RU2319033C1 - Method of blowing launch vehicle engines with nitrogen and system for realization of this method - Google Patents

Abstract

FIELD: rocketry and space engineering.

SUBSTANCE: in case of non-standard situation before starting of engines, blowing of tail compartments is continued, after which standard blowing is performed; in case of non-standard situation after starting of engines, blowing of fuel line and tail compartments is continued at simultaneous switching-on of emergency oxidizer line blowing, after which standard blowing is performed; in case of inflammation before arising of non-standard situation and after occurrence of non-standard situation, blowing of tail compartments is continued before start of engine plants and simultaneously oxidizer fire line blowing is switched-on; in case of inflammation after arising of non-standard situation and after start of engine plants, blowing of fuel line and tail compartments is continued and simultaneously oxidizer fire line is switched on; in case oxidizer emergency line was switched on, it is changed-over for blowing the oxidizer fire line; in case pressure in oxidizer fire line drops below preset limit, bypass pipe line running from fuel line and tail compartments to oxidizer fire line of launch vehicles and spacecraft on launch complexes during preparation for launch is opened. Proposed method is performed with the aid of nitrogen blowing system of launch vehicle engines whose manifolds are made in form of supply lines 19 and 20, four connecting pipe lines 21 thru 24 and four ring-shaped pipe lines: fuel pipe line 25, tail compartment pipe line 26, oxidizer emergency pipe line 27 and oxidizer fire pipe line 28. One supply pipe line 19 is connected with the aid of connecting pipe lines 21 and 22 with ring-shaped fuel pipe lines and tail compartment pipe line and other supply line is connected with ring-shaped oxidizer emergency pipe line and oxidizer fire pipe line; each ring-shaped pipe line 25 thru 28 is connected with launch vehicle modules A, B, C, D, E by means of supply pipe lines. System is provided with two pneumatic pressure control boards 29 and 30; control board 29 is connected with supply lines 19 and 20 at points between pneumatic valves 4 and 6, 7; 5 and 8,9 before connection of bypass pipe line 1 and with bypass pipe line 1; control board 30 is connected with supply pipe lines 10 thru 13 to unit D of launch vehicle which is farthest from pneumatic valves. All pneumatic valves are normally-closed.

EFFECT: enhanced reliability at preparation stage of launch vehicles and at launching them from launch complexes.

3 cl, 4 dwg, 1 Fig

Description

The proposed invention relates to rocket and space technology, and more specifically to methods and means of purging the engines of launch vehicles and controlling them during regular operations at ground-based launch complexes.

A known method of pressurization of tanks, carried out by a system of pressurization of containers with compressed gas according to the description of the invention to AS No. 666373, cl. F17C 7/00, 1979.

The known method consists in boosting the capacities of launch vehicles and spacecraft at launch complexes during the preparation for launch. The system that implements the known method consists of several parallel delivery lines, each of which includes a receiver connected in series, a pneumatic valve, a check valve and a control line with pneumatic automation elements. However, these method and system for pressurizing containers with compressed gas do not provide the possibility of re-starting the launch vehicle engines on space-rocket complexes in case of emergency situations.

A known method of purging engines, carried out by a system of purging engines, as described in the book "Launchers" under the general editorship of prof. S.O. Osipova. M .: Military publishing house of the Ministry of Defense, 1981, - 315 s, see p. 218-219. The known method consists in purging the engines of launch vehicles in preparation for launch at space-rocket complexes. The system implementing the known method consists of cylinders with a supply of high-pressure gas, manifolds, valves and pipelines for supplying gas to the engines.

However, the known method and system of purging engines do not provide the ability to re-start the engines of launch vehicles in case of emergency and passing the command "Emergency Shutdown of Engines (AED)".

There is also known a method and system for purging the engines of launch vehicles as described in patent No. 2270929, IPC 6: F02K 9/00, B64G 5/00, 02/27/2006, which are closest in technical essence and achieved effect to the claimed technical solution.

The known method consists in the regular purge of the engines of launch vehicles at the launch complex during the prelaunch preparation for launch and at the start-up phase, abnormal purge during the passage of the “AED” command and purge in the event of a fire. The system that implements this method consists of air and nitrogen receivers, manifolds with pneumatic valves installed in them, non-return valves and jets, a bypass pipeline with pneumatic valve and non-return valve and supply pipelines to the launch vehicle blocks.

The indicated method and purge system are adopted as prototypes. The disadvantage of the prototypes is that they do not provide purging along the fuel line in case of fire, uniform distribution of gas to the blocks of the launch vehicle, and control of the parameters of the emitted gas.

The technical result of the invention is to increase reliability at the stage of preparation for launch and at launch of launch vehicles from launch complexes.

The required technical result is achieved by the fact that in the method of nitrogen purging the rocket engines, which consists in regular purges along the fuel line and tail compartments during preparation for launch, emergency purges in the event of an emergency and fire purges in the event of a fire, in the event of an emergency before starting the engines, they continue to purge the tail compartments, after which regular purges are carried out, and in case of an emergency after starting the engines, they continue wiring along the line of fuel and tail compartments and at the same time turn on purging along the emergency line of the oxidizer, after which regular purging is carried out, in case of fire before an emergency occurs and after an emergency occurs before starting the propulsion systems, they continue to blow through the tail compartments and simultaneously turn on purging along the fire line of the oxidizer and in case of fire after an emergency and after starting the propulsion systems continue to purge along the fuel line and tail compartments and at the same time they turn on purging along the oxidizer fire line, and if purging along the oxidizer emergency line was turned on, then it is switched to purging along the oxidizer fire line, and when the pressure in the oxidizer fire line drops below a predetermined value, the bypass pipeline from the fuel line and tail compartments to the fire line is opened oxidizer line.

To implement this method of nitrogen purging the rocket engines, a nitrogen purging system for the launch rocket engines is proposed, consisting of lines of fuel, oxidizer and tail compartments, which are connected to each other by the bypass pipe, pneumatic valve and non-return valve manifolds with pneumatic valves installed in them, connected to pipelines of supply to the launch vehicle blocks, check valves and jets, while the collectors are made in the form of delivery lines, four connecting and four three ring pipelines: a fuel pipeline, a tail compartment pipe, an emergency oxidizer pipe and an oxidizer fire pipe, one of the delivery lines is connected via connecting pipelines to the ring pipelines of the fuel and tail compartments, and the other to the ring emergency pipelines of the oxidizer and the oxidizer fire pipe, and each from annular pipelines connected to each of the launch vehicle blocks by means of supply pipelines with return circuits installed in them valves and jets, moreover, the pipelines for supplying fuel, tail compartments and the emergency piping for supplying oxidizer are equipped with nozzles, and the emergency and fire pipelines for supplying oxidizer are equipped with check valves and are connected to each other at the point behind them, while the system is equipped with two pressure control pneumatic panels, one of which connected to each delivery line at a point between the pneumatic valves before connecting the bypass pipe and to the bypass pipe equipped with a nozzle installed between the pneumatic valves a valve and a non-return valve at a point between the jet and a non-return valve, and the second air shield is connected to each of the supply pipelines to the booster unit farthest from the pneumatic valves, at the points behind the nozzles on the fuel and tail compartments, at the point in front of the non-return valve on the oxidizer supply fire line and at the point between the nozzle and the non-return valve on the emergency oxidizer supply line, and in the delivery line connected to the oxidizer annular pipelines, between the pneumatic valve At the same time and a connection point for the bypass pipe, a non-return valve is installed, and all pneumatic valves are made normally closed.

Distinctive features from the prototype are that in the event of an emergency before starting the engines, they continue to purge the tail compartments, after which regular purges are carried out, and in the event of an emergency after starting the engines, they continue to purge along the fuel line and tail compartments and simultaneously include an emergency purge oxidizer lines, after which regular purges are carried out, in case of fire before an emergency occurs and after an emergency occurs before starting engine systems continue to purge the tail compartments and simultaneously turn on purging along the oxidizer fire line, and in case of fire after an emergency and after starting the propulsion systems, purges continue along the fuel line and tail compartments and simultaneously turn on purging along the oxidizer fire line, if purge was switched on on the emergency line of the oxidizer, then it is switched to purge on the fire line of the oxidizer, while with a pressure drop in the fire line of the oxidizer below the rear Nogo open the bypass conduit from the fuel line and the tail sections oxidant in the fire line. In addition, in the nitrogen purge system of launch vehicle engines, the collectors are made in the form of delivery lines, four connecting and four ring pipelines: a fuel pipeline, a tail compartments pipeline, an emergency oxidizer pipe and an oxidizer fire pipe, one of the delivery pipes is connected via ring pipelines pipelines of fuel and tail compartments, and the other with the annular emergency pipeline of the oxidizer and the fire pipeline of the oxidizer, and each Each of the annular pipelines is connected to each of the rocket launcher units through the supply pipelines, the fuel supply pipelines, tail compartments and the emergency oxidizer supply piping being equipped with nozzles, and the emergency and fire oxidizing piping are equipped with check valves and interconnected at the point after them, the system is equipped with two pressure control pneumatic panels, one of which is connected to each delivery line at the point between the pneumatic valves before connecting the bypass pipe water and with a bypass pipe equipped with a nozzle installed between the pneumatic valve and the non-return valve at a point between the nozzle and the non-return valve, and the second pneumatic shield is connected to each of the supply pipelines to the booster unit farthest from the pneumatic valves, at points beyond the nozzles on the supply pipelines fuel and tail compartments, at the point in front of the check valve on the fire line of the oxidizer supply and at the point between the jet and the check valve on the emergency line of the oxidizer supply, in the delivery line connected to the annular pipelines of the oxidizing agent, a non-return valve is installed between the pneumatic valve and the connection point of the bypass pipe, and all pneumatic valves are normally closed.

The authors are not aware of technical solutions with the essential features given in the distinguishing part of the formulas.

The system that implements the proposed method is illustrated by drawings, in which Fig. 1 shows the lines, connecting and ring pipelines of the system, Fig. 2 shows the pipelines of the supply of the system for blocks A, B, C, D, Fig. 3 shows the pipelines of the supply of the system for block G, figure 4 presents the sequence diagram of the system with the launch vehicle.

The nitrogen purge system of launch vehicle engines consists of a fuel line “G”, an oxidizer line, including an emergency oxidizer line “O1”, a fire line of an oxidizer “O” and a line of tail compartments XO, which communicate with each other through a bypass pipe 1 (figure 1 ), pneumatic valve (PC) 2, non-return valve (OK) 3 manifolds with PC 4 ... 9 installed in them, connected to supply pipelines 10 ... 13 (Fig. 3), OK 14, 15 and nozzles 16 .. .eighteen. The collectors are made in the form of pipelines 19, 20, four connecting 21 ... 24 and four annular pipelines: pipeline "G" 25, pipeline ХО 26, emergency pipeline "O1" 27 and fire pipeline "O" 28. One of the delivery pipelines 19 is connected through connecting pipelines 21, 22 to the annular pipelines "G" and XO, and the other 20 to the annular pipelines "O1" and "O", and each of the annular pipelines 25 ... 28 is connected to each of the blocks A, B, B, D, D of the launch vehicle through the supply line. The pipelines for supplying fuel 10, tail compartments 11 and the emergency piping for supplying oxidizer 14 are provided with nozzles 15 ... 18, and the emergency 10 and fire 15 pipelines for supplying oxidizer are equipped with OK 14, 15 and connected to each other at point “a” behind them. The system is equipped with two pneumatic pressure control panels (1SCHKD, 2SCHKD) 29, 30, one of which (1SCHKD) 29 is connected to each delivery line 19, 20 at points "b", "c" between the PCs 4 and 6, 7, respectively; 5 and 8, 9 before connecting the bypass pipe 1 and with the bypass pipe 1, equipped with a nozzle 31 installed between PC 2 and OK 3 at point “d” between the nozzle 31 and OK 3, and the second (2SCHKD) 30 is connected to each of the pipelines supply 10 ... 13 to the block G of the launch vehicle farthest from the pneumatic valves at points "e", "f" behind the nozzles 16, 17 on the pipelines for the supply of fuel 10 and tail compartments 11, at point "g" before OK 15 on the fire line for the supply of oxidizer 13 and at point “h” between the nozzle 18 and OK 14 on the emergency pipeline of the oxidizer 12. In the master whether issuance between the PC 20 and the point 5 «k» bypass duct connecting one set Ok 32. All PC performed normally closed. All PCs are controlled by supplying control air through electro-pneumatic valves (EPCs). Figure 1 shows two such EPAs 33, 34, respectively controlling PC 4, 5.

A specific example of the implementation of the proposed method and system for purging with nitrogen the launch vehicle (LV) engines will be considered during the launch of the launch vehicle from the ground launch complex.

In preparation for launching the launch vehicle from the ground-based launch complex after completion of fueling with fuel components, regular nitrogen purges of the launch vehicles through the fuel line (Purge command) and the tail compartments (Start command) are carried out by nitrogen, for which PC 4 is opened by supplying control air through EPK 33 and further PC 6, 7. Compressed nitrogen from a single receiver of compressed gases (not shown) under a pressure of about 12 MPa along the delivery line 19, through connecting pipelines 21, 22, ring pipelines 25, 26 and supply pipelines 10, 11 through nozzles 16, 17 where nitrogen throttled to a pressure of about 6.5 ... 7.5 MPa, enters the blocks A, B, C, D, D PH. The control air pressure, nitrogen pressure in the delivery line 19 is controlled by 1SCHKD 29, consisting of pressure sensors and signaling devices, and the nitrogen pressure control in the supply pipelines 10, 11 to the PH block farthest from the PC (block G is such block) is 2SCHKD 30 At the same time, pressure sensors record gas pressure in the delivery line and supply pipelines. If the pressure differs from the preset working one, a signal passes about the failure of the corresponding technological operation.

After completion of regular purges, the nitrogen supply to the LV blocks stops, for which purpose removing the supply of control air closes PCs 4, 6, 7 and launches the LV from the launch complex.

In the event that the LV engines do not reach the specified operating mode or other types of failures, the command for "AED" passes to the "Lift Contact (KP)" command. In the period from "AED" to a restart, emergency engine purges are carried out. Let's consider two possible emergency situations: “AED” before starting engines and “AED” after starting engines.

In the event of an emergency before starting the engines, the CW purge is resumed, for which PC 4 and then PC 7 are opened by supplying control air. Compressed nitrogen on the delivery line 19, through the connecting pipe 22, the annular pipe 26, the supply pipe 11 and the nozzle 17, where it is throttled to a given pressure, it enters the pH blocks. After emergency purges and preventive measures, regular purges are carried out and the launch vehicle is launched.

In the event of an emergency after starting the engines, purges on the G and XO lines are continued or resumed, for which supply of control air through EPK 33 opens PC 4 and then PC 6, 7. Compressed nitrogen at a pressure of about 12 MPa along delivery line 19, through connecting pipelines 21, 22, annular pipelines 25, 26 and supply pipelines 10, 11 through jets 16, 17, where nitrogen is throttled to a pressure of about 6.5 ... 7.5 MPa, it flows to blocks A, B, C, G, D PH. The control air pressure, nitrogen pressure in the delivery line 19 is controlled by 1SCHKD 29, consisting of pressure sensors and signaling devices, and the nitrogen pressure control in the supply pipelines 10, 11 to the PH block farthest from the PC (block G is such block) is 2SCHKD 30 At the same time, pressure sensors record the real gas pressure in the delivery line and supply pipelines. If the pressure differs from the preset working one, a signal passes about the failure of the corresponding technological operation. Simultaneously with the purges along the “G” and XO lines, they include purging along the emergency line “O1”, for which PC 5 and then PC 8 are opened by supplying control air. Compressed nitrogen at a pressure of about 2.8 MPa along delivery line 20, through a connecting pipe 23 , emergency ring pipeline “O1” 28, supply pipe 12, nozzle 18, where it is throttled to a pressure of 0.8 MPa, and OK 14 enters the PH blocks. The control air pressure, nitrogen pressure in the line 20 is also controlled by 1SCHKD 29, which consists of pressure sensors and signaling devices, and the nitrogen pressure in the supply line 12 to the PH block farthest from the PC (such block is block G) is 2SCHKD 30. When this pressure sensors record the gas pressure in the delivery line and supply pipelines. If the pressure differs from the preset working one, a signal passes about the failure of the corresponding technological operation. After emergency blowdowns, preventive measures are also taken and regular blowdowns are carried out again, after which, by removing the control air supply, PCs 4 ... 9 are closed and the launch vehicle is launched.

In the process of preparation and at the stage of launching the launch vehicle from ground launch complexes, fire may occur in separate launch vehicle blocks. Consider possible situations during a fire: fire before an emergency occurs, fire after an emergency before turning on the engines, and fire after an emergency and after turning on the engines.

In the event of a fire before an emergency and after an emergency, before starting the engines, the purge of the exhaust gas is continued or resumed, for which PC 4 and then PC 7 are opened by supplying control air. Compressed nitrogen on the delivery line 19, through the connecting pipe 22, the annular pipe 26, the supply pipe 11 and the nozzle 17, where it is throttled to a predetermined pressure, enters the pH blocks. At the same time, blowdown is started along the fire line “O”, for which PC 5 and then PC 9 are opened by supplying control air. Compressed nitrogen from a single receiver of compressed gases (not shown) at a pressure of about 2.8 MPa along the delivery line 20, through a connecting pipe 24, the fire ring pipeline "O" 27, the supply pipe 13 and OK 15 enters the PH blocks. The emergency and fire oxidizer supply pipelines are combined into a common supply pipeline to the PH blocks at point “a” behind OK 14, 15. Installation of OK on the supply pipelines is necessary for separation of pipelines with different operating pressures. The control air pressure, nitrogen pressure in the delivery line 20 is also controlled by 1SCHKD 29, which consists of pressure sensors and signaling devices, and the nitrogen pressure control in the supply line 13 to the PH block farthest from the PC (such block is block G) is 2SCHKD 30 At the same time, pressure sensors record gas pressure in the delivery line and supply pipelines. If the pressure differs from the preset working one, a signal passes about the failure of the corresponding technological operation. Connecting 2SCHKD to the oxidant supply pipelines is carried out to OK, which allows you to determine the real pressure in each line.

In the event of a fire after an emergency and after starting the engines, purging is continued or resumed along the “G” and XO lines, for which PC 4 and then PC 7 are opened by supplying control air. Compressed nitrogen through the delivery line 19, through a connecting pipe 22, an annular pipe 26 , the supply pipe 11 and the nozzle 17, where it is throttled to a predetermined pressure, enters the pH blocks. At the same time as purging along the G and XO lines, they include purging along the fire line O, for which PC 5 and then PC 9 are opened by supplying control air. Compressed nitrogen at a pressure of about 2.8 MPa along delivery line 20, through connecting pipe 24 , fire ring pipeline "O" 27, the supply pipe 13 and OK 15 enters the pH blocks. If purge on the oxidizer emergency line “O1” was previously turned on, then it is switched to fire purge on the oxidizer line “O”, for which PC 8 is closed by removing the control air pressure and PC 9 is opened by supplying control air. Compressed nitrogen under a pressure of about 2 , 8 MPa along the delivery line 20, through the connecting pipe 24, the fire ring pipe "O" 27, the supply pipe 13 and OK 15 enters the PH blocks. In this case, the pressure is controlled by 2SCHKD 30.

At the end of the purge by removing the supply of control air, close all PCs. After purging during ignition in separate LV blocks, the latter is removed from the starting position and delivered to the assembly and test building to determine the degree of suitability for further operation.

If the pressure in the fire line of oxidizer “O” drops below a predetermined (2.8 MPa), open the bypass pipe 1 and compressed nitrogen from the delivery line “G” and ХО 19, the pressure in which is about 12 MPa, through PC 2, nozzle 31, where it is throttled to a working pressure of about 2.8 MPa, and OK 3 enters the delivery line 20 and then, as intended, to the LV blocks. The nitrogen pressure in the line 20 is controlled by 1SCHKD 29, which is connected to the bypass pipe at the point “α” between OK 3 and the nozzle 31, while if the pressure behind the nozzle 31 exceeds the set pressure, then the 1SCHKD 29 will give a command to refuse this technological operation. At the end of work, PC 2 also closes. The OK 32 installation prevents compressed nitrogen from flowing back into the receiver when opening the bypass pipeline from the “G” line and XO to the “O” line in the event of a drop in pressure in the latter below a predetermined one, that is, the entire volume of bypassed gas is supplied directly to the “O” line, thereby allowing you to maintain the set pressure and nitrogen flow rate to prevent ignition in individual LV blocks, especially after abnormal purges during AED, when the pressure and flow rate in the “O” line may be insufficient.

Thus, the proposed method and system of nitrogen purging of the launch vehicle engines ensures high reliability of the LV launches, guarantee safety at launch complexes due to the uniform distribution of compressed nitrogen to all LV blocks due to the introduction of ring collectors; providing for purging through the “G” line in case of fire; reducing the number of shut-off and control valves (PC, EPK), as well as by separating blowdowns along the “O” line into emergency and fire-fighting valves, they allow controlling pressure in delivery lines and supply pipelines to LV blocks, in particular to block G, as the most remote from shutoff valves (PC).

Currently, design documentation is being developed for the nitrogen purge and fire protection system, which is supposed to be used at the Soyuz in the Guiana Space Center launch complex.

Claims (2)

1. The method of purging with nitrogen the engines of launch vehicles, which consists in regular purges along the fuel line and tail compartments during preparation for launch, emergency purges in the event of an emergency and fire purges in the event of a fire, characterized in that in the event of an emergency before starting engines continue to purge the tail compartments, after which regular purges are carried out, and in the event of an emergency after starting the engines, purges are continued along the fuel line and tail of compartments and simultaneously turn on purging along the emergency line of the oxidizer, after which regular purging is carried out, in case of fire before an emergency occurs and after an emergency occurs before starting the engines continue to purge the tail compartments and at the same time turn on purging along the fire line of the oxidizer, and in case of fire after the occurrence of an emergency situations and after starting the engines continue to purge along the fuel line and tail compartments and at the same time include purging along the fire line oxidize In addition, if purge was activated on the oxidizer emergency line, then it is switched to purge on the oxidizer fire line; in this case, when the pressure in the oxidizer fire line drops below a predetermined value, the bypass pipe is opened from the fuel line and tail compartments to the oxidizer fire line. 2. Nitrogen purge system for launch vehicle engines, consisting of fuel lines, oxidizer and tail compartments, containing manifolds communicating with each other via a bypass pipe, pneumatic valve and check valve, and pneumatic valves connected to the supply pipelines to the launch vehicle blocks; and jets, characterized in that the collectors are made in the form of delivery lines, four connecting and four annular pipelines: a fuel pipeline, a tail pipe of the compartments, the emergency oxidizer pipe and the oxidizer fire pipe, one of the delivery lines is connected via connecting pipelines to the ring pipelines of the fuel and tail compartments, and the other to the ring emergency pipelines of the oxidizer and the oxidizer fire piping, and each of the ring pipelines is connected to each of the blocks launch vehicles by means of supply pipelines with non-return valves and jets installed in them, moreover, fuel supply pipelines, tail pipes from The emergency and fire oxidizer supply pipelines are equipped with nozzles, and the emergency and fire oxidizer supply pipelines are equipped with check valves and interconnected at a point behind them, while the system is equipped with two pressure control pneumatic panels, one of which is connected to each delivery line at the points between the pneumatic valves up to connecting the bypass pipe and with the bypass pipe equipped with a nozzle installed between the pneumatic valve and the non-return valve at the point between the nozzle and the non-return valve, and the second air shield is connected to each of the supply pipelines to the booster unit farthest from the pneumatic valves, at points behind the nozzles on the fuel and tail compartments, at the point in front of the check valve on the oxidizer supply fire line and at the point between the nozzle and the check valve on the emergency oxidizer supply pipe, while in the delivery line connected to the oxidizer annular pipelines, the return valve is installed between the pneumatic valve and the bypass pipe connection point th valve, and all pneumatic valves are normally closed.

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