RU2320884C2 - Device for supply of water for reduction of acoustic action on launch vehicle and cooling of rocket engine gaseous jet - Google Patents

Abstract

FIELD: device being a member of launchers of the launching complexes providing reduction of the acoustic action on the launch vehicle and cooling of the rocket engine gaseous jet at a take-off.

SUBSTANCE: the device has a closed-type water conduit with branch pipes and slots for water supply. The inner space of the water conduit is separated by a partition into two isolated chambers with individual branch pipes for water supply. The mentioned slots are made on the upper end surface of one of the chambers and on the lower end surface of the other chamber providing for formation of a hollow water curtain around the rocket engine gaseous jet. The water conduit may have a rectangular section and be installed on the bearing posts of the launching structure. In the preferable modification of the device the slots form a ring-shaped contour so that each subsequent slot overlaps the previous one at least by half-the length of the latter.

EFFECT: enhanced intensity of cooling of the rocket engine gaseous jet and reduction of the acoustic action on the launch vehicle and it payload.

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Description

The invention relates to rocket and space technology, namely to devices as part of the launchers of the launch complexes, which provide cooling of the gas stream of the rocket engine of the launch vehicle at the launch site of its trajectory.

A known system for cooling a gas jet of a booster engine, including nozzles with slotted nozzles used in the space launch complex (see patent No. 2099255, IPC: B64G 5/00, F42B 15/00).

There is also a known system for cooling a gas jet of a launch vehicle engine, including pipelines laid from a water tank to nozzles with slotted nozzles mounted on a launch pad, through which water pipes are supplied to cool the gas reflector (see "Technological objects of the ground infrastructure of rocket and space technology ", engineering manual, general edition: Doctor of Technical Sciences, Professor I.V. Barmin, Moscow, 2005).

Both systems are designed to protect the gas reflector and cover the duct from the effects of a high-temperature gas stream and to protect the tail of a space rocket, starting from the moment the rocket engine starts. At the same time, nozzles with slotted nozzles supply water directly to the gas stream.

The reasons that impede the achievement of the required technical result when using known devices include a decrease in the effect of the supplied water on the acoustic radiation of the gas jet of the rocket engine after the start of the movement of the launch vehicle at the starting portion of its trajectory.

The technical problem solved by the invention is to increase the cooling rate of the gas stream of the rocket engine and reduce the acoustic impact on the launch vehicle and its payload by reducing the acoustic radiation of the gas stream of the rocket engine at the starting portion of the launch vehicle trajectory.

The specified technical result in the implementation of the invention is achieved by the fact that in the water supply device to reduce the acoustic impact on the launch vehicle and to cool the gas jet of the rocket engine, containing a closed conduit with water inlets and slots for water supply, the inner cavity of the water conduit being divided by a partition on two isolated chambers with individual nozzles for water supply, and these slots are made on the upper end surface of one chamber and on the lower end surface the other chamber, providing the formation around the gas stream of the rocket engine of a hollow water curtain.

In addition, a device in which the conduit has a rectangular cross-section.

In addition, a device in which a water conduit is configured to be mounted on supporting posts of a launching facility.

In addition, a device in which the slots form an annular contour so that each subsequent slit overlaps the previous one by at least half the length of the latter.

The analysis of the prior art by the applicant, including a search by patent and scientific and technical sources of information and identification of sources containing information about analogues of the claimed invention, allowed to establish that the applicant did not find an analogue characterized by features identical to all the essential features of the claimed invention, and the definition from the list identified analogues of the prototype, as the closest in the totality of the characteristics of the analogue, allowed to identify the set of essential in relation to claimed by the applicant the technical result of the distinguishing features in the claimed object set forth in the claims.

Therefore, the claimed invention meets the requirement of "novelty" under applicable law.

To verify the conformity of the claimed invention to the requirements of the inventive step, the applicant conducted an additional search for known solutions in order to identify features that match the distinctive features of the claimed invention, the results of which show that the claimed invention does not follow explicitly from the prior art, as the prior art defined by the applicant, the effect of the transformations provided for by the essential features of the claimed invention is not revealed In order to achieve a technical result, in particular, the claimed invention does not provide for the following transformations:

- the addition of a known means by any known part, attached to it according to known rules, to achieve a technical result, in respect of which the influence of such additions is established;

- replacement of any part of a known product with another known part to achieve a technical result, in respect of which the effect of such a replacement is established;

- the exclusion of any part of the funds with the simultaneous exclusion of the function due to its presence and the achievement of the usual result for such exclusion;

- an increase in the number of elements of the same type to enhance the technical result due to the presence in the tool of just such elements;

- the implementation of a known tool or part of a known material to achieve a technical result due to the known properties of the material;

- the creation of a tool consisting of known parts, the choice of which and the relationship between them are based on known rules, and the technical result achieved in this case is due only to the known properties of the parts of this object and the relationships between them.

Therefore, the claimed invention meets the requirement of "inventive step" under applicable law.

The drawings show a diagram of an implementation of the inventive method, where Fig.1 shows a General view of the device; figure 2 is a view along arrow a in figure 1; figure 3 is a section along b - B in figure 1 along the water curtain.

The proposed device contains a conduit 1 of a closed rectangular shape, which is installed on the launch site 2 coaxially with the gas stream 3 of the rocket engine 4 on the supporting posts 5. The internal cavity of the conduit 1 is divided by a partition 6 into two separate chambers 7 and 8 with individual supply pipes 9 water. On the upper 10 and lower 11 end surfaces of the chambers 7 and 8, equally spaced slots of outflow 12 of length L are made, forming a closed loop 13 (for example, annular), with each subsequent outflow gap located at an angle α to the previous one, depending on the number of slots forming closed loop, and overlaps the previous slit in length (size l) by at least half the length of the slit of the outflow L.

The claimed invention - the device operates as follows.

The water supplied under pressure to the conduit 1 through the nozzles 9 fills the chambers 7, 8 and flows out of the slots 12 of the conduit 1, forming a hollow water curtain 14 in the form of a closed collection of flat water films around the gas stream 3 of the rocket engine 4 and the launch vehicle 13.

Due to the interaction of the water curtain 14 with the gas stream of the rocket engine 4, its acoustic radiation decreases and, consequently, the acoustic impact on the launch vehicle and its payload is reduced.

Thus, the above information indicates the fulfillment of the following set of conditions when using the claimed invention:

- a tool embodying the claimed invention in its implementation, is intended for use in industry, for example in some areas of mechanical engineering, namely in space rocket technology, where the use of this technical solution is most appropriate;

- for the claimed invention in the form as described in the independent and dependent claims of the claims below, the possibility of its implementation using the means and methods described above or known prior to the priority date is confirmed;

- means embodying the claimed invention in its implementation, are able to ensure the achievement of the perceived by the applicant technical result.

Therefore, the claimed invention meets the requirement of "industrial applicability" under applicable law.

Claims (4)

1. A water supply device for reducing the acoustic impact on the launch vehicle and cooling the gas jet of the rocket engine, comprising a closed-shaped water conduit with water inlets and slots for water supply, wherein the internal water conduit cavity is divided by a partition into two insulated chambers with individual water inlets water, and these slots are made on the upper end surface of one chamber and on the lower end surface of another chamber, ensuring the formation of a rocket engine around a gas jet For a hollow water curtain. 2. The device according to claim 1, in which the conduit has a rectangular cross-section. 3. The device according to claim 1 or 2, in which the conduit is configured to be installed on the supporting posts of the launch structure. 4. The device according to claim 1 or 2, in which the slots form an annular contour so that each subsequent slit overlaps the previous one by at least half the length of the latter.

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