à la surface du cadre en des points diamétralement opposés.
PCT/RU1995/000100 1994-05-26 1995-05-24 Aerostat dirigeable semi-rigide WO1995032894A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU25811/95A AU2581195A (en) 1994-05-26 1995-03-24 Semi-rigid dirigible aerostat

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU94019770 1994-05-26
RU94019770A RU2114027C1 (ru) 1994-05-26 1994-05-26 Полужесткий управляемый аэростатический летательный аппарат

Publications (1)

Publication Number Publication Date
WO1995032894A1 true WO1995032894A1 (fr) 1995-12-07

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1995/000100 WO1995032894A1 (fr) 1994-05-26 1995-05-24 Aerostat dirigeable semi-rigide

Country Status (3)

Country Link
AU (1) AU2581195A (fr)
RU (1) RU2114027C1 (fr)
WO (1) WO1995032894A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7487936B2 (en) * 2006-10-23 2009-02-10 Ltas Holdings, Llc Buoyancy control system for an airship
US7866601B2 (en) 2006-10-20 2011-01-11 Lta Corporation Lenticular airship
US8297550B2 (en) 2007-08-09 2012-10-30 Lta Corporation Lenticular airship and associated controls
USD670638S1 (en) 2010-07-20 2012-11-13 Lta Corporation Airship
US8596571B2 (en) 2011-03-31 2013-12-03 Lta Corporation Airship including aerodynamic, floatation, and deployable structures
US8894002B2 (en) 2010-07-20 2014-11-25 Lta Corporation System and method for solar-powered airship
CN105363205A (zh) * 2015-11-20 2016-03-02 郑州中德美游乐设备有限公司 重量为负数的金飞碟
US9802690B2 (en) 2013-11-04 2017-10-31 Lta Corporation Cargo airship

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
RU2449919C1 (ru) * 2010-10-01 2012-05-10 Юлия Алексеевна Щепочкина Воздухоплавательный аппарат
RU2556493C1 (ru) * 2014-02-25 2015-07-10 Юлия Алексеевна Щепочкина Диск для метания
RU2662593C1 (ru) * 2017-08-17 2018-07-26 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Высотный дирижабль

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US4269375A (en) * 1979-10-31 1981-05-26 Hickey John J Hybrid annular airship
US4326681A (en) * 1979-09-20 1982-04-27 Fredrick Eshoo Non-rigid airship

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US4326681A (en) * 1979-09-20 1982-04-27 Fredrick Eshoo Non-rigid airship
US4269375A (en) * 1979-10-31 1981-05-26 Hickey John J Hybrid annular airship

Non-Patent Citations (2)

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Title
M.YA. ARIE, "Dirizhabli", OPUBL.-, IZD. NAUKOVA GUMKA (Kiew), pages 105-106. *
V.M. SHASHIN, "Vozdukhoplavatelnaya Tekhnika", Itogi Nauki Tekhniki, Seriya Aviastroenie, t.8, OPUBL.-. IZD. VINITI, (MOSCOW), pages 17-18. *

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7866601B2 (en) 2006-10-20 2011-01-11 Lta Corporation Lenticular airship
US8109462B2 (en) 2006-10-20 2012-02-07 Lta Corporation Lenticular airship
US7487936B2 (en) * 2006-10-23 2009-02-10 Ltas Holdings, Llc Buoyancy control system for an airship
US8616503B2 (en) 2007-08-09 2013-12-31 Lta Corporation Lenticular airship and associated controls
US8297550B2 (en) 2007-08-09 2012-10-30 Lta Corporation Lenticular airship and associated controls
US9840318B2 (en) 2007-08-09 2017-12-12 Pierre Balaskovic Lenticular airship and associated controls
US9828082B2 (en) 2007-10-18 2017-11-28 Lta Corporation Airship having a cargo compartment
USD670638S1 (en) 2010-07-20 2012-11-13 Lta Corporation Airship
US8894002B2 (en) 2010-07-20 2014-11-25 Lta Corporation System and method for solar-powered airship
US8899514B2 (en) 2010-07-20 2014-12-02 Lta Corporation System and method for varying airship aerostatic buoyancy
US8596571B2 (en) 2011-03-31 2013-12-03 Lta Corporation Airship including aerodynamic, floatation, and deployable structures
US9745042B2 (en) 2011-03-31 2017-08-29 Lta Corporation Airship including aerodynamic, floatation, and deployable structures
US9802690B2 (en) 2013-11-04 2017-10-31 Lta Corporation Cargo airship
CN105363205A (zh) * 2015-11-20 2016-03-02 郑州中德美游乐设备有限公司 重量为负数的金飞碟
CN105363205B (zh) * 2015-11-20 2018-10-12 郑州中德美游乐设备有限公司 金飞碟

Also Published As

Publication number Publication date
RU2114027C1 (ru) 1998-06-27
AU2581195A (en) 1995-12-21
RU94019770A (ru) 1996-07-10

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