CN114776480A - Liquid rocket engine propellant storage tank based on piston drive - Google Patents
Liquid rocket engine propellant storage tank based on piston drive Download PDFInfo
- Publication number
- CN114776480A CN114776480A CN202210555626.3A CN202210555626A CN114776480A CN 114776480 A CN114776480 A CN 114776480A CN 202210555626 A CN202210555626 A CN 202210555626A CN 114776480 A CN114776480 A CN 114776480A
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- shell
- piston
- propellant
- outlet
- casing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/563—Control of propellant feed pumps
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Reciprocating Pumps (AREA)
Abstract
The invention discloses a liquid rocket engine propellant storage tank based on piston driving, which comprises: the device comprises a shell, a driving motor, a piston, a screw rod, a bearing seat, a piston and a pressure sensor, wherein the shell is of a closed structure, an outlet of the shell is communicated with a thrust chamber of a liquid rocket engine through a pipeline, the screw rod is positioned in an inner cavity of the shell, the screw rod is connected with the driving motor through a coupler, the direction of the screw rod is vertical to the direction of the piston, the screw rod penetrates through the center of the piston and extends to the outlet of the shell, the bearing seat is positioned in the inner cavity of the shell, is fixed at the outlet of the shell and is fixedly connected with the inner wall of the shell, the center position of the bearing seat is fixedly connected with the free end of the screw rod, the installation axis of the bearing seat is overlapped with the axis of the screw rod, and the piston is used for pushing liquid propellant in the shell to move to the outlet of the shell under the driving of the screw rod so as to further improve the pressure of the liquid propellant flowing through the outlet; the liquid propellant is extruded by the linear motion of the piston, so that the pressurization of the propellant is realized; the linear motion speed of the piston is controlled, so that the propellant is supplied according to the flow rate.
Description
Technical Field
The invention belongs to the field of liquid propellant storage tanks, and particularly relates to a liquid rocket engine propellant storage tank based on piston driving.
Background
The liquid propellant storage tank is mainly used for storing and managing liquid rocket engine propellant, and belongs to a component of a propellant supply system. Propellant supply systems are primarily comprised of both squeeze and pump types. The extrusion type supply system is generally used for small engines, the pumping type supply system can realize higher pressurization, but the system structure is complex, and the extrusion type supply system is mainly used for large and medium engines.
As engine technology advances, it is desirable that propellant supply systems be lighter and smaller. The extrusion type supply system is provided with a high-pressure gas cylinder, in order to ensure the pressurization effect capable of meeting the system requirement, gas stored in the gas cylinder needs to reach high pressure, so that the wall thickness of the gas cylinder needs to be designed to be thick, the mass of the gas cylinder is large, and the mass of the gas cylinder is negative for an engine; at the same time, in order to ensure that the propellant can be completely pressed out of the tank, the gas cylinder also takes up a certain amount of space, which is an inherent disadvantage of the pressed supply system.
The pumping type supply system adopts a turbine pump to pressurize the propellant, although the turbine pump is not as heavy as a gas cylinder, the structure of the turbine pump is complex, and the design of the turbine pump with good performance has certain difficulty. For some simple engines, it is desirable to be able to mitigate the negative mass of the supply system without at the same time making the system too complex.
Disclosure of Invention
The invention aims to provide a liquid rocket engine propellant storage tank based on piston driving, and aims to solve the problems that the existing storage tank is complex in structure, large in mass and volume and difficult to accurately control the outflow of propellant.
The invention adopts the following technical scheme: a piston-driven liquid rocket engine propellant tank comprising:
a shell which is a closed structure, is stored with liquid propellant and is provided with an inlet and an outlet which are oppositely arranged, the outlet of the shell is communicated with a thrust chamber of the liquid rocket engine through a pipeline,
a driving motor arranged opposite to the casing and near the inlet of the casing,
a piston which is positioned in the inner cavity of the shell,
the screw rod is positioned in the inner cavity of the shell, is connected with the driving motor through the coupler, has the direction vertical to the direction of the piston, penetrates through the center of the piston and extends to the outlet of the shell,
a bearing seat which is positioned in the inner cavity of the shell, is fixed at the outlet of the shell, is fixedly connected with the inner wall of the shell, is fixedly connected with the free end of the screw at the central position, and has the installation axis coincident with the axis of the screw,
the piston is used for pushing the liquid propellant in the shell to move towards the shell outlet under the driving of the screw rod, and further the pressure of the liquid propellant flowing through the outlet is improved.
Further, still include: the fixed bolster, the fixed bolster has the fixed horizontal pole of many level settings to constitute, and many fixed horizontal poles are parallel to each other, and encircle the casing entry setting, and the one end and the casing outer wall fixed connection of many fixed horizontal poles, its other end respectively with driving motor fixed connection for support and fix driving motor.
Further, still include: and the positioning support is positioned in the inner cavity of the shell and consists of a plurality of positioning support rods, each positioning support rod is arranged around the outlet of the shell, one end of each positioning support rod is fixedly connected with the inner wall of the shell, and the other end of each positioning support rod is fixedly connected with one side, close to the outlet, of the bearing block and is used for supporting and positioning the bearing block.
Further, the shell is formed by connecting a shell body and two end sockets through flanges.
Furthermore, the shell is provided with an air exhaust hole, and the air exhaust hole is used for vacuumizing the shell and filling nitrogen after propellant is filled, so that the shell is ensured to be free of oxygen.
The beneficial effects of the invention are: the liquid propellant is extruded by the linear motion of the piston, so that the pressurization of the propellant is realized; the linear motion speed of the piston is controlled, so that the propellant is supplied according to the flow rate; the motor drives the screw rod to rotate through the coupler, and the screw rod can drive the connected piston to do linear motion, so that the rotary motion is converted into linear motion, the space occupied by the pressurization conveying system is greatly reduced, and the space utilization rate of the engine is improved; the invention adopts the motor and the piston to realize the supply of the propellant, and compared with the mode of extruding the gas cylinder, the system has lighter weight; the pressurization and flow-based conveying of the propellant can be realized only by controlling the movement of the piston through the motor, and the system is simple in composition and strong in controllability.
Drawings
FIG. 1 is a schematic view of the present invention.
Wherein: 1. a housing; 2. a drive motor; 3. a piston; 4. a screw; 5. a bearing seat; 6. fixing a bracket; 7. positioning the bracket; 8. and (4) air exhaust holes.
Detailed Description
The invention is described in detail below with reference to the drawings and the detailed description.
The invention discloses a liquid rocket engine propellant storage tank based on piston driving, which comprises a shell 1, a driving motor 2, a piston 3, a screw rod 4 and a bearing seat 5, as shown in figure 1.
Casing 1 is enclosed construction, and the storage has liquid propellant in the casing 1, and casing 1 has the relative entry and the export that sets up, and casing 1 export is through pipeline and liquid rocket engine thrust chamber intercommunication, and driving motor 2 sets up with casing 1 relatively, and driving motor 2 is close to the entrance setting of casing 1.
Piston 3 is located 1 inner chamber of casing, screw rod 4 is connected with driving motor 2 through the shaft coupling, screw rod 4 moves towards perpendicular with piston 3's trend, screw rod 4 runs through the piston 3 center and extends to the exit of casing 1, bearing frame 5 is located 1 inner chamber of casing, bearing frame 5 is fixed in the exit of casing 1, bearing frame 5 and 1 inner wall fixed connection of casing, the central point of bearing frame 5 puts and the free end fixed connection of screw rod 4, the installation axis of bearing frame 5 and the coincidence of the axis of screw rod 4, wherein, piston 3 is used for promoting the liquid propellant in the casing 1 to the export motion under screw rod 4's the drive, and then improve the pressure when liquid propellant flows through the export.
The invention also includes: fixed bolster 6, fixed bolster 6 have the fixed horizontal pole of many levels setting to constitute, and many fixed horizontal poles are parallel to each other and encircle 1 entry settings of casing, the one end and the 1 outer wall fixed connection of casing of many fixed horizontal poles, the other end of many fixed horizontal poles respectively with driving motor 2 fixed connection, fixed bolster 6 is used for supporting and fixing driving motor 2.
The invention also includes: the positioning support 7, positioning support 7 are located 1 inner chamber of casing, and positioning support 7 comprises many location branch, and each location branch sets up around the export of casing 1, and the one end and the 1 inner wall fixed connection of casing of each location branch, the other end and the one side fixed connection that the bearing frame 5 is close to the export of each location branch, and positioning support 7 is used for supporting and the location bearing frame 5.
The shell 1 is formed by connecting a shell body and two end sockets through flanges. The casing 1 is provided with an air exhaust hole 8, and the air exhaust hole 8 is used for vacuumizing the casing 1 and filling nitrogen after propellant is filled, so that the casing 1 is ensured to be free of oxygen.
When the system works, a rotating shaft output by the motor drives the screw rod 4 to rotate through the coupler, the piston 3 can move rightwards along the screw rod 4 due to the connection effect of threads to extrude the liquid propellant, and the pressure of the propellant flowing through the outlet of the shell 1 is improved; the rotating speed of the screw rod 4 can be changed by controlling the output power of the motor, so that the moving speed of the piston 3 is controlled, and the flow of the propellant at the outlet of the shell 1 is further controlled.
After the propellant is filled, the inner cavity of the shell 1 is vacuumized through the air exhaust hole 8, and then nitrogen is filled, so that the situation that no oxygen exists in the shell 1 is ensured, and the propellant is safely stored is ensured. When the propellant automatic control device works, the motor is started to drive the piston 3 to extrude the propellant, so that the pressure of the propellant is increased to a preset value, then the propellant supply valve is opened, and the flow of the propellant is changed by controlling the moving speed of the piston 3.
The propellant supply system of a liquid rocket engine occupies a larger space and mass of the engine, and if a smaller and lighter supply system can be designed, the performance of the engine can be improved. The invention adopts the motor servo piston to drive the propellant supply, thereby not only realizing the self-adaptive adjustment of the supply pressure, but also changing the supply flow of the propellant by adjusting the rotating speed of the motor, and realizing the intelligent adjustment. In addition, the motor and the piston are adopted to replace a traditional air bottle and component in an extrusion type supply mode or a turbine pump and component of a pumping type supply system, so that the complexity of the system can be reduced, the mass of the system is reduced, and the volume of the system is reduced.
In order to improve the space utilization rate of the storage tank and reduce the weight of the storage tank in the prior art, a flexible film can be additionally arranged between gas and propellant of an extrusion type propellant storage tank, the flexible film is connected with the inner wall of the storage tank through a piston, and the filling and the supply of the propellant are realized through the movement of the piston. The method fully utilizes the space of the storage tank, but still needs the gas cylinder to realize the supply of the propellant, so that the extrusion of the gas cylinder can be replaced by mechanical pressurization, thereby lightening the quality of a supply system and improving the space utilization rate.
The invention adopts the piston 3 to extrude the propellant to realize supply, can simplify a supply system, carries out pressurization conveying on the propellant by the movement of the piston 3 and can realize the flow regulation of the propellant by controlling the movement speed of the piston 3.
Example 1
The example design was made for a certain hydrogen peroxide storage tank. The shell 1 is a cylindrical storage tank made of aluminum alloy 1100, the inner diameter of the storage tank is 430mm, the length of the storage tank is 800mm, the outlet pressure P of the shell 1 is 2MPa, the flow rate is 1.3kg/s, and the area A of the piston 3 is 0.1452m according to the inner diameter of the storage tank2。
Design of a screw rod 4: the diameter D of the screw rod 4 is 55mm, and the thread minor diameter D152.5mm, mounting spacing la800mm, coefficient η related to the mounting method210. The maximum axial load Fa of the screw 4 is 290400N according to the tank outlet pressure. Buckling load of screw 4
Allowable tensile compression load of screw 4
The maximum axial load is no greater than the buckling load and the allowable tensile compression load and therefore can be used.
Selecting a lead P of the screw 4 according to the diameter of the screw 4h10mm, the motor is selected from: the rated speed of the motor is selected to be n-1000 min-1. The flow rate is 1.3kg/s and the density of the hydrogen peroxide is 1400kg/m3Then the volume flow of hydrogen peroxide is required
The moving speed v of the piston 3 is QVWhen A is 0.0064m/s, the motor speed reduction ratio i is PhXn/v/60/1000 ═ 26.04, i ═ 27. Rotating torque T Fa × PhAnd/2 pi/eta/i is 19.02 N.m. The rated torque of the selected motor must be above 19.02N · m. Referring to a model selection manual, a loose MGME202GCM servo motor is selected, the rated power is 2000W, the rated rotating speed is 1000r/min, and the rated torque is 19.1 N.m.
The present invention is not limited to the above embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A liquid rocket engine propellant tank based on piston actuation, characterized in that it comprises:
the shell (1) is a closed structure, is stored with liquid propellant and is provided with an inlet and an outlet which are oppositely arranged, the outlet of the shell is communicated with a thrust chamber of the liquid rocket engine through a pipeline,
a drive motor (2) arranged opposite to the housing (1) and close to the inlet of the housing (1),
a piston (3) positioned in the inner cavity of the shell (1),
the screw (4) is positioned in the inner cavity of the shell (1), is connected with the driving motor (2) through a coupler, has a trend vertical to that of the piston (3), penetrates through the center of the piston (3) and extends to the outlet of the shell (1),
the bearing seat (5) is positioned in the inner cavity of the shell (1), is fixed at the outlet of the shell (1), is fixedly connected with the inner wall of the shell (1), is fixedly connected with the free end of the screw rod (4) at the central position, and has the installation axis coincident with the axis of the screw rod (4),
the piston (3) is used for pushing the liquid propellant in the shell (1) to move towards an outlet of the shell (1) under the driving of the screw (4), and further the pressure of the liquid propellant flowing through the outlet is improved.
2. A piston-drive-based liquid rocket engine propellant tank as claimed in claim 1, further comprising: fixed bolster (6), fixed bolster (6) have the fixed horizontal pole of many level settings to constitute, many fixed horizontal pole is parallel to each other and encircles casing (1) entry setting, many the one end and casing (1) outer wall fixed connection of fixed horizontal pole, its other end respectively with driving motor (2) fixed connection for support and fix driving motor (2).
3. A piston-drive based liquid rocket engine propellant tank according to claim 2, further comprising: locating support (7) is located casing (1) inner chamber comprises many location branch, each location branch sets up around casing (1) export, each location branch's one end and casing (1) inner wall fixed connection, its other end and bearing frame (5) are close to one side fixed connection of export for support and location bearing frame (5).
4. -liquid rocket engine propellant tank based on piston actuation according to any one of claims 1 to 3, characterized in that the housing (1) is formed by a shell body and two end closures which are flanged to each other.
5. The propellant tank of liquid rocket engine based on piston driving according to any one of claims 1-3, wherein said casing (1) is opened with a bleeder hole (8), said bleeder hole (8) is used for evacuating the casing (1) and filling nitrogen after the propellant is filled, so as to ensure that there is no oxygen in the casing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210555626.3A CN114776480A (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propellant storage tank based on piston drive |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210555626.3A CN114776480A (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propellant storage tank based on piston drive |
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| Publication Number | Publication Date |
|---|---|
| CN114776480A true CN114776480A (en) | 2022-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210555626.3A Pending CN114776480A (en) | 2022-05-20 | 2022-05-20 | Liquid rocket engine propellant storage tank based on piston drive |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040055642A1 (en) * | 2002-07-12 | 2004-03-25 | Dominique Valentian | Cryogenic rotary coupling, and use thereof in particular in articulated fluid feed lines, and in cryogenic propellant rocket engines |
| RU2459971C1 (en) * | 2011-03-23 | 2012-08-27 | Николай Борисович Болотин | Carrier rocket, liquid-propellant rocket engine and roll nozzle block |
| CN204738886U (en) * | 2015-06-29 | 2015-11-04 | 南京理工大学 | Use lotion propellant feed device of solid propellant as power supply |
| CN213807886U (en) * | 2020-11-19 | 2021-07-27 | 太原四度空间科技有限公司 | Pressurizing conveying device for liquid rocket engine storage tank |
| CN113586286A (en) * | 2021-07-08 | 2021-11-02 | 北京星途探索科技有限公司 | Liquid oxygen methane propellant supply system |
-
2022
- 2022-05-20 CN CN202210555626.3A patent/CN114776480A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040055642A1 (en) * | 2002-07-12 | 2004-03-25 | Dominique Valentian | Cryogenic rotary coupling, and use thereof in particular in articulated fluid feed lines, and in cryogenic propellant rocket engines |
| RU2459971C1 (en) * | 2011-03-23 | 2012-08-27 | Николай Борисович Болотин | Carrier rocket, liquid-propellant rocket engine and roll nozzle block |
| CN204738886U (en) * | 2015-06-29 | 2015-11-04 | 南京理工大学 | Use lotion propellant feed device of solid propellant as power supply |
| CN213807886U (en) * | 2020-11-19 | 2021-07-27 | 太原四度空间科技有限公司 | Pressurizing conveying device for liquid rocket engine storage tank |
| CN113586286A (en) * | 2021-07-08 | 2021-11-02 | 北京星途探索科技有限公司 | Liquid oxygen methane propellant supply system |
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