CN112360647A - Multiple starting system of liquid rocket engine and starting control method thereof - Google Patents
Multiple starting system of liquid rocket engine and starting control method thereof Download PDFInfo
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- CN112360647A CN112360647A CN202010897756.6A CN202010897756A CN112360647A CN 112360647 A CN112360647 A CN 112360647A CN 202010897756 A CN202010897756 A CN 202010897756A CN 112360647 A CN112360647 A CN 112360647A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention relates to a multiple starting system of a liquid rocket engine and a starting control method thereof, belonging to the technical field of liquid rocket engines. When the engine is started, the battery supplies power to drive the electric coaxial pump to work, and liquid oxygen and liquid methane respectively enter the fuel gas generator and the thrust chamber after being pressurized by the electric pump and are ignited in an electric ignition mode; the liquid oxygen and the liquid methane entering the fuel gas generator are combusted to generate fuel gas which drives a main turbine pump of the engine to start rotating, so that the starting process of the engine is completed; the propellant provided by the electric coaxial pump for the fuel gas generator and the thrust chamber is used as a torch to ignite the main flow of the propellant in the ignition state, so that the ignition of the engine combustion chamber is completed.
Description
Technical Field
The invention relates to a multiple starting system of a liquid rocket engine and a starting control method thereof, belonging to the technical field of liquid rocket engines.
Background
The low cost and the repeated use are the ultimate pursuit targets of space transportation, and in recent years, the liquid oxygen methane engine becomes one of the popular research directions of domestic and foreign space power due to the excellent low cost and the repeated use performance. In the same launching task and the repeated use task, the engine needs to be repeatedly started for many times, and a simple and reliable multiple starting technology is important for reducing the cost of the engine and improving the performance of the engine.
The starting process of the generator circulating liquid oxymethane engine mainly comprises two parts, namely starting rotation of a turbine pump and ignition of a combustion chamber, wherein the two parts work independently at present. The starting mode of the turbopump mainly comprises starting of a gunpowder starter, gas cylinder cyclone and the like, and multiple times of starting of the engine require multiple gunpowder starters or carry multiple gas cylinders; the ignition mode of the combustion chamber mainly comprises the ignition of a cartridge igniter, torch type electric ignition and the like, the ignition mode of the cartridge igniter also has the problem that a plurality of cartridge igniters are needed when the cartridge igniter is started for a plurality of times, and the torch type electric ignition has excellent multi-ignition capability but needs a set of independent complex ignition system. The mode is acceptable for the engine with one-time starting or two-time starting, and if the engine needs to have the capabilities of three-time starting and more than three-time repeated use, the design difficulty of the engine is greatly increased and the use and maintenance of the engine are reduced.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the generator circulating liquid oxygen methane engine multi-starting system integrating ignition and rotation is designed, external energy is not needed, and the engine can be started for multiple times infinitely.
The technical scheme of the invention is as follows: a liquid rocket engine multi-starting system comprises a fuel gas generator, a main turbine pump, an electric coaxial pump, a thrust chamber, a generator oxygen valve, a generator methane valve, a generator ignition oxygen valve, a generator ignition methane valve, a thrust chamber oxygen valve, a thrust chamber methane valve and a battery;
the liquid oxygen output port of the main turbine pump is respectively connected with one end of the generator oxygen valve and one end of the thrust chamber oxygen valve, and the liquid oxygen input port of the electric coaxial pump is used as an oxidant input port of the multiple starting system of the engine;
the methane output port of the main turbine pump is respectively connected with one end of a methane valve of the generator, one end of a methane valve of the thrust chamber and a methane input port of the electric coaxial pump and is used as a fuel input port of the engine multi-time starting system;
the other end of the generator oxygen valve is connected with an oxidant input port of the gas generator; the other end of the methane valve of the generator is connected with a fuel input port of the gas generator;
the other end of the thrust chamber oxygen valve is connected with an oxidant input port of the thrust chamber; the other end of the thrust chamber methane valve is connected with a fuel input port of the thrust chamber;
one end of the generator ignition oxygen valve is communicated with a liquid oxygen output port of the electric coaxial pump, and the other end of the generator ignition oxygen valve is connected with an ignition chamber oxidant input port of the fuel gas generator;
one end of the generator ignition methane valve is communicated with a methane output port of the electric coaxial pump, and the other end of the generator ignition methane valve is connected with a fuel input port of an ignition chamber of the fuel gas generator;
the outlet of the fuel gas generator is connected with the fuel gas input port of the main turbine pump of the engine;
the battery is connected with the electric coaxial pump through a cable.
The electric coaxial pump comprises a motor, an oxygen pump and a methane pump, the motor is connected with the battery, and an output shaft of the motor is coaxially connected with the oxygen pump and the methane pump;
when the engine is started, the battery provides electric energy for the motor to start rotation, so that the outlet pressure of the oxygen pump and the outlet pressure of the methane pump of the electric coaxial pump are increased; after the engine is started, the motor stops working, the oxygen pump is driven to rotate by liquid oxygen, the liquid methane is driven to rotate by the liquid methane, and then electricity is generated to charge the battery to prepare for the next starting of the engine.
Based on the engine system, the invention also provides an engine starting control method, which comprises the following steps:
s0, respectively introducing the liquid oxygen and the liquid methane into the electric coaxial pump through the main turbine pump;
s1, controlling the electric coaxial pump to start rotating to reach a first rotating speed, simultaneously opening the generator ignition oxygen valve and the generator ignition methane valve, pressurizing liquid oxygen and liquid methane by the electric coaxial pump, then entering the ignition chamber of the fuel gas generator, and igniting by an electric igniter to form a fuel gas torch;
s2, a gas torch in the gas generator enters the main turbine pump and then drives a turbine to do work, and the main turbine pump starts rotating;
s3, opening the thrust chamber oxygen valve and the thrust chamber methane valve to enable fuel and propellant to enter the thrust chamber and be ignited, and simultaneously controlling the electric coaxial pump to reach a second rotating speed;
s4, controlling the electric coaxial pump to reach a third rotating speed, so that the pressure in the fuel gas generator is increased;
s5, opening the generator oxygen valve and the generator methane valve, and enabling oxidant and fuel to enter the fuel gas generator through the generator oxygen valve and the generator methane valve respectively and to be ignited by a fuel gas torch, so that the engine gradually transits to the main-stage working condition and the starting process of the engine is completed.
The first speed is such that the pressure in the gas generator is 10% of the nominal pressure of the gas generator.
The value range of the second rotating speed is that the pressure in the thrust chamber reaches 10% of the rated pressure of the thrust chamber.
The third rotating speed is in a value range such that the pump outlet pressure of the main turbine pump is increased to 20% of the rated pressure of the main turbine pump.
Compared with the prior art, the invention has the beneficial effects that:
(1) the engine is started by pressurizing a small amount of propellant by the electric pump, burning the propellant in the fuel gas generator to generate fuel gas and driving the main turbine pump to start, so that the engine has excellent multi-starting capability and better starting process consistency.
(2) The ignition device and the turbine pump rotation starting device are integrated into a whole, so that an engine system is simplified, and the reliability of the engine is improved.
(3) The invention adopts electric energy as external energy for starting, the engine is reversely charged when the main stage works, and compared with the starting of a gunpowder starter, the invention does not need to replace initiating explosive devices and does not need to charge or discharge gas when compared with the starting of a gas cylinder, thereby greatly improving the repeated use and maintenance of the engine.
(4) The invention can enable the engine to be used in different scenes and task profiles under the condition of not changing the technical state, broadens the application range of the engine and reduces the cost of the engine.
(5) The invention can realize the repeated starting of the engine by using the same device, releases the space occupied by initiating explosive devices and gas cylinders, and greatly optimizes the layout of the engine.
Drawings
FIG. 1 is a structural diagram of a multiple-starting system of a generator circulating liquid oxygen methane engine integrating ignition and rotation in the embodiment of the invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
Fig. 1 is a system configuration diagram of an embodiment of the present invention, and referring to fig. 1, the multiple start system of a liquid rocket engine provided by the present invention includes a gas generator 1, a main turbo pump 2, an electric coaxial pump 3, a thrust chamber 4, a generator oxygen valve 5, a generator methane valve 6, a generator ignition oxygen valve 7, a generator ignition methane valve 8, a thrust chamber oxygen valve 9, a thrust chamber methane valve 10, and a battery 11;
a liquid oxygen output port of the main turbine pump 2 is respectively connected with one end of a generator oxygen valve 5 and one end of a thrust chamber oxygen valve 9, and a liquid oxygen input port of the electric coaxial pump 3 is used as an oxidant input port of an engine multi-starting system;
a methane output port of the main turbopump 2 is respectively connected with one end of a methane valve 6 of the generator, one end of a methane valve 10 of the thrust chamber and a methane input port of the electric coaxial pump 3 and is used as a fuel input port of the engine multi-starting system;
the other end of the generator oxygen valve 5 is connected with an oxidant input port of the gas generator 1; the other end of the generator methane valve 6 is connected with a fuel input port of the gas generator 1;
the other end of the thrust chamber oxygen valve 9 is connected with an oxidant input port of the thrust chamber 4; the other end of the thrust chamber methane valve 10 is connected with a fuel input port of the thrust chamber 4;
one end of the generator ignition oxygen valve 7 is communicated with a liquid oxygen output port of the electric coaxial pump 3, and the other end of the generator ignition oxygen valve is connected with an ignition chamber oxidant input port of the fuel gas generator 1;
one end of the generator ignition methane valve 8 is communicated with the methane output port of the electric coaxial pump 3, and the other end is connected with the fuel input port of the ignition chamber of the gas generator 1;
the outlet of the gas generator 1 is connected with the gas input port of the engine main turbine pump 2;
the battery 9 is connected with the electric coaxial pump 3 through a cable.
The electric coaxial pump 3 comprises a motor, an oxygen pump and a methane pump, the motor is connected with the battery 9, and an output shaft of the motor is coaxially connected with the oxygen pump and the methane pump;
when the engine is started, the battery provides electric energy for the motor to start rotation, so that the outlet pressure of the oxygen pump and the outlet pressure of the methane pump of the electric coaxial pump are increased; after the engine is started, the motor stops working, the oxygen pump is driven to rotate by liquid oxygen, the liquid methane is driven to rotate by the liquid methane, and then electricity is generated to charge the battery to prepare for the next starting of the engine.
Based on the liquid rocket engine multi-starting system, the invention also provides a corresponding engine starting control method, which comprises the following steps:
s0, and the liquid oxygen and the liquid methane respectively enter the electric coaxial pump 3 through the main turbopump 2;
s1, supplying power to the electric coaxial pump 3 by a battery 11, controlling the electric coaxial pump 3 to start rotating to reach a first rotating speed, simultaneously opening the generator ignition oxygen valve 7 and the generator ignition methane valve 8, pressurizing liquid oxygen and liquid methane by the electric coaxial pump 3, then entering an ignition chamber of the fuel gas generator 1, and igniting by an electric igniter to form a fuel gas torch; the first rotational speed is set to a value that the pressure in the gas generator 1 is 10% of the nominal pressure of the gas generator 1.
s2, after a gas torch in the gas generator 1 enters the main turbine pump 2, driving a turbine to do work, and rotating the main turbine pump 2, so that the pump outlet pressure of the main turbine pump 2 is increased to 10% of the rated pressure;
s3, opening the thrust chamber oxygen valve 9 and the thrust chamber methane valve 10 to enable fuel and propellant to enter the thrust chamber 4 and be ignited, and simultaneously controlling the electric coaxial pump 3 to reach a second rotating speed; the second rotational speed is set to a value in such a range that the pressure in the thrust chamber 4 reaches 10% of the rated pressure.
s4, controlling the electric coaxial pump 3 to reach a third rotating speed, so that the pressure in the fuel gas generator 1 is increased; the third rotation speed is in a range that the pump outlet pressure of the main turbine pump 2 is increased to 20% of the rated pressure.
s5, opening the generator oxygen valve 5 and the generator methane valve 6, respectively, the oxidant and the fuel enter the gas generator 1 through the generator oxygen valve 5 and the generator methane valve 6, and are ignited by a gas torch, so that the engine gradually transits to the main-stage working condition, and the engine starting process is completed.
Further, after the engine enters the main-stage working condition and works stably, the electric coaxial pump 3 stops supplying power, meanwhile, high-pressure liquid oxygen and liquid methane flow through the electric coaxial pump 3 to enter the fuel gas generator 1 under the action of pressure difference to drive the electric coaxial pump 3 to rotate, and a motor therein generates power and charges the battery 11 to prepare for the next starting of the engine.
The fuel gas generator is provided with a generator oxygen valve and a generator methane valve in a liquid oxygen path and a liquid methane path respectively, and a bypass path is arranged in front of the two valves respectively to enable the liquid oxygen and the liquid methane to enter the electric coaxial pump. Liquid oxygen and liquid methane are respectively divided into two paths after being pressurized by the electric coaxial pump, wherein one path of liquid oxygen and liquid methane enters the fuel gas generator through the ignition oxygen valve and the ignition methane valve of the generator, and the other path of liquid oxygen and liquid methane enters the thrust chamber through the ignition oxygen valve and the ignition methane valve of the thrust chamber.
When the engine is started, the battery supplies power to drive the electric coaxial pump to work, and liquid oxygen and liquid methane respectively enter the fuel gas generator and the thrust chamber after being pressurized by the electric pump and are ignited in an electric ignition mode; the liquid oxygen and the liquid methane entering the fuel gas generator are combusted to generate fuel gas which drives a main turbine pump of the engine to start rotating, so that the starting process of the engine is completed; the propellant provided by the electric coaxial pump for the fuel gas generator and the thrust chamber is used as a torch to ignite the main flow of the propellant in the ignition state, so that the ignition of the engine combustion chamber is completed.
Further, after the engine is started, the motor of the electric coaxial pump stops working, the electric coaxial pump is driven to rotate by high-pressure liquid oxygen and liquid methane at the inlet, and then power is generated to charge the battery, so that preparation is made for the next starting of the engine, and the function of starting for multiple times is realized.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (6)
1. A liquid rocket engine multi-starting system is characterized by comprising a fuel gas generator (1), a main turbine pump (2), an electric coaxial pump (3), a thrust chamber (4), a generator oxygen valve (5), a generator methane valve (6), a generator ignition oxygen valve (7), a generator ignition methane valve (8), a thrust chamber oxygen valve (9), a thrust chamber methane valve (10) and a battery (11);
a liquid oxygen output port of the main turbine pump (2) is respectively connected with one end of a generator oxygen valve (5) and one end of a thrust chamber oxygen valve (9), and a liquid oxygen input port of the electric coaxial pump (3) is used as an oxidant input port of an engine multi-starting system;
a methane output port of the main turbine pump (2) is respectively connected with one end of a generator methane valve (6), one end of a thrust chamber methane valve (10) and a methane input port of the electric coaxial pump (3) and is used as a fuel input port of an engine multi-starting system;
the other end of the generator oxygen valve (5) is connected with an oxidant input port of the gas generator (1); the other end of the generator methane valve (6) is connected with a fuel input port of the gas generator (1);
the other end of the thrust chamber oxygen valve (9) is connected with an oxidant input port of the thrust chamber (4); the other end of the thrust chamber methane valve (10) is connected with a fuel input port of the thrust chamber (4);
one end of the generator ignition oxygen valve (7) is communicated with a liquid oxygen output port of the electric coaxial pump (3), and the other end of the generator ignition oxygen valve is connected with an ignition chamber oxidant input port of the fuel gas generator (1);
one end of the generator ignition methane valve (8) is communicated with a methane output port of the electric coaxial pump (3), and the other end of the generator ignition methane valve is connected with a fuel input port of an ignition chamber of the gas generator (1);
the outlet of the gas generator (1) is connected with the gas input port of the engine main turbine pump (2);
the battery (9) is connected with the electric coaxial pump (3) through a cable.
2. A multiple start system for a liquid rocket engine according to claim 1, wherein said electric coaxial pump (3) comprises an electric motor, an oxygen pump, a methane pump, said electric motor being connected to said battery (9), the output shaft of said electric motor being coaxially connected to said oxygen pump and said methane pump;
when the engine is started, the battery provides electric energy for the motor to start rotation, so that the outlet pressure of the oxygen pump and the outlet pressure of the methane pump of the electric coaxial pump are increased; after the engine is started, the motor stops working, the oxygen pump is driven to rotate by liquid oxygen, the liquid methane is driven to rotate by the liquid methane, and then electricity is generated to charge the battery to prepare for the next starting of the engine.
3. An engine start control method based on the system of claim 1, characterized by comprising the steps of:
s0, and the liquid oxygen and the liquid methane respectively enter the electric coaxial pump (3) through the main turbopump (2);
s1, controlling the electric coaxial pump (3) to start rotating to reach a first rotating speed, simultaneously opening the generator ignition oxygen valve (7) and the generator ignition methane valve (8), pressurizing liquid oxygen and liquid methane by the electric coaxial pump (3), then entering an ignition chamber of the fuel gas generator (1), and igniting by an electric igniter to form a fuel gas torch;
s2, a gas torch in the gas generator (1) enters the main turbine pump (2) and then drives a turbine to do work, and the main turbine pump (2) starts rotating;
s3, opening the thrust chamber oxygen valve (9) and the thrust chamber methane valve (10) to enable fuel and propellant to enter the thrust chamber (4) and be ignited, and simultaneously controlling the electric coaxial pump (3) to reach a second rotating speed;
s4, controlling the electric coaxial pump (3) to reach a third rotating speed, so that the pressure in the fuel gas generator (1) is increased;
s5, opening the generator oxygen valve (5) and the generator methane valve (6), and enabling oxidant and fuel to enter the fuel gas generator (1) through the generator oxygen valve (5) and the generator methane valve (6) respectively and to be ignited by a fuel gas torch, so that the engine gradually transits to a main-stage working condition and the starting process of the engine is completed.
4. The engine start control method as set forth in claim 3, wherein the first rotational speed is in a range such that the pressure in the gas generator (1) reaches 10% of a rated pressure of the gas generator (1).
5. The engine start control method according to claim 3, characterized in that the second rotation speed is set to a value in a range such that the pressure in the thrust chamber (4) reaches 10% of the rated pressure of the thrust chamber (4).
6. The engine start control method according to claim 3, characterized in that the third rotational speed takes a range such that the pump outlet pressure of the main turbo pump (2) is raised to 20% of the rated pressure of the main turbo pump (2).
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| CN202010897756.6A CN112360647A (en) | 2020-08-31 | 2020-08-31 | Multiple starting system of liquid rocket engine and starting control method thereof |
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| CN202010897756.6A CN112360647A (en) | 2020-08-31 | 2020-08-31 | Multiple starting system of liquid rocket engine and starting control method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114483380A (en) * | 2021-12-23 | 2022-05-13 | 北京航天动力研究所 | Small-sized gas generating device capable of being started for multiple times |
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| JP2017218899A (en) * | 2016-06-03 | 2017-12-14 | 三菱重工業株式会社 | Rocket engine, missile, and method of operating rocket engine |
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Application publication date: 20210212 |