Power plants – Reaction motor – Liquid oxidizer
Reexamination Certificate
1999-08-26
2001-09-04
Kim, Ted (Department: 3746)
Power plants
Reaction motor
Liquid oxidizer
C060S232000, C060S266000, C285S226000, C239S265350, C239S127300
Reexamination Certificate
active
06282887
ABSTRACT:
FIELD OF THE INVENTION
The invention relates to the field of rocket manufacturing, in particular to bellows units and a rocking unit of a combustion chamber of a liquid-propellant rocket engine (LPE) with afterburning, and may be used in pipeline systems operating under high-temperature and high-pressure conditions.
BACKGROUND OF THE INVENTION
Both gas dynamic and mechanical methods and means for acting on the gas stream flowing out of the nozzle of a rocket engine in order to create control moments causing the rocket to turn in three planes (pitch, yaw and roll) are known.
The present invention relates to mechanical means ensuring the generation of control moments influencing the rocket during its flight.
In particular, the following methods and means relate to mechanical methods and means for controlling the flight of a rocket by acting on the gas stream.
An engine mounted with the possibility of its rocking in two mutually perpendicular planes is known (“Liquid-Propellant Rocket Engine Construction and Design” edited by Prof. G. G. Gakhun, Moscow, Mashinostroenie, 1989, p. 355, FIG. 14.3).
Limitations of this technical solution include first of all the placement of a hinge between the structural frame and the engine, and, accordingly, the necessity to ensure a turn of the whole engine when the gas stream is acted on. This increases the weight of the control actuators and makes flight control more difficult in the rocket stabilization mode. Furthermore, it not possible to reduce the load on the hinge by the thrust force, since the hinge is mounted between the frame and the engine.
Mounting the chamber with the possibility of its rocking in a gimbal is known (“Liquid-Propellant Rocket Engine Construction and Design ” edited by Prof. G. G. Gakhun, Moscow, Mashinostroenie, 1989, p. 374, FIG. 14.10).
Disadvantages of this known technical solution include the substantial weight of the gimbal and the bearing unit, since they take up the whole thrust of the engine chamber, and it is not possible to reduce the load on these units.
Mounting the chamber with the possibility of its rocking in one plane on a bearing unit relative to an immovably fixed tube through which one of the propellant components is fed is known (GB, A, 1008156).
Limitations of this technical solution include the necessity for accurate assembly and adjustment of the position of the bearing unit supports in order to achieve the required coaxiality and uniformity of the transfer of thrust to the structural frame, and also the possibility for the chamber to only turn in one plane, which limits its use in single-chamber engines.
A rocking unit for the chamber of a liquid-propellant rocket engine with afterburning is known, which comprises a chamber, mounted on a gimbal, and a bellows unit (“Liquid-Propellant Rocket Engine Construction and Design” edited by Prof. G. G. Gakhun, Moscow, Mashinostroenie, 1989, p. 375, FIG. 14.11).
The known technical solution ensures rocking of the chamber in two mutually perpendicular planes. At the same time, this technical solution, in the form in which it is presented in the above publication does not have means ensuring the serviceability of the bellows unit in a medium of oxidizing, high-temperature, high-pressure gas, means ensuring a reduction of the load on the bearing supports of the gimbal, and also means ensuring stability of the bellows envelope when it is bent to a substantial angle, for example, within the range of 10-12 degrees.
DISCLOSURE OF THE INVENTION
Consequently, an object of the invention is to develop such a bellows unit for a combustion chamber of a liquid-propellant rocket engine with afterburning, which would be serviceable in a medium of high-temperature, high-pressure gas.
Another object of the invention is to develop such a bellows unit for a combustion chamber, mounted in a gimbal, of a liquid-propellant rocket engine with afterburning, which would ensure a reduction of the load on the bearing supports of the gimbal.
One more object of the invention is to develop such a bellows unit for a rocking unit of the combustion chamber of a liquid-propellant rocket engine with afterburning, which would ensure stability of the bellows envelope when it is bent to a substantial angle.
Finally, the last object of the invention is to develop a rocking unit of the combustion chamber of a liquid-propellant rocket engine with afterburning, in which such a bellows unit could be used.
These objects in accordance with one aspect of the invention are achieved by means of a bellows unit for a combustion chamber of a liquid-propellant rocket engine with afterburning, the unit comprising a bellows having two end faces and a corrugated envelope positioned at its periphery along a longitudinal axis of the aforesaid bellows, an internal shield of the bellows that has an internal cavity of the shield which is limited by a first envelope of the shield and a second envelope of the shield, each of the aforesaid shield envelopes being a body of rotation positioned along the longitudinal axis of the bellows, adjoining end faces of the aforesaid first and second shield envelopes being telescopically installed one in another with a gap between them, a bellows cooling chamber positioned between the aforesaid internal shield and the aforesaid corrugated envelope, the bellows cooling chamber communicating via the aforesaid gap with the aforesaid internal cavity of the shield, a first support ring and a second support ring which are positioned coaxially with the aforesaid bellows at both end faces thereof and fixed in cantilever to corresponding end faces of the first and second shield envelopes, channels for feeding a cooling working medium which are made in the aforesaid rings and serve for feeding the cooling working medium into the cooling chamber of the bellows.
In order to ensure a reduction of the load on the bearing supports of the gimbal, the average diameter of the bellows is selected from the following relationship:
D
c
≥
1.13
R
P
,
where
D
c
is the average diameter of the bellows,
R is the engine chamber thrust force,
P is the turbine gas pressure.
In order to enhance cooling of the bellows, an adjoining end face of the aforesaid first shield envelope is made in the form of a nipple with a spherical end.
In order to enhance the efficiency of the engine, one of the propellant components is used as the cooling working medium.
In order to enhance the strength of the construction, protective structural rings of the bellows are positioned in depressions of the outer corrugations of the aforesaid corrugated envelope of the bellows.
These objects according to the following aspect of the invention are achieved by means of a bellows unit for a combustion chamber of a liquid-propellant rocket engine with afterburning mounted in a gimbal, the unit comprising a bellows having two end faces and a corrugated envelope positioned at its periphery along a longitudinal axis of the aforesaid bellows, an internal shield of the bellows that has an internal cavity of the shield which is limited by a first envelope of the shield and a second envelope of the shield, each of the aforesaid shield envelopes being a body of rotation positioned along the longitudinal axis of the bellows, adjoining end faces of the aforesaid first and second shield envelopes being telescopically installed one in another with a gap between them, a bellows cooling chamber positioned between the aforesaid internal shield and the aforesaid corrugated envelope, the bellows cooling chamber communicating via the aforesaid gap to the aforesaid internal cavity of the shield, a first support ring and a second support ring which are positioned coaxially with the aforesaid bellows at both end faces thereof and fixed in cantilever to corresponding end faces of the first and second shield envelopes, channels for feeding a cooling working medium which are made in the aforesaid rings and serve for feeding the cooling working medium into the cooling chamber of the bellows, wherein the average diameter
Kolosova Inna Alexandrovna
Osokin Mikhail Ivanovich
Polushin Valentin Georgievich
Postnikov Ivan Denisovich
Sarafaslanjan Khachatur Begoevich
Kenyon & Kenyon
Kim Ted
Otkrytoe Aktsionernoe Obschestvo “Nauchno Proizwodstvennoe Obied
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