A thrust control device for a methane rocket engine and a thrust control method

Abstract

The present invention relates to a thrust control device for a methane rocket engine and a thrust control method thereof, and more particularly to a thrust control device for a methane rocket engine and a thrust control method thereof that facilitates thrust control of a rocket by controlling the amount of liquid propellant supplied by providing a thrust control means that moves back and forth according to the amount (quantity) of propellant supplied to adjust the opening and closing area of ​​the propellant inlet and the propellant outlet. The configuration is characterized by comprising: a thrust setting means formed inside one side of the propellant inlet of a housing and moving left and right to set the opening and closing area of ​​the propellant inlet so as to control the amount of propellant supplied; and a thrust control means formed in the middle of the interior of the housing and moving back and forth according to the amount (pressure) of the supplied propellant to adjust the opening and closing area of ​​the propellant inlet and the propellant outlet.

Description

Technology Field

[0001] The present invention relates to a thrust control device for a methane rocket engine and a thrust control method, and more particularly to a thrust control device for a methane rocket engine and a thrust control method that facilitates thrust control of a rocket by controlling the amount of liquid propellant supplied by providing a thrust control means that moves back and forth according to the amount of propellant supplied and controls the opening and closing area of ​​the propellant inlet and the propellant outlet. Background Technology

[0002] Generally, rockets are equipped with a thrust control device to generate thrust under specific conditions pre-set to suit the rocket's characteristics prior to assembly.

[0003] As an example, as shown in FIG. 1, a conventional rocket engine (100) is configured such that a thrust control valve (130) and a thrust control shut-off valve (140) are formed between an oxidizer pump (110) and a pre-burner (120) to control the amount (quantity) of oxidizer supplied to the thrust chamber (150).

[0004] And, above and on one side of the upper part of the pre-burner (120) and thrust chamber (150), a fuel pump (160), a pre-burner (120) that heats fuel supplied from the fuel pump (160), a turbine (170) that extracts energy from the flow of fluid supplied from the pre-burner (120) and converts it into useful work, and a gear (180) formed between the turbine (170) and the oxidizer pump (110).

[0005] In addition, as shown in FIG. 2, a conventional flow control valve (thrust control device) for thrust control comprises a valve body (110) having a flow path (111) formed therein, a first poppet (120) fixedly installed within the valve body (110) having an inlet (121) formed on one side for fluid to flow in and an outlet hole (123) formed for the fluid to flow out to the flow path (111) of the valve body (110), a second poppet (130) fixedly installed within the valve body (110) having an outlet (131) formed on one side for the fluid to flow out and an inlet hole (133) formed for the fluid to flow in from the flow path (111) of the valve body (110), and a first poppet (130) that slides along the outer surface of the first poppet (120) by means of an actuator to cover the outlet hole (123) of the first poppet (120). It includes a sleeve (140) for adjusting the area of ​​the outflow hole (123), and a spool (150) that is slidably provided between the first poppet (120) and the second poppet (130) along the outer surface of the first poppet (120) and the second poppet (130), is elastically supported by the second poppet (130), and slides by the pressure of the fluid flowing into the first poppet (120) to cover the inflow hole (133) of the second poppet (130) and adjust the area of ​​the inflow hole (133).

[0006] In such a conventional flow control valve, pressure is introduced through the through hole (H), and the fluid force is transmitted to the diaphragm plate (151) of the spool (150), causing the spool (150) to move to the right.

[0007] Accordingly, the inlet hole (133) becomes smaller than the initial area. (However, the conventional patent does not explain whether it is completely closed.)

[0008] When an actuator connected to the drive shaft (T) moves the sleeve (140) to the left, the area of ​​the outflow hole (123) increases. (However, the conventional patent does not explain whether it is completely closed.)

[0009] More flow is transmitted through the increased area and pressure is transmitted to the communication hole (153) to counteract the force of the first chamber (C1) and move the diaphragm plate (151) to the left by the force of the spring.

[0010] Accordingly, the area of ​​the inlet hole (133) increases, and the flow rate increases.

[0011] Furthermore, thrust-controllable rockets, such as the reusable launch vehicle developed by SpaceX, have recently been developed. While various concepts of thrust control methods have been researched or patents registered, most describe conceptual rocket thrust control.

[0012] Due to the nature of rockets, where inlet and outlet pressures constantly fluctuate, conventional thrust control systems required real-time adjustment of the thrust control device's trajectory via a separate external actuator to regulate the amount of propellant needed for thrust control (when thrust adjustment is required under arbitrary conditions). This necessitates the integration of complex electronic equipment, actuators, and mechanical devices. Furthermore, since a completely airtight structure is impossible with conventional thrust control systems, a shut-off valve must be used in conjunction with the thrust control device.

[0013] Conventional shut-off valves required a large force to drive the internal poppet valve, so they were operated using a separate pneumatic valve or solenoid valve.

[0014] However, conventional thrust control devices had the problem of complex configuration and increased costs because they required real-time adjustment of the device's trajectory using a separate externally installed drive unit to control the amount of propellant for thrust control (when thrust control is required under arbitrary conditions), which necessitated the combination of complex electronic equipment, drive units, and mechanical devices.

[0015] In addition, conventional thrust control devices cannot have a hermetic structure that completely closes the propellant inlet and propellant outlet, so the Shut-off valve and thrust control device must be used together, which also has the problem of making the structure complex, adding weight, and causing costs to increase. Prior art literature

[0016] Publication No. 10-2010-0027424 The problem to be solved

[0017] Accordingly, the present invention has been devised to solve the above-mentioned problems, and the objective of the present invention is to provide a thrust control device for a methane rocket engine and a thrust control method thereof, which improve combustion efficiency by automatically driving a thrust control valve in response to structurally set propellant supply conditions to automatically control the propellant supply. means of solving the problem

[0018] The present invention for achieving the above-mentioned purpose comprises a thrust control device for a liquid rocket engine, wherein the thrust setting means is formed inside one side of a propellant inlet of a housing and moves left and right to set the opening and closing area of ​​the propellant inlet so as to control the amount of propellant flowing in; and a thrust control means is formed in the middle of the inside of the housing and moves forward and backward according to the amount (pressure) of the supplied propellant to control the opening and closing area of ​​the propellant inlet and the propellant outlet.

[0019] The present invention relates to a thrust control device for a liquid rocket engine, wherein the thrust setting means is composed of a thrust setting valve and a driving means.

[0020] The present invention relates to a thrust control device for a liquid rocket engine, wherein the thrust control means comprises a case, a front thrust control valve poppet, a rear thrust control valve poppet, and a piston and an elastic body formed between the front and rear thrust control valve poppets.

[0021] The present invention relates to a thrust control device for a liquid rocket engine, wherein the case is characterized by having an open flow path formed in the middle portion for the inflow of propellant and an elastic support surface formed inside.

[0022] The present invention relates to a thrust control device for a liquid rocket engine, wherein the forward thrust control valve poppet is characterized by having a closed passage formed in the central portion for the inflow of propellant.

[0023] In addition, the present invention is a thrust control method using a thrust control device for a methane rocket engine, characterized by comprising: (a) a step of supplying propellant to a propellant inlet of a housing; (b) a step of setting the opening / closing area of ​​the propellant inlet to a target value using a driving means; and (c) a step of controlling thrust by controlling the amount of propellant supplied to the propellant inlet of the housing.

[0024] The present invention relates to a thrust control method using a thrust control device for a methane rocket engine, wherein in step (c), when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet is greater than the past (k-1) external supply pressure P1, the rear thrust control valve poppet moves toward the propellant outlet, and the amount of propellant supplied through the propellant inlet is reduced by the difference in the amount of rear thrust control valve poppet moved toward the propellant outlet.

[0025] The present invention relates to a thrust control method using a thrust control device for a methane rocket engine, wherein in step (c), when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet is smaller than the past (k-1) external supply pressure P1, the rear thrust control valve poppet moves in the opposite direction of the propellant outlet, and the amount of propellant supplied through the propellant inlet increases by the difference in the direction of the rear thrust control valve poppet moving in the opposite direction of the propellant outlet.

[0026] The present invention relates to a thrust control method using a thrust control device for a methane rocket engine, wherein in step (c), when the external supply pressure P2 of the current (k) propellant outlet according to the amount of propellant flowing into the propellant inlet is smaller than the external supply pressure P2 of the past (k-1), the amount of propellant supplied through the propellant inlet is reduced by the difference in the movement of the rear thrust control valve poppet toward the propellant outlet. Effects of the invention

[0027] As explained above, the present invention has the effect of simplifying the structure of a methane rocket engine and achieving weight reduction through a simple configuration without complex electrical, electronic, driving, or mechanical devices.

[0028] In addition, compared to conventional technology, the present invention does not require a shut-off, thereby reducing the cost of the thrust control device, and has the effect of simplifying the thrust control system by integrating the shut-off and thrust control functions. Brief explanation of the drawing

[0029] Figure 1 is a schematic diagram showing a conventional thrust control device for a rocket engine. Figure 2 is a schematic cross-sectional view of a conventional flow control valve for a rocket engine. FIG. 3 is a diagram showing the schematic configuration of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 4 is a schematic flowchart of the valve poppet closing during the initial operation of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 5 is a schematic diagram showing the initial parallel state of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 6 is a schematic flowchart of the opening of the valve poppet during the initial operation of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIGS. 7 and 8 are schematic diagrams showing the state in which the area of ​​the propellant inlet and the propellant outlet are adjusted by the thrust setting means during the initial operation of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 9 is an enlarged view of a key part showing the state in which the area of ​​the rear thrust control valve poppet is determined by the initial flow rate setting of the thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 10 is a schematic diagram showing a state in which the piston of a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention performs the function of closing a rear thrust control valve poppet to offset the increased flow rate and automatically control the flow rate. FIG. 11 is an enlarged view of a key part showing the state in which the area of ​​the rear thrust control valve poppet is determined by the initial flow rate setting of the thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 12 is a schematic diagram showing a state in which the area of ​​the rear thrust control valve poppet is determined as in FIG. 11, and the rear thrust control valve poppet of the thrust control device is opened to increase the flow rate by the amount of the reduced flow rate, thereby maintaining it at the same level. FIG. 13 is a schematic diagram showing a state in which the rear thrust control valve poppet according to the present invention is closed to maintain the same flow rate through automatic control. FIG. 14 is a schematic flowchart of a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 15 is a schematic diagram showing the state of supplying propellant to the propellant inlet in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 16 is a schematic diagram showing the state in which a target value is set as a thrust setting means in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 17 is a schematic diagram showing the operating state of the front and rear thrust control valve poppets in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. FIG. 18 shows thrust control P1 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) >>P1 (k-1) This is a schematic flowchart for. FIG. 19 shows P1 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) >>P1 (k-1) This is a diagram schematically showing the operating state of the front and rear thrust control valve poppets under certain conditions. FIG. 20 shows thrust control P1 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) < <P1 (k-1) This is a schematic flowchart for. FIG. 21 shows P1 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) < <P1 (k-1) This is a diagram schematically showing the operating state of the front and rear thrust control valve poppets under certain conditions. FIG. 22 shows thrust control P2 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) >>P2 (k-1) This is a schematic flowchart for. FIG. 23 shows P2 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) >>P2 (k-1) This is a diagram schematically showing the operating state of the front and rear thrust control valve poppets under certain conditions. FIG. 24 shows thrust control P2 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) < <P2 (k-1) This is a schematic flowchart for. FIG. 25 shows P2 in a thrust control method using a thrust control device for a methane rocket engine according to a preferred embodiment of the present invention. (k) < <P2 (k-1) This is a diagram schematically showing the operating state of the front and rear thrust control valve poppets under certain conditions. Specific details for implementing the invention

[0030] Hereinafter, preferred embodiments of the thrust control device for a methane rocket engine and the thrust control method according to the present invention will be described in more detail with reference to the attached drawings.

[0031] Here, components having the same function in all the drawings below use the same reference numerals, and repetitive descriptions are omitted. Additionally, it is specified that the terms described below are defined in consideration of their functions in the present invention and should be interpreted according to their inherent common meanings.

[0032] As shown in FIG. 3, the thrust control device (200) for a methane rocket engine according to the present invention is broadly divided into a thrust setting means (210) and a thrust control means (220).

[0034] The thrust setting means (210) is formed inside one side of the propellant inlet (231) of the housing (230) and moves left and right to set the opening and closing area of ​​the propellant inlet (231), thereby controlling the amount of propellant flowing in.

[0035] To this end, the thrust setting means (210) is composed of a thrust setting valve (211) and a driving means (212) capable of moving the thrust setting valve (211) left and right.

[0036] Here, the driving means (212) is preferably formed inside the propellant inlet (231) formed on one side of the housing (230) of the thrust control device (200).

[0037] Additionally, the propellant inlet (231) and propellant outlet (232) of the housing (230) are formed with an inlet connection part (231a) and an outlet connection part (232a) that are connected to the outside, and a thrust setting valve support part (231b) and a thrust control valve poppet support part (232b) are formed in the inside.

[0038] And, the driving means (212) is preferably composed of a first gear (212a) that is driven by receiving power from a power source (not shown), such as an actuator or a motor, and a second gear (212b) that is coupled to the first gear (212a).

[0039] Here, it is preferable that the first gear (212a) be coupled and fixed to the rotation axis of a fixed power source, and the second gear (212b) be formed to be movable in conjunction with the rotation of the first gear (212a).

[0040] Additionally, the first gear (212a) may be formed as a pinion gear, and the second gear (212b) may be formed as a rack gear.

[0041] The thrust setting valve (211) is coupled to the outside of the thrust setting valve support (231b) formed in the housing (230) so as to be movable by a rail (not shown), etc.

[0042] Additionally, the second gear (212b) of the driving means (212) is coupled to the outside of the thrust setting valve (211) so as to form a single unit, and the first gear (212a) is coupled to the upper surface of the second gear (212b).

[0043] Accordingly, when a power source (not shown), such as an actuator or motor, is operated, the first gear (212a) of the driving means (212) rotates in conjunction with it, and the second gear (212b) and the thrust setting valve (211) move left and right in conjunction with it, so that they come into contact with or separate from the thrust control means (220) to be described later, thereby allowing the opening and closing area of ​​the propellant inlet (231) to be adjusted.

[0045] The thrust control means (220) is formed in the middle of the housing (230) and moves back and forth according to the amount (pressure) of the propellant supplied, thereby controlling the opening and closing area of ​​the propellant inlet (231) and the propellant outlet (232).

[0046] That is, the thrust control means (220) is formed between the propellant inlet (231) and the propellant outlet (232) of the housing (230) and moves back and forth according to the amount of propellant supplied, thereby controlling the opening and closing area of ​​the propellant inlet (231) and the propellant outlet (232).

[0047] To this end, the thrust control means (220) comprises a case (221), a front thrust control valve poppet (222) formed on one side inside the case (221), a rear thrust control valve poppet (223), a piston (224) and an elastic body (225) formed between the front and rear thrust control valve poppets (222) and (223).

[0048] Additionally, a first chamber (C1) for receiving a fluid such as a propellant is formed between the front thrust control valve poppet (222) and the piston (224), and a second chamber (C2) for receiving a fluid such as a propellant is formed between the rear thrust control valve poppet (232) and the piston (224).

[0049] Here, the front and rear thrust control valve poppets (222) and (223) are designed to perform the function of a completely closed valve by applying the poppet method, which is already widely used for shut-off.

[0050] The above case (221) has an open channel (221a) formed in the middle portion for the inflow of propellant, and an elastic support surface (221b) formed inside to support one end of the elastic body (225).

[0051] Additionally, the forward thrust control valve poppet (222) has a closed passage (222a) formed in the central part for the longitudinal flow of propellant.

[0052] In the thrust control means (220) of this configuration, the propellant is supplied through the propellant inlet (231) of the housing (230), so that the external pressure supplied is greater than the internal pressure of the housing (230), resulting in a state where P1 > 0. The propellant is then introduced into the closed passage (222a) formed in the front thrust control valve poppet (222), and a fluid force equal to the difference between the external pressure P1 supplied and the force of the elastic body (225) is transmitted to the piston (224), causing the rear thrust control valve poppet (223) to close without a separate driving device.

[0053] Conversely, if the propellant is supplied through the open channel (221a), the external supply pressure P1 is transmitted, causing a force equilibrium to occur, and the force of the elastic body (225) alone Rear thrust control The valve poppet (223) is opened again so that the propellant is supplied to the propellant outlet (232).

[0055] As shown in FIGS. 4 and 5, the thrust control device (200) for a liquid rocket engine according to the present invention has an initial state in which there is no propellant in the propellant inlet (231) of the housing (230), and the rear thrust control valve poppet (223) is separated from the propellant outlet (232) by the elastic support force of the elastic body (225), so that the propellant outlet (232) is open.

[0056] And, as shown in FIGS. 5 and 6, when the external pressure is supplied to the propellant inlet (231) of the housing (230) and the external pressure is greater than the force of the elastic body (225) in the state P1 > 0, the propellant is delivered to the closed passage (222a), and a fluid force equal to the difference between the external pressure P1 and the force of the elastic body (225) is delivered to the piston (224), causing the rear thrust control valve poppet (223) to close without a separate driving device.

[0057] Also, the rear thrust control valve poppet (223) is It is characterized by the ability to perform the function of a completely closed valve by applying the poppet method, which is already widely used for shut-off.

[0058] Additionally, as shown in FIG. 8, when a power source (not shown), such as an actuator or a motor, is operated, the first gear (212a) of the driving means (212) rotates in conjunction with this, and the second gear (212b) and the thrust setting valve (211) move left and right in conjunction with this, thereby allowing the opening and closing area of ​​the propellant inlet (231) to be adjusted.

[0059] At this time, the propellant is introduced into the open channel (221a) and the external supply pressure P1 is transmitted, causing a force equilibrium to occur, so that the force of the elastic body (225) alone The rear thrust control valve poppet (223) It opens again and the propellant is discharged through the propellant outlet (232).

[0060] If the external supply pressure P1 changes (goes down or up from the initial level), most conventional technologies require the supply flow rate to decrease, so the rear thrust control valve poppet (223) must be opened further using a separate control system. However, the present invention is automatically controlled without a separate additional driving device.

[0061] That is, by setting the target thrust and moving the thrust setting valve (211) to a desired position, the thrust control means (220) has a structure that allows for the supply of flow to maintain the target thrust by pressure equilibrium within the thrust control means (220) without additional operation of the thrust setting valve (211), even if disturbances occur at the front / rear ends of the thrust control means (220) due to pressure perturbation or the like during engine operation.

[0063] Meanwhile, since the input fluid flow rate and combustion pressure constantly change due to the nature of rockets, real-time propellant control is required; however, by utilizing the mechanical structure of the thrust control device, automatic control is achieved without separate control, and control is required only when a thrust change is necessary.

[0064] In this way, the thrust control device (200) according to the present invention is a device for a rocket engine capable of real-time thrust control during flight. When a desired propellant flow rate is set during flight using a power source (not shown) such as an actuator or a motor, the opening and closing area of ​​the propellant inlet (231) and the propellant outlet (232) is controlled, thereby controlling the flow rate and consequently controlling the thrust.

[0065] Here, the flow rate is given by the following equation ( A The flow rate is determined by :cross-sectional area, :velocity), and the flow rate control technique in the present invention consequently controls the pressure change. The flow rate is calculated using the formula. (Note: The above is for reference only for understanding; the valve's flow rate formula requires general reference.)

[0066] in other words, Change in flow rate according to change in Change it to offset the amount of flow rate fluctuation.

[0067] In the flow rate control of the present invention, disturbance (referring to an external action that attempts to subtract the controlled amount value from the target value in a control system) exists in two conditions: when the propellant inlet (upstream) (231) changes, or when the propellant outlet (downstream) (232) changes.

[0068] First, the conditions under which the flow path area of ​​the propellant inlet (upstream) (231) changes can be explained as shown in FIGS. 9 and FIGS. 10.

[0069] That is, the area of ​​the rear thrust control valve poppet (232) is determined by the initial flow rate setting. Under the conditions, the pressure of P4 in the first chamber (C1) increases, and the piston (224) performs the function of closing the rear thrust control valve poppet (232) with the fluid force of P4 in the first chamber (C1), thereby automatically controlling to maintain the flow rate by offsetting the increased flow rate.

[0070] Next, the conditions under which the propellant outlet (downstream) (232) changes can be explained as shown in FIG. 11.

[0071] in other words, When the state is Since the flow rate decreases as [value] decreases, relatively in the present invention Increase to offset the reduced flow rate.

[0072] As shown in FIG. 12, the area of ​​the rear thrust control valve poppet (232) is determined by the initial flow rate setting, and If Although the rear thrust control valve poppet (232) according to the present invention is reduced, the rear thrust control valve poppet (232) is further opened to increase the area of ​​the rear thrust control valve poppet (232), and as a result It is automatically controlled so that the flow rate is increased by the amount of the decrease in flow rate, and consequently maintained at the same level.

[0073] on the other way When the state is Since the flow rate increases as [value] increases, relatively in the present invention Reduce it to offset the increased flow rate.

[0074] That is, as illustrated in FIG. 13, the thrust control device for a methane rocket engine according to the present invention automatically closes the rear thrust control valve poppet (232). It is automatically controlled to reduce the flow rate and consequently maintain the same flow rate.

[0076] A thrust control method using the thrust control device for a methane rocket engine according to the present invention configured as described above will be explained with reference to FIGS. 14 to 24 as follows.

[0077] First, in order to obtain thrust of a liquid rocket equipped with a thrust control device (200) for a liquid rocket engine according to the present invention, as shown in FIG. 14 and FIG. 16,

[0078] (a) Propellant is supplied to the propellant inlet (231) of the housing (230). (S10)

[0079] That is, when the propellant is supplied through the propellant inlet (231) of the housing (230) in a manner that increases or decreases according to the thrust to be controlled, and the propellant supply amount or propellant supply pressure becomes greater than the elastic support force of the elastic body (225) of the thrust control device (200), i.e., P1 > 0, the propellant is delivered to the closed passage (222a) formed in the front thrust control valve poppet (222), and a fluid force equal to the difference in force between the propellant supply amount, i.e., the external supply pressure P1, and the elastic support force of the elastic body (225) is delivered to the piston (224).

[0080] Accordingly, the piston (224) moves to the right and pushes the rear thrust control valve poppet (223) to close the propellant outlet (232) without a separate driving device.

[0081] At this time, the rear thrust control valve poppet (223) is characterized by being able to perform the function of a completely closed valve by applying the poppet method, which is already widely used for shut-off.

[0083] (b) Using the above driving means (212), the opening and closing area of ​​the propellant inlet (231) is set to a target value. (S20)

[0084] That is, as shown in FIG. 17, a power source (not shown), such as an actuator or a motor, is rotated clockwise or counterclockwise to transmit the rotational force to the first gear (212a) of the driving means (212).

[0085] In conjunction with this, the first gear (212a) rotates clockwise or counterclockwise, and in conjunction with this, the second gear (212b) and the thrust setting valve (211) move left and right to adjust the opening and closing area of ​​the propellant inlet (231) so that it comes into contact with or is separated from the front thrust control valve poppet (222) of the thrust control means (220), thereby setting it to a target value.

[0087] (c) The thrust is controlled by adjusting the amount of propellant supplied to the propellant inlet (231) of the housing (230). (S30)

[0088] That is, the amount of propellant supplied through the propellant inlet (231) is increased or decreased according to the required thrust.

[0089] Here, as illustrated in FIGS. 18 and 19, when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet (231) is greater than the past (k-1) external supply pressure P1, an increase in the external supply pressure P1 flowing through the propellant inlet (231) occurs due to disturbance (disturbance: refers to an external action in a control system that attempts to subtract the controlled amount value from the target value).

[0090] And, the P4 pressure of the first chamber (C1) increases compared to the previous pressure, and fluid force is transmitted to the piston (224) by the difference in previous pressure, that is, the difference in fluid force.

[0091] As a result, the piston (224) is pushed to the right, and in conjunction with this, the rear thrust control valve poppet (223) moves toward the propellant outlet (232).

[0092] The amount of propellant supplied through the propellant inlet (231) is reduced by the difference in the direction of the rear thrust control valve poppet (223) moving toward the propellant outlet (232).

[0093] In other words, the increase in flow rate due to the increase in pressure is offset by the decrease in area, thereby offsetting the difference in flow rate.

[0094] Accordingly, the thrust control means (220) located between the propellant inlet (231) and the propellant outlet (232) can maintain a state and a constant flow rate of the set state by generating a balance of forces.

[0096] Also, as shown in FIGS. 20 and 21, when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet (231) is smaller than the past (k-1) external supply pressure P1, a decrease in the external supply pressure P1 of the propellant inlet (231) occurs due to disturbance (disturbance: refers to an external action in a control system that attempts to subtract the controlled amount value from the target value).

[0097] And, the external supply pressure P4 of the first chamber (C1) is reduced compared to the previous pressure, and fluid force is transmitted to the piston (224) by the difference from the previous pressure, that is, the difference in fluid force.

[0098] As a result, the piston (224) is pushed to the left, and in conjunction with this, the rear thrust control valve poppet (223) moves in the opposite direction of the propellant outlet (232).

[0099] The amount of propellant supplied through the propellant inlet (231) increases by the difference in the direction in which the rear thrust control valve poppet (223) moves opposite to the propellant outlet (232).

[0100] In other words, the decrease in flow rate due to the decrease in pressure is offset by the increase in area, thereby compensating for the difference in flow rate.

[0101] Accordingly, the thrust control means (220) located between the propellant inlet (231) and the propellant outlet (232) can maintain a state and a constant flow rate of the set state by generating a balance of forces.

[0103] Additionally, as shown in FIGS. 22 and 23, when the external supply pressure P2 of the current (k) propellant outlet (232) is greater than the external supply pressure P2 of the past (k-1) according to the amount of propellant flowing into the propellant inlet (231), an increase in the external supply pressure P2 of the propellant outlet (232) occurs due to disturbance (disturbance: refers to an external action in a control system that attempts to subtract the controlled amount value from the target value).

[0104] And, the fluid force is transmitted to the rear thrust control valve poppet (223) by the difference in previous pressure, that is, the difference in fluid force.

[0105] As a result, the rear thrust control valve poppet (223) is pushed to the left, thereby opening the propellant outlet (232).

[0106] The amount of propellant supplied through the propellant inlet (231) increases by the difference in the direction in which the rear thrust control valve poppet (223) moves opposite to the propellant outlet (232).

[0107] In other words, the decrease in flow rate due to the increase in pressure is offset by the increase in area, thereby compensating for the difference in flow rate.

[0108] Accordingly, the thrust control means (220) located between the propellant inlet (231) and the propellant outlet (232) can maintain a state and a constant flow rate of the set state by generating a balance of forces.

[0110] And, as shown in FIGS. 24 and 25, when the external supply pressure P2 of the current (k) propellant outlet (232) is smaller than the past (k-1) external supply pressure P2 according to the amount of propellant flowing into the propellant inlet (231), a decrease in the external supply pressure P2 of the propellant outlet (232) occurs due to disturbance (disturbance: refers to an external action in a control system that attempts to subtract the controlled amount value from the target value).

[0111] And, the fluid force is transmitted to the rear thrust control valve poppet (223) by the difference in previous pressure, that is, the difference in fluid force.

[0112] As a result, the rear thrust control valve poppet (223) is pushed to the right and closes the propellant outlet (232).

[0113] The amount of propellant supplied through the propellant inlet (231) is reduced by the difference in the direction of the rear thrust control valve poppet (223) moving toward the propellant outlet (232).

[0114] In other words, the increase in flow rate due to the decrease in pressure is offset by the decrease in area, thereby offsetting the difference in flow rate.

[0115] Accordingly, the thrust control means (220) located between the propellant inlet (231) and the propellant outlet (232) can maintain a state and a constant flow rate of the set state by generating a balance of forces.

[0117] Therefore, by configuring a simple thrust control device without complex electrical, electronic, driving, or mechanical components, the present invention simplifies the structure of a rocket engine. Compared to conventional technology, it eliminates the need for a shut-off mechanism, thereby enabling cost reduction and engine weight reduction. Furthermore, by integrating the shut-off and thrust control functions compared to conventional technology, it simplifies the control system and allows for expanded application not only to methane rockets but also to rocket systems using liquid propellants.

[0118] The present invention described above is not limited by the aforementioned embodiments and attached drawings, and it will be obvious to those skilled in the art that various substitutions, modifications, and changes to equivalent alternative embodiments are possible within the scope of the technical concept of the present invention. Explanation of the symbols

[0119] 200: Thrust control device for methane rocket engine 210: Thrust setting means 211: Thrust setting valve 212: Driving means 212a: 1st gear 212b: 2nd gear 220 : Thrust control means 221 : Case 221a: Open channel 221b: Elastic support surface 222: Forward thrust control valve poppet 222a: Closed passage 223: Rear thrust control valve poppet 224: Piston 225 : Elastomer 230 : Housing 231: Propellant inlet 231a: Inlet connection 231b: Thrust setting valve support 232: Propellant outlet 232a: Outlet connection 232b: Thrust control valve poppet support C1: 1st chamber C2: 2nd chamber

Claims

Claim 1 A thrust control device for a liquid rocket engine, characterized by comprising: a thrust setting means formed inside one side of a propellant inlet of a housing and moving left and right to set the opening and closing area of ​​the propellant inlet so as to control the amount of propellant flowing in; and a thrust control means formed in the middle of the interior of the housing and moving forward and backward according to the amount (pressure) of the supplied propellant to control the opening and closing area of ​​the propellant inlet and the propellant outlet. Claim 2 A thrust control device for a liquid rocket engine according to claim 1, characterized in that the thrust setting means comprises a thrust setting valve and a driving means. Claim 3 A thrust control device for a liquid rocket engine according to claim 1, wherein the thrust control means comprises a case, a front thrust control valve poppet, a rear thrust control valve poppet, and a piston and an elastic body formed between the front and rear thrust control valve poppets. Claim 4 A thrust control device for a liquid rocket engine according to paragraph 3, characterized in that the case has an open flow path formed in the middle part for the inflow of propellant and an elastic support surface formed inside. Claim 5 A thrust control device for a liquid rocket engine according to paragraph 3, characterized in that the forward thrust control valve poppet has a closed passage formed in the central part for the inflow of propellant. Claim 6 A thrust control method using a thrust control device for a methane rocket engine, characterized by comprising: (a) a step of supplying propellant to a propellant inlet of a housing; (b) a step of setting the opening / closing area of ​​the propellant inlet to a target value using a driving means; and (c) a step of controlling thrust by adjusting the amount of propellant supplied to the propellant inlet of the housing. Claim 7 A thrust control method using a thrust control device for a methane rocket engine, characterized in that, in step (c) above, when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet is greater than the past (k-1) external supply pressure P1, the rear thrust control valve poppet moves toward the propellant outlet, and the amount of propellant supplied through the propellant inlet is reduced by the difference in the amount of rear thrust control valve poppet moved toward the propellant outlet. Claim 8 A thrust control method using a thrust control device for a methane rocket engine, characterized in that, in step (c) above, when the current (k) external supply pressure P1 according to the amount of propellant flowing into the propellant inlet is smaller than the past (k-1) external supply pressure P1, the rear thrust control valve poppet moves in the opposite direction of the propellant outlet, and the amount of propellant supplied through the propellant inlet increases by the difference in the direction of the rear thrust control valve poppet moving in the opposite direction of the propellant outlet. Claim 9 A thrust control method using a thrust control device for a methane rocket engine, characterized in that, in step (c) above, when the external supply pressure P2 of the current (k) propellant outlet according to the amount of propellant flowing into the propellant inlet is smaller than the external supply pressure P2 of the past (k-1), the amount of propellant supplied through the propellant inlet is reduced by the difference in the movement of the rear thrust control valve poppet toward the propellant outlet.

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