CN117869119A - Low-temperature propellant pressurizing and conveying system and pressure control method thereof - Google Patents
Low-temperature propellant pressurizing and conveying system and pressure control method thereof Download PDFInfo
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- CN117869119A CN117869119A CN202311808092.1A CN202311808092A CN117869119A CN 117869119 A CN117869119 A CN 117869119A CN 202311808092 A CN202311808092 A CN 202311808092A CN 117869119 A CN117869119 A CN 117869119A
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- 239000003380 propellant Substances 0.000 title claims abstract description 261
- 238000000034 method Methods 0.000 title claims abstract description 31
- 238000003860 storage Methods 0.000 claims abstract description 144
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 130
- 239000001301 oxygen Substances 0.000 claims abstract description 130
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 130
- 239000007788 liquid Substances 0.000 claims description 38
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 19
- 230000002265 prevention Effects 0.000 claims description 10
- 238000005192 partition Methods 0.000 claims description 6
- 230000003405 preventing effect Effects 0.000 abstract description 10
- 238000013461 design Methods 0.000 abstract description 4
- 239000000446 fuel Substances 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 18
- 238000010586 diagram Methods 0.000 description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000001105 regulatory effect Effects 0.000 description 4
- 238000004880 explosion Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000001257 hydrogen Substances 0.000 description 2
- 229910052739 hydrogen Inorganic materials 0.000 description 2
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
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- 230000001154 acute effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 230000009977 dual effect Effects 0.000 description 1
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- 238000012423 maintenance Methods 0.000 description 1
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- 239000013585 weight reducing agent Substances 0.000 description 1
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Abstract
The embodiment of the invention provides a low-temperature propellant pressurizing and conveying system and a pressure control method thereof, wherein the system adopts a common-bottom storage tank structure, and a storage tank common bottom divides a container tank into a low-temperature propellant storage tank and an oxygen tank which are stacked up and down; a flow outlet pipe extending obliquely downwards is arranged at the included angle between the inner side wall of the low-temperature propellant storage tank and the common bottom of the storage tank; the outlet pipe is connected with the rocket engine through a propellant conveying main pipeline; the rocket engine is provided with a propellant self-generating supercharger; the rocket engine is also provided with an oxygen self-generating supercharger, and in addition, the embodiment of the invention provides a supercharging control method for preventing the common-bottom storage tank from generating common-bottom back pressure. Through the technical scheme, the low-temperature propellant storage tank and the oxygen tank adopt the form of sharing the bottom storage tank from top to bottom, so that the structural length of the whole rocket is reduced, the structural efficiency of the rocket is improved, meanwhile, the design of the outflow device enables the fuel to be fully utilized, and the design of the main propellant conveying pipeline further improves the use safety.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a low-temperature propellant pressurizing and conveying system and a pressure control method thereof, and more particularly relates to a double-low-temperature propellant pressurizing and conveying system and a pressure control method thereof.
Background
The main function of the pressurizing and conveying system is to convey propellant with certain flow and certain pressure to the inlet of the engine pump in the rocket flight process, and in the whole rocket flow working process, the pressure of the storage tank of the propellant can meet the structural rigidity requirement of the storage tank. At present, low-temperature propellants (liquid methane, liquid hydrogen, and the like) are increasingly widely used.
In the prior art, the low-temperature propellant storage tank and the oxygen tank are respectively two independent tanks, so that the two tanks can be stacked up and down (not directly connected) for saving space, and a tunnel pipe is usually arranged in the middle of the lower tank, and an output pipe of the upper tank passes through the tunnel pipe and directly reaches the rocket engine.
In the process of implementing the present invention, the inventor finds that at least the following problems exist in the prior art:
at this time, a certain space still exists between the low-temperature propellant storage tank and the oxygen tank, so that a certain space waste is caused. Therefore, how to further compress the space between the cryogenic propellant reservoir and the oxygen tank and reduce the volume and weight of the cryogenic propellant booster delivery system is a problem to be solved.
Disclosure of Invention
The embodiment of the invention provides a low-temperature propellant pressurizing and conveying system and a pressure control method thereof, which are used for compressing a space between a low-temperature propellant storage tank and an oxygen tank and reducing the volume and the weight of the low-temperature propellant pressurizing and conveying system.
In order to achieve the above object, in one aspect, an embodiment of the present invention provides a low-temperature propellant booster delivery system, including a container tank and a rocket engine; an arc-shaped storage tank common bottom arched upwards is fixedly connected to the inner side wall of the container tank, and the storage tank common bottom divides the container tank into an upper low-temperature propellant storage tank and a lower oxygen tank; a flow outlet pipe extending obliquely downwards is arranged at an included angle between the inner side wall of the low-temperature propellant storage tank and the common bottom of the storage tank; the outlet pipe is connected with the rocket engine through a main propellant conveying pipeline arranged outside the oxygen tank; the oxygen tank is connected with the rocket engine through a liquid oxygen conveying pipeline; the rocket engine is provided with a propellant self-generating booster, the top in the low-temperature propellant storage tank is provided with a propellant storage tank energy dissipater, and the propellant self-generating booster is connected with the propellant storage tank energy dissipater through a propellant storage tank boosting pipeline; the rocket engine is also provided with an oxygen self-generating supercharger, the top in the oxygen tank is provided with an oxygen tank energy dissipater, and the oxygen self-generating supercharger is connected with the oxygen tank energy dissipater through an oxygen tank supercharging pipeline.
In another aspect, an embodiment of the present invention further provides a method for controlling pressure of a low-temperature propellant booster delivery system, including: pressurizing the air pillow of the low-temperature propellant storage tank through the propellant autogenous pressurizer; pressurizing the air pillow of the oxygen box through the oxygen autogenous pressurizer; the pressure of the air pillow of the low-temperature propellant storage tank is regulated through the pressurizing electromagnetic valve group and the propellant storage tank safety valve, the air pillow of the oxygen tank is regulated through the oxygen tank safety valve, and the air pillow pressure of the oxygen tank is larger than the sum of the air pillow pressure of the low-temperature propellant storage tank and the propellant liquid column pressure in the low-temperature propellant storage tank.
The technical scheme has the following beneficial effects:
in the technical scheme of the invention, the low-temperature propellant storage tank is arranged on the upper part, the liquid oxygen tank is arranged on the lower part, and the upper storage tank and the lower storage tank are connected together through the common bottom of the storage tank, so that the gap between the upper tank and the lower tank commonly existing in the prior art is eliminated, the structure is greatly simplified, the space occupation is reduced, the weight is reduced, the arrow body arrangement is more facilitated, and the carrying capacity is improved. In the storage tank with the storage tank common-bottom type, through a specially designed air pillow pressure control mode and an upward convex storage tank common-bottom structure, the negative pressure working condition in the oxygen tank during the working process can be avoided, and the stability and reliability of the structure are ensured.
In addition, the technical scheme also has the following characteristics:
1) The density of the rocket cryogenic propellant is generally lower than the liquid oxygen density, and the propellant in the propellant conveying main pipeline of the upper tank is unavailable, so that the situation that the upper tank is the cryogenic propellant can greatly reduce the amount of unavailable propellant compared with the conventional mode that the upper tank is liquid oxygen. Therefore, the low-temperature propellant has the structural form of being under the upper liquid oxygen and the lower liquid oxygen, can reduce dead weight of the rocket, and can improve carrying capacity of the rocket.
2) In the technical scheme, the low-temperature propellant pressurizing and conveying system adopts the structure form of the common-bottom storage tank, so that the effective length of the rocket is shortened, and the structural efficiency of the rocket is improved.
3) The utility model discards the prior oxygen box tunnel pipe scheme, and effectively prevents the problem of explosion caused by mixing of low-temperature propellant and oxygen due to leakage of the low-temperature propellant. Meanwhile, the main propellant conveying pipeline is distributed outside the oxygen tank, so that a series of operation difficulties such as installation, maintenance and repair of the main propellant conveying pipeline are reduced.
4) The outflow device in the main propellant conveying pipeline consists of a vortex-preventing plate and a collapse-preventing circular plate, and the unique structural form can effectively inhibit vortex generated by the low-temperature liquid propellant and prevent the collapse of the liquid in the low-temperature propellant conveying process.
5) Compared with the traditional mode of adopting a propellant to convey the main pipeline, the two propellant conveying main pipelines are symmetrical, and liquid propellant is conveyed through the side wall layout in the technical scheme, so that the diameter of the propellant conveying main pipeline can be effectively reduced, the processing difficulty of the propellant conveying main pipeline is reduced, the mutual influence between power systems when 8 engines work together can be reduced, and the hydrodynamic characteristic coupling influence of the power systems is reduced.
6) The embodiment of the invention provides a pressurizing control method and pressurizing control logic for preventing a common-bottom storage tank from generating negative pressure, which can effectively avoid the condition of structural instability and even structural damage caused by the negative pressure generated by the common-bottom storage tank, and ensure the flight safety.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic system diagram of a cryogenic propellant booster delivery system according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of the connection of an oxygen tank to a rocket engine in a cryogenic propellant booster delivery system according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of the arrangement of a main propellant delivery line and a branch propellant delivery line in an embodiment of the present invention;
FIG. 4 is a schematic illustration of the connection of a branch propellant delivery pipe to a five-way pipe in an embodiment of the present invention;
FIG. 5 is a schematic diagram of the internal structure of the five-way valve in the embodiment of the invention;
FIG. 6 is a schematic view of a portion of the interior of a cryogenic propellant reservoir in accordance with an embodiment of the present invention;
FIG. 7 is a schematic diagram of an outflow device according to an embodiment of the invention;
fig. 8 is a schematic structural view of an anti-sloshing apparatus according to an embodiment of the present invention;
FIG. 9 is a diagram of the pressure control band and the remaining pressure profile of the booster solenoid valve block in an embodiment of the invention;
FIG. 10 is a graph showing the pressure and remaining pressure profiles of the oxygen tank air pillow in an embodiment of the present invention;
FIG. 11 is a schematic diagram of control logic of a booster solenoid valve block in an embodiment of the invention;
reference numerals: 1. a low temperature propellant reservoir; 2. an oxygen tank; 3. a rocket engine; 4. a propellant autogenous booster; 5. a filter; 6. a pressurizing electromagnetic valve group; 7. an orifice plate; 8. propellant storage tank energy dissipater; 9. a propellant reservoir safety valve; 10. a propellant reservoir pressure sensor; 11. a propellant reservoir pressurization controller; 12. an oxygen autogenous booster; 13. the oxygen box pressurizing adapter; 14. an oxygen tank energy dissipater; 15. an oxygen tank pressure sensor; 16. an oxygen box safety valve; 17. the storage tanks are shared at the bottom; 18. an anti-shake device; 181. an anti-shake plate; 182. a deflector aperture; 183. a notch; 19. an outflow device; 191. a swirl preventing plate; 192. a collapse-preventing circular plate; 20. a propellant reservoir delivery flange; 21. a propellant delivery main line; 22. five-way; 221. five-way anti-swirling baffle; 222. a five-way shell; 23. a propellant delivery branch pipe; 24. an accumulator; 25. a propellant pump inlet; 26. an oxygen box rear bottom; 27. an oxygen box conveying flange; 28. a liquid oxygen delivery line; 29. and a liquid oxygen pump inlet.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and 2 (in which fig. 2 illustrates the connection of the oxygen tank 2 and the rocket engine 3 separately, so that the low-temperature propellant tank 1 and its related components are not shown in the drawings), the embodiment of the present invention provides a low-temperature propellant pressurizing and conveying system, which comprises a container tank and the rocket engine 3; an arc-shaped storage tank common bottom 17 arched upwards is fixedly connected to the inner side wall of the container tank, and the storage tank common bottom 17 divides the container tank into an upper low-temperature propellant storage tank 1 and a lower oxygen tank 2; a flow outlet pipe extending obliquely downwards is arranged at the included angle between the inner side wall of the low-temperature propellant storage tank 1 and the storage tank common bottom 17; the outlet pipe is connected with the rocket engine 3 through a main propellant conveying pipeline 21 arranged outside the oxygen tank 2; the oxygen tank 2 is connected with the rocket engine 3 through a liquid oxygen conveying pipeline 28; the rocket engine 3 is provided with a propellant self-generating booster 4, the top in the low-temperature propellant storage tank 1 is provided with a propellant storage tank energy dissipater 8, and the propellant self-generating booster 4 is connected with the propellant storage tank energy dissipater 8 through a propellant storage tank pressurizing pipeline; the rocket engine 3 is also provided with an oxygen self-generating booster 12, the top in the oxygen tank 2 is provided with an oxygen tank energy dissipater 14, and the oxygen self-generating booster 12 is connected with the oxygen tank energy dissipater 14 through an oxygen tank boosting pipeline; .
In order to solve the foregoing problems, to reduce the space occupation and the structural weight of the rocket hull section, in this embodiment, the low-temperature propellant tank 1 and the oxygen tank 2 are stacked up and down and are tightly connected, the bottom of the low-temperature propellant tank 1 is the top of the oxygen tank 2 (i.e. the tank common bottom 17), that is, the tank structure shown in fig. 1 is formed (the low-temperature propellant tank 1 and the oxygen tank 2 together form a container tank, an elliptical head is adopted in the middle as the tank common bottom 17, thereby dividing the container tank into two parts, the upper part is filled with the low-temperature propellant, and the lower part is filled with liquid oxygen). The structure can also be called as the structure form of a common-bottom storage tank, and the gap between the upper storage tank and the lower storage tank in the prior art is eliminated, so that the volume is reduced to a great extent, and the aim of the invention is fulfilled. Also, since the cryogenic propellant tank 1 may be used to hold liquid methane or liquid hydrogen, the system may also be referred to as a dual cryogenic propellant booster delivery system.
In order to obtain a better pressure-bearing effect in the pressure container, the pressure-bearing member is generally in an arc-shaped or spherical surface structure, and in the technical scheme, the storage tank common bottom 17 can adopt a ready-made sealing head, and the ready-made sealing head is welded with the side edges of the upper storage tank and the lower storage tank. Moreover, it is necessary to ensure that the tank common bottom 17 is upwardly arched, because if the tank common bottom 17 is downwardly arched, the lowest position thereof is located at the middle position, and the middle position of the tank common bottom 17 is located at the middle position of the low-temperature propellant tank 1 and the oxygen tank 2, at this time, if the low-temperature propellant in the upper low-temperature propellant tank 1 is to be delivered to the engine, only a tunnel tube type scheme of the prior art (i.e., a tunnel tube is opened at the middle of the lower tank, and the output tube of the upper tank passes through the tunnel tube to reach the rocket engine) can be adopted, and this scheme has a disadvantage that if the liquid (low-temperature propellant) in the tunnel tube leaks, the leaked low-temperature propellant is easily accumulated in the tunnel tube of the oxygen tank 2 and cannot be dissipated, and when the concentration is large, the mixture of the gaseous propellant and oxygen can be exploded, so that the scheme of passing through the tunnel tube through the low-temperature propellant delivery tube has safety. In this solution, the tank common bottom 17 is arched upward, and the lowest position thereof is located at the side, that is, the junction between the inner side wall of the low-temperature propellant tank 1 and the tank common bottom 17 (similar to two acute angles of two sides, but actually a ring-shaped area as seen in fig. 1), at which the low-temperature propellant can be led out, so that even if the propellant conveying main pipeline 21 leaks, the leaked low-temperature propellant can be directly discharged out of the atmosphere, is difficult to mix with gaseous oxygen and reaches the explosion limit, and therefore, the safety risk cannot exist.
In this configuration, it is necessary to keep the low temperature propellant reservoir 1 up and the oxygen reservoir 2 down, because: the density of the low-temperature propellant is smaller than that of liquid oxygen, and the liquid column pressure generated by the common bottom part of the storage tank is smaller (P=ρgh), so that the back pressure generated by the common bottom 17 of the storage tank can be prevented (namely, the common bottom 17 of the storage tank is prevented from being changed from upward bulge to downward bulge due to the excessive upper pressure) by only having a lower air cushion pressure in the lower storage tank, and the structure of the stacked storage tank is ensured not to be unstable; if the liquid oxygen is placed in the upper tank, the liquid injection pressure generated by the high density of the liquid oxygen is high, the lower tank needs a high air pillow pressure to ensure that the tank common bottom 17 is not unstable, the tank is a pressure container, and the high air pillow pressure necessarily needs to increase the structural wall thickness to increase the weight and further reduce the rocket payload, so that the best implementation is that the low-temperature propellant tank 1 is arranged above and the oxygen tank 2 is arranged below.
Further, the number of the outflow pipes is two, the number of the propellant conveying main pipelines 21 is two, the two propellant conveying main pipelines 21 are symmetrically arranged at the side of the low-temperature propellant storage tank 1, and each propellant conveying main pipeline 21 is connected with a plurality of rocket engines 3.
The preferred mode is to use two main propellant delivery lines 21 for symmetrical delivery, and to use symmetrical side delivery to average the outflow of low temperature propellant, while the symmetrical mode design maintains the centre of gravity of the delivery tube in the exact centre, which is advantageous for balance.
As shown in fig. 7, further, an outflow device 19 is arranged in the main propellant conveying pipeline 21; the outflow device 19 includes a collapse prevention circular plate 192 perpendicular to the axis of the propellant transportation main pipe 21, and a plurality of swirl prevention plates 191 vertically connected below the collapse prevention circular plate 192; the anti-swirling plates 191 are uniformly distributed in the circumferential direction of the anti-collapse circular plate 192, and a preset gap is reserved between two adjacent anti-swirling plates 191; the outer side of the anti-swirling plate 191 is connected to the inner wall of the propellant conveying main pipe 21; the outer edge of the collapse prevention disc 192 has a predetermined gap with the inner wall of the propellant transportation main tube 21.
When the tank common bottom 17 is arched upwards, a tunnel pipe type conveying scheme with explosion risk is abandoned, and a side conveying mode is adopted, at this time, in the side conveying mode, as the pipe diameter of a main propellant conveying pipeline 21 is relatively small and is not arranged at the lower side of the low-temperature propellant tank 1, at this time, the condition that vortex and liquid collapse occur easily to circulating liquid in the pipeline, particularly at the front end of a flow outlet pipe, is easy to cause the phenomenon that gaseous propellant in the air pillow space at the top of the tank is sucked into liquid flow to generate liquid air inclusion, and the problem influences the normal operation of a rocket engine 3. The structure of the outflow device 19 is shown in fig. 6 and 7, and the outflow device is fixedly connected to the inner wall of the propellant conveying main pipeline 21 through the outer side edge of the anti-swirling plates 191, the anti-swirling plates 191 are unfolded from inside to outside along the radial direction of the pipeline, and enough gaps are reserved between the adjacent anti-swirling plates 191 to enable liquid to pass through, but the plate surface of the outflow device is arranged in a manner that the liquid is prevented from swirling; meanwhile, the collapse prevention circular plate 192 connected to the anti-swirling plate 191 is perpendicular to the flow direction of the liquid, and is located at the middle of the pipe so that the liquid can only flow through the gap between the outer edge of the collapse prevention circular plate 192 and the inner wall of the pipe, but cannot pass through the middle of the pipe, thus preventing the liquid from collapsing (the liquid collapsing is generated at the central part of the liquid surface). The structure ensures the smooth outflow of the low-temperature propellant, thereby ensuring that the low-temperature propellant in the low-temperature propellant storage tank 1 can be utilized to the greatest extent without residue and eliminating the problem of liquid air inclusion.
As shown in fig. 1, further, each main propellant conveying pipeline 21 is connected with four rocket engines 3 through five-way pipes 22; as shown in fig. 5, the five-way housing 22 includes a five-way housing 222 and a five-way swirl baffle 221; the five-way shell 222 comprises a top connecting port and four bottom connecting ports, wherein the four bottom connecting ports are uniformly distributed in the circumferential direction, and the axis of each bottom connecting port is perpendicular to the axis of each top connecting port; the five-way anti-swirling baffle 221 is formed by fixedly connecting two crisscrossed baffles, and the intersecting line of the two baffles coincides with the axis of the top connecting port; the axis of the bottom connecting port is positioned on the plate surface of the partition plate.
As shown in fig. 3, 4 and 5, a multi-way (preferably five-way 22) is connected to the lower end of each main propellant conveying pipeline 21, the top connecting port of the five-way 22 is connected to the main propellant conveying pipeline 21, and the four bottom connecting ports are all horizontally arranged and are respectively connected to a rocket engine 3 through branch propellant conveying pipelines 23. In operation, besides the liquid air entrainment caused by the swirl at the outflow pipe, the swirl at the five-way pipe 22 is easy to occur, and the liquid in the propellant conveying main pipeline 21 is easy to remain and cannot flow completely, therefore, the cross baffle (the five-way anti-swirling baffle 221) can be arranged inside the five-way shell 222 of the five-way pipe 22 to realize the stabilization of the flow field, thereby preventing the liquid air entrainment caused by the swirl at the five-way pipe 22, and making full use of all the low-temperature propellant in the propellant conveying main pipeline 21.
As shown in fig. 5, when the five-way swirl preventing partition 221 is provided in the five-way pipe 22, the side edge of the plate surface of the five-way swirl preventing partition 221 is preferably faced to the center of the bottom connecting port, that is, the bottom connecting port is uniformly divided from left to right by the five-way swirl preventing partition 221, so that a better swirl preventing effect can be achieved.
Further, the low-temperature propellant storage tank 1 is connected with a propellant storage tank safety valve 9, the oxygen tank 2 is connected with an oxygen tank safety valve 16, and the low-temperature propellant storage tank safety valve 9 and the oxygen tank safety valve 16 are important safety devices for protecting the corresponding storage tanks from damage possibly caused by excessive pressure.
Further, as shown in fig. 1, the five-way pipe 22 is connected with the rocket engine 3 through a propellant conveying branch pipe 23; the branch propellant-conveying pipe 23 is further provided with an accumulator 24. The accumulator 24 can keep the liquid flow of the propellant conveying branch pipe 23 more stable and better meet the use requirement. An oxygen tank pressurizing adapter 13 is further arranged in the liquid oxygen conveying pipeline 28, and the oxygen tank pressurizing adapter 13 can be used for simultaneously connecting the oxygen tank pressure sensor 15 and the oxygen tank safety valve 16. The oxygen box safety valve 16 is used for relieving pressure when the pressure of the air pillow of the oxygen box 2 exceeds the standard, so as to avoid safety accidents. In this embodiment, the oxygen tank pressure sensor 15 functions in two ways: one is to measure the air pillow pressure of the oxygen box 2, accumulate flight data through measuring parameters in the flight process, but do not participate in control; two are that before the rocket is launched, the oxygen tank 2 needs to be pressurized, and the opening and closing of a ground pressurizing electromagnetic valve (not shown in the figure) are controlled by an oxygen tank pressure sensor 15. The oxygen tank pressure sensor 15 only plays a role in measurement during the flying process because the rocket is disconnected from the ground after flying.
Further, the low-temperature propellant storage tank 1 is also provided with an anti-shaking device 18 shown in fig. 8; the bottom of the anti-shake device 18 is connected to the top surface of the tank common bottom 17; the anti-shake device 18 is formed by fixedly connecting two crisscross anti-shake plates 181, and the intersecting line of the two anti-shake plates 181 is overlapped with the axial direction of the low-temperature propellant storage tank 1; the bottom edge shape of the anti-shaking plate 181 is matched with the top surface shape of the storage tank common bottom 17, and the side edge of the anti-shaking plate 181 is propped against the inner wall of the low-temperature propellant storage tank 1; the anti-sloshing plate 181 is also provided with a plurality of guide holes 182.
The crisscross anti-shaking device 18 can effectively inhibit the shaking of the liquid in the low-temperature propellant storage tank 1, is favorable for keeping rocket bodies stable, and normally, a plurality of flow guide holes 182 are also formed in the plate surface of the anti-shaking plate 181, so that the instant impact of the liquid on the anti-shaking plate 181 is eliminated, a small amount of liquid circulation in each partition is kept, the stability is further favorable, and meanwhile, the flow guide holes 182 have a certain weight reduction effect.
Further, a notch 183 is also formed at the lower edge of the side edge of the anti-shake plate 181.
As shown in fig. 6 and 8, in the present solution, since two propellant conveying main pipes 21 are adopted and the bottom of the low-temperature propellant storage tank 1 is divided into four areas by the anti-sloshing plate 181, two areas are easily caused to be not directly connected with the outflow pipe, so that the low-temperature propellant is easily remained in the two areas, and fuel is wasted, therefore, the inventor also sets a notch 183 with a shape similar to 1/4 circle at the lower edge of the outer side of the anti-sloshing plate 181, and the bottommost parts in the four areas are mutually communicated through the notch 183, thereby avoiding the residue of the low-temperature propellant, fully utilizing the fuel, and effectively reducing the dead weight of the rocket.
Further, a pressurizing electromagnetic valve group 6 is arranged in a pressurizing pipeline of the propellant storage tank, and a pressure sensor 10 of the propellant storage tank is connected to the low-temperature propellant storage tank 1; the propellant storage tank pressure sensor 10 is connected with the pressurizing electromagnetic valve group 6 through the propellant storage tank pressurizing controller 11; the booster solenoid valve group 6 includes a plurality of booster solenoid valves, and the operating pressures of the plurality of booster solenoid valves are all unequal.
In the technical scheme, the pressurizing electromagnetic valve group 6 can comprise a plurality of electromagnetic valves so as to realize decision logic and pressurizing and pressure compensating pressure control bands of the tank pressurizing and pressure compensating control system in the technical scheme, thereby realizing more accurate pressure control in the working process and providing more safety redundancy. Taking the booster solenoid valve group 6 as an example, as shown in fig. 1, the booster solenoid valve group 6 includes four solenoid valves K1, K2, K3, and K4, and the four solenoid valves divide the corresponding propellant tank booster line into a plurality of branches. Essentially, one pressurizing pipeline meets the requirements of a rocket power system, and the other branches are added to increase the redundancy of the pressurizing pipeline and improve the reliability of the system. Even if one main electromagnetic valve fails, the parallel shunt electromagnetic valve can still be kept normal, and the pressure supplementing requirement of test run is met. Meanwhile, the plurality of parallel electromagnetic valves define different pressure ranges (namely pressure control bands), and the plurality of pressure control bands are defined mainly for ensuring accurate control of the pressure of the air pillow in the low-temperature propellant storage tank 1, so that the pressure of the air pillow is controlled to be relatively stable and is always controlled within the pressure range. If there is only one pressure zone, the actual pressure in the air pillow and the pressure control zone are far apart due to the opening and closing response time of the electromagnetic valve, and the actual pressure in the air pillow and the pressure control zone are not in accordance with the design expectations.
Meanwhile, the embodiment of the invention also provides a pressure control method of the low-temperature propellant pressurizing and conveying system, which comprises the following steps:
s101, pressurizing a gas pillow of the low-temperature propellant storage tank 1 through a propellant autogenous booster 4;
s102, pressurizing the air pillow of the oxygen box 2 through the oxygen autogenous booster 12;
and S103, in the rocket flight process, keeping the air pillow pressure of the oxygen tank 2 to be larger than the sum of the air pillow pressure of the low-temperature propellant storage tank 1 and the propellant liquid column pressure in the low-temperature propellant storage tank 1.
As previously mentioned, in this embodiment, it is necessary to ensure that the pressure in the lower tank is greater than the sum of the pressure in the upper tank plus the liquid column pressure of the propellant in the upper tank (i.e., P R0 +ρghn x ＜P Y0 Wherein P is R0 Is the pressure of the air pillow of the low-temperature propellant storage tank, P R0 Is the pressure of the oxygen box air pillow) can ensure the stability of the common bottom 17 of the storage box, thereby ensuring that the whole structure cannot be unstable. In the first-stage flight process, the pressure control belt of the air pillow pressure of the oxygen tank 2 and the pressure control belt of the air pillow pressure of the low-temperature propellant storage tank 1 are set through the pressurizing electromagnetic valve group 6, and the action pressures of the propellant storage tank safety valve 9 and the oxygen tank safety valve 16 are reasonably set, so that the air pillow pressure range of the oxygen tank 2 and the low-temperature propellant storage tank 1 can be controlled, and the stability of the storage tank common bottom 17 is ensured.
The low-temperature propellant pressurizing and conveying system and the pressure control method thereof are described below by a specific embodiment, in the specific embodiment, the pressurizing and conveying system of the core primary rocket adopts the low-temperature propellant pressurizing and conveying system shown in fig. 1 and 2, and the on-rocket pressurizing flow and the characteristics of the low-temperature propellant pressurizing and conveying system in the primary flight stage after the ignition of an engine are as follows:
1) In the first-stage flight stage, the oxygen tank 2 adopts a self-generating pressurizing scheme, and high-temperature oxygen generated by the oxygen self-generating pressurizer 12 pressurizes the oxygen tank 2 on an arrow through an oxygen tank pressurizing pipeline, an oxygen tank pressurizing adapter 13 and an oxygen tank energy dissipater 14.
2) In the first-stage flight stage, high-temperature propellant gas generated by the propellant self-generating booster 4 passes through the filter 5, the booster solenoid valve group 6 and the orifice plate 7, and then the propellant tank energy dissipater 8 pressurizes the low-temperature propellant tank 1 on an arrow.
3) In the first-stage flight stage, the pressure sensor 10 senses the air pillow pressure of the low-temperature propellant storage tank 1 in the flight process, data is transmitted to the propellant storage tank pressurizing controller 11, and then the propellant storage tank pressurizing controller 11 calculates and makes a decision. The boost electromagnetic valve group 6 is controlled to be opened and closed by the propellant storage tank boost controller 11, so that the accurate control of the air pillow pressure of the low-temperature propellant storage tank 1 is realized.
4) The pressurizing electromagnetic valve group 6 mainly comprises a main pressurizing electromagnetic valve K1, an adjusting pressurizing electromagnetic valve K2 and two standby pressurizing electromagnetic valves K3 and K4.
5) In the first-stage flight process, when the air pillow pressure of the oxygen box 2 is higher than the opening pressure of the oxygen box safety valve 16, the oxygen box safety valve 16 is opened, and when the air pillow pressure of the oxygen box 2 is lower than the closing pressure of the oxygen box safety valve 16, the oxygen box safety valve 16 is closed. In the first-stage flight process, when the air cushion pressure of the low-temperature propellant storage tank 1 is higher than the opening pressure of the propellant storage tank safety valve 9, the propellant storage tank safety valve 9 is opened, and when the air cushion pressure of the low-temperature propellant storage tank 1 is lower than the closing pressure of the propellant storage tank safety valve 9, the propellant storage tank safety valve 9 is closed.
6) The liquid low-temperature propellant in the low-temperature propellant tank 1 flows into the propellant pump inlet 25 via the anti-sloshing device 18, the tank common base 17, the outflow device 19, the propellant tank conveying flange 20, the propellant conveying main pipeline 21, the five-way pipe 22, the propellant conveying branch pipe 23 and the accumulator 24.
7) The liquid oxygen in the oxygen tank 2 passes through the oxygen tank rear bottom 26 and the oxygen tank conveying flange 27, enters the liquid oxygen conveying pipeline 28, and then flows into the liquid oxygen pump inlet 29.
8) The outflow device 19 not only can realize the outflow function of the low-temperature propellant, but also the outflow device 19 is provided with the anti-swirling plate 191 which can prevent the liquid (the low-temperature propellant) from swirling, and the outflow device 19 is also provided with the anti-collapse circular plate 192 which can effectively prevent the liquid from collapsing at the end stage, so that the outflow device 19 can effectively play the role of preventing swirling and collapsing.
9) In the low-temperature propellant tank 1, an anti-sloshing device 18 is arranged above the tank common bottom 17, so that sloshing of liquid can be effectively inhibited.
10 The low-temperature propellant is conveyed in the mode of symmetrical side conveying, main conveying pipes, five-way and branch conveying pipelines, and symmetrical propellant conveying main pipelines 21 are arranged on two sides of the low-temperature propellant storage tank 1.
11 Two main propellant conveying pipelines 21 are arranged, so that the low-temperature propellant storage tank 1 can realize average outflow, and the gravity center of the conveying pipe can be kept at the right center through symmetrical mode pipeline arrangement.
12 The main way pressurizing electromagnetic valve K1 and the regulating way pressurizing electromagnetic valve K2 in the propellant storage box pressurizing pipeline are provided with the filter 5, the standby way pressurizing electromagnetic valve K3 and the standby way pressurizing electromagnetic valve K4 are not provided with the filter, the filter flow resistance 5 is prevented from being too large, and the pressurizing flow of the standby way is ensured.
13 The orifice plate 7 is arranged behind the main-path pressurizing electromagnetic valve K1 and the regulating-path pressurizing electromagnetic valve K2 in the pressurizing pipeline of the propellant storage tank, and the orifice plates are not arranged behind the standby-path pressurizing electromagnetic valve K3 and the standby-path pressurizing electromagnetic valve K4, so that the pressurizing flow of the standby path is ensured, and the system structure is simplified.
In the above embodiment, the pressurizing and pressure supplementing pressure control band of the low-temperature propellant storage tank 1 in the working process is shown in fig. 9, wherein P R0 Is the air pillow pressure, P, of the low-temperature propellant storage tank 1 Rmin Minimum air pillow pressure, P, of the low-temperature propellant reservoir 1 required for the rocket engine 3 R1 To prepare the opening threshold value P of the boost solenoid valves K3 and K4 of the protection path R2 To adjust the opening threshold value of the road pressurizing electromagnetic valve K2 (simultaneously, the closing threshold value of the standby road pressurizing electromagnetic valves K3 and K4), P R3 To adjust the closing threshold value of the road supercharging solenoid valve K2, P RBXFDK For opening pressure of propellant reservoir safety valve 9, P RBXFGB For the closing pressure of the propellant reservoir safety valve 9, P RBXFQM The airtight pressure of the propellant reservoir safety valve 9.
Meanwhile, in the above embodiment, the air pillow pressure and the rest pressure distribution of the oxygen tank 2 are shown in FIG. 10, wherein P YBXFDK Pressure P for opening the safe valve 16 of the oxygen tank YBXFGB Closing pressure, P, for the oxygen tank relief valve 16 YBXFQM Airtight pressure, P, for the oxygen tank relief valve 16 Y0 Is the pressure of the air pillow of the oxygen box 2, P Ymin The minimum air pillow pressure of the oxygen tank 2 required for the rocket motor 3.
Furthermore, in the above-described specific embodiment, with reference to fig. 9 and 10, the air pillow pressure control requirements of the low-temperature propellant tank 1 and the oxygen tank 2 are:
1)、t 0 representing the ignition time, t, of the core primary rocket engine 3 1 Representing the shutdown time of the core primary rocket engine 3.
2) The pressure born by the upper side of the common bottom 17 of the storage tank is the air pillow pressure of the low-temperature propellant storage tank 1 plus the injection pressure of the low-temperature propellant liquid, namely P R0 +ρgh nx The pressure born by the lower side of the common bottom 17 of the storage tank is the pressure of the air pillow of the oxygen tank 2, namely P Y0 When P R0 +ρgh nx Greater than P Y0 When the storage tank is at the bottom 17, a negative pressure working condition can occur. Wherein ρghnx is continuously reduced in the first-order flight process, so ρghnx is at t 0 The moment is the maximum. In order to ensure that the negative pressure working condition does not exist on the common bottom 17 of the storage tank, the embodiment uses the air pillow pressure P of the oxygen tank 2 Y0 Remains in the upper state.
3) When the lateral pressure on the upper side of the common bottom 17 of the storage tank is larger than that on the lower side, the common bottom 17 of the storage tank can generate a negative pressure working condition, and when the negative pressure working condition occurs, the common bottom 17 of the storage tank can collapse, and finally the common bottom 17 of the storage tank is deformed and damaged.
4) Before time t1, the air pillow pressure of the low-temperature propellant storage tank 1 is lower, the air pillow pressure of the oxygen tank 2 is higher, and the situation that the air pillow pressure of the low-temperature propellant storage tank 1 is overlarge in the first-stage flying process, so that the negative pressure working condition of the storage tank common bottom 17 at the end of the first-stage flying is caused is prevented.
5) The pressure of the air pillow of the oxygen box 2 is higher, the oxygen box 2 adopts oxygen autogenous pressurization in the flight process, the oxygen box safety valve 16 is opened for about 3 times in the primary flight process, and the pressure of the air pillow of the oxygen box 2 is controlled by utilizing the oxygen box safety valve 16.
6) The primary oxygen tank adopts an open autogenous pressurizing scheme, the system is simple and reliable, and the degree of dependence on a control system is low. The reliability is improved, and the development difficulty, the production cost and the alignment period of products of the system are reduced due to the simple characteristics of the system.
7) The oxygen box safety valve 16 is a mechanical safety valve, and the control of the air pillow pressure of the oxygen box 2 can be realized by using the mechanical safety valve, and the oxygen box safety valve 16 is expected to be opened for 3 times, so that the opening times of the oxygen box safety valve 16 are less, the service life requirement of the oxygen box safety valve 16 can be met, and the problem of insufficient supercharging pressure caused by calculation and simulation deviation can be prevented.
In addition, in the above embodiment, the supplementary pressure control logic of the booster solenoid valve group 6 is specifically shown in fig. 11 (wherein, P R31 A pressure control belt of the low-temperature propellant storage tank 1 is taken off line; p (P) R32 A pressure control belt center line of the low-temperature propellant storage tank 1 is shown; p (P) R33 Indicating the pressure control belt of the low temperature propellant reservoir 1 is on line):
1) Starting rocket ignition;
2) Igniting the rocket core first stage, wherein the rocket core first stage enters a flight stage;
3) The propellant reservoir pressure sensor 10 detects the air pillow pressure P R0 And sent to the propellant tank boost controller 11;
4) Judging whether the flight time t of the rocket is less than or equal to t 1 If not, turning to the step 8;
5) If yes, further judge whether P R0 Whether or not it is greater than or equal to P R31 If not, opening the electromagnetic valve K1, the electromagnetic valve K2, the electromagnetic valve K3 and the electromagnetic valve K4, and returning to the step 3; if yes, further judge P R0 Whether or not it is greater than P R31 And is less than P R32 ；
6) If yes, opening the electromagnetic valve K1 and the electromagnetic valve K2, keeping the electromagnetic valve K3 and the electromagnetic valve K4 in the previous state, and returning to the step 3; if not, further judging P R0 Whether or not it is greater than P R32 And is less than P R33 ；
7) If yes, opening the electromagnetic valve K1, closing the electromagnetic valve K3 and the electromagnetic valve K4, keeping the electromagnetic valve K2 in the previous state, and returning to the step 3; if not, opening the electromagnetic valve K1, closing the electromagnetic valve K2, the electromagnetic valve K3 and the electromagnetic valve K4, and returning to the step 3;
8) Ending the first-stage flight stage of the rocket core, and ending the first-stage work of the rocket core;
9) Opening the electromagnetic valve K1, and closing the electromagnetic valve K2, the electromagnetic valve K3 and the electromagnetic valve K4;
10 And (3) ending.
Namely, the overall idea of the control logic is: when the pressure of the air pillow of the low-temperature propellant storage tank 1 is lower than the pressure control belt of the low-temperature propellant storage tank 1, all electromagnetic valves are opened; when the air pillow pressure of the low-temperature propellant storage tank 1 is between the lower line and the middle line of the pressure control belt, the standby path-keeping pressurizing electromagnetic valves K3 and K4 keep the previous state; when the air pillow pressure of the low-temperature propellant storage tank 1 is between the middle line and the upper line of the pressure control belt, the standby circuit-protecting pressurizing electromagnetic valves K3 and K4 are closed, and the circuit-protecting pressurizing electromagnetic valve K2 is regulated to keep the previous state; when the pressure of the air pillow of the low-temperature propellant storage tank 1 is above the upper line of the pressure control belt, the pressure-maintaining pressure valves K3 and K4 and the pressure-increasing pressure-regulating electromagnetic valve K2 are closed.
In the foregoing detailed description, various features are grouped together in a single embodiment for the purpose of streamlining the disclosure. This method of disclosure is not to be interpreted as reflecting an intention that the claimed embodiments of the subject matter require more features than are expressly recited in each claim. Rather, as the following claims reflect, invention lies in less than all features of a single disclosed embodiment. Thus the following claims are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate preferred embodiment of this invention.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. As will be apparent to those skilled in the art; various modifications to these embodiments will be readily apparent, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the disclosure. Thus, the present disclosure is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (10)
1. A cryogenic propellant booster delivery system, characterized by comprising a tank and a rocket engine (3);
an arc-shaped storage tank common bottom (17) arched upwards is fixedly connected to the inner side wall of the container tank, and the storage tank common bottom (17) divides the container tank into an upper low-temperature propellant storage tank (1) and a lower oxygen tank (2);
a flow outlet pipe extending obliquely downwards is arranged at the included angle between the inner side wall of the low-temperature propellant storage tank (1) and the storage tank common bottom (17); the outlet pipe is connected with the rocket engine (3) through a propellant conveying main pipeline (21) arranged at the outer side of the oxygen tank (2); the oxygen tank (2) is connected with the rocket engine (3) through a liquid oxygen conveying pipeline (28);
the rocket engine (3) is provided with a propellant self-generating booster (4), the top in the low-temperature propellant storage tank (1) is provided with a propellant storage tank energy dissipater (8), and the propellant self-generating booster (4) is connected with the propellant storage tank energy dissipater (8) through a propellant storage tank boosting pipeline;
the rocket engine (3) is further provided with an oxygen self-generating booster (12), the top in the oxygen tank (2) is provided with an oxygen tank energy dissipater (14), and the oxygen self-generating booster (12) is connected with the oxygen tank energy dissipater (14) through an oxygen tank boosting pipeline.
2. The low-temperature propellant pressurizing and conveying system according to claim 1, wherein the number of the outflow pipes is two, the number of the propellant conveying main pipelines (21) is two, the two propellant conveying main pipelines (21) are symmetrically arranged at the side of the low-temperature propellant storage tank (1), and each propellant conveying main pipeline (21) is connected with a plurality of rocket engines (3).
3. A cryogenic propellant booster delivery system according to claim 1, characterized in that an outflow device (19) is provided in the propellant delivery main line (21); the outflow device (19) comprises a collapse prevention circular plate (192) perpendicular to the axis of the propellant conveying main pipeline (21), and a plurality of swirl prevention plates (191) vertically connected below the collapse prevention circular plate (192); the anti-swirling plates (191) are uniformly distributed in the circumferential direction of the anti-collapse circular plate (192), and a preset gap is reserved between every two adjacent anti-swirling plates (191); the outer side of the anti-swirling plate (191) is connected to the inner wall of the propellant conveying main pipeline (21); a preset gap is reserved between the outer edge of the collapse prevention circular plate (192) and the inner wall of the propellant conveying main pipeline (21).
4. A cryogenic propellant booster delivery system according to claim 2, wherein each of the propellant delivery main lines (21) is connected to four rocket engines (3) by means of five-way lines (22); the five-way shell (22) comprises a five-way shell (222) and a five-way anti-swirling baffle (221); the five-way shell (222) comprises a top connecting port and four bottom connecting ports, the four bottom connecting ports are circumferentially and uniformly distributed, and the axis of each bottom connecting port is perpendicular to the axis of each top connecting port; the five-way anti-swirling baffle plate (221) is formed by fixedly connecting two crisscross baffle plates, and the intersecting lines of the two baffle plates are overlapped with the axis of the top connecting port; the axis of the bottom connecting port is positioned on the plate surface of the partition plate.
5. The cryogenic propellant booster delivery system of claim 4, wherein the cryogenic propellant reservoir (1) is connected to a propellant reservoir safety valve (9) and the oxygen reservoir (2) is connected to an oxygen reservoir safety valve (16).
6. A cryogenic propellant booster delivery system according to claim 4, characterized in that the five-way connection (22) is connected to the rocket engine (3) by a propellant delivery branch (23); the propellant conveying branch pipe (23) is also provided with an accumulator (24); an oxygen box pressurizing adapter (13) is further arranged in the liquid oxygen conveying pipeline (28), and an oxygen box pressure sensor (15) is arranged on the oxygen box pressurizing adapter (13).
7. The cryogenic propellant booster delivery system of claim 1, wherein an anti-sloshing device (18) is further provided within the cryogenic propellant reservoir (1); the bottom of the anti-shaking device (18) is connected to the top surface of the storage tank common bottom (17); the anti-shaking device (18) is formed by fixedly connecting two crisscross anti-shaking plates (181), and the intersecting lines of the two anti-shaking plates (181) are overlapped with the axial direction of the low-temperature propellant storage tank (1); the bottom edge shape of the anti-shaking plate (181) is matched with the top surface shape of the storage tank common bottom (17), and the side edge of the anti-shaking plate (181) is propped against the inner wall of the low-temperature propellant storage tank (1); the anti-shaking plate (181) is also provided with a plurality of diversion holes (182).
8. The cryogenic propellant booster delivery system of claim 7, wherein the anti-sloshing plate (181) is further notched (183) at a lower side edge thereof.
9. The low-temperature propellant booster delivery system according to claim 1, wherein a booster electromagnetic valve group (6) is arranged in the propellant storage tank booster pipeline, and a propellant storage tank pressure sensor (10) is connected to the low-temperature propellant storage tank (1); the propellant storage tank pressure sensor (10) is connected with the pressurizing electromagnetic valve group (6) through a propellant storage tank pressurizing controller (11); the pressurizing electromagnetic valve group (6) comprises a plurality of pressurizing electromagnetic valves, and the working pressures of the pressurizing electromagnetic valves are different.
10. A method of controlling the pressure of a cryogenic propellant booster delivery system as defined in claim 1, comprising:
pressurizing the air pillow of the low-temperature propellant storage tank (1) through the propellant autogenous pressurizer (4);
pressurizing the air pillow of the oxygen box (2) through the oxygen autogenous pressurizer (12);
during rocket flight, the air pillow pressure of the oxygen tank (2) is kept to be larger than the sum of the air pillow pressure of the low-temperature propellant storage tank (1) and the propellant liquid column pressure in the low-temperature propellant storage tank (1).
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| CN117869120A (en) * | 2023-12-26 | 2024-04-12 | 北京天兵科技有限公司 | One-stage rocket, booster conveying system and control method thereof |
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