Aeronautics and astronautics – Aircraft – heavier-than-air – Airplane and fluid sustained
Patent
1996-08-01
1998-11-17
Grant, William
Aeronautics and astronautics
Aircraft, heavier-than-air
Airplane and fluid sustained
244 123, 244 124, 244 23B, 244 23C, B64C 1512, B64C 3000
Patent
active
058365435
DESCRIPTION:
BRIEF SUMMARY
CROSS REFERENCE TO RELATED APPLICATIONS
This application is a national stage of PCT/DE95/01430 filed 16 Oct. 1995 and based, in turn, on German national application P4439073.4 of 2 Nov. 1994 under the International Convention.
FIELD OF THE INVENTION
The present invention relates to a discus-shaped aerodyne for extremely high velocities and extreme altitudes, the aerodyne having an outer casing generating buoyancy when horizontally flying through a gas atmosphere, a jet arrangement located in a peripheral region of the aerodyne and serving for the generation of a vertical movement and at least one rocket engine for the combustion of silicon hydride compounds for the generation of a horizontal movement of the aerodyne.
BACKGROUND OF THE INVENTION
In order to fly long distances, long-distance aircraft flying in the supersonic range must travel for a long time. Supersonic aircrafts with a very high fuel consumption, as for instance the Concorde, must have intermediate stops to supplement their fuel stock. Accordingly, there is a need for a long-distance aircraft which can be economically operated and with which a great number of passengers or a large quantity of freight can be transported.
An aerodyne of the above-described kind which is designed as spacecraft is known from German patent 42 15 835. The known aerodyne has three drive means. In the start phase it operates as a helicopter by using jets acting on two oppositely driven rings through gear means. The rings have adjustable blades and operate as turbine blade rings. The aerodyne is kept in suspension by this drive.
In this phase the aerodyne is accelerated by means of at least one rocket drive adapted to be swung out from a bottom area of the discus-shaped outer casing and oriented laterally obliquely. When this second drive is effective the helicopter drive can be switched off and the casing of the turbine blade rings can be pulled in so that the aerodyne is occluded with respect to the outside air. The aerodyne is adapted to be lifted to the upper level of the stratosphere with this rocket drive.
Furthermore, the known aerodyne includes at least one main thruster centrally located with respect to the discus-shaped outer casing and adapted to move the spacecraft through the vacuum space.
The main thruster and the rocket drive are formed in such a manner that they can be driven by a silane oil of the chemical formula Si.sub.5 H.sub.12 to Si.sub.9 H.sub.20 as rocket propellant.
In the cited publication (see U.S. Pat. No. 5,730,390 based on application Ser. No. 08/353,355) liquid oxygen is mentioned as oxidizing agent for the combustion of the silane oils in the two rocket engines, namely the rocket drive and the main thruster, wherein liquid chlorine or fluorine are also cited. This liquid oxidizing agent has to be carried along within the aerodyne. However, this fact practically excludes the use of such an aerodyne for aviation and makes the same only suited as spacecraft, as has also been described in German patent 42 15 835. That is, the large amount of oxidizing agents carried along does not make such aerodynes suitable for the transport of freight or passengers for long-distance flights.
OBJECT OF THE INVENTION
It is the object of the invention to provide an aerodyne of the cited kind which is suitable for flights within the terrestric area with a high load capacity and especially high velocities.
SUMMARY OF THE INVENTION
This object is attained in a discus-shaped aerodyne, according to the invention by providing at least one rocket drive in the form of a nitrogen burner in which the silicon hydride compounds are burned with atmospheric nitrogen at high temperatures in the presence of atmospheric oxygen as oxidizing agent for the hydrogen of the silicon hydride compounds.
Preferably, silane oils, having the chemical formula Si.sub.5 H.sub.12 to Si.sub.9 H.sub.20, are burned in the nitrogen burner.
Accordingly, with the inventive solution the rocket drive providing for the horizontal movement of the discus-shaped aerodyne is formed as a
REFERENCES:
patent: 2939648 (1960-06-01), Fleissner
patent: 3020003 (1962-02-01), Frost et al.
patent: 3132827 (1964-05-01), Roy et al.
patent: 3336753 (1967-08-01), Mullen, II
patent: 3503573 (1970-03-01), Modesti
patent: 5039031 (1991-08-01), Valverde
patent: 5064143 (1991-11-01), Bucher
DATABASE WPI, Derwent Publications Ltd., London, GB, AN, 85-108095 & JP, A, 60 052 578.
Chemical Abstracts, vol. 119, No. 20, Abstract No. 206577c, Nov. 1993.
Journal of the American Ceramic Society, Bd. 69, Nr. 4, ISSN 0002-7820, C60-C61, Apr. 1986.
Journal of Spacecraft and Rockets, Bd. 19, Nr. 4, 294-306.
Kunkel Klaus
Plichta Peter
Dubno Herbert
Grant William
Kunkel Klaus
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