CN116044609A - Engine propellant self-balancing discharge device and design method thereof - Google Patents

Engine propellant self-balancing discharge device and design method thereof Download PDF

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CN116044609A
CN116044609A CN202211630667.0A CN202211630667A CN116044609A CN 116044609 A CN116044609 A CN 116044609A CN 202211630667 A CN202211630667 A CN 202211630667A CN 116044609 A CN116044609 A CN 116044609A
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CN116044609B (en
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张众
赵俊淇
纪彦宇
于泽游
马晨曦
张�成
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Shanghai Aerospace System Engineering Institute
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/46—Feeding propellants using pumps
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation

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Abstract

The invention provides a simple and efficient engine propellant self-balancing discharge device and a design method thereof based on the requirement of reducing the propellant discharge interference of a pump system before restarting a liquid rocket engine, wherein the device comprises the following components: the structure of the discharge pipe adopts a discharge mode of plugging balance holes which are arranged at two sides of the end socket in opposite directions; the design principle of the installation layout of the discharge pipe requires that no or reduced shielding object is arranged in the 120-degree cone angle range of the outlet of the discharge pipe, and the direction of the discharge port is vertical to the plane where the axes of the discharge pipe and the arrow body are positioned; according to different numbers of engines, the plane formed by the outlet axis of the discharge pipe and the longitudinal axis of the arrow body and the pitch/yaw plane of the arrow body form different included angles, and the propellant discharge pipe with large discharge force or large outlet shielding objects is close to the longitudinal axis of the arrow body so as to reduce the moment arm. The invention realizes the self-balancing of the engine propellant discharge force, and avoids the adverse effect of the interference force generated in the discharge process on the rocket attitude; and the structure is simple, and engineering application is convenient.

Description

Engine propellant self-balancing discharge device and design method thereof
Technical Field
The invention belongs to the technical field of liquid rocket engines, and relates to an emission device suitable for reducing the interference of propellant emission of a pump system to the attitude of a rocket body before restarting the rocket engine.
Background
The multiple starting technology of the liquid rocket engine is an effective means for improving the carrying capacity of the rocket. For the main-flow pumping type engine, in the previous working, the temperature of the turbine structure of the turbine pump of the engine is increased to a higher level, and when the engine is restarted, the temperature of a pump cavity is higher due to heat conduction between the turbine and the pump, so that the temperature of the flowing propellant in a starting section is higher and even is vaporized, the requirements of the pumping system on non-air-clamping starting and self cooling of a thrust chamber cannot be met, the cavitation of the pump of the engine or the abnormal starting time sequence of the thrust chamber can be caused, and even other faults such as local burning-through of a combustion chamber wall and an injector can be caused in serious cases. To solve this problem, a propellant discharge system is generally provided, and the temperature of the pump chamber is lowered by propellant liquid discharge before restarting, so that the engine is started again reliably.
In the propellant discharging process, the magnitude of the discharging force is dynamically changed, the direction of the vector of the discharging force is related to the actual machining pointing precision of the discharging port, even under the condition of designing symmetrical discharging, the disturbing force to the pitching, yawing and rolling directions of an arrow body can be generated due to various deviations, and the disturbing force occurs in a sliding section with smaller control moment of the attitude control spray pipe, so that adverse effects are brought to the stable attitude of the arrow body, even the unstable attitude of the arrow body is caused when the problem is serious, and the launching task is disfavored.
With the wide application of multiple starts of the liquid rocket engine, on one hand, the propellant discharge is required to be reliably completed to create good conditions for restarting, on the other hand, the discharge device is optimally designed, and the interference of the discharge force on the posture of the rocket body is reduced.
At present, the propellant discharge systems at home and abroad are generally complex in design, symmetrical discharge has high requirements on the machining and mounting precision of discharge pipes, and the interference caused by random change of discharge force can not be effectively solved.
No description or report of similar technology is found at present, and similar data at home and abroad are not collected.
Disclosure of Invention
The invention aims to provide a self-balancing engine propellant discharge device and a design method thereof.
An engine propellant self-balancing discharge apparatus and method of designing the same, the apparatus and method comprising:
the oxidant discharge pipe is separately arranged from the fuel discharge pipe and is led to the outlet of the engine pump system;
one end of the oxidant discharge pipe adopts a blanking cover, and one end of the fuel discharge pipe adopts a blanking cover to respectively block the two side split balance hole structures, so that self-balancing of thrust generated by a discharge medium is realized;
the direction of the balance hole of the discharge pipe is vertical to the plane where the axes of the discharge pipe and the arrow body are positioned, and no or reduced shielding object exists within the 120-DEG cone angle range;
the installation layout requirement is that in a single engine state, a plane formed by the axis of the tail section discharge pipe with the balance hole and the longitudinal axis of the arrow body forms an included angle of 45 degrees with the plane of the pitch axis and the yaw axis of the arrow body, so that unbalanced force is distributed in the pitch direction and the yaw direction, and the difficulty of overcoming interference is reduced;
in the state of double engines, when the two engines are positioned on the arrow I-III reference yaw shaft, a plane formed by the axis of the tail section discharge pipe provided with the balance hole and the longitudinal axis of the arrow is positioned on the plane of the yaw shaft, and the propellant discharge pipe with large discharge force or multiple outlet shields is close to the longitudinal axis of the arrow so as to reduce the moment arm and reduce potential interference.
The invention provides a design method of a self-balancing discharge device of an engine propellant, which is characterized by comprising the following steps:
step 1: according to the restarting emission requirement of the engine, designing propellant emission parameters and pipeline structures;
step 2: according to the layout of the engine, the trend and the installation layout of a propellant discharge pipeline are designed;
step 3: according to the structural size and layout trend of the propellant discharge pipeline, the size and direction of the self-balancing opening are designed;
step 4: analyzing the change of the state of the medium in the propellant discharge process, and confirming whether the self-balancing hole is blocked; according to the extreme working condition of 'ice blockage' caused by the fact that the propellant is vaporized and cooled at one side of the self-balancing opening, the disturbance moment is simulated and analyzed, and compared with the control moment of the attitude control spray pipe, the attitude stability margin is determined.
Preferably, the step 1 includes: according to the requirements of propellant discharge quantity before restarting engine, said requirements include 21kg of oxidant and 7kg of fuel, combining with discharge medium pressure 0.4MPa, defining that the discharge time is 12s and the internal diameter size of discharge pipe is oxidant
Figure BDA0004005596470000031
Fuel->
Figure BDA0004005596470000032
Preferably, the step 2 includes: for an engine layout state, the plane formed by the outlet axis of the exhaust pipe and the longitudinal axis of the arrow body forms an included angle of 45 degrees with the plane of the pitch axis and the yaw axis of the arrow body; the layout design can distribute the residual unbalanced force after self-balancing in the pitching direction and the yawing direction, reduce the difficulty of overcoming interference and increase the stability margin.
Preferably, the step 2 includes: for the states of the two engines, the two engines are set to be positioned on the arrow I-III reference yaw shaft, the plane formed by the outlet axis of the discharge pipe and the longitudinal axis of the arrow is positioned on the plane of the yaw shaft, and meanwhile, the discharge pipe of the propellant components with large discharge force or large outlet shielding objects is close to the longitudinal axis of the arrow so as to reduce the moment arm, reduce possible interference and increase stability margin.
Preferably, the axial direction of the tail section of the discharge pipe forms an angle of 45 degrees with the axis of the arrow body.
Preferably, the step 3 includes: the outlet of the discharge pipe adopts a structure of end head plugging two side-by-side balance holes, and the diameters of the holes of the balance holes are according to70-80% of the inner diameter of the pipeline is taken as an oxidant
Figure BDA0004005596470000033
Fuel->
Figure BDA0004005596470000034
The total flow area is not lower than the discharge pipe flow area.
Preferably, the design should be such that no or reduced shielding occurs within a 120 ° cone angle of the discharge port of the discharge tube medium, and the direction of the discharge port should be perpendicular to the plane of the discharge tube and the arrow axis.
Drawings
FIG. 1 is a schematic diagram of an oxidant discharge port single-sided "ice blockage" extreme condition in a dual-engine state of the present invention;
FIG. 2 is an engine exhaust duct structure of the present invention;
FIG. 3 is a single engine state rocket discharge tube exit layout of the present invention;
FIG. 4 is a dual engine state rocket discharge tube exit layout of the present invention.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
An engine propellant self-balancing discharge apparatus and method of designing the same, the apparatus and method comprising:
the oxidant discharge pipe 1 is arranged separately from the fuel discharge pipe 4 and is led to the outlet of the engine pump system;
one end of the oxidant discharge pipe 1 adopts a blanking cover 2, one end of the fuel discharge pipe 4 adopts a blanking cover 5 to respectively block the two side split balance holes 3 and 6, so that the self-balance of the thrust generated by the discharged medium is realized;
the direction of the balance hole (phie in fig. 2b and phid in fig. 2 c) of the discharge pipe is perpendicular to the plane of the axes of the discharge pipes 1,4 and the arrow body, and no or reduced shielding is arranged within the 120 DEG cone angle range;
the installation layout requirement is that in a single engine state, a plane formed by the axis of the tail section discharge pipe provided with a balance hole (phi e in fig. 2b and phi d in fig. 2 c) and the longitudinal axis of the arrow body forms an included angle of 45 degrees with the plane of the pitch axis and the yaw axis of the arrow body, unbalanced force is distributed in the pitch direction and the yaw direction, and the difficulty in overcoming interference is reduced, as shown in fig. 3;
in the double engine state, when two engines are positioned on the arrow body I-III reference yaw shaft, a plane formed by the tail section exhaust pipe axis with balance holes (phi e in fig. 2b and phi d in fig. 2 c) and the arrow body longitudinal axis is positioned on the plane of the yaw shaft, and a propellant exhaust pipe (fig. 2 b) with large exhaust force or large outlet shielding object is close to the arrow body longitudinal axis so as to reduce the moment arm and reduce potential interference, as shown in fig. 4.
The invention also provides a design method of the engine propellant self-balancing discharge device, which comprises the following steps:
step 1: according to the restarting emission requirement of the engine, designing propellant emission parameters and pipeline structures;
step 2: according to the layout of the engine, the trend and the installation layout of a propellant discharge pipeline are designed;
step 3: according to the structural size and layout trend of the propellant discharge pipeline, the size and direction of the self-balancing opening are designed;
step 4: analyzing the change of the state of the medium in the propellant discharge process, and confirming whether the self-balancing hole is blocked; according to the extreme working condition of 'ice blockage' caused by the fact that the propellant is vaporized and cooled at one side of the self-balancing opening, the disturbance moment is simulated and analyzed, and compared with the control moment of the attitude control spray pipe, the attitude stability margin is determined.
The invention will now be described in detail by way of example with reference to the accompanying drawings in which a self-balancing discharge device for engine propellant is implemented.
1. Step 1
According to the requirements of propellant discharge amount (21 kg of oxidant and 7kg of fuel) before restarting the engine, combining the discharge medium pressure of 0.4MPa, determining discharge time (12 s) and discharge pipe size (inner diameter of oxidant)
Figure BDA0004005596470000051
Figure BDA0004005596470000052
Fuel->
Figure BDA0004005596470000053
)。
2. Step 2
Determining the trend and the installation layout of the exhaust pipe according to the layout state of the engine:
for an engine layout state, the plane formed by the outlet axis of the exhaust pipe and the longitudinal axis of the rocket body forms an included angle of 45 degrees with the plane of the pitching axis and the yaw axis of the rocket body, and the layout design can distribute the residual unbalanced force after self-balancing in the pitching direction and the yaw direction, so that the difficulty in overcoming interference is reduced, and the stability margin is increased;
for the two engine states (two engines are set to be positioned on the arrow I-III reference yaw axis), the plane formed by the outlet axis of the discharge pipe and the longitudinal axis of the arrow is positioned on the plane of the yaw axis, and meanwhile, the discharge pipe of the propellant component with large discharge force or large outlet shielding object is close to the longitudinal axis of the arrow so as to reduce the moment arm, reduce possible interference and increase stability margin.
In order to further reduce the disturbance moment, the axial direction of the tail section of the discharge pipe forms an included angle of 45 degrees with the axis of the arrow body.
3. Step 3
The outlet of the discharge pipe adopts a structure of end head plugging two side-by-side balance holes, and the diameters of the balance holes are 70% -80% of the inner diameter of the pipeline, so that the balance holes are determined as oxidizing agents
Figure BDA0004005596470000054
Fuel->
Figure BDA0004005596470000055
The total flow area is not lower than the discharge pipe flow area.
The design should meet that the 120-degree cone angle range of the medium outlet of the discharge pipe has no or reduced shielding, and the direction of the outlet is perpendicular to the plane of the axis of the discharge pipe and the arrow body.
4. Step 4
In the case that all outlets are normally discharged, in theory, both the thrust generated by the discharge outlet and the interference force generated by the plume after discharge are offset by symmetrical arrangement, and no additional interference force or moment is generated.
The vacuum discharge tests at home and abroad show that: the higher the temperature, the greater the outlet air content and the greater the plume angle; the larger the outlet pipe diameter, the larger the flash surface, the larger the outlet gas content and the larger the plume angle. As shown in table 1, 9 times of vacuum discharge time are performed in a certain unit in China, different discharge interval tests are performed, dinitrogen tetroxide can be smoothly discharged in a heating state and a non-heating state, no icing blocking phenomenon occurs, after discharge, due to gasification heat absorption, icing phenomenon occurs at a discharge port, but the normal operation of the next discharge is not affected by icing.
Table 1 results of 9 vacuum discharge tests performed at a certain unit in China
Figure BDA0004005596470000061
The discharge test results of different pipe diameters carried out by other units show that the larger the pipe diameter is, the more the temperature of the propellant is reduced, but no icing and blocking phenomenon occurs in the discharge process of phi 4 to phi 10. Comparison of plume angle images of different pipe diameters shows that the larger the pipe diameter is, the larger the plume angle is, see table 2.
Table 2 domestic test conditions of different pipe diameters of other units
Figure BDA0004005596470000062
Based on the above results, the self-balancing discharge hole (oxidizer
Figure BDA0004005596470000071
Fuel->
Figure BDA0004005596470000072
) No discharge blockage phenomenon occurs.
In order to further ensure stable and controlled attitude, analysis is carried out on extreme working conditions of two engine state discharge icing blockage. According to theoretical and experimental studies, the oxidant emission disturbance force is significantly greater than that of fuel, so analysis with the oxidant emission regime can cover fuel emissions. FIG. 1 shows that the oxidant discharge ports are subjected to severe rolling conditions, namely, the oxidant discharge ports of two extensions are subjected to axisymmetric blocking, so that the most severe rolling disturbance moment is generated.
Since the moving speed of the solid along with the fluid is small in the gas, liquid and solid three-phase flow, the influence of solid particles is not considered in the calculation of the thrust of the propellant discharge, and only the gas and the liquid in the pipeline are considered. The discharge pipe orifice is used for simultaneously discharging gas-liquid two-phase flow to generate thrust. The outlet discharge force can be obtained according to formula (1):
F＝ρ m u m A·u m ……………………………………(1)
wherein, the gas-liquid mixing density ρ m ＝αρ g +(1-α)ρ l Gas-liquid mixing speed
Figure BDA0004005596470000073
A is the outlet cross-sectional area ρ g Density of gas phase ρ l Liquid phase density, alpha is aeration rate (gas volume fraction), u l For the outlet liquid phase velocity, u g Is the outlet gas phase velocity.
Analyzing the rolling direction moment closest to the disturbance force and the control force, wherein the gas volume fraction is alpha=0.83, the gas-liquid mixing density is 246.65kg/M3, the gas-liquid mixing outlet speed is 38.2M/s, the outlet section is phi 7.5mm, therefore, the thrust of a single oxidation stage discharge outlet is 15.9N by utilizing a thrust formula (1), the rolling moment arm is calculated to be 0.346M by considering the 3 DEG installation angle of the engine, the rolling moment generated by two oxygen discharge outlets is Mx= 11.003Nm, and the value is smaller than the moment M of a rolling attitude control spray pipe nozzle = 12.852Nm, so in the worst case of disturbance, the arrow body pose is still controllable with a stability margin of 16.8%.
The self-balancing discharging device can meet the restarting and discharging requirements and the posture stability requirements of the rocket engine, and has a large safety margin.
The invention realizes the self-balancing of the engine propellant discharge force, and avoids the adverse effect of the interference force generated in the discharge process on the rocket attitude; and the structure is simple, and engineering application is convenient.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.

Claims (8)

1. An engine propellant self-balancing discharge apparatus and method of designing the same, the apparatus and method comprising:
the oxidant discharge pipe (1) is arranged separately from the fuel discharge pipe (4) and is led to the outlet of the engine pump system;
one end of the oxidant discharge pipe (1) adopts a blanking cover (2), one end of the fuel discharge pipe (4) adopts a blanking cover (5) to respectively block the two sides of the oxidant discharge pipe with a structure with balance holes (3 and 6) which are oppositely opened, so that self-balancing of thrust generated by a discharge medium is realized;
the directions of the balance holes (3, 6) of the discharge pipe are vertical to the planes of the discharge pipes (1, 4) and the axes of the arrow body, and no or reduced shielding object exists in the 120 DEG cone angle range;
the installation layout requirement is that in a single engine state, a plane formed by the axis of the tail section discharge pipe provided with a balance hole (phi e in fig. 2b and phi d in fig. 2 c) and the longitudinal axis of the arrow body forms an included angle of 45 degrees with the plane of the pitch axis and the yaw axis of the arrow body, unbalanced force is distributed in the pitch direction and the yaw direction, and the difficulty in overcoming interference is reduced, as shown in fig. 3;
in the double engine state, when two engines are positioned on the arrow body I-III reference yaw shaft, a plane formed by the tail section exhaust pipe axis with balance holes (phi e in fig. 2b and phi d in fig. 2 c) and the arrow body longitudinal axis is positioned on the plane of the yaw shaft, and a propellant exhaust pipe (fig. 2 b) with large exhaust force or large outlet shielding object is close to the arrow body longitudinal axis so as to reduce the moment arm and reduce potential interference, as shown in fig. 4.
2. A method of designing a self-balancing exhaust device for an engine-out propellant as claimed in claim 1, the method comprising:
step 1: according to the restarting emission requirement of the engine, designing propellant emission parameters and pipeline structures;
step 2: according to the layout of the engine, the trend and the installation layout of a propellant discharge pipeline are designed;
step 3: according to the structural size and layout trend of the propellant discharge pipeline, the size and direction of the self-balancing opening are designed;
step 4: analyzing the change of the state of the medium in the propellant discharge process, and confirming whether the self-balancing hole is blocked; according to the extreme working condition of 'ice blockage' caused by the fact that the propellant is vaporized and cooled at one side of the self-balancing opening, the disturbance moment is simulated and analyzed, and compared with the control moment of the attitude control spray pipe, the attitude stability margin is determined.
3. The method for designing a self-balancing discharge apparatus for an engine-out propellant as recited in claim 2, wherein said step 1 comprises: according to the requirements of propellant discharge quantity before restarting engine, said requirements include 21kg of oxidant and 7kg of fuel, combining with discharge medium pressure 0.4MPa, defining discharge time as 12s and discharge pipe size as oxidant internal diameter
Figure FDA0004005596460000021
Fuel->
Figure FDA0004005596460000022
4. The method of designing a self-balancing exhaust device for an engine-out propellant as recited in claim 2, wherein said step 2 comprises: for an engine layout state, the plane formed by the outlet axis of the exhaust pipe and the longitudinal axis of the arrow body forms an included angle of 45 degrees with the plane of the pitch axis and the yaw axis of the arrow body; the layout design can distribute the residual unbalanced force after self-balancing in the pitching direction and the yawing direction, reduce the difficulty of overcoming interference and increase the stability margin.
5. The method of designing a self-balancing exhaust device for an engine-out propellant as recited in claim 2, wherein said step 2 comprises: for the states of the two engines, the two engines are set to be positioned on the arrow I-III reference yaw shaft, the plane formed by the outlet axis of the discharge pipe and the longitudinal axis of the arrow is positioned on the plane of the yaw shaft, and meanwhile, the discharge pipe of the propellant components with large discharge force or large outlet shielding objects is close to the longitudinal axis of the arrow so as to reduce the moment arm, reduce possible interference and increase stability margin.
6. The method of designing a self-balancing exhaust device for engine propellant as recited in claim 2, wherein the end portion of the exhaust tube is axially oriented at an angle of 45 ° to the axis of the rocket body.
7. The method of designing a self-balancing exhaust device for an engine-out propellant as recited in claim 2, wherein said step 3 comprises: the outlet of the discharge pipe adopts a structure of end head plugging two side-by-side balance holes, and the diameters of the balance holes are 70% -80% of the inner diameter of the pipeline, so that the balance holes are determined as oxidizing agents
Figure FDA0004005596460000023
Fuel->
Figure FDA0004005596460000024
The total flow area is not lower than the discharge pipe flow area. />
8. The method of designing a self-balancing exhaust apparatus for an engine propellant as recited in claim 2, wherein the design is such that no or reduced shielding is provided within a 120 ° cone angle of the medium outlet of the exhaust duct, the outlet being oriented perpendicular to the plane of the exhaust duct and the arrow axis.
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