RU2815457C1 - Method for elements of launch vehicle discharger by supplying liquid - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: equipment for rocket launching systems, in particular a method for cooling elements of a launch vehicle discharger. To do this, when the launch vehicle is launched, the coolant constantly circulates through the heat removal channels in the metal lining of the launcher flue. The liquid is supplied simultaneously with the start of the propulsion system.

EFFECT: cooling of the elements of the starting device and ensuring their long-term operation.

1 cl, 2 dwg

Description

The invention relates to equipment for missile launch systems, in particular to a method for reducing temperature loads on elements of the launch device.

During the launch of a launch vehicle, the technological equipment of the system and structures of the launch rocket complexes operate under very specific conditions, which is determined by the action of a number of characteristic loads. These include, first of all, the high-temperature effects of a gas jet during launch of the launch vehicle propulsion system. Also, the physical picture of the loading processes occurring near the launch equipment before the launch of the propulsion system during launch of the launch vehicle complicates the spilling of rocket fuel components and filling the space of the gas ducts with their vapors. This negatively affects the technical condition and the possibility of long-term operation of both the elements of the launch equipment themselves and the elements of the launch structure.

To neutralize such factors, a special composition can be additionally introduced through the pipes of this cooling system along with water. Such a mixture will compensate for the negative impact of vapors of rocket fuel components and the high-temperature effects of a gas jet on both the technological equipment of the launch complex and the elements of the launch structure, which will also increase the operating time of this equipment. This solution is most relevant when using toxic components of rocket fuels at the launch complex.

Currently, a number of methods and devices are known to reduce launch loads on the launch vehicle and elements of the launch complex.

A known system for cooling the gas jet of a launch complex rocket engine includes pipelines laid from a container with water to nozzles equipped with slotted nozzles installed on the launch table, through the conduits of which water is supplied to cool the gas reflector (see the book "Technological objects of ground-based infrastructure of rocket and space technology" (engineering manual) under the general editorship of Doctor of Technical Sciences, Professor I.V. Barmin. Moscow, 2005).

The system involves introducing a cooling water flow through a pipe into the center of the supersonic gas jet of the launch vehicle propulsion system after it exits the engine nozzle.

It is designed to protect the gas reflector from the effects of high-temperature gas flow, as well as to cool this flow and protect the tail section of a space rocket.

Also known is the “Method of reducing launch loads on a launch vehicle during its launch,” which includes the creation of a closed water curtain around the tail section of the launch vehicle and a jet of combustion products (RF Patent No. 2320883, IPC F02K 1/34, A62C 2/08, B64G 5 /00, dated 2006).

In this case, water is supplied up and down parallel to the launch vehicle and the gas jet in the form of a water film of a closed annular shape.

The disadvantage of this method is that it only reduces the acoustic loads on the launch vehicle during its launch; it also provides protection for the equipment installed on the launch pad and elements of the launch structure located behind the water curtains.

All of the above methods involve the use of coolant supply pipes mounted on the frame of the starting device. In the case of cooling the gas jet of the propulsion system, the water flow is introduced into the center of the supersonic jet under the nozzle of the propulsion system. When performing the task of reducing the acoustic load on the launch vehicle and elements of the launch equipment, the water flow spreads to create a water curtain under the tail section of the launch vehicle.

This does not allow us to say that the problem of long-term operation of the launch equipment and launch facility, and specifically the gas ducts of the launch device, is completely solved. Therefore, a new method is proposed for cooling the elements of the launch device during launch of a launch vehicle by supplying liquid.

When developing the proposed method for cooling the elements of the launch device during the launch of a launch vehicle, the method of cooling the chamber of liquid rocket engines is taken into account (see “Design and design of rocket engines”, edited by V.P. Sovetsky. - M.: Mashinostroenie, 1984).

In this case, external flow cooling is used to cool the walls of the combustion chambers of liquid rocket engines (LPRE). With this cooling method, heat flows are removed from the chamber walls using a coolant flowing through a cooling path of an appropriate shape inside the walls of the liquid-propellant rocket engine chamber. After the cooling path, the coolant is introduced into the liquid-propellant rocket engine without afterburning through the head into the combustion chamber.

The efficiency of external flow cooling largely depends on the size and shape of the cooling path, which must provide the required values of the cooler speed and heat transfer coefficient from the cooler along the length of the path.

The disadvantage of this method of cooling a liquid-propellant rocket engine chamber is that it can be used in cooling systems only to reduce the temperature loads of liquid-propellant rocket engine chambers that have small overall dimensions.

The closest in technical essence (prototype) to the proposed method of cooling the elements of the launch device during the launch of a launch vehicle by supplying liquid is a method for reducing the destructive effect on the elements of the launch device and the launch structure during the launch of the launch vehicle (see RF patent No. 2773482, IPC A62S 35/00, B64G 5/00, dated 06/06/2022).

The essence of this method and means of protection is to create a film water curtain on the surface of the metal lining of the gas duct of the launching device by supplying water from the opening of the launch structure before starting the engine at the launch of the launch vehicle.

The technical result in this method of protection is achieved by the synchronous construction of film protective dispersed formations on the metal lining of the gas duct of the starting device.

The disadvantage of this method is that it can be used in cooling systems for small-sized structures, since the implementation of the method requires the consumption of significant volumes of water. In addition, launch facilities must additionally be equipped with systems for collecting and neutralizing waste liquid, and water storage systems occupy a significant amount of space in the structures.

All of the above methods do not fully solve the problem of reducing thermal loads on elements of launch equipment and launch structures, which reduces the durability of these objects.

The objective of the proposed invention is to solve the problem of the negative impact of thermal loads of a gas jet of a rocket engine on elements of launch equipment and large launch facilities, in which the technical result will be an increase in the operating time of these elements of the launch complex.

The essence of the proposed method is to create heat-removing channels with a closed loop in the metal lining of the launching device by supplying coolant into them from a supply container located in the launch structure before starting the engine at the launch of the launch vehicle.

The technical result in this method of protection is achieved by cooling the metal lining of the starting device flue due to heat removal by a coolant constantly circulating inside the starting device flue plates.

The essence of the invention can also be illustrated using Figs. 1, 2.

The jet 2 coming out of the nozzle of the propulsion system 1 at the launch of the launch vehicle, in a fraction of a second reaches the metal lining 10 of the gas duct 14 of the launch device, thereby creating a thermal destructive effect on the elements of the launch device and the launch structure 3 in which the launch device is located (Fig. 1 ).

To reduce this thermal effect, coolant is supplied through pipelines 12 to the heat removal channels 11 in the metal lining 10 of the starting device flue (Fig. 2).

Water or a special mixture is used as a coolant.

To create the required pressure in pipeline 4, a system of pumps 9 and shut-off valves 7 and 8 is created (Fig. 1). The necessary supply of coolant to complete the task is stored in container 5, and coolant is supplied from it through filter 6 (Fig. 1). The movement of the coolant inside the metal lining 10 of the gas duct of the starting device is carried out through heat removal channels 11 (Fig. 2) and is carried out in direction 13, which allows for a closed annular circuit of the movement of the coolant (Fig. 1). According to the ring circuit, the coolant through the return pipeline, after completing the task, returns to container 5 (Fig. 1). In this way, it is possible to remove heat from the heating plates of the metal lining 10 of the flue 14 of the starting device (Fig. 1) without additionally creating systems for collecting and neutralizing the waste liquid.

Technically, this method of cooling the elements of the launch device during the launch of a launch vehicle by supplying liquid can be implemented using the technological equipment of the launch complex.

Thus, the proposed method provides a technical result consisting in reducing temperature loads on the elements of the starting device in order to ensure long-term operation of the elements of the starting device and the launch structure.

Claims (1)

A method for cooling the elements of a launch device during the launch of a launch vehicle by supplying liquid, characterized in that constant circulation of the coolant is carried out through heat-removing channels created inside the plates in the metal lining of the gas duct of the launch device, while the coolant is supplied simultaneously with the start of the propulsion system.