CN213540585U - Rocket engine high-precision metering device capable of stabilizing mass flow - Google Patents
Rocket engine high-precision metering device capable of stabilizing mass flow Download PDFInfo
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- CN213540585U CN213540585U CN202022840311.2U CN202022840311U CN213540585U CN 213540585 U CN213540585 U CN 213540585U CN 202022840311 U CN202022840311 U CN 202022840311U CN 213540585 U CN213540585 U CN 213540585U
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- mass flow
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Abstract
The utility model discloses a metering device of mass flow is stabilized to rocket engine high accuracy, include: the sonic nozzle is cylindrical, one end of the sonic nozzle is provided with an air inlet, the other end of the sonic nozzle is provided with an air outlet, the side wall close to the air outlet is inwards sunken to form a throat part, two ends of the fixed rod are fixedly connected to the edge of the air outlet of the sonic nozzle, the adjusting cone valve is conical, the reset spring is connected with the fixed rod, one end of the reset spring is connected with the hammer-shaped end of the adjusting cone valve, the temperature cam is used for pushing or loosening the adjusting cone valve through the connecting rod after being deformed due to the influence of temperature, so that the cone-shaped end of the adjusting cone valve moves relative to the throat part of the sonic nozzle, the gap between the cone-shaped end and the throat part is adjusted, and further the flow of gas passing through the gap is adjusted; the utility model discloses according to the medium temperature, compensate the roar area of sonic nozzle throat portion, greatly reduced gas supply system's mass flow change.
Description
Technical Field
The utility model belongs to rocket engine gas medium measures the regulation field, especially relates to a metering device of mass flow is stabilized to rocket engine high accuracy.
Background
The gas supply and regulation system of the rocket engine is a system for providing various gases for the operation of the engine through a storage tank valve combination, an electromagnetic valve, a pipeline and the like. The gas supply and regulation system mainly comprises a pump valve regulation scheme and a gas bottle decompression scheme, wherein the pump valve regulation scheme has large flow, good regulation performance but complex system and heavy weight, and is generally used for engines with complex working conditions; the gas cylinder decompression scheme reduces the high gas pressure of the gas cylinder into the gas with the pressure required by the engine to provide oxygen for the engine to work.
No matter what kind of gas is supplied, high-pressure gas is converted into low-pressure gas through a pressure reducer after a high-pressure gas cylinder, and elements such as a buffer, a sonic nozzle and the like are added according to different system requirements. The typical gas supply system comprises a controller, a gas cylinder, an electromagnetic stop valve, a pressure reducing valve, a pressure sensor before measurement, a sonic nozzle, a temperature sensor after measurement and a connector leading to a combustion chamber, wherein gas flows out of the gas cylinder, the electromagnetic stop valve controls whether the gas is led to a subsequent component or not, if the electromagnetic stop valve is opened, the gas outputs stable pressure after passing through the pressure reducing valve and then leads to the combustion chamber after passing through the sonic nozzle, and the pressure sensors are arranged in front of and behind the sonic nozzle.
The volume flow of the gas is only related to the pressure in front of the sonic nozzle and the throat area according to the characteristics of the sonic nozzle, and when the pressure in front of the sonic nozzle is constant, the volume flow of the gas is also constant. However, although the gas supply path, especially the oxidant supply path and the sonic nozzle can ensure stable volume flow, the temperature of the gas path including the gas cylinder outlet, the front and the back of the pressure reducing valve and the whole gas path is changed, and according to the gas characteristics, under the working environmental condition of the gas supply system, the density of the gas is greatly influenced by the temperature, so that the mass flow is greatly changed, and the performance of the engine is greatly influenced.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a metering device of mass flow is stabilized to rocket engine high accuracy to solve the gas mass flow that current gas supply system supplied with and cause the great problem of error because of temperature variation.
The utility model adopts the following technical scheme: a rocket engine high-precision mass flow stabilizing metering device comprises:
the sonic nozzle is cylindrical, one end of the sonic nozzle is provided with an air inlet, the other end of the sonic nozzle is provided with an air outlet, the side wall close to the air outlet is inwards sunken to form a throat part,
two ends of the fixed rod are fixedly connected with the edge of the air outlet of the sonic nozzle,
the adjusting cone valve is conical and is positioned in the sonic nozzle, the two ends of the adjusting cone valve are respectively a cone end and a flat bottom end, the cone end of the adjusting cone valve is used for extending into the throat part of the sonic nozzle,
a return spring which is positioned in the sonic nozzle, one end of the return spring is connected with the fixed rod, the other end of the return spring is connected with the hammer-shaped end of the adjusting cone valve,
the temperature cam is located outside the sonic nozzle, is fixedly connected with the flat bottom end of the adjusting cone valve through the connecting rod, is used for being influenced by temperature to generate deformation, pushes or loosens the adjusting cone valve through the connecting rod, so that the cone end of the adjusting cone valve moves relative to the throat part of the sonic nozzle, the gap between the cone end and the throat part is adjusted, and the flow of gas passing through the gap is adjusted.
Further, the air inlet is formed in one end side wall of the sonic nozzle.
Further, the connecting end of connecting rod and temperature cam is the arc, and the connecting end supports on temperature cam, and temperature cam receives the temperature influence to produce the deformation back, and its conflict point with the connecting end produces along the arc of connecting end and removes, and then makes connecting rod lateral shifting to make and adjust cone valve lateral shifting.
Furthermore, the fixing rod passes through the axis of the air outlet of the sonic nozzle, and one end of the return spring is fixed at the central position of the fixing rod.
The utility model has the advantages that: the utility model compensates the roar area of throat part of the sonic nozzle according to the medium temperature, greatly reduces the mass flow change of the gas supply system, improves the combustion efficiency of the engine, and simultaneously improves the performance, economy and reliability of the engine; the mechanical principle compensates the gas mass flow, thereby reducing the complexity of the system, simplifying the control calculation difficulty and improving the metering precision; can output gas with stable mass flow.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Wherein: 1. a sonic nozzle; 2. an air outlet; 3. adjusting a cone valve; 4. a return spring; 5. a temperature cam; 6. a tapered end; 7. flattening the bottom end; 8. a connecting rod; 9. the throat; 10. an air inlet.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
The utility model discloses a metering device of mass flow is stabilized to rocket engine high accuracy, as shown in figure 1, including sonic nozzle 1, dead lever, regulation cone valve 3, reset spring 4, temperature cam 5, sonic nozzle 1 is cylindricly, and air inlet 10 has been seted up to 1 one end of sonic nozzle, and gas outlet 2 has been seted up to the 1 other end of sonic nozzle, and air inlet 10 is seted up on one end lateral wall of sonic nozzle 1, and sonic nozzle 1 is close to the inside sunken throat portion 9 that forms of lateral wall of gas outlet 2.
The both ends fixed connection of dead lever is in the border department of the gas outlet 2 of sonic nozzle 1, adjust the cone valve 3 and be coniform, adjust the cone valve 3 and be located sonic nozzle 1, the both ends of adjusting the cone valve 3 are cone end 6 and flat bottom 7 respectively, the cone end 6 of adjusting the cone valve 3 is used for stretching into the throat 9 of sonic nozzle 1, reset spring 4 is located sonic nozzle 1, reset spring 4's one end and the connection of fixed lever, reset spring 4's the other end and the cone end 6 of adjusting the cone valve 3 are connected. The dead lever crosses the axle center of the 2 air outlets of the sonic nozzle 1, one end of the reset spring 4 is fixed in the central position of the dead lever.
Connecting rod 8 is the arc with temperature cam 5's link, and the link supports on temperature cam 5, and temperature cam 5 receives the temperature influence to produce the deformation back, and the conflict point of temperature cam 5 and link produces along the arc of link and removes, and then makes connecting rod 8 lateral shifting to make 3 lateral shifting of regulation cone valve.
The utility model discloses a possess sonic nozzle 1 of temperature correction function, be gas supply device before sonic nozzle 1, the gas after through sonic nozzle 1 finally accesss to rocket engine's combustion chamber, can obtain gaseous volume flow by sonic nozzle 1's characteristic and only be relevant with pressure before sonic nozzle 1 and throat area, when pressure is constant before sonic nozzle 1, gaseous volume flow is also invariable.
The temperature cam 5 can change the angular displacement of itself according to the temperature of medium, adjusts cone valve 3 and passes through connecting rod 8 with temperature cam 5 and contact each other, adjusts cone valve 3 and is fixed with reset spring 4 again. At normal temperature, the pressure in front of the sonic nozzle 1 is constant, i.e., the throttle area, as the output value of the pressure reducing valve and the position of the adjusting cone valve 3 are not changed, and thus the flow rate is constant.
When the gas temperature changes, the angular displacement of the temperature cam 5 changes, namely the contact point of the connecting end of the temperature cam 5 and the connecting rod 8 moves along the arc of the connecting end, so that the connecting rod 8 is pushed or loosened, the connecting rod 8 moves transversely, the adjusting cone valve 3 moves transversely, the gap between the cone end 6 and the throat part 9 is changed, namely the throttle area is changed, the pressure in front of the sonic nozzle 1 is constant as the output value of the pressure reducing valve, and therefore the gas volume flow to the combustion chamber of the rocket engine changes, and the effect of correcting the gas mass flow is achieved.
The temperature cam 5 can be any temperature sensing element, or can be a single temperature compensation sheet or formed by combining temperature compensation sheets with different numbers in parallel and in series; the temperature cam 5 can also be a corrugated pipe with temperature sensitivity, and when the gas density variation range is small, the corrugated pipe can be selected to increase the metering precision; the temperature cam 5 can also be formed by combining a temperature-sensitive corrugated pipe and different numbers of temperature compensation plates in parallel and in series.
The gas medium can be oxygen, hydrogen and other common gases, when the types of the gases are different, the structural size change of the temperature cam 5 is in positive correlation or negative correlation with the gas temperature change according to the gas characteristics, if the gas supply device is provided with a plurality of metering spray pipes which are connected in parallel, a stop valve can be arranged in front of each metering spray pipe, the controller receives the state information of the metering device and the expected index information of a controlled object, and the control signal of the stop valve is calculated through a preset algorithm; the metering flow is adjusted by controlling the on-off of each stop valve.
The above description is only for the preferred embodiment of the present invention, and should not be construed as limiting the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.
Claims (4)
1. A rocket engine high accuracy stabilizes metering device of mass flow, its characterized in that includes:
the sonic nozzle (1) is cylindrical, one end of the sonic nozzle is provided with an air inlet (10), the other end of the sonic nozzle is provided with an air outlet (2), the side wall close to the air outlet (2) is inwards sunken to form a throat part (9),
two ends of the fixed rod are fixedly connected with the edge of the air outlet (2) of the sonic nozzle (1),
the adjusting cone valve (3) is conical and is positioned in the sonic nozzle (1), the two ends of the adjusting cone valve are respectively a cone-shaped end (6) and a flat bottom end (7), the cone-shaped end (6) is used for extending into the throat part (9) of the sonic nozzle (1),
a return spring (4) which is positioned in the sonic nozzle (1), one end of the return spring is connected with the fixed rod, the other end of the return spring is connected with the hammer-shaped end of the adjusting cone valve (3),
temperature cam (5), be located outside sonic nozzle (1), through flat bottom (7) fixed connection of connecting rod (8) and regulation cone valve (3), temperature cam (5) are used for receiving temperature influence to produce the deformation after, promote or loosen through connecting rod (8) and adjust cone valve (3) for cone end (6) relative sonic nozzle (1) throat (9) of adjusting cone valve (3) move, and then adjust the clearance between cone end (6) and throat (9), and then adjust the flow of the gas through this clearance.
2. A rocket engine high accuracy mass flow metering device according to claim 1, characterized in that said air inlet (10) is opened on one end side wall of sonic nozzle (1).
3. The rocket engine high-precision mass flow metering device of claim 2, wherein the connecting end of the connecting rod (8) and the temperature cam (5) is arc-shaped, the connecting end abuts against the temperature cam (5), after the temperature cam (5) is deformed under the influence of temperature, the contact point of the temperature cam and the connecting end moves along the arc-shaped connecting end, so that the connecting rod (8) moves transversely, and the adjusting cone valve (3) moves transversely.
4. A rocket engine high-precision mass flow rate metering device according to any one of claims 1-3, characterized in that the fixed rod crosses the axle center of the air outlet (2) of the sonic nozzle (1), and one end of the return spring (4) is fixed at the center of the fixed rod.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022840311.2U CN213540585U (en) | 2020-12-01 | 2020-12-01 | Rocket engine high-precision metering device capable of stabilizing mass flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022840311.2U CN213540585U (en) | 2020-12-01 | 2020-12-01 | Rocket engine high-precision metering device capable of stabilizing mass flow |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213540585U true CN213540585U (en) | 2021-06-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022840311.2U Active CN213540585U (en) | 2020-12-01 | 2020-12-01 | Rocket engine high-precision metering device capable of stabilizing mass flow |
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| CN (1) | CN213540585U (en) |
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2020
- 2020-12-01 CN CN202022840311.2U patent/CN213540585U/en active Active
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