RU2703076C1 - Multi-chamber liquid-propellant rocket engine with afterburning with controlled thrust vector - Google Patents

Abstract

FIELD: engine building.

SUBSTANCE: invention relates to multichamber liquid-propellant rocket engines with afterburning and controlled thrust vector. Multichamber liquid-propellant rocket engine with afterburning and controlled thrust vector comprises frame, gas generator, turbo pump unit with pumps, input manifolds of oxidizer and fuel with inlet pipes and installed on them starting valves, several fixed main chambers connected by gas ducts with turbine cavity and lines with cavities of pumps, and control nozzles connected by main lines with start-shutoff valves with turbine pump turbine pump turbine cavity, wherein an additional pump unit is installed with fuel and oxidizer pumps and an electric drive in the form of an electric motor, connected by an electrical system to the installed battery, Inputs of similar components of the latter are connected by mains with start-shutoff valves installed thereon with cavities of inlet branch pipes before start-shutoff valves. Besides, in it the second additional unit is installed with a current generator with a hydraulic turbine, which inlet is connected to a pumping cavity of one of the turbo-pump unit components, and outlet – main line with installed on it starting-shut-off valve with cavity of control element with same name component, and current generator is connected to accumulator by means of feeder with possibility of disconnection at main cameras switching-off.

EFFECT: invention provides expansion of functional capabilities due to operation of control chambers at switched off turbo-pump unit and fixed main chambers and due to conversion of rocket stage to new orbit.

1 cl, 4 dwg

Description

The invention relates to rocket technology, in which the creation of multi-chamber liquid-propellant rocket engines with afterburning with a controlled thrust vector intended for installation in compartments of minimum radial and axial dimensions with a minimum mass, especially the upper stages of launch vehicles, is an urgent task.

Known multi-chamber liquid-propellant rocket engines with controlled thrust vectoring, comprising a frame, a gas generator, a turbopump assembly with pumps, oxidizer and fuel inlet lines with inlet pipes and starting valves mounted on them, several fixed main chambers connected by gas ducts to the turbine cavity and highways with cavities of pumps, and control nozzles connected by highways with start-shut-off valves with a turbine cavity of a turbopump unit (book "Scientific and technical development Works of Salyut Design Bureau 2012-2013 N 34 (Issue 4) Edited by Yu.O. Bakhvalov. M., “Mechanical Engineering-Flight”, pp. 218-223, Fig. 1-6).

In the well-known multi-chamber liquid-propellant rocket engine with controlled thrust vectoring with fixed main chambers, there is no need for flexible pipelines installed on oscillating chambers on generator gas lines with an excess of one of the components with high temperatures and pressures, as well as on the lines of the other component, which allows to reduce engine weight due to the lack of need for nodes of flexible pipelines. However, with a small mass and significant simplicity of the thrust vector control system using control nozzles, such a control system with significant required control efforts, for example, for continuous operation of control nozzles when transferring a rocket stage to a new orbit, becomes uneconomical due to unreasonably large expenses of the generator gas after a turbine with relatively low temperatures for a long time.

Also known is a multi-chamber liquid-propellant rocket engine with controlled thrust vectoring, comprising a frame, a gas generator, a turbopump unit with pumps, oxidizer and fuel inlet lines with inlet nozzles mounted on them by start valves, several fixed main chambers connected by gas ducts to the turbine pump turbine unit and highways with pump cavities, and control chambers equipped with steering machines, connected with highways with start-shut-off valves with cavities behind pumps of a turbopump assembly (see the book by V. A. Aleksandrov et al. Launch vehicles. Under the general editorship of S.O. Osipov Launch vehicles, p. 215) - prototype.

In the well-known multi-chamber liquid-propellant rocket engine with afterburning with a controlled thrust vector with fixed main chambers and swinging control chambers connected by highways with start-shut-off valves with cavities behind the pumps of the turbopump unit, due to the organization of optimal mixing of the components in the control chambers, the components in them burn up when high temperature and pressure, which when organizing reliable cooling of the chambers, it is possible to obtain even greater than the pressure of the generator gas in the turbine cavity high degree of expansion of combustion products in the nozzles of the control chamber, since the selection of the components is carried out from the cavities for the fuel and oxidizer pumps omitting one of the components of the gas generator and the turbine of the turbopump unit.

However, such a multi-chamber liquid-propellant rocket engine with controlled thrust vector during the selection of fuel components from one turbopump unit, both for supplying fixed main chambers and for supplying control chambers equipped with steering machines connected by highways with start-and-shut off valves with cavities behind pumps of a turbopump unit, does not have sufficient functionality that does not allow the control cameras to work when the fixed main cameras are off and, therefore Note that the turbo pump unit is turned off. Such a problem arises when it is necessary to transfer the rocket stage to a new orbit or to the orbit of the stage utilization with the fixed main cameras turned off with relatively traction chambers less traction than the traction of fixed main chambers. In addition, the task of obtaining maximum fuel efficiency is solved precisely with the complete generation of residual fuel components. When the fixed main chambers of large thrusts are in operation and the turbopump unit is operating, full simultaneous production of two fuel components cannot always be obtained without the risk of a multi-chamber liquid propellant rocket engine afterburning with a controlled thrust vector to an uncontrolled mode of operation during the early production of one of the fuel components, which is caused by large component costs on the mode and, consequently, the large possible deviations of their mass costs.

The objective of the proposed invention is to eliminate the above drawbacks and expand the functionality by ensuring the operation of the control chambers with the turbo pump unit turned off and the main chambers stationary and by transferring the rocket stage to a new orbit or into the orbit of the stage utilization with the most complete simultaneous production of fuel components with less risk of getting an off-design impulse of the traction force, although with a smaller spread, during the early development of one of the fuel components.

The above object of the invention is solved by the fact that in the known multi-chamber liquid rocket engine with afterburning with a controlled thrust vector, an additional pumping unit is installed with fuel and oxidizer pumps and an electric drive in the form of an electric motor connected by an electric system to an installed battery, the inputs of the same components are connected by highways with trigger-shut-off valves installed on them with cavity cavities in front of the start-up valves.

The above objective of the invention is also solved by the fact that in the known multi-chamber liquid propellant rocket engine with afterburning with a controlled thrust vector, a second additional unit with a current generator with a hydraulic turbine is installed, the input of which is connected to the drift cavity of one of the components of the turbopump unit, and the output is a trunk with an installed on it with a start-shut-off valve with a cavity of the same component of the control chambers, and the current generator is connected to the battery by means of feeders with the possibility of switching off tions when turning off the main chamber.

The proposed multi-chamber liquid-propellant rocket engine with controlled thrust vector is shown in the drawing (Fig. 1-4, Fig. 1 - pneumohydraulic diagram of the engine with the image of the connections of gas, hydraulic lines with units and the electrical connection of the electric drives of additional pumps and a current generator with battery; Fig. 2 is a top view of a multi-chamber liquid-propellant rocket engine with afterburning with a controlled thrust vector with the image of fixed main cameras, as Ep er of control, additional oxidizer and fuel pumps with electric drives, accumulator; Fig. 3 - general side view (View A) with the image of the accumulator, control cameras and steering machines; Fig. 4 - general axonometric view of a multi-chamber liquid-propellant rocket engine with afterburning with a controlled vector traction with the image of a frame, a turbopump unit, fixed main chambers, control chambers, steering machines, gas ducts, branched highways for supplying fuel and oxidizer to control chambers), where the following Ata:

1. Frame;

2. Gas generator;

3. Turbopump unit;

4. Fuel pump;

5. The oxidizer pump;

6. The input line of the oxidizer;

7. Entrance line of fuel;

8. The inlet pipe of the oxidizing agent;

9. Fuel inlet pipe;

10. Start-shut-off valve of the oxidizer;

11. Starting and shut-off valve for fuel;

12. Fixed main camera;

13. The gas pipeline;

14. The turbine cavity;

15. Turbine;

16. The highway;

17. Start and shut-off valve;

18. Throttle;

19. The cavity of the fuel pump;

20. The trunk of a combustible gas generator;

21. Start-shut-off valve of a combustible gas generator;

22. Regulator;

23. The line of the oxidizer of the gas generator;

24 Start-shut-off valve of the oxidizer of the gas generator;

25. The cavity of the oxidizer pump;

26. Camera control;

27. Branched highway;

28. Start-shut-off valve;

29. Branched highway;

30. Start-shut-off valve;

31. Steering machine;

32. Additional fuel pump;

33. Highway;

34. Start-shut-off valve;

35. Electric drive;

36. Electric drive shaft;

37. Coupling;

38. The shaft of the additional fuel pump;

39. Electric drive system;

40. switch;

41. Battery;

42. The container;

43. Bracket;

44. Additional oxidizer pump;

45. Highway;

46. Start-shut-off valve;

47. Electric drive;

48. Electric drive shaft;

49. Coupling;

50. The shaft of the additional oxidizer pump;

51. Electric drive system;

52. switch;

53. Additional unit;

54. current generator;

55. Hydroturbine;

56. Inlet of a hydraulic turbine;

57. Hydroturbine output;

58. Highway;

59. Start-shut-off valve;

60. The cavity of the combustible control chamber;

61. Feeder.

A multi-chamber liquid-propellant rocket engine with controlled thrust vectoring comprises a frame 1, a gas generator 2, a turbopump unit 3 with fuel pumps 4 and an oxidizer 5, input lines of the oxidizer 6 and fuel 7 with the input pipes of the oxidizer 8 and the input pipes of the fuel 9 and installed on them start-up shut-off valves of the oxidizer 10 and start-shut-off valves of fuel 11. Four fixed main chambers 12 are connected by gas ducts 13 to the turbine cavity 14 of the turbine 15 by highways 16 with the start-cut-off installed on them and valves 17 and a throttle 18 with a cavity 19 of the fuel pump 4. The gas generator 2 is connected to the cavity 19 of the fuel pump 4 by a fuel line 20 with a start-shut-off valve 21 and a regulator 22 installed on it. The gas generator 2 is connected by an oxidizer line 23 with a start-up valve installed on it shut-off valve 24 with a cavity 25 of the oxidizer pump 5. The control chambers 26 are connected by a branched line 27 with a start-shut-off valve 28 installed on it with the cavity of the oxidizer 25 behind the oxidizer pump 5 of the turbopump assembly 3. Control chambers 26 also with They are dindered by a branched trunk 29 with a start-shut-off valve 30 installed with a fuel cavity 19 of the fuel pump 4 of the turbopump assembly 3. The control chambers 26 are equipped with steering machines 31, which are designed to interact with the frame 1 on one side and the control chambers 19 on the other to control the thrust vector. An additional fuel pump 32 is fixed to the frame 1, the input of which is connected by a highway 33 with a start-and-shut off valve 34 installed on it with an fuel inlet pipe 9, with an electric drive 35, the shaft of which 36 is connected through a sleeve 37 to the shaft 38 of the additional fuel pump 32. Electrical system 39 of the electric drive 35 is connected through a switch 40 connected to the missile control system (not shown in FIGS. 1-8), with a battery 41 installed using the container 42 and brackets 43 on the frame 1. An additional oxidizer pump 44 is fixed to the frame 1, in which is connected by line 45 with a start-off valve 46 installed on it with an oxidizer inlet port 8, with an electric actuator 47, the shaft of which 48 is connected through a coupling 49 to the shaft 50 of the additional oxidizer pump 44. The electric system 51 of the electric actuator 47 is connected through a switch 52 connected with a missile control system (not shown in FIGS. 1-8), with a battery 41.

An additional unit 53 with a current generator 54 with a hydraulic turbine 55, the input 56 of which is connected to the cavity 19 of the fuel pump 4 of the turbopump unit 3, and the output 57 of the hydraulic turbine 55 is connected to the trunk 58 with the start-and-shut valve 59 installed on it with the fuel cavity 60 of the control chamber 26 moreover, the current generator 54 is connected to the battery 41 by means of a feeder 61 with the possibility of turning it off at the command of the control system when turning off the fixed main cameras 12.

A multi-chamber liquid propellant rocket engine with controlled thrust vector works as follows. In the main operating mode, the start-shut-off valve of the oxidizer 10 and the start-shut-off valve of the fuel 11 are brought into the open position, the oxidizer and fuel enter the inlet pipes of the oxidizer 8 and the inlet pipes of the fuel 9 to the inputs of the fuel pumps 4 and oxidizer 5, and then after the fuel pumps 4 , one part of the fuel through the regulator 22 and the open start-shut-off valve 21 to the gas generator 2, and the other part through the open throttle 18 and the open start-shut-off valves 17 enters the stationary main chamber 12. After the gas generator 2, the generator gas enters the turbine 15 of the turbopump assembly 3, then from the turbine cavity 14 it enters the gas ducts 13 and into the fixed main chambers 12. From the cavity 19 of the fuel pump 4, the fuel passes through the branched line 29 and the open start-shutoff valve 30 to the control chambers 26, controlled with the help of steering machines 31, and to a hydraulic turbine 55 connected to a current generator 54 to recharge the installed battery 41. From the cavity 25 of the oxidizer pump 5, the oxidizer through the branch line 27 and the open start-shutoff valve 28 enters amers control 26.

The fixed main chambers 12 are turned off by sending a command from the control system (not shown in FIGS. 1-8) to close the start-shut-off valves 10, 11, start-shut-off valves 21 and 24, start-shut-off valves 17. After that, the flow of components is stopped to the gas generator 2, the turbine speed of the turbopump assembly 3 decreases to zero, the pressure behind the fuel pumps 4 and the oxidizer 5 decreases, the start-shut-off valves 21 and 24 are closed, the fixed main chambers 12 stop working, the feeder 56 connected to the control system receives Andu to turn off the electrical part of the current generator 54 and stop charging the battery 41, and the start-shut-off valves 33 and 46 are opened, ensuring the flow of fuel from the fuel inlet pipe 9 in front of the fuel start valve 10 to the input of the additional fuel pump 32 and the oxidizer from the cavity of the inlet pipe oxidizer 8 in front of the start valve of the oxidizer 11 to the input of the additional oxidizer pump 44 while turning on the electric drive 47 of the additional oxidizer pump 44, while of the electric drive 28 of the additional fuel pump 25. The control chambers 26 in this mode work from the additional oxidizer pump 44 and the additional fuel pump 32, the electric drives 35 and 47 of which operate from the accumulator 41, which ensures the transfer of the rocket stage to a new trajectory with small rods of control chambers 26, due to which they ensure sufficient removal accuracy, in addition, they ensure the generation of fuel residues in fuel tanks with lower mass flow rates using an additional fuel pump 32 and will complement ceiling elements oxidant pump 44, the performance of which is considerably smaller than that of the fuel pump 4 and the oxidizer pump 5 turbopump unit 3 fixed to the main chambers 12 on the main mode multichamber liquid rocket engine with afterburning with thrust vector control.

In this case, there is no need to develop a separate autonomous engine with an additional gas generator, a turbopump unit driven by a turbine using generator gas, as well as with additional automation and control units in this case, and there is no need to utilize the generator gas after a turbine with irrational discharge of components.

The application of the proposed invention extends the functionality of a liquid-propellant rocket engine with a controlled thrust vector by providing control chambers with the turbo pump unit and fixed main chambers turned off, generating residual fuel components and ensuring the rocket stage is transferred to a new trajectory with sufficient accuracy with the use of control cameras small rods in the final mode of operation.

Claims (2)

1. A multi-chamber liquid-propellant rocket engine with controlled thrust vectoring, comprising a gas generator, a turbopump unit with pumps, oxidizer and fuel inlet lines with inlet pipes with start-and-shut valves installed on them, several fixed main chambers connected by gas ducts to the turbine cavity and mains with pump cavities and control chambers connected by highways with start-shut-off valves with cavities behind the pumps of the turbopump unit, characterized in that it has an additional pump unit with fuel and oxidizer pumps and electric drive as an electric motor connected to the electrical system with the battery pack attached, the inputs of similar components, which are connected to highways fitted with the balancing and isolation valves with cavities inlets before start-shutoff valves. 2. A multi-chamber liquid-propellant rocket engine with a controlled thrust vector according to claim 1, characterized in that it has a second additional unit with a current generator with a hydraulic turbine, the input of which is connected to the drift cavity of one of the components of the turbopump unit, and the output is connected to a trunk with an installed on it with a start-shut-off valve with a cavity of the same component of the control chambers, the current generator being connected to the battery by means of a feeder with the possibility of shutdown when the main chambers are turned off.

Images