CN117869118A - Low-temperature propellant cross pressurization conveying system and parallel rocket - Google Patents

Abstract

The embodiment of the invention provides a low-temperature propellant cross pressurizing and conveying system and a parallel rocket, which comprise a plurality of pressurizing and conveying units, wherein each pressurizing and conveying unit comprises a liquid oxygen tank and a low-temperature propellant tank, the liquid phase spaces of the liquid oxygen tanks are mutually communicated, the liquid phase spaces of the low-temperature propellant tanks are mutually communicated, the gas phase spaces of the liquid oxygen tanks are mutually communicated, and the gas phase spaces of the low-temperature propellant tanks are mutually communicated. In the technical scheme, the liquid oxygen levels in the multiple sets of pressurizing and conveying units are consistent, and the low-temperature propellant levels are also consistent, so that the fuel in each storage tank is consumed at the same time, the safety margin of the residual fuel is reduced, the dead weight of the rocket is reduced, and the carrying capacity of the rocket is improved; meanwhile, as the air pillow pressure of each liquid oxygen tank is the same and the air pillow pressure of each low-temperature propellant tank is the same, the safety valves can be shared, thereby reducing the cost.

Description

Low-temperature propellant cross pressurization conveying system and parallel rocket

Technical Field

The invention relates to the technical field of rocket engines, in particular to a low-temperature propellant cross supercharging conveying system and a parallel rocket.

Background

Currently, the requirements of various aerospace countries on earth-month, earth-fire and other deep space exploration tasks are increasing, along with the development of industrialization and commercialization of space technology, large and heavy carrier rockets with green research and low cost and high reliability become hot spots, and in the process, bundled rockets are increasingly applied. The binding rocket is characterized in that a plurality of rocket bodies (comprising a core stage and a boosting stage) are arranged in each stage assembly, and each rocket body is provided with an independent pressurizing and conveying system, so that the thrust is increased, and the carrying capacity is improved.

In the process of implementing the present invention, the inventor finds that at least the following problems exist in the prior art:

in the current stage of carrier rocket development, the mode of simply increasing the fuel carrying capacity inevitably increases the dead weight of the rocket greatly, and the mode is difficult to obtain larger breakthrough, so that the problem to be solved is how to improve a pressurizing and conveying system based on the integral structure of the existing rocket, realize power redundancy and improve the carrying capacity of the rocket.

Disclosure of Invention

The embodiment of the invention provides a low-temperature propellant cross pressurizing conveying system and a parallel rocket, which are used for improving the carrying capacity of the rocket.

To achieve the above objective, in one aspect, an embodiment of the present invention provides a cryogenic propellant cross pressurization and transportation system, which includes multiple sets of pressurization and transportation units, each set of pressurization and transportation units includes a liquid oxygen tank and a cryogenic propellant tank, liquid phase spaces of the liquid oxygen tanks are mutually communicated through a liquid oxygen tank cross transportation pipeline, and liquid phase spaces of the cryogenic propellant tanks are mutually communicated through a propellant tank cross transportation pipeline.

On the other hand, the embodiment of the invention also provides a parallel rocket, wherein the first-stage assembly of the parallel rocket is provided with the low-temperature propellant cross pressurizing and conveying system; the primary assembly of the parallel rocket comprises a core primary rocket body and two boosting primary rocket bodies arranged at the sides of the core primary rocket body; the core primary arrow body) and each boosting primary arrow body are respectively provided with a set of pressurizing and conveying unit.

The technical scheme has the following beneficial effects:

the technical scheme of the invention adopts a cross pressurizing conveying mode, namely, through communicating liquid-oxygen tanks and liquid-phase spaces of the propelling tanks of the pressurizing conveying system, simultaneously communicating liquid-oxygen tank air pillow parts and propelling tank air pillow parts, the same air pillow pressure and the same liquid level in corresponding storage tanks (comprising the liquid-oxygen tank and the low-temperature propelling tank) in the multiple sets of systems can be ensured, so that fuel in each storage tank is consumed at the same time, the problem of large residual quantity caused by inconsistent liquid levels in the corresponding storage tanks at the shutdown time in the prior art is avoided, the safety margin of residual fuel is effectively reduced, the dead weight of a rocket is further reduced, and the carrying capacity of the rocket is improved.

In addition, the technical scheme also has the following characteristics:

1) Because the multiple sets of pressurizing and conveying systems are in cross parallel connection, when an engine in an arrow body is shut down accidentally due to a fault, the residual fuel in the fault arrow body can be transferred to other normal arrow bodies for use in a cross pressurizing and conveying mode, so that the complete utilization of the fuel is realized, and the power redundancy is realized.

2) Meanwhile, under the cross pressurizing mode of the embodiment, the pressure of the air pillow of each liquid oxygen tank is the same, and the pressure of the air pillow of each low-temperature propellant tank is the same, so that the liquid oxygen tank safety valves can be shared, the propellant tank safety valves can be shared, and only one safety valve is needed to be configured, thereby reducing the number of the safety valves and reducing the cost.

3) The liquid oxygen tank and the low-temperature propellant tank are all in an open self-generating pressurizing scheme, the system is simple and reliable, the degree of dependence on a control system is low, the reliability is improved, the development difficulty of the system and the production cost of the system are reduced, and the matching period of products is shortened.

4) In the embodiment of the invention, the mechanical safety valve is adopted to control the air pillow pressure of the oxygen tank and the low-temperature propellant tank, and the safety valves of the oxygen tank and the low-temperature propellant tank are opened for 4-5 times through simulation calculation, so that the opening times are less, the service life requirement of the safety valve can be met, and the problem of insufficient supercharging pressure caused by calculation and simulation deviation can be prevented.

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 cross boost delivery system according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of a system of a parallel rocket in accordance with an embodiment of the present invention;

FIG. 3 is a schematic diagram of a multi-pass architecture in one embodiment of the invention;

FIG. 4 is a graph showing the oxygen tank air pillow pressure and the rest of the pressure distribution in an embodiment of the present invention;

FIG. 5 is a graph of cryogenic tank air pillow pressure and residual pressure profile for an embodiment of the present invention;

reference numerals: 1. a liquid oxygen tank; 2. a low temperature propellant tank; 3. an engine; 4. an oxygen autogenous booster; 5. an oxygen self-pressurization pipeline; 6. a first tee; 7. a liquid oxygen tank energy dissipater; 8. a liquid oxygen tank safety valve; 9. a propellant autogenous booster; 10. a propellant self-pressurizing pipeline; 11. a propellant tank energy dissipater; 12. a propellant tank top interface; 13. a propellant tank safety valve; 14. a liquid oxygen tank bottom interface; 15. a propellant tank bottom interface; 16. a liquid oxygen delivery main line; 17. a propellant tank tunnel pipe; 18. liquid oxygen delivery manifold; 19. a liquid oxygen branch conveying pipe; 20. a liquid oxygen tank cross pressurizing pipeline; 21. the liquid oxygen tank is crossed with the conveying pipeline; 22. a propellant tank cross pressurization pipeline; 23. the propellant tanks cross the conveying pipeline; 24. a second tee; 25. a third tee; 26. a fourth tee; 27. a fifth tee; 28. a liquid oxygen pump inlet; 100. a core primary arrow body; 200. and (5) boosting the primary arrow body.

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, an embodiment of the present invention provides a cryogenic propellant cross pressurization and transportation system, which includes multiple sets of pressurization and transportation units, each set of pressurization and transportation unit includes a liquid oxygen tank 1 and a cryogenic propellant tank 2, liquid phase spaces of the liquid oxygen tank 1 are mutually communicated through a liquid oxygen tank cross transportation pipeline 21, and liquid phase spaces of the cryogenic propellant tank 2 are mutually communicated through a propellant tank cross transportation pipeline 23.

The inventor researches that the bundled rocket has a plurality of rocket bodies, so that the carrying capacity can be improved to a large extent, but at the shutdown time of the bundled rocket, the problem that a large amount of fuel (including liquid oxygen or low-temperature propellant) remains in a pressurizing and conveying unit in one or more rocket bodies always occurs, so that the fuel actually consumed is reduced, the dead weight of the rocket is further increased, and the carrying capacity of the rocket is further improved. Further studies have found that this problem is caused by the fact that the liquid level falling speeds in the plurality of liquid oxygen tanks 1 are not uniform among the plurality of pressurizing and transporting units, and that the liquid level falling speeds in the plurality of low temperature propellant tanks 2 are also not uniform, and when the fuel in one of the tanks (including the liquid oxygen tank 1 and the low temperature propellant tank 2) is exhausted and needs to be shut down, the remaining tanks still have unconsumed fuel.

In order to solve the problem, in the embodiment of the invention, the liquid parts of the plurality of low-temperature propellant tanks 2 on the bundled rocket are connected together, and the liquid parts of the liquid oxygen tanks 1 are also connected together, so that the liquid level can be kept consistent all the time when the fuel in each tank is conveyed to the engine, the fuel in all the tanks can be exhausted when the engine is shut down, the residual quantity of the fuel is reduced, the dead weight of the rocket is further reduced, and the carrying capacity of the rocket is improved.

Further, the gas phase spaces of the liquid oxygen tanks 1 are communicated with each other through a liquid oxygen tank cross pressurizing pipe 20, and the gas phase spaces of the low-temperature propellant tanks 2 are communicated with each other through a propellant tank cross pressurizing pipe 22.

After the liquid oxygen in different storage tanks is communicated with the low-temperature propellant in a crossing way, the gas phase spaces of the storage tanks are communicated, so that the same pressure of the gas pillow of each storage tank is ensured, and the gas pillow is an important condition for ensuring that the liquid level can synchronously drop.

Further, the booster delivery unit further includes an engine 3; the liquid oxygen tank 1 is arranged above the low-temperature propellant tank 2; the liquid oxygen tank 1 is connected with the engine 3 through a liquid oxygen conveying main pipeline 16, and the low-temperature propellant tank 2 is connected with the engine 3 through a propellant conveying main pipeline; the engine 3 is provided with a propellant autogenous booster 9 and an oxygen autogenous booster 4, the top of the inner side of the low-temperature propellant tank 2 is provided with a propellant tank energy dissipater 11, the top of the inner side of the liquid oxygen tank 1 is provided with a liquid oxygen tank energy dissipater 7, the propellant autogenous booster 9 is connected with the propellant tank energy dissipater 11 through a propellant autogenous booster pipeline 10, and the oxygen autogenous booster 4 is connected with the liquid oxygen tank energy dissipater 7 through an oxygen autogenous booster pipeline 5.

The structure of each booster delivery unit is shown in fig. 1, which is basically the same as the prior art, in this embodiment of the present invention, a tunnel pipe type delivery scheme is still adopted, that is, a main liquid oxygen delivery pipe 16 is disposed at the bottom of the liquid oxygen tank 1 at the upper part, and then the main liquid oxygen delivery pipe 16 passes through a tunnel pipe 17 of the propellant tank, which is disposed at the middle part of the low-temperature propellant tank 2 below, and finally the propellant is delivered to the engine 3 (the communication mode between the liquid oxygen tank 1 and the engine is the same as the prior art and is not shown in the drawing). Meanwhile, in the embodiment of the invention, the liquid oxygen tank 1 and the low-temperature propellant tank 2 both adopt an open self-pressurization mode to provide air pillow pressure.

Further, the oxygen self-pressurization pipeline 5 is communicated with the liquid oxygen tank cross pressurization pipeline 20; the bottom of the liquid oxygen tank 1 is provided with a liquid oxygen tank bottom connector 14, and the liquid oxygen tank bottom connector 14 is communicated with a liquid oxygen tank cross conveying pipeline 21; the top of the cryogenic tank 2 is provided with a tank top interface 12, the bottom of the cryogenic tank 2 is provided with a tank bottom interface 15, the tank top interface 12 communicates with a tank crossover pressurization line 22, and the tank bottom interface 15 communicates with a tank crossover delivery line 23.

In order to realize cross pressurizing conveying, a top port 12 of the low-temperature propellant tank 2 is arranged at the top of the low-temperature propellant tank 2, and a bottom port 15 of the low-temperature propellant tank 2 is arranged at the bottom of the low-temperature propellant tank 2 and is respectively used for realizing communication of air pillow pressure and liquid level between the low-temperature propellant tanks 2; a liquid oxygen tank bottom interface 14 is arranged at the bottom of the liquid oxygen tank 1 and is used for realizing liquid level communication among the liquid oxygen tanks 1; the top of the liquid oxygen tank 1 is not required to be additionally provided with an interface, the first tee joint 6 can be directly arranged on the oxygen self-pressurization pipeline 5 before entering the liquid oxygen tank 1, and the first tee joints 6 are connected together through the liquid oxygen tank cross-pressurization pipeline 20, so that the same air pillow pressure among the liquid oxygen tanks 1 can be ensured.

Further, the cryogenic propellant crossover pressurized delivery system further includes a propellant tank relief valve 13, the propellant tank relief valve 13 being disposed in the propellant tank crossover pressurized line 22.

In the prior art, the propellant tank safety valves 13 are all arranged at the top of the low-temperature propellant tank 2 and are communicated with the low-temperature propellant tank 2 to directly obtain the air pillow pressure of the low-temperature propellant tank 2; in the embodiment of the invention, since the gas phase spaces (i.e. the air pillow parts) of the plurality of low-temperature propellant tanks 2 are already cross-connected through the propellant tank cross-pressurization pipelines 22, only one propellant tank safety valve 13 is needed to be arranged on the propellant tank cross-pressurization pipelines 22, so that overpressure protection can be provided for three cross-connected low-temperature propellant tanks 2 at the same time, the configuration quantity of the propellant tank safety valves 13 is reduced, and the cost is reduced.

Further, the cryogenic propellant cross pressurization delivery system further comprises a liquid oxygen tank safety valve 8, wherein the liquid oxygen tank safety valve 8 is arranged in the liquid oxygen tank cross pressurization pipeline 20.

Correspondingly, the liquid oxygen box safety valve 8 can provide overpressure protection for the three cross-connected liquid oxygen boxes 1 only by arranging one liquid oxygen box cross pressurizing pipeline 20.

Further, the cryogenic propellant cross boost delivery system also includes a liquid oxygen delivery manifold 18; each set of supercharging conveying unit comprises a plurality of engines 3; the liquid oxygen delivery manifold 18 includes a top connection port and a plurality of side connection ports, the top connection port is communicated with the liquid oxygen delivery main pipeline 16, and the side connection ports are connected with the engine 3 through a liquid oxygen branch delivery pipe 19; the number of the side connection ports is the same as the number of the engines 3 in each set of the booster delivery unit.

Since the booster delivery unit is generally provided with a plurality of engines 3 connected in parallel, the provision of the liquid oxygen delivery manifold 18 can better distribute the liquid oxygen delivered from the liquid oxygen delivery main pipe 16 to the respective engines 3 uniformly, and the structure of the liquid oxygen delivery manifold 18 is shown in fig. 3.

Further, in general, the number of engines 3 in each set of booster delivery units is eight, or nine, or even more, and in the embodiment of the present invention, the most common configuration of 8 engines is preferably adopted; at this time, 8 engines 3 require 8 side connection ports and a single top connection port for connecting the liquid oxygen transfer main pipe 16, and therefore, the liquid oxygen transfer manifold 18 at this time is nine-way.

Furthermore, in practical application, the rocket primary assembly is preferably composed of a core primary rocket body and two boosting primary rocket bodies at two sides, and each rocket body is internally provided with a set of pressurizing and conveying units, so that three sets of pressurizing and conveying units are arranged in each primary assembly.

As shown in fig. 2, the embodiment of the invention further provides a parallel rocket, wherein the first-stage assembly of the parallel rocket is provided with the low-temperature propellant cross pressurizing and conveying system; the primary assembly of the parallel rocket comprises a primary rocket body 100 with a core and two boosting primary rocket bodies 200 arranged at the sides of the primary rocket body with the core; a set of pressurizing and conveying units are respectively arranged on the core primary arrow body 100 and each boosting primary arrow body 200.

The low-temperature propellant cross pressurizing and conveying system is mainly applied to a rocket primary assembly, the primary assembly is of a binding structure, the rocket primary assembly comprises a middle core primary rocket body 100 and two boosting primary rocket bodies 200 bound on two sides, a pressurizing and conveying unit is arranged in each rocket body, and the configuration mode is widely applied. In the embodiment of the invention, the pressurizing and conveying units in the rocket bodies are arranged in a cross communication way, so that the liquid levels in the low-temperature propellant tank 2 and the liquid oxygen tank 1 can be synchronously lowered, the fuel in each storage tank is completely consumed at the same time at the time of shutting down the primary assembly, the safety margin of residual fuel is reduced, the dead weight of the rocket is reduced, and the carrying capacity of the rocket is improved.

The working process of the low-temperature propellant cross pressurization conveying system and the parallel rocket is described in detail below by using a specific embodiment:

1) In the flight stage of the rocket stage assembly, the liquid oxygen tank 1 adopts a self-generating pressurizing scheme, the oxygen self-generating pressurizer 4 heats liquid oxygen into high-temperature oxygen, and then the high-temperature oxygen pressurizes the liquid oxygen tank 1 on an rocket through the oxygen self-pressurizing pipeline 5, the first tee joint 6 and the liquid oxygen tank energy dissipater 7. In the process, the pressurizing mode of the liquid oxygen tank 1 is open pressurizing, and a control system is not used for closed feedback.

2) Simultaneously, the low-temperature propellant tank 2 adopts a self-generated pressurizing scheme, the low-temperature propellant is gasified by the propellant self-generated pressurizer 9, and propellant gas pressurizes the low-temperature propellant tank 2 on an arrow through the propellant self-pressurizing pipeline 10 and the propellant tank energy dissipater 11. In the process, the pressurization mode of the low-temperature propellant tank 2 is open pressurization, and a control system is not used for closed feedback.

3) In the flying process of the rocket primary assembly, when the air pillow pressure of the liquid oxygen tank 1 is higher than the opening pressure of the liquid oxygen tank safety valve 8, the liquid oxygen tank safety valve 8 is opened, and when the air pillow pressure of the liquid oxygen tank 1 is lower than the closing pressure of the liquid oxygen tank safety valve 8, the liquid oxygen tank safety valve 8 is closed. When the pressurizing flow of the liquid oxygen tank 1 is larger, the liquid oxygen tank safety valve 8 is opened, and the liquid oxygen tank safety valve 8 is used for controlling the air pillow pressure of the liquid oxygen tank 1.

4) During the first-stage flight of the rocket first-stage assembly, when the air cushion pressure of the low-temperature propellant tank 2 is higher than the opening pressure of the propellant tank safety valve 13, the propellant tank safety valve 13 is opened, and when the air cushion pressure of the low-temperature propellant tank 2 is lower than the closing pressure of the propellant tank safety valve 13, the low-temperature propellant tank safety valve 13 is closed. If the pressure-increasing flow of the cryogenic propellant tank 2 is larger, the propellant tank safety valve 13 is opened, and the pressure of the air cushion of the cryogenic propellant tank 2 is controlled by the propellant tank safety valve 13.

5) The liquid oxygen of the liquid oxygen tank 1 is conveyed to a liquid oxygen pump inlet 28 of the engine 3 through an oxygen tank rear bottom, a liquid oxygen conveying main pipeline 16, a liquid oxygen conveying manifold 18 and a liquid oxygen branch conveying pipe 19.

6) To increase the thrust of the primary assembly and improve the carrying capacity of the rocket, as shown in fig. 2, the primary core rocket body 100 is duplicated into two boosting primary rocket bodies 200, (or called boosting primary rocket body a and boosting primary rocket body B), and the primary core rocket body 100, the boosting primary rocket body a and the boosting primary rocket body B are bound.

7) In order to realize the cross pressurization of the liquid oxygen boxes 1 on the primary assembly, as shown in fig. 2, a first tee joint 6 on the primary arrow body 100 of the core, a first tee joint 6 on the primary arrow body A of the boosting and a first tee joint 6 on the primary arrow body B of the boosting are mutually communicated by utilizing a liquid oxygen box cross pressurization pipeline 20 and a second tee joint 24, so that the three liquid oxygen boxes 1 on the primary assembly are mutually communicated, the air pillow pressure of the three liquid oxygen boxes 1 is kept uniform, and the cross pressurization of the liquid oxygen boxes 1 is realized. Meanwhile, a liquid oxygen tank safety valve 8 is arranged on a liquid oxygen tank cross pressurizing pipeline 20, so that the air pillow pressure control of the liquid oxygen tank 1 of the primary assembly is realized.

The cross pressurization of the liquid oxygen boxes 1 on the primary assembly is realized, the air pillow pressure of the three liquid oxygen boxes 1 can be kept consistent, the pressure control of the liquid oxygen boxes 1 can be realized only by using 1 liquid oxygen box safety valve 8, and compared with the traditional mode that each liquid oxygen box 1 uses one liquid oxygen box safety valve 8, the system saves 2 liquid oxygen box safety valves 8.

8) In order to realize the cross conveying of the liquid oxygen boxes 1 on the primary assembly, the liquid oxygen box bottom connector 14 of the core primary arrow body 100, the liquid oxygen box bottom connector 14 of the boosting primary arrow body A and the liquid oxygen box bottom connector 14 of the boosting primary arrow body B are respectively communicated with each other by utilizing the liquid oxygen box cross conveying pipeline 21 and the third tee joint 25, so that the mutual cross conveying of liquid parts of three liquid oxygen boxes 1 on the primary assembly is realized, the consistency of liquid oxygen levels of the three liquid oxygen boxes 1 is ensured, the consumption of liquid oxygen of the three liquid oxygen boxes 1 at the same moment is ensured, and the cross conveying of the liquid oxygen boxes 1 is realized.

Through the cross conveying of three liquid oxygen boxes 1 on the primary assembly, the pressure of the rear bottoms of the three liquid oxygen boxes 1 can be guaranteed to be consistent, so that the liquid oxygen liquid levels of the three liquid oxygen boxes 1 are guaranteed to be consistent, the liquid oxygen of the three liquid oxygen boxes 1 can be consumed at the same time, and each liquid oxygen box in the prior art can independently outflow. The system can reduce the residual liquid oxygen safety margin, reduce the dead weight of the rocket and improve the carrying capacity of the rocket by realizing the unification of the liquid oxygen liquid level.

9) The cross pressurization of the liquid oxygen tank 1 of the primary assembly realizes the unification of the air pillow pressure of the liquid oxygen tank 1, and provides a necessary condition for realizing the unification of the liquid oxygen liquid level by the cross conveying of the liquid oxygen tank 1.

10 To realize the cross pressurization of the low-temperature propellant tank 2 on the primary assembly, the top interfaces 12 of the propellant tank on the primary rocket body 100, the top interfaces 12 of the propellant tank on the secondary rocket body A and the top interfaces 12 of the propellant tank on the secondary rocket body B are mutually communicated by utilizing the cross pressurization pipelines 22 of the propellant tank and the fourth tee joint 26, so that the low-temperature propellant tank 2 of the primary rocket body 100, the low-temperature propellant tank 2 of the secondary rocket body A and the low-temperature propellant tank 2 of the secondary rocket body B are mutually communicated, the air pillow pressure of the three low-temperature propellant tanks 2 is kept uniform, and the cross pressurization of the three low-temperature propellant tanks 2 is realized. A tank safety valve 13 is arranged on the tank cross pressurizing pipeline 22 to control the air pillow pressure of the three low-temperature tanks 2.

Through the cross pressurization of the low-temperature propellant tanks 2 of the primary assembly, the pressure of the air pillow of the three low-temperature propellant tanks 2 can be kept consistent, the pressure control of the low-temperature propellant tanks 2 can be realized only by using 1 propellant tank safety valve 13, and compared with the traditional mode that each low-temperature propellant tank 2 uses one propellant tank safety valve 13, the system saves 2 propellant tank safety valves 13.

11 To achieve cross-transportation of the first-stage low-temperature propellant tank 2, the bottom interfaces 15 of the propellant tank on the first-stage rocket body 100, the bottom interfaces 15 of the propellant tank on the boosting first-stage rocket body A and the bottom interfaces 15 of the low-temperature propellant tank on the boosting first-stage rocket body B are mutually communicated by utilizing the cross-transportation pipeline 23 of the propellant tank and the fifth tee joint 27, so that the mutual communication of liquid parts of three low-temperature propellant tanks 2 on the first-stage assembly is achieved, the consistent liquid level of the liquid propellant in the three low-temperature propellant tanks 2 is ensured, the consumption of the liquid propellant of the three low-temperature propellant tanks 2 is ensured at the same time, and the cross-transportation of the low-temperature propellant tank 2 of the first-stage assembly is achieved.

The cross conveying of the low-temperature propellant tanks 2 of the primary assembly is realized, the pressure of the rear bottoms of the three low-temperature propellant tanks 2 can be guaranteed to be consistent, so that the low-temperature propellant liquid levels of the three low-temperature propellant tanks 2 are guaranteed to be consistent, the low-temperature propellant of the three low-temperature propellant tanks 2 can be consumed at the same time, in the prior art, each low-temperature propellant tank 2 independently carries out outflow, the low-temperature propellant liquid levels of the three low-temperature propellant tanks 2 are inconsistent at the shutdown time of the low-temperature propellant tanks 2 due to the differences of the rotation speed, the supercharging pressure, the engine thrust and the mixing ratio of the turbine pump and the single engine 3, and the residual propellant safety margin of the three low-temperature propellant tanks 2 is caused to be larger according to the minimum liquid level as a system design requirement. The system can reduce the safety margin of the residual propellant, reduce dead weight of the rocket and improve carrying capacity of the rocket by realizing unification of the liquid level of the low-temperature propellant.

12 The cross pressurization of the low-temperature propellant tank 2 of the primary assembly realizes the unification of the air pillow pressure of the low-temperature propellant tank 2, and provides a necessary condition for realizing the unification of the liquid level of the low-temperature propellant by the cross conveying of the low-temperature propellant tank 2.

13 In addition, if one of the engines 3 on the core primary arrow 100 or one of the boost primary arrow 200 fails, the remaining propellant of that tank can be delivered to the tanks of the other arrow (including the liquid oxygen tank 1 or the cryogenic propellant tank 2), thereby achieving full utilization of the fuel.

In addition, in the above specific embodiment, the method for pressurizing the rocket on the rocket in the flight phase of the rocket ignition after the rocket is as follows:

1) The safety valve is a pressure release safety device of a storage tank (comprising a liquid oxygen tank 1 or a low-temperature propellant tank 2), can be opened and closed according to preset pressure, is applied to the overpressure protection of the rocket storage tank, is a key valve for ensuring the pressure bearing safety of the storage tank, and is automatically opened to discharge redundant gas when the pressure of the storage tank exceeds a specified value in the flight process; when the exhaust pressure of the storage tank is reduced to a specified value, the safety valve can be automatically closed and kept sealed, and in the embodiment of the invention, the safety valve (comprising the liquid oxygen tank safety valve 8 and the propellant tank safety valve 13) is of a mechanical structure and has no control system.

2) In the embodiment of the invention, the liquid oxygen tank 1 and the low-temperature propellant tank 2 are both open self-generated pressurization schemes, the participation of a control system is avoided, and the pressurization schemes are simple and reliable. According to the simulation calculation, it can be determined that the liquid oxygen tank safety valve 8 and the propellant tank safety valve 13 are opened for 4-5 times during the flight of the rocket primary assembly, and the opening times are obviously lower than the average level in the prior art, so that the service life requirement of the safety valve can be met, and the problem of insufficient supercharging pressure caused by calculation deviation can be prevented.

3) The liquid oxygen box 1 utilizes the liquid oxygen box safety valve 8 to control the pressure of the liquid oxygen box air pillow, and the liquid oxygen box 1 air pillow pressure is controlled by opening and closing the liquid oxygen box safety valve 8; the low-temperature tank 2 controls the air pillow pressure of the low-temperature tank 2 by using the tank safety valve 13, and the low-temperature tank 2 is controlled by opening and closing the tank safety valve 13.

In the above embodiment, the air pillow pressure and other pressure distribution of the liquid oxygen tank 1 are shown in fig. 4, wherein P _Ybxfkq For the opening pressure, P, of the oxygen tank safety valve 16 _Ybxfgb For closing pressure, P, of the relief valve of the liquid oxygen tank _Ybxfqm Is the airtight pressure of a safety valve of the liquid oxygen box, P _Y0 Is the actual boost pressure of the liquid oxygen tank 1, P _Ymin Minimum air pillow pressure of liquid oxygen tank 1 required for rocket engine 3Force.

In the above embodiment, the air pillow pressure and the rest pressure distribution of the cryogenic propellant tank 2 are shown in fig. 5, wherein P _R0 Is the actual boost pressure, P, of the cryogenic propellant tank 2 _Rmin Minimum air pillow pressure, P, for the cryogenic propellant tank 2 required for the engine 3 _Rbxfkq To the opening pressure of the safe valve of the propellant tank, P _Rbxfgb For closing pressure of the tank fuse, P _Rbxfqm The airtight pressure for the propellant tank relief valve.

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. The utility model provides a cryogenic propellant cross boost conveying system, includes many sets of boost conveying unit, every set boost conveying unit all includes a liquid oxygen case (1) and a cryogenic propellant case (2), its characterized in that, the liquid phase space of liquid oxygen case (1) is through the mutual intercommunication of liquid oxygen case cross conveying pipeline (21), the liquid phase space of cryogenic propellant case (2) is through the mutual intercommunication of propellant case cross conveying pipeline (23).

2. Cryogenic propellant crossover pressurized delivery system according to claim 1, characterized in that the gas phase spaces of the liquid oxygen tanks (1) are interconnected by a liquid oxygen tank crossover pressurized line (20) and the gas phase spaces of the cryogenic propellant tanks (2) are interconnected by a propellant tank crossover pressurized line (22).

3. The cryogenic propellant cross boost delivery system of claim 2, wherein the boost delivery unit further comprises an engine (3); the liquid oxygen tank (1) is arranged above the low-temperature propellant tank (2); the liquid oxygen tank (1) is connected with the engine (3) through a liquid oxygen conveying main pipeline (16), and the low-temperature propellant tank (2) is connected with the engine (3) through a propellant conveying main pipeline; be provided with propellant autogenous booster (9) and oxygen autogenous booster (4) on engine (3), low temperature propellant case (2) inboard top is equipped with propellant case energy absorber (11), liquid oxygen case (1) inboard top is equipped with liquid oxygen case energy absorber (7), propellant autogenous booster (9) with be connected through propellant autogenous booster line (10) between propellant case energy absorber (11), oxygen autogenous booster (4) with be connected through oxygen autogenous booster line (5) between liquid oxygen case energy absorber (7).

4. A cryogenic propellant crossover pressurized delivery system as claimed in claim 3, wherein said oxygen self-pressurizing line (5) communicates with said liquid oxygen tank crossover pressurizing line (20); the bottom of the liquid oxygen tank (1) is provided with a liquid oxygen tank bottom interface (14), and the liquid oxygen tank bottom interface (14) is communicated with the liquid oxygen tank cross conveying pipeline (21); the top of low temperature propellant tank (2) is provided with propellant tank top interface (12), the bottom of low temperature propellant tank (2) is provided with propellant tank bottom interface (15), propellant tank top interface (12) with the crossing booster line (22) intercommunication of propellant tank, propellant tank bottom interface (15) with crossing delivery line (23) intercommunication of propellant tank.

5. The cryogenic propellant crossover delivery system of claim 2, further comprising a propellant tank relief valve (13), the propellant tank relief valve (13) being disposed in the propellant tank crossover line (22).

6. The cryogenic propellant crossover pressurized delivery system of claim 2, further comprising a liquid oxygen tank relief valve (8), the liquid oxygen tank relief valve (8) being disposed in the liquid oxygen tank crossover pressurized line (20).

7. A cryogenic propellant crossover pressurized delivery system as claimed in claim 3, further comprising a liquid oxygen delivery manifold (18); each set of said booster delivery unit comprises a plurality of said engines (3); the liquid oxygen delivery manifold (18) comprises a top connecting port and a plurality of side connecting ports, wherein the top connecting port is communicated with the liquid oxygen delivery main pipeline (16), and the side connecting ports are connected with the engine (3) through liquid oxygen branch delivery pipes (19); the number of the side connection ports is the same as the number of the engines (3) in each set of the booster delivery system.

8. The cryogenic propellant crossover boost feed system of claim 7, wherein each of the boost feed units comprises eight of the engines (3), and the liquid oxygen feed manifold (18) is nine-way.

9. The cryogenic propellant crossover pressurized delivery system of claim 2, wherein there are three sets of pressurized delivery units.

10. A parallel rocket, characterized in that a first stage assembly of the parallel rocket is provided with a low-temperature propellant cross-supercharging conveying system as claimed in any one of claims 1 to 8; the primary assembly of the parallel rocket comprises a core primary rocket body (100) and two boosting primary rocket bodies (200) arranged at the sides of the core primary rocket body; and a set of pressurizing and conveying units are respectively arranged on the core primary arrow body (100) and each boosting primary arrow body (200).