A multiple launch vehicle power system

Abstract

A multi-start carrier power system, the design includes the power system architecture of the main power module, the auxiliary power module and the supercharged delivery module, the reusable carrier power scheme, the unified propellant type used by the main and auxiliary power systems, the simplified carrier power system, the improved reusable maintenance of the carrier power system, the realization of the multi-start function and the start number not limited by the starting device, with the multi-start, multi-reuse ability, while reducing the difficulty of power architecture design, the internal design optimizes the layout space, which simplifies the ignition system, improves the ignition reliability and stability, and the ignition number is not limited.

Description

Technical Field

[0001] This invention relates to a power system for a multi-start vehicle, belonging to the field of vehicle liquid propulsion technology. Background Technology

[0002] Low cost and reusability are among the future development goals of space transportation systems. Both domestic and international organizations are formulating relevant development strategies, and developing reusable launch vehicles has become an important way to implement these strategies. One of the keys to achieving launch vehicle reusability is the need for a launch vehicle propulsion system capable of multiple restarts. This system needs to be simple, reliable, capable of multiple restarts, and have good reusability and maintainability.

[0003] Space launch vehicle propulsion systems generally consist of a primary propulsion system and an auxiliary propulsion system. The primary propulsion system provides the launch vehicle with power, while the auxiliary propulsion system enables the launch vehicle to perform large-scale inter-orbit transfers, attitude adjustments, orbital changes, and propellant sinking. The primary and auxiliary propulsion systems are generally independent of each other and have their own independent pressurization and delivery systems.

[0004] Auxiliary propulsion systems currently commonly use conventional liquid propellant combinations (e.g., nitrogen tetroxide / methylhydrazine). Their advantages include mature technology and spontaneous combustion. However, for reusable launch vehicles, conventional propellant combinations have low specific impulse and are toxic, posing health risks to passengers and maintenance personnel. They are also inconvenient to use and maintain; after a launch vehicle returns to Earth for another flight, the auxiliary propulsion system needs cleaning or replacement, which is inconvenient for routine maintenance at launch and landing sites. Combustion products pollute the atmosphere. Furthermore, as an independent system, it is complex and costly.

[0005] For future reusable launch vehicles, their main propulsion systems often employ cryogenic propellant combinations, primarily liquid oxygen / hydrocarbons, which offer advantages such as easy space storage, high specific impulse, good maintainability, non-toxicity, and low cost. The main propulsion unit generally adopts a gas generator cycle, characterized by system simplicity and reliable operation. The starting process of a gas generator cycle engine mainly includes two parts: turbopump swirl starting and combustion chamber ignition. Turbopump swirl starting methods include propellant starter swirl starting and high-pressure gas cylinder swirl starting, while combustion chamber ignition methods include propellant igniter ignition and flare-type electric ignition. For one or two engine starts, the above methods are acceptable. However, if three or more starts and multiple reuses are required, turbopump swirl starting necessitates carrying multiple propellant starters or increasing the total gas volume, and combustion chamber ignition requires multiple propellant igniters or a complex flare-type electric ignition system. This results in a complex engine system and structure, reduced maintainability, and the number of starts within a mission cycle is limited by the number of devices in the starting system. Summary of the Invention

[0006] The technical problem solved by this invention is to address the issues of complex structure, low maintainability, and limited number of starts in traditional power systems in the current technology, and to propose a power system for a vehicle that can be started multiple times.

[0007] The present invention solves the above-mentioned technical problem through the following technical solution:

[0008] A multi-start vehicle propulsion system includes a main power module, an auxiliary power module, and a pressurization and delivery module. The pressurization and delivery module provides propellant to the main power module and the auxiliary power module, and the main power module and the auxiliary power module jointly output starting power. The operating mode of the propulsion system is determined according to the speed mode of the propellant electric pump in the pressurization and delivery module. The propellant electric pump includes a fuel electric pump and an oxidizer electric pump. In the first speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the main power module. In the second speed mode, the main power module ignites and outputs main thrust. In the third speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the auxiliary power module, and the auxiliary power module ignites and outputs auxiliary thrust after pre-cooling. In the fourth speed mode, both the main power module and the auxiliary power module ignite and output thrust until the power of the propellant electric pump in the pressurization and delivery module reaches the starting requirements and operates stably.

[0009] The booster delivery module includes a fuel tank, a fuel electric pump, an oxidizer tank, an oxidizer electric pump, a fuel discharge valve, and an oxidizer discharge valve. The fuel tank and oxidizer tank store fuel and oxidizer respectively, and are driven by the fuel electric pump and oxidizer electric pump respectively. The fuel discharge valve and oxidizer discharge valve control the output to the main power system and auxiliary power system.

[0010] The auxiliary power system includes an auxiliary power engine, an auxiliary power fuel valve, and an auxiliary power oxidizer valve. The auxiliary power engine is connected to the output port of the booster delivery module through the auxiliary power fuel valve and the auxiliary power oxidizer valve, receives the fuel and oxidizer delivered by the booster delivery module, and provides auxiliary thrust according to the speed mode of the booster delivery module.

[0011] The main power module includes a swirl-starting fuel valve, a swirl-starting oxidizer valve, a swirl-starting igniter, a plasma igniter, a turbine, a swirl-starting gas valve, a fuel pump, an oxidizer pump, a fuel discharge valve, an igniter fuel valve, an igniter oxidizer valve, a gas generator, a thrust chamber oxidizer valve, a thrust chamber fuel valve, an oxidizer discharge valve, and a thrust chamber.

[0012] The booster delivery module is connected to the swirl-starting igniter in the main power module via a swirl-starting fuel valve and a swirl-starting oxidizer valve. The swirl-starting igniter is equipped with a plasma igniter. The swirl-starting igniter is connected to the gas generator and turbine. The oxidizer tank is connected to the thrust chamber via an oxidizer pump and a thrust chamber oxidizer valve. The fuel tank is connected to the gas generator via a fuel pump and an igniter fuel valve. The gas generator is connected to the turbine. The fuel pump is connected to the bottom of the thrust chamber and simultaneously discharges excess fuel through a fuel discharge valve. The oxidizer pump is connected to the top of the thrust chamber and simultaneously discharges excess oxidizer through an oxidizer discharge valve. A plasma igniter is installed on the top of the thrust chamber.

[0013] Both the auxiliary power module and the main power module are controlled and transported by the pressurized delivery module. The fuel electric pump and the oxidizer electric pump in the pressurized delivery module have the same structure, both of which are integrated centrifugal pumps and motors. The fuel electric pump and the oxidizer electric pump are respectively located at the bottom of the fuel tank and the oxidizer tank, and are cooled by the propellant in the tank.

[0014] The propellant is fed into the swirl generator of the main propulsion module via the fuel electric pump and the oxidizer electric pump, respectively. When the plasma igniter is activated, the swirl fuel valve and the swirl oxidizer valve open, the fuel discharge valve and the oxidizer discharge valve close, and the swirl gas valve opens. After receiving the propellant, the swirl generator ignites it. The ignition of the swirl generator generates gas, which starts the turbine through the swirl gas valve and is discharged from the turbine outlet. The plasma igniter then stops working.

[0015] After the fuel valve and oxidizer valve of the igniter are opened, the gas generator receives the gas ignition action and continuously drives the turbine to provide thrust; after the main power module stably provides thrust, the swirl gas valve, swirl fuel valve, and swirl oxidizer valve are all closed, and the fuel electric pump and oxidizer electric pump stop operating.

[0016] In the main power module, a fuel pump, an oxidizer pump, and a turbine form a coaxial turbopump. A swirl-starting gas valve, a swirl-starting igniter, and a plasma igniter form a turbopump swirl-starting gas supply circuit for the turbopump of the swirl-starting main power module. The swirl-starting igniter generates gas as an ignition source for the plasma igniter. In the auxiliary power module, the auxiliary power engine receives fuel and oxidizer according to the on / off status of the auxiliary power fuel valve and the auxiliary power oxidizer valve to provide auxiliary thrust.

[0017] Before restarting, when the main power module is in a stable working state, the fuel electric pump and oxidizer electric pump are in the second speed mode. The fuel drain valve and oxidizer drain valve are opened to pre-cool the connecting pipeline. After the pre-cooling is completed, the fuel drain valve and oxidizer electric pump are raised to the third speed mode. The fuel drain valve and oxidizer drain valve are closed. The auxiliary power fuel valve and auxiliary power oxidizer valve are opened until the propellant enters the auxiliary power engine and completes ignition. The auxiliary power engine provides auxiliary thrust.

[0018] In the auxiliary power module, the auxiliary power engine, auxiliary power fuel valve, and auxiliary power oxidizer valve are redundantly configured. When any auxiliary power engine stops working, the corresponding auxiliary power fuel valve and auxiliary power oxidizer valve are closed. If all auxiliary power engines are shut down, the fuel electric pump and oxidizer electric pump are stopped.

[0019] The advantages of this invention compared to the prior art are:

[0020] (1) The present invention provides a power system for a multi-start vehicle, which, by setting up an electric pump for fuel and an electric pump for oxidizer, enables the auxiliary power module to share a set of pressurization and delivery modules with the main power module, abandons the conventional toxic propellant combination, and keeps consistent with the propellant combination of the main power module, simplifies the power system and structure of the vehicle, reduces the total mass, and improves reusability and maintainability;

[0021] (2) In this invention, the supply of propellant is not affected by the operation of the turbine pump of the main power system. The turbine pump swirl gas provided is regulated by the working characteristics of the electric pump and can be output stably. The swirl gas can be used as an ignition source, saving the ignition device of the gas generator. When the gas generator is ignited and the gas power can continue to increase the turbine pump speed, the gas supply of the swirl generator is cut off by closing the swirl gas valve, realizing the relay with the swirl generator. The working process of the electric pump and the swirl generator and the end of the working process are not coupled with the working process of the turbine pump of the main power system, which can reduce the design difficulty of the electric pump and the swirl generator.

[0022] (3) This invention replaces the gunpowder starter or the high-pressure gas cylinder's swirl turbine pump by setting a relatively independent swirl igniter, which also serves to ignite the gas generator. This not only makes the number of times the main power system starts not limited by the number of swirl devices, gas volume or ignition devices, but also controls the swirl process of the turbine pump by adjusting the power of the electric pump, so as not to change the original starting sequence of the main power system.

[0023] (4) The fuel electric pump and oxidizer electric pump used in this invention have the same structure, both consisting of a centrifugal pump and a motor. The pump and motor are designed as an integrated unit. The motor part uses an integrated shielding sleeve solution, which can improve the sealing performance and prevent the leakage of low-temperature propellant. The electric pump has a compact overall structure and can also use the flow medium to cool the motor.

[0024] (5) The present invention places the fuel electric pump and the oxidizer electric pump in the fuel tank and the oxidizer tank respectively and close to the bottom. There is no flow resistance loss in the inlet pipe during operation, which avoids cavitation of the pump under high flow conditions. Immersed in the tank, the propellant in the tank can also cool the motor, which avoids the motor from overheating and failure. Placing the electric pump in the tank can optimize the layout space.

[0025] (6) The fuel electric pump and oxidizer electric pump of the present invention provide two main functions: one is to send the propellant into the swirl generator, and the generated gas swirls the turbine pump and ignition gas generator of the main power system; the other is to provide propellant to the auxiliary power to generate thrust, so as to realize the functions of large-scale inter-orbit transfer, attitude adjustment, orbit change, and propellant sinking. In particular, before the main power system starts multiple times, the auxiliary power thrust is used to make the propellant sink to the bottom, increase the turbine pump inlet pressure and avoid pump cavitation.

[0026] (7) The electric pump of the present invention can realize multiple working modes and achieve the effect of "one pump for multiple uses": in the first speed mode, it provides pre-cooling flow to the auxiliary power system circuit and the pipeline before the swirl fuel / oxidant valve; in the second speed mode, it provides propellant for the turbine pump to start swirl in the swirl-starting burner; in the third speed mode, it provides propellant for the auxiliary power; and in the fourth speed mode, it provides propellant to both the auxiliary power and the turbine pump of the main power system for the propellant sinking to the bottom during the restart (multiple) start-up phase.

[0027] (8) This invention applies plasma ignition technology, which has advantages such as high ignition energy, high ignition reliability, wide availability and low price of ionization medium, and small amount of ionization medium used. The thrust chamber and the swirl-starting igniter adopt a plasma ignition system of uniform specifications, share a set of auxiliary systems and the same ionization medium (e.g., nitrogen). Different ignition energies are achieved by adjusting the plasma generator power of each igniter, replacing traditional gunpowder igniters, torch-type electric igniters, etc., which simplifies the ignition system, improves ignition reliability and stability, and allows for unlimited ignition times. Attached Figure Description

[0028] Figure 1 A schematic diagram of the power system for a multi-start vehicle provided for the invention;

[0029] Figure 2 Schematic diagram of the booster delivery module system provided for the invention;

[0030] Figure 3 A schematic diagram of the auxiliary power module system provided for the invention;

[0031] Figure 4 The schematic diagram of the main power module system provided for the invention; Detailed Implementation

[0032] A reusable launch vehicle power system is designed with a power system architecture including a main power module, an auxiliary power module, and a pressurization and delivery module. It is a reusable launch vehicle power solution that standardizes the types of propellants used in the main and auxiliary power systems, simplifies the launch vehicle power system, improves its reusability and maintainability, enables its multiple start-up function and the number of starts is not limited by the starting device, and has the ability to start and reuse multiple times. At the same time, it reduces the design difficulty of the power architecture, optimizes the layout space of the internal design, and has the effects of simplifying the ignition system, improving ignition reliability and stability, and allowing the number of ignitions to be unlimited.

[0033] In the multi-start launch vehicle power system, the pressurization and delivery module provides propellant to the main power module and auxiliary power module, while the main power module and auxiliary power module jointly output starting power. The operating mode of the power system is determined according to the speed mode of the propellant electric pump in the pressurization and delivery module, which includes a fuel electric pump and an oxidizer electric pump. In the first speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the main power module. In the second speed mode, the main power module ignites and outputs main thrust. In the third speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the auxiliary power module, and the auxiliary power module ignites and outputs auxiliary thrust after pre-cooling. In the fourth speed mode, both the main power module and the auxiliary power module ignite and output thrust until the propellant electric pump in the pressurization and delivery module reaches the starting requirements and operates stably.

[0034] The booster delivery module includes a fuel tank, a fuel electric pump, an oxidizer tank, an oxidizer electric pump, a fuel discharge valve, and an oxidizer discharge valve. The fuel tank and oxidizer tank store fuel and oxidizer respectively, and are driven by the fuel electric pump and oxidizer electric pump respectively. The fuel discharge valve and oxidizer discharge valve control the output to the main power system and auxiliary power system.

[0035] The auxiliary power system includes an auxiliary power engine, an auxiliary power fuel valve, and an auxiliary power oxidizer valve. The auxiliary power engine is connected to the output port of the booster delivery module through the auxiliary power fuel valve and the auxiliary power oxidizer valve. It receives the fuel and oxidizer delivered by the booster delivery module and provides auxiliary thrust according to the speed mode of the booster delivery module.

[0036] The main power module includes a swirl-starting fuel valve, a swirl-starting oxidizer valve, a swirl-starting igniter, a plasma igniter, a turbine, a swirl-starting gas valve, a fuel pump, an oxidizer pump, a fuel discharge valve, an igniter fuel valve, an igniter oxidizer valve, a gas generator, a thrust chamber oxidizer valve, a thrust chamber fuel valve, an oxidizer discharge valve, and a thrust chamber;

[0037] The booster delivery module is connected to the swirl-starting igniter in the main power module via a swirl-starting fuel valve and a swirl-starting oxidizer valve. The swirl-starting igniter is equipped with a plasma igniter. The swirl-starting igniter is connected to the gas generator and turbine. The oxidizer tank is connected to the thrust chamber via an oxidizer pump and a thrust chamber oxidizer valve. The fuel tank is connected to the gas generator via a fuel pump and an igniter fuel valve. The gas generator is connected to the turbine. The fuel pump is connected to the bottom of the thrust chamber and simultaneously discharges excess fuel through a fuel discharge valve. The oxidizer pump is connected to the top of the thrust chamber and simultaneously discharges excess oxidizer through an oxidizer discharge valve. A plasma igniter is installed on the top of the thrust chamber.

[0038] Both the auxiliary power module and the main power module are controlled and transported by the pressurized delivery module. The fuel electric pump and the oxidizer electric pump in the pressurized delivery module have the same structure, both of which are integrated centrifugal pumps and motors. The fuel electric pump and the oxidizer electric pump are respectively located at the bottom of the fuel tank and the oxidizer tank, and are cooled by the propellant in the tank.

[0039] Both the auxiliary power module and the main power module are controlled and transported by the pressurized delivery module. The fuel electric pump and the oxidizer electric pump in the pressurized delivery module have the same structure, both of which are integrated centrifugal pumps and motors. The fuel electric pump and the oxidizer electric pump are respectively located at the bottom of the fuel tank and the oxidizer tank, and are cooled by the propellant in the tank.

[0040] After the fuel valve and oxidizer valve of the ignition generator are opened, the gas generator receives the gas ignition action and continuously drives the turbine to provide thrust; after the main power module stably provides thrust, the swirl gas valve, swirl fuel valve, and swirl oxidizer valve are all closed, and the fuel electric pump and oxidizer electric pump stop operating.

[0041] In the main power module, the fuel pump, oxidizer pump, and turbine form a coaxial turbopump, while the swirl-starting gas valve, swirl-starting igniter, and plasma igniter form the turbopump's swirl-starting gas supply circuit for the turbopump of the swirl-starting main power module. The swirl-starting igniter generates gas as an ignition source for the plasma igniter. In the auxiliary power module, the auxiliary power engine receives fuel and oxidizer according to the on / off status of the auxiliary power fuel valve and auxiliary power oxidizer valve to provide auxiliary thrust.

[0042] Before restarting, when the main power module is in a stable working state, the fuel electric pump and oxidizer electric pump are in the second speed mode. The fuel drain valve and oxidizer drain valve are opened to pre-cool the connecting pipeline. After the pre-cooling is completed, the fuel drain valve and oxidizer electric pump are raised to the third speed mode. The fuel drain valve and oxidizer drain valve are closed. The auxiliary power fuel valve and auxiliary power oxidizer valve are opened until the propellant enters the auxiliary power engine and completes ignition. The auxiliary power engine provides auxiliary thrust.

[0043] In the auxiliary power module, the auxiliary power engine, auxiliary power fuel valve, and auxiliary power oxidizer valve are redundantly configured. When any auxiliary power engine stops working, the corresponding auxiliary power fuel valve and auxiliary power oxidizer valve are closed. If all auxiliary power engines are shut down, the fuel electric pump and oxidizer electric pump are stopped.

[0044] The following description, in conjunction with the accompanying drawings and preferred embodiments, provides further details:

[0045] In the current embodiment, such as Figure 1 As shown, the launch vehicle's power system consists of a main power module, an auxiliary power module, and a pressurized delivery module. The main power module and the auxiliary power module share the pressurized delivery module. The main power module and the pressurized delivery module constitute the main power system, and the auxiliary power module and the pressurized delivery module constitute the auxiliary power system.

[0046] like Figure 4 As shown, the fuel circuit of the main propulsion system consists of 1 fuel tank, 3 electric fuel pump, 5 fuel pump, 7 fuel drain valve 1, 9 combustor fuel valve, 11 thrust chamber fuel valve, 13 fuel drain valve 2, and 15 swirl-starting fuel valve; the oxidizer circuit consists of 2 oxidizer tank, 4 electric oxidizer pump, 6 oxidizer pump, 8 oxidizer drain valve 1, 10 combustor oxidizer valve, 12 thrust chamber oxidizer valve, 14 oxidizer drain valve 2, and 16 swirl-starting oxidizer valve; the gas circuit consists of 17 gas generator, 18 turbine, 19 swirl-starting gas valve, 20 thrust chamber, 21 swirl-starting combustor, and 25(b) plasma ignition system.

[0047] 5. Fuel pump, 6. Oxidant pump, and 18. Turbine form a coaxial turbopump for the main power system; 19. Swirling gas valve, 21. Swirling igniter, and 25(a) plasma ignition system constitute the turbopump swirl gas supply system, which is used for the turbopump of the swirl-starting main power system, replacing the functions of the gunpowder starter and high-pressure gas cylinder; the high-temperature gas used for swirl-starting can be used as an ignition source to ignite 17 gas generator.

[0048] like Figure 3As shown, the auxiliary power system's fuel route consists of 1 fuel tank, 3 fuel electric pump, 13 fuel drain valve 2, and 23 auxiliary power fuel valve; the oxidizer route consists of 2 oxidizer tank, 4 oxidizer electric pump, 14 oxidizer drain valve 2, and 24 auxiliary power oxidizer valve; the gas route consists of 22 auxiliary power engines, which can be divided into different types according to their functions such as enabling large-scale inter-orbit transfer, attitude adjustment, orbit change, and propellant sinking, and each engine has its own electric ignition system; the auxiliary power engines can be equipped in different quantities and types according to actual needs.

[0049] like Figure 2 As shown, the 3 fuel-electric pump and the 4 oxidizer-electric pump have the same structure, both consisting of a centrifugal pump and a motor. They adopt an integrated pump and motor design, with the motor using an integrated shielded sleeve scheme, allowing for cooling of the motor by the flow medium. The electric pump is placed inside a storage tank, eliminating inlet flow resistance loss during operation, and the motor can also be cooled by the propellant in the storage tank. The electric pump primarily provides two functions: first, it delivers propellant to the swirl-starting burner, generating gas to start the turbine pump of the main power system and ignite the gas generator; second, it provides propellant to the auxiliary power system to generate thrust. The electric pump can achieve multiple operating modes: in the first speed mode, it provides pre-cooling flow to the auxiliary power system; in the second speed mode, it provides propellant for the turbine pump to start the swirl of the swirl-starting burner; and in the third speed mode, it provides propellant to the auxiliary power system.

[0050] The 20 thrust chamber and 21 swirl igniter adopt a unified plasma ignition system, share a set of auxiliary systems and the same ionization medium (such as nitrogen), and achieve different ignition energies by adjusting the plasma generator power of each igniter, replacing traditional gunpowder igniters, torch-type electric igniters, etc.

[0051] The specific method for implementing a multiple-start vehicle power system is as follows:

[0052] 1. First start of the main power system

[0053] (1) Before starting, the pipelines between the 3 fuel electric pump and the 15 swirl-starting fuel valve and the 4 oxidant electric pump and the 15 swirl-starting oxidant valve need to be pre-cooled: first open the 13 fuel drain valve 2 and the 14 oxidant drain valve 2, and then make the 3 fuel electric pump and the 4 oxidant electric pump reach their respective first speed mode until the pipelines that provide propellant for the turbine pump to start swirl are pre-cooled.

[0054] (2) Make the 3 fuel electric pump and the 4 oxidizer electric pump reach the second speed mode respectively; 25(a) The plasma ignition system works, open the 15 swirl-starting fuel valve and the 16 swirl-starting oxidizer valve, close the 13 fuel discharge valve 2 and the 14 oxidizer discharge valve 2, open the 19 swirl-starting gas valve, the 21 swirl-starting burner is successfully ignited, and the generated gas starts the 18 turbine through the 19 swirl-starting gas valve and is discharged from the outlet of the 18 turbine. 25(a) The plasma ignition system stops working; adjust the power of the 3 fuel electric pump and the 4 oxidizer electric pump to make the gas power reach the required value and stabilize;

[0055] (3) Open the fuel valve of the 9 igniter and the oxidizer valve of the 10 igniter. The gas generator of 17 is successfully ignited by the swirling gas, and the generated gas continues to drive the turbine of 18.

[0056] (4) Close the 19 starting gas valve, the 15 starting fuel valve, and the 16 starting oxidizer valve. The 3 fuel electric pump and the 4 oxidizer electric pump stop working, and the main system power is working normally.

[0057] (5) During the operation of the main power system or before restarting after stopping, start the 3 fuel electric pump and 4 oxidizer electric pump according to actual needs and open the 13 fuel drain valve 2 and 14 oxidizer drain valve 2 to pre-cool the pipeline. After the auxiliary power system is pre-cooled, raise the 3 fuel electric pump and 4 oxidizer electric pump to the third speed mode, close the 13 fuel drain valve 2 and 14 oxidizer drain valve 2, open the 23 auxiliary power fuel valve and 24 auxiliary power oxidizer valve, and the propellant enters the 22 auxiliary power engine and is ignited to generate the required thrust.

[0058] (6) When one of the auxiliary power units stops working, simply close its own 23 auxiliary power fuel valve and 24 auxiliary power oxidant valve; if all auxiliary power units stop, close their respective 23 auxiliary power fuel valve and 24 auxiliary power oxidant valve, and stop the 3 fuel electric pump and 4 oxidant electric pump.

[0059] 2. Second or subsequent starts of the main power system

[0060] (1) Same as step 1-(1), but the engine pipeline used for sinking propellant in the auxiliary power unit needs to be pre-cooled.

[0061] (2) Increase the 3 fuel electric pump and 4 oxidizer electric pump to the third speed mode, close the 13 fuel drain valve 2 and 14 oxidizer drain valve 2, open the 23 auxiliary power fuel valve and 24 auxiliary power oxidizer valve, and the propellant enters the 22 auxiliary power engine and is ignited to generate the required thrust;

[0062] (3) Make the 3 fuel electric pump and the 4 oxidizer electric pump reach the fourth speed mode respectively; 25(a) The plasma ignition system works, open the 15 swirl-starting fuel valve and the 16 swirl-starting oxidizer valve, open the 19 swirl-starting gas valve, and the 21 swirl-starting burner is successfully ignited. The generated gas starts the 18 turbine through the 19 swirl-starting gas valve and is discharged from the outlet of the 18 turbine. 25(a) The plasma ignition system stops working; Adjust the power of the 3 fuel electric pump and the 4 oxidizer electric pump to make the gas power reach the required value and stabilize it;

[0063] (4) The subsequent steps are the same as steps 1 (3) and (4), to complete the second or more starts of the main power system.

[0064] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

[0065] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A power system for a multi-start vehicle, characterized in that: The system comprises a main power module, an auxiliary power module, and a pressurization and delivery module. The pressurization and delivery module provides propellant to the main power module and the auxiliary power module, and the main power module and the auxiliary power module jointly output swirl power. The operating mode of the power system is determined based on the speed mode of the propellant electric pump in the pressurization and delivery module, which includes a fuel electric pump and an oxidizer electric pump. In the first speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the main power module. In the second speed mode, the main power module ignites and outputs main thrust. In the third speed mode, the pressurization and delivery module pre-cools the pipeline between the pressurization and delivery module and the auxiliary power module, and the auxiliary power module ignites and outputs auxiliary thrust after pre-cooling. In the fourth speed mode, both the main power module and the auxiliary power module ignite and output thrust until the propellant electric pump in the pressurization and delivery module reaches the starting power requirement and operates stably. The pressurized delivery module includes a fuel tank, an oxidant tank, a first fuel discharge valve, and a first oxidant discharge valve. The fuel tank and the oxidant tank store fuel and oxidant respectively. The fuel tank is driven by a fuel electric pump, and the oxidant tank is driven by an oxidant electric pump. The fuel tank and the oxidant tank are controlled by the first fuel discharge valve and the first oxidant discharge valve to output to the main power module and the auxiliary power module. The auxiliary power module includes an auxiliary power engine, an auxiliary power fuel valve, and an auxiliary power oxidizer valve. The auxiliary power engine is connected to the output port of the booster delivery module through the auxiliary power fuel valve and the auxiliary power oxidizer valve, receives the fuel and oxidizer delivered by the booster delivery module, and provides auxiliary thrust according to the speed mode of the booster delivery module. The main power module includes a swirl-starting fuel valve, a swirl-starting oxidizer valve, a swirl-starting igniter, a plasma igniter, a turbine, a swirl-starting gas valve, a fuel pump, an oxidizer pump, a second fuel discharge valve, an igniter fuel valve, an igniter oxidizer valve, a gas generator, a thrust chamber oxidizer valve, a thrust chamber fuel valve, a second oxidizer discharge valve, and a thrust chamber; The booster delivery module is connected to the swirl starter in the main power module via a swirl starter fuel valve and a swirl starter oxidizer valve. The swirl starter is equipped with a plasma igniter. The swirl starter is connected to the gas generator and turbine. The oxidizer tank is connected to the thrust chamber via an oxidizer pump and a thrust chamber oxidizer valve. The fuel tank is connected to the gas generator via a fuel pump and a starter fuel valve. The gas generator is connected to the turbine. The fuel pump is connected to the bottom of the thrust chamber and simultaneously discharges excess fuel through a second fuel discharge valve. The oxidizer pump is connected to the top of the thrust chamber and simultaneously discharges excess oxidizer through a second oxidizer discharge valve. A plasma igniter is installed on the top of the thrust chamber. The propellant is fed into the swirl generator of the main propulsion module via the fuel electric pump and the oxidizer electric pump, respectively. When the plasma igniter is activated, the swirl fuel valve and the swirl oxidizer valve open, the second fuel discharge valve and the second oxidizer discharge valve close, and the swirl gas valve opens. After receiving the propellant, the swirl generator ignites it. The ignition of the swirl generator generates gas, which starts the turbine through the swirl gas valve and is discharged from the turbine outlet. The plasma igniter then stops working.

2. The power system for a multi-start vehicle according to claim 1, characterized in that: Both the auxiliary power module and the main power module are controlled and transported by the pressurized delivery module. The fuel electric pump and the oxidizer electric pump in the pressurized delivery module have the same structure, both of which are integrated centrifugal pumps and motors. The fuel electric pump and the oxidizer electric pump are respectively located at the bottom of the fuel tank and the oxidizer tank, and are cooled by the propellant in the tank.

3. The power system for a multi-start vehicle according to claim 2, characterized in that: After the fuel valve and oxidizer valve of the igniter are opened, the gas generator receives the gas ignition action and continuously drives the turbine to provide thrust; after the main power module stably provides thrust, the swirl gas valve, swirl fuel valve, and swirl oxidizer valve are all closed, and the fuel electric pump and oxidizer electric pump stop operating.

4. The power system for a multi-start vehicle according to claim 3, characterized in that: In the main power module, a fuel pump, an oxidizer pump, and a turbine form a coaxial turbopump. A swirl-starting gas valve, a swirl-starting igniter, and a plasma igniter form a turbopump swirl-starting gas supply circuit for the turbopump of the swirl-starting main power module. The swirl-starting igniter generates gas as an ignition source for the plasma igniter. In the auxiliary power module, the auxiliary power engine receives fuel and oxidizer according to the on / off status of the auxiliary power fuel valve and the auxiliary power oxidizer valve to provide auxiliary thrust.

5. A power system for a multi-start vehicle according to claim 4, characterized in that: Before restarting, when the main power module is in a stable working state, the fuel electric pump and oxidizer electric pump are in the second speed mode. The second fuel discharge valve and the second oxidizer discharge valve are opened to pre-cool the connecting pipeline. After the pre-cooling treatment is completed, the fuel electric pump and oxidizer electric pump are raised to the third speed mode. The second fuel discharge valve and the second oxidizer discharge valve are closed. The auxiliary power fuel valve and the auxiliary power oxidizer valve are opened until the propellant enters the auxiliary power engine and completes ignition. The auxiliary power engine provides auxiliary thrust.

6. The power system for a multi-start vehicle according to claim 5, characterized in that: In the auxiliary power module, the auxiliary power engine, auxiliary power fuel valve, and auxiliary power oxidizer valve are redundantly configured. When any auxiliary power engine stops working, the corresponding auxiliary power fuel valve and auxiliary power oxidizer valve are closed. If all auxiliary power engines are shut down, the fuel electric pump and oxidizer electric pump are stopped.

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