CN117184457B - Device and method for stabilizing pressure and liquid level of aerospace craft - Google Patents
Device and method for stabilizing pressure and liquid level of aerospace craft Download PDFInfo
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- CN117184457B CN117184457B CN202310922218.1A CN202310922218A CN117184457B CN 117184457 B CN117184457 B CN 117184457B CN 202310922218 A CN202310922218 A CN 202310922218A CN 117184457 B CN117184457 B CN 117184457B
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Abstract
The invention discloses a device for stabilizing pressure and liquid level of an aerospace craft, which comprises: the storage box is arranged on the aircraft and used for cooling the aircraft, and a high-temperature bin and a low-temperature bin are arranged in the storage box; the high temperature bin stores the same cooling working medium with the low temperature bin, and the periphery of the storage box is sequentially provided with: the storage tank low pressure sensor, the check valve, the heat exchanger, the pressure relief electromagnetic valve, the pressure boosting electromagnetic valve and the pressure reducing valve; a method is also disclosed: when the aircraft takes off and enters an acceleration state, the heat exchanger absorbs aerodynamic heat of the aircraft and transfers the aerodynamic heat to working media in the heat exchanger, so that the working media are in a high-temperature and high-pressure state; meanwhile, the high-pressure gas of the heat exchanger supplements pressure to the storage tank; when the aircraft is overloaded, the piston is prevented from moving reversely, and the pressure of the low-temperature bin of the storage tank is kept unchanged. The invention solves the problems that the prior art can not stabilize the liquid level of the storage tank, and additionally needs to be provided with a storage tank for storing a second working medium, so that the load of the aerospace craft is increased, and the production and operation costs are increased.
Description
Technical Field
The invention belongs to the technical field of storage tanks of aerospace vehicles, and particularly relates to a device and a method for stabilizing pressure and liquid level of an aerospace vehicle.
Background
The existing space craft carries a storage tank medium which is generally high-pressure liquid, the pressure drop in the medium discharge process can lead to the thermal property drop of the medium, and the reasonable pressure of the liquid side of the storage tank must be maintained in a pressurizing mode; in addition, radial and axial overload generated in the maneuvering processes of acceleration, deceleration, overturning and the like of the aerospace craft makes the liquid level of the storage tank difficult to keep stable, and the unstable liquid flow is easy to cause, and meanwhile, the gravity center of the storage tank is unstable, so that the attitude of the aerospace craft and the safety of the aerospace craft are directly influenced.
When the existing liquid carrier rocket device with the publication number of CN114607528A is used, hydrogen and liquid oxygen can be input through the top of the storage tank for mixed combustion, and the heat released by combustion enables helium to be heated to realize volume expansion, so that the purpose of pressurization is achieved; the method of soaking cold helium in liquid oxygen can be adopted, the helium can be gradually released after the temperature is raised, the volume is increased, and the purpose of pressurization is further realized; the cold helium can also be used for absorbing the waste heat of the engine, and the waste heat can be injected from the top of the storage tank after being heated to 300 ℃, so that the purpose of hot pressurization can also be realized.
Although the device can play a role in pressurizing in the storage tank of the aerospace vehicle, the liquid level of the storage tank cannot be stabilized, and the heated pressurized gas easily forms intense heat exchange with the liquid of the storage tank, so that the device is not beneficial to maintaining the thermophysical property of the liquid of the storage tank, and greatly reduces the operation stability of a thermal management system of the aerospace vehicle; and the pressurized gas is helium, so that ultralow temperature storage is needed, the volume expansion rate is low, and an additional helium storage device is needed, so that the load of the aerospace craft is increased, and the production and operation costs are increased. Therefore, there is a need for a regulated tank system that aims to improve the operational stability of a thermal management system of an aerospace vehicle, and there is a need for developing a device and method for regulating the pressure and the liquid level of an aerospace vehicle.
Disclosure of Invention
The invention provides a device and a method for stabilizing the pressure and the liquid level of an aerospace vehicle, which aim to solve the problems that the prior art cannot stabilize the liquid level of a storage tank, heated pressurized gas easily forms intense heat exchange with the liquid of the storage tank, and the operation stability of a thermal management system of the aerospace vehicle is greatly reduced; the second purpose is to solve the problems that in the prior art, the pressurized gas is helium, and a storage tank for storing a second working medium is additionally required to be equipped, so that the load of the aerospace craft is increased, and the production and operation costs are increased.
The invention adopts the following technical scheme for solving the technical problems:
a pressure and fluid level stabilizing device for an aerospace vehicle, comprising: the storage box 1 is arranged on the aircraft and used for cooling electronic equipment and high-temperature wall surfaces on the aircraft, and a high-temperature bin 101 and a low-temperature bin 102 are arranged in the storage box 1; the high temperature bin 101 and the low temperature bin 102 store the same cooling working medium, and the periphery of the storage tank 1, along the low temperature end of the storage tank 1 to the high temperature end of the storage tank 1, are sequentially provided with: a storage tank pressure sensor 8, a check valve 11, a heat exchanger 3, a pressure relief electromagnetic valve 7, a pressure boosting electromagnetic valve 6 and a pressure reducing valve 4; one side of the heat exchanger 3, which is close to the low temperature end of the storage tank, is connected with a check valve 11, and one side of the heat exchanger, which is close to the high temperature end of the storage tank, is connected with a pressure relief electromagnetic valve 7; the other end of the heat exchanger 3 is connected with a heat exchanger high pressure sensor 9 and a heat exchanger temperature sensor 10; the other end of the pressure relief electromagnetic valve 7 is connected with an overflow valve 5 matched with the pressure relief electromagnetic valve; the working medium of the high-temperature bin 101 is in a high-temperature and high-pressure state, and the cooling working medium of the low-temperature bin 101 is in a low-temperature and low-pressure state;
the method is characterized in that:
the heat exchanger 3 heats the cooling working medium in a low-temperature low-pressure state to a high-temperature high-pressure state by absorbing aerodynamic heat of the aircraft:
when the control system judges that the pressure of the low-temperature bin 102 is reduced and needs to be increased, the pressurizing electromagnetic valve 6 is opened, high-pressure gas in the heat exchanger 3 is conveyed to the high-temperature bin 101 of the storage tank 1 through the pressurizing electromagnetic valve 6 and the pressure reducing valve 4, and then the pressure is conveyed to the low-temperature bin 102 through the high-temperature bin 101, so that the low-temperature bin 102 is ensured to stabilize the pressure and the liquid level;
when the control system judges that working medium needs to be supplemented to the heat exchanger 3, the pressure relief electromagnetic valve 7 and the overflow valve 5 are opened to relieve pressure, and at the moment, the stored low-temperature working medium in the low-temperature bin 102 of the storage tank 1 is conveyed to the heat exchanger 3 through the check valve 11, so that the heat exchanger is changed from an under-pressure state to an accumulation state;
further, the storage tank 1 adopts an aluminum alloy lining, and carbon fiber materials are wound outside the storage tank, so that high pressure resistance and light weight are ensured; the storage tank 1 is internally separated from the low-temperature working medium by a piston 103; the storage tank 1 comprises a double-layer shell 107, a piston 103, a movable connecting rod 105 and a brake pad 104, wherein triangular ridges with opposite directions are arranged on the inner surface of the storage tank 1 and the outer surface of the piston 103.
Further, the piston 103 divides the tank 1 into a high temperature chamber 101 and a low temperature chamber 102, and the constant pressure control system is configured to: when the pressure of the low-temperature bin is lower than the specified pressure 102, the pressurizing electromagnetic valve 6 is opened, and the cooling working medium is heated and expanded into the high-temperature bin 101 through the heat exchanger 3, so that the pressure of the high-temperature bin 101 and the pressure of the low-temperature bin are balanced; when the working medium in the low-temperature bin 102 extrudes the piston 103, the piston 103 bulges to drive the connecting rod 105 to move, the linkage brake pad 104 forms extrusion force on the side surface of the piston 103, and the friction force is increased by matching with the triangular edges, so that the effect of preventing the piston from moving to the high-temperature bin is achieved.
A method for stabilizing the pressure and the liquid level of an aerospace vehicle by using a device for stabilizing the pressure and the liquid level of the aerospace vehicle is characterized by comprising the following steps of: the method comprises the following steps:
step one, when an aircraft takes off and enters an acceleration state, the heat exchanger 3 absorbs aerodynamic heat of the aircraft and transfers the aerodynamic heat to working media in the heat exchanger 3, so that the working media are in a high-temperature and high-pressure state; meanwhile, the storage tank 1 cools the aircraft, the pressure of the storage tank 1 is gradually reduced in the cooling process, and at the moment, the high-pressure gas of the heat exchanger 3 supplements the pressure to the storage tank 1, so that the pressure of the low-temperature bin 102 of the storage tank 1 is kept unchanged;
and step two, when the aircraft is overloaded and a reverse inertia force occurs, the reverse inertia force is prevented from extruding the piston 103 to move reversely, so that the pressure of the low-temperature bin 102 of the storage tank 1 is further ensured to be unchanged.
Further, the first step ensures that the pressure of the low-temperature chamber 102 of the storage tank 1 is unchanged, wherein the action process of the electromagnetic valve outside the storage tank 1 is as follows:
1) The cooling electromagnetic valve 12 of the storage tank is opened to provide cold energy for the aircraft, and at the moment, the low-temperature working medium of the low-temperature bin 102 of the storage tank enters a cooling system of the aircraft, and the pressure of the low-temperature bin 102 of the storage tank gradually drops;
2) When the control system judges that the pressure sensor 8 of the storage tank is lower than the specified pressure, the pressure reducing electromagnetic valve 6 at the high-temperature end of the storage tank is opened, and the high-temperature and high-pressure working medium in the heat exchanger 3 is supplemented into the high-temperature bin 101 of the storage tank through the pressure increasing electromagnetic valve 6 and the one-way pressure reducing valve 4 and then is transmitted to the low-temperature bin 102 through the high-temperature bin 101; when the pressure of the low-temperature bin 102 of the storage tank reaches the specified pressure, the pressurizing electromagnetic valve 6 at the high-temperature end of the storage tank is closed, and the pressurizing is stopped.
Further, the pressure of the low-temperature bin 102 of the storage tank 1 is kept unchanged, wherein the piston 103 in the storage tank (1) acts as follows:
1) When pressurizing the low-temperature bin 102, the pressure of the high-temperature bin 101 is higher than that of the low-temperature bin 102;
the piston 103 is extruded towards the direction of the low-temperature bin 102 under the action of pressure difference; the outer surface of the piston 103 and the anti-skid saw teeth on the inner surface of the storage tank 1 rub in the forward direction, and the friction force is small at the moment;
2) The bottom of the piston protrudes to the side of the low-temperature bin 102 under the action of pressure difference, the chassis 106 moves to the side of the low-temperature bin 102 relative to the piston, and the brake pad 104 contracts under the linkage action of the connecting rod 105 and is in a loose state;
3) When the pressure difference is larger than the critical value, the piston moves to the side of the low-temperature bin 102; when the pressure difference is larger than a critical value, namely in a non-extrusion state, the pressure difference required by the minimum thrust of the piston to move towards the low-temperature bin is generated.
Further, the pre-tightening force of the piston 103 is adjusted in advance according to the magnitude of the overload force by the adjustable link mechanism 105.
Further, the specific process of the second step is as follows:
1) When the heat exchanger is under-pressure, namely the pressure of the high-pressure sensor 9 on the heat exchanger 3 is lower than the specified pressure, and the temperature sensor 10 is higher than the set temperature, the pressurizing electromagnetic valve 6 is closed to stop pressurizing;
2) Opening a pressure relief electromagnetic valve 7, performing injection cooling on the high Wen Duanbi surface through an overflow valve 5, and simultaneously enabling a low-temperature working medium to enter a heat exchanger to cool the heat exchanger; the high-temperature end wall surface is the end surface of the outlet of the overflow valve 5.
3) When the temperature of the temperature sensor 10 is lower than the predetermined temperature, the electromagnetic valve 7 is closed, and the heat exchanger 3 starts heat absorption and pressure accumulation.
Further, after the heat exchanger 3 finishes pressure accumulation, when the control system judges that the pressure of the low-temperature bin 102 of the storage tank 1 is reduced, the electromagnetic valve 6 is opened, high-temperature high pressure is supplemented to the high-temperature bin 101 of the storage tank, and the pressure of the low-temperature bin 102 of the storage tank is continuously increased through the high-temperature bin 101 of the storage tank, so that a pressure stabilizing cycle is formed.
Further, an electric heater is arranged in the heat exchanger 3, and when the pneumatic heat is low and the pressure of the storage tank is required to be supplemented, an onboard power supply is used for heat source compensation.
Advantageous effects of the invention
1. The device has low manufacturing cost and the used medium is environment-friendly and safe: the storage medium of the storage tank takes organic working medium CO2 as an example, can effectively perform transcritical heat exchange, and has safe and simple process operation and low cost;
2. the circulation cooling efficiency is high, and the device lightweight degree is high: the cooling working medium absorbs heat required by cooling the wall surface and is used for self-pressurization, pressurized air is released when the temperature exceeds the temperature, the high-temperature end of the heat pipe heat exchanger is subjected to jet cooling, and the combination of heat conduction cooling and jet cooling realizes circulation cooling. Meanwhile, the mode does not need to carry other pressurizing air of non-cooling working media, is favorable for reducing the number of components of a cooling system, and realizes light weight.
3. The response speed of the stable pressure and the stable liquid level of the storage tank is high, and the controllability and the stability of the system are high: the pressure-stabilizing and liquid-stabilizing device automatically adjusts the liquid level and pressure balance through the movement of the piston according to pressure change by adding a piston with a connecting rod structure, ensures the stable flow of an outlet of the storage tank, and improves the stability of the aircraft;
drawings
FIG. 1 is a schematic diagram of an aerospace vehicle voltage and liquid level stabilizing device in actual use;
FIG. 2 is a schematic diagram of a cross-sectional structure of a tank of a pressure and liquid level stabilizing device of an aerospace vehicle.
FIG. 2a is an enlarged view of a portion of FIG. 2 in accordance with the present invention;
FIG. 2b is a partial exploded view of FIG. 2 in accordance with the present invention;
FIG. 3a is a schematic flow chart of the method of the present invention;
FIG. 3b is a detailed flow chart of an embodiment of the method of the present invention;
in the figure, 1 is a storage tank; 101-a high temperature bin; 102-a low-temperature bin; 103-a piston; 104-a brake pad; 105-an adjustable linkage; 106, a chassis; 107-a housing;
2-a three-way valve; 3-a heat exchanger; 4-a pressure reducing valve; 5-an overflow valve; 6-a pressurizing electromagnetic valve; 7-a pressure relief electromagnetic valve; 8-a low pressure sensor; 9-a high pressure sensor; 10-a temperature sensor; 11-check valve; 12-cooling the electromagnetic valve;
Detailed Description
The innovation point of the invention
1. The invention has the design difficulty that: the aerospace craft has the characteristics of high speed and strong maneuverability, and the storage tank of the aircraft in the prior art is difficult to meet the liquid level stability under the condition of high overload. The known tank solutions applied to vertical launch rockets and satellites all provide a series of solutions in this respect, but at present only very small normal overload conditions can be met, and even reverse overload conditions can not be met. The known storage tank cannot be directly applied to an aerospace vehicle, and the device and the method are provided for breaking through the key technology of stabilizing the pressure and the liquid level of the storage tank of the aerospace vehicle, which is needed urgently.
2. Three key points of the invention are: the aerospace craft liquid storage tank aims to solve three key technical problems: pressurizing, stabilizing and light weight.
Pressurizing: in the prior art, the pressurization is carried out by using another working medium, and the pressurization by using the other working medium needs to be additionally provided with a storage tank for storing a second working medium, so that the lightweight is not facilitated. The embodiment uses the working medium to fully utilize waste heat to carry out self-pressurization without carrying other working mediums, and the relationship between the air quantity and the heat absorption can be regulated through pressure feedback in the self-pressurization process, so that the pressure stability is realized. The relation between the air quantity and the heat absorption is adjusted through pressure feedback, namely: when the control system judges that the air quantity of the heat exchanger 3 is insufficient, the pressure release valve 7 is opened to discharge the waste gas with insufficient air quantity, and then the working medium of the low-temperature bin 102 enters the heat exchanger from the check valve 11 for continuous pressure; when the control system determines that the heat quantity of the heat exchanger 3 is insufficient, that is, the current aerodynamic heat absorbed by the heat exchanger 3 is low enough to generate high-pressure gas, an electric heater built in the heat exchanger 3 is adopted, and an onboard power supply is used for heat source compensation.
Stabilizing the liquid level: in the prior art, the liquid level shaking is reduced from the angles of pressurizing the high temperature bin 101 and supplementing the pressure of the low temperature bin 102, the liquid level shaking of the low temperature bin 102 can be generated under the condition that overload is not considered (when the liquid level shaking, high temperature gas can enter the low temperature bin 102, the cooling liquid discharged from the low temperature bin 102 is doped with gas, and the cooling effect is influenced because the temperature of the gas is higher than that of the liquid), for example, the reverse thrust formed by factors such as flight steering, faults and the like causes instant reverse pressure loss. The reverse braking device and the structure are designed, so that the liquid level cannot reversely travel under the extreme overload condition.
And (3) light weight: in this embodiment, after the heat absorption and cooling functions are completed by using the working medium of the self-body, the self-body is punched. Compared with the prior art, the prior art needs to carry a second working medium, so that the carrying work mass and the weight of extra equipment are increased; in the prior art, working medium (combustion) is directly discharged, and the working medium of the embodiment is used for pressurizing the working medium (heat exchange) after working, so that the heat and power conversion is realized, the utilization efficiency is improved, and the improvement of the efficiency is also a key technology for reducing the carrying capacity of the working medium.
The invention is further explained below with reference to the drawings:
a space vehicle voltage and liquid level stabilizing device, as shown in fig. 1, 2a and 2b, comprising: the storage box 1 is arranged on the aircraft and used for cooling electronic equipment and high-temperature wall surfaces on the aircraft, and a high-temperature bin 101 and a low-temperature bin 102 are arranged in the storage box 1; the high temperature bin 101 and the low temperature bin 102 store the same cooling working medium, and the periphery of the storage tank 1, along the low temperature end of the storage tank 1 to the high temperature end of the storage tank 1, are sequentially provided with: a storage tank low pressure sensor 8, a check valve 11, a heat exchanger 3, a pressure relief electromagnetic valve 7, a pressure boosting electromagnetic valve 6 and a pressure reducing valve 4; one side of the heat exchanger 3, which is close to the low temperature end of the storage tank, is connected with a check valve 11, and one side of the heat exchanger, which is close to the high temperature end of the storage tank, is connected with a pressure relief electromagnetic valve 7; the other end of the heat exchanger 3 is connected with a heat exchanger high pressure sensor 9 and a heat exchanger temperature sensor 10; the other end of the pressure relief electromagnetic valve 7 is connected with an overflow valve 5 matched with the pressure relief electromagnetic valve; the working medium of the high-temperature bin 101 is in a high-temperature and high-pressure state, and the cooling working medium of the low-temperature bin 101 is in a low-temperature and low-pressure state.
Supplementary explanation 1
In the embodiment, the working medium is in a high-temperature and high-pressure state of supercritical CO with the temperature of more than 35 ℃ and the pressure of more than 8.0MPa 2 The supercritical state is a third phase state that is distinguished from the gaseous and liquid states. The working medium is in a low-temperature and low-pressure state and is liquid CO with the temperature lower than 31.1 ℃ and the pressure between 7.5MPa and 8MPa 2 。
The method is characterized in that:
the heat exchanger 3 heats the cooling working medium in a low-temperature low-pressure state to a high-temperature high-pressure state by absorbing aerodynamic heat of the aircraft:
when the control system judges that the pressure of the low-temperature bin 102 is reduced and needs to be increased, the pressurizing electromagnetic valve 6 is opened, high-pressure gas in the heat exchanger 3 is conveyed to the high-temperature bin 101 of the storage tank 1 through the pressurizing electromagnetic valve 6 and the pressure reducing valve 4, and then the pressure is conveyed to the low-temperature bin 102 through the high-temperature bin 101, so that the low-temperature bin 102 is ensured to stabilize the pressure and the liquid level;
when the control system judges that working medium needs to be supplemented to the heat exchanger 3, the pressure relief electromagnetic valve 7 and the overflow valve 5 are opened to relieve pressure, and at the moment, the stored low-temperature working medium in the low-temperature bin 102 of the storage tank 1 is conveyed to the heat exchanger 3 through the check valve 11, so that the heat exchanger is changed from an under-pressure state to an accumulation state;
supplementary explanation 2
In this embodiment, the meaning of "the high temperature bin 101 and the low temperature bin 102 store the same cooling medium" is: because the same cooling working medium is adopted, the storage tank for storing the second working medium is not required to be additionally arranged, and only one storage tank for storing the same working medium is required, thereby being beneficial to light weight.
Further, the storage tank 1 adopts an aluminum alloy lining, and carbon fiber materials are wound outside the storage tank, so that high pressure resistance and light weight are ensured; the storage tank 1 is internally separated from the low-temperature working medium by a piston 103; the storage tank 1 comprises a double-layer shell 107, a piston 103, a movable connecting rod 105 and a brake pad 104, wherein triangular ridges with opposite directions are arranged on the inner surface of the storage tank 1 and the outer surface of the piston 103.
Supplementary explanation 3
In the prior art, two storage tanks are adopted to store two working mediums respectively, one storage tank is used in the embodiment, and in order to prevent the working mediums of the high-temperature bin from being mixed with the working mediums of the low-temperature bin, the piston 103 is ingeniously utilized to separate the working mediums of the high-temperature bin from the working mediums of the low-temperature bin, so that the two working mediums of the high-temperature bin and the low-temperature bin can be used as the high-temperature bin 101 and the low-temperature bin 102 at the same time by one storage tank;
further, the piston 103 divides the tank 1 into a high temperature chamber 101 and a low temperature chamber 102, and the constant pressure control system is configured to: when the pressure of the low-temperature bin is lower than the specified pressure 102, the pressurizing electromagnetic valve 6 is opened, and the cooling working medium is heated and expanded into the high-temperature bin 101 through the heat exchanger 3, so that the pressure of the high-temperature bin 101 and the pressure of the low-temperature bin 102 are balanced; when the working medium in the low-temperature bin 102 extrudes the piston 103, the piston 103 bulges to drive the connecting rod 105 to move, the linkage brake pad 104 forms extrusion force on the side surface of the piston 103, and the friction force is increased by matching with the triangular edges, so that the effect of preventing the piston from moving to the high-temperature bin is achieved.
Supplementary explanation 4
(1) The inner surface of the storage tank 1 and the outer surface of the piston 103 are provided with triangular ribs with opposite directions, and in the embodiment, the triangular ribs with opposite directions play roles in that: preventing the piston from moving in the reverse (upward) direction without affecting the forward movement of the piston. The purpose of preventing the reverse movement of the piston is to maintain the pressure of the low-temperature bin when the aircraft is reversely overloaded, because the piston generates reverse acting force under the inertia of the piston and the inertia of working medium of the low-temperature bin under the reverse overload condition, the reverse movement of the piston can cause the instant decompression of the low-temperature bin, which is not beneficial to maintaining the pressure stability of the low-temperature bin.
(2) The method for keeping the liquid level stable in this embodiment comprises the following steps: first, when the pressure of the low-temperature chamber 102 is reduced, that is, when a gap is formed between the liquid surface and the piston, the piston 103 is moved downward, so that the piston 103 is always attached to the low-temperature liquid surface, and the liquid surface is prevented from shaking up and down. And secondly, the liquid level is prevented from moving reversely by the triangular ribs, the movable connecting rods 105 and the brake pads 104 which are opposite in direction, and if the liquid level moves reversely, the gas and the liquid on the upper layer are mixed together, so that the cooling liquid discharged from the low-temperature bin 102 is mixed with the gas to influence the temperature reduction of the aircraft.
A method for stabilizing pressure and liquid level of an aerospace craft is shown in fig. 3a and 3b, and is characterized in that: the method comprises the following steps:
step one, when an aircraft takes off and enters an acceleration state, the heat exchanger 3 absorbs aerodynamic heat of the aircraft and transfers the aerodynamic heat to working media in the heat exchanger 3, so that the working media are in a high-temperature and high-pressure state; meanwhile, the storage tank 1 cools the aircraft, the pressure of the storage tank 1 is gradually reduced in the cooling process, and at the moment, the high-pressure gas of the heat exchanger 3 supplements the pressure to the storage tank 1, so that the pressure of the low-temperature bin 102 of the storage tank 1 is kept unchanged;
supplementary explanation 5
As shown in fig. 3b, in this embodiment, when the hypersonic aeroplane is launched, the initial state is checked: the pressure of the storage tank is 7.5 to 8MPa; the pressure of the heat exchanger is 7.5 to 8MPa, and the temperature is less than 50 ℃.
And step two, when the aircraft is overloaded and a reverse inertia force occurs, the reverse inertia force is prevented from extruding the piston 103 to move reversely, so that the pressure of the low-temperature bin 102 of the storage tank 1 is further ensured to be unchanged.
Further, the first step ensures that the pressure of the low-temperature chamber 102 of the storage tank 1 is unchanged, wherein the action process of the electromagnetic valve outside the storage tank 1 is as follows:
1) The cooling electromagnetic valve 12 of the storage tank is opened to provide cold energy for the aircraft, and at the moment, the low-temperature working medium of the low-temperature bin 102 of the storage tank enters a cooling system of the aircraft, and the pressure of the low-temperature bin 102 of the storage tank gradually drops;
2) The control system judges that the storage tank low-pressure sensor 8) is lower than the specified pressure, a pressure reducing electromagnetic valve 6 at the high-temperature end of the storage tank is opened, and a high-temperature high-pressure working medium in the heat exchanger 3 is supplemented into a high-temperature storage tank bin 101 through the pressure increasing electromagnetic valve 6 and the one-way pressure reducing valve 4 and then is transmitted to a low-temperature bin 102 through the high-temperature bin 101; when the pressure of the low-temperature bin 102 of the storage tank reaches the specified pressure, the pressurizing electromagnetic valve 6 at the high-temperature end of the storage tank is closed, and the pressurizing is stopped.
Supplementary explanation 6
As shown in fig. 3b, in this embodiment, there are 3 actions for the boost solenoid valve 6: the electromagnetic valve is opened, closed and has no action, and the specific conditions are as follows:
(1) the control system judges that the storage tank low pressure sensor 8 is lower than a specified pressure, the specified pressure is P < 7.5MPa, and the pressurizing electromagnetic valve 6 is opened when the P of the low pressure sensor 8 of the low temperature bin 102 is less than 7.5 MPa;
(2) the pressure of the low-temperature bin 102 of the storage tank reaches a specified pressure, and the specified pressure is P & gt8 MPa; when the pressure of the low-temperature bin 102 of the storage tank reaches P & gt 8MPa, the pressurizing electromagnetic valve 6 at the high-temperature end of the storage tank is closed, and pressurizing is stopped.
(3) When the pressure of the low pressure sensor 8 is 7.5MPa < P < 8MPa, no action is performed;
further, the pressure of the low-temperature bin 102 of the storage tank 1 is kept unchanged, wherein the piston 103 in the storage tank (1) acts as follows:
1) When pressurizing the low-temperature bin 102, the pressure of the high-temperature bin 101 is higher than that of the low-temperature bin 102;
the piston 103 is extruded towards the direction of the low-temperature bin 102 under the action of pressure difference; the outer surface of the piston 103 and the anti-skid saw teeth on the inner surface of the storage tank 1 rub in the forward direction, and the friction force is small at the moment;
2) The bottom of the piston protrudes to the side of the low-temperature bin 102 under the action of pressure difference, the chassis 106 moves to the side of the low-temperature bin 102 relative to the piston, and the brake pad 104 contracts under the linkage action of the connecting rod 105 and is in a loose state;
3) When the pressure difference is larger than the critical value, the piston moves to the side of the low-temperature bin 102; when the pressure difference is larger than a critical value, namely in a non-extrusion state, the pressure difference required by the minimum thrust of the piston to move towards the low-temperature bin is generated.
Further, the pre-tightening force of the piston 103 is adjusted in advance according to the magnitude of the overload force by the adjustable link mechanism 105.
Further, the specific process of the second step is as follows:
1) When the heat exchanger is under-pressure, namely the pressure of the high-pressure sensor 9 on the heat exchanger 3 is lower than the specified pressure, and the temperature sensor 10 is higher than the set temperature, the pressurizing electromagnetic valve 6 is closed to stop pressurizing;
supplementary explanation 7
As shown in fig. 3b, in the present embodiment, the heat exchanger 3 has 5 states in total, and each state is explained separately:
(1) the initial pressure of the heat exchanger 3 is 7.5MPa __ MPa, and the pressure in the range is insufficient for pressurizing the storage tank;
(2) when the pressure of the heat exchanger 3 rises and P is more than 8MPa and less than 20MPa, the condition of pressurizing the storage tank is met, and the storage tank can be pressurized;
(3) when the pressure P of the heat exchanger 3 is less than 8MPa, if the temperature sensor T of the heat exchanger is less than 50 ℃, the pressure is insufficient, but the temperature is not increased to be more than or equal to 50 ℃, so that the pressure relief valve 7 does not need to be opened;
(4) when the pressure P of the heat exchanger 3 is less than 8MPa, if the heat exchanger temperature sensor T is greater than 50 ℃, then 2 conditions for opening the pressure relief valve 7 are satisfied: the pressure is insufficient, the temperature T is more than or equal to 50 ℃, and the pressure relief valve 7 must be opened; the pressure shortage means shortage to pressurize the pressurizing solenoid valve 6.
(5) When the pressure P of the heat exchanger 3 is more than 20MPa, the continuous pressure capacity range of the heat exchanger 3 is exceeded, and at the moment, the pressure relief valve 7 must be opened even if the temperature is not more than 50 ℃;
summarizing: the relief valve 7 can be opened as long as one of two conditions is provided: or the pressure is too small but the temperature exceeds the limit temperature T by more than or equal to 50 ℃, or the pressure is too high P by more than 20MPa, but the temperature does not exceed the limit temperature.
2) Opening a pressure relief electromagnetic valve 7, performing injection cooling on the high Wen Duanbi surface through an overflow valve 5, and simultaneously enabling a low-temperature working medium to enter a heat exchanger to cool the heat exchanger; the high-temperature end wall surface is the end surface of the outlet of the overflow valve 5.
3) When the temperature of the temperature sensor 10 is lower than the predetermined temperature, the electromagnetic valve 7 is closed, and the heat exchanger 3 starts heat absorption and pressure accumulation.
Further, after the heat exchanger 3 finishes pressure accumulation, when the control system judges that the pressure of the low-temperature bin 102 of the storage tank 1 is reduced, the electromagnetic valve 6 is opened, high-temperature high pressure is supplemented to the high-temperature bin 101 of the storage tank, and the pressure of the low-temperature bin 102 of the storage tank is continuously increased through the high-temperature bin 101 of the storage tank, so that a pressure stabilizing cycle is formed.
Further, an electric heater is arranged in the heat exchanger 3, and when the pneumatic heat is low and the pressure of the storage tank is required to be supplemented, an onboard power supply is used for heat source compensation.
Example 1
The storage medium in the storage tank is exemplified by CO2, and in the storage tank in the low-temperature bin 102 in FIG. 2, the critical CO2 is 18 ℃ and 8MPa lower than Wen Ya. Initially, the critical CO2 was lower Wen Ya than 4MPa at 18 ℃ in heat exchanger 3 in fig. 1. The heat exchanger 3 is inlaid or stuck on the wall surface with high aerodynamic heat in the form of coil pipe which is stuck on the wall surface.
1. Stabilized liquid level in plane take-off accelerating state
When the aircraft takes off and accelerates, the electromagnetic valves 6 and 7 are closed, and under the action of pneumatic heating, the temperature of the critical CO2 (35 ℃) of which the temperature is lower than Wen Ya in the heat exchanger is raised by 18 ℃ and the expansion is carried out, and the pressure is raised by 5 times and is about 20 MPa. When the heat exchanger 3 is over-temperature and over-pressure (50 ℃ and 20 MPa), and the storage tank has no pressure supplementing requirement, the electromagnetic valve 7 is opened to release pressure, so that the high-temperature pneumatic wall surface jet cooling is realized.
1) The working process of the electromagnetic valve in the pressurizing process is as follows: after the aircraft takes off, the storage tank (1) cools the aircraft, the storage tank enters a working state, at the moment, the electromagnetic valve 12 is opened, the low Wen Ya critical CO2 enters a cooling system, and the pressure of the storage tank gradually drops. When the control system judges that the storage tank low-pressure sensor 8) is lower than 7.5MPa, the pressurizing electromagnetic valve 6 is opened, supercritical CO2 (> 35 ℃) in the heat exchanger 3 is supplemented into the storage tank high-temperature bin 101 through the one-way overflow valve 4 (back pressure 8 MPa), then the pressure is transmitted to the storage tank low-temperature bin 102 through the storage tank high-temperature bin 101, and when the pressure of the storage tank low-temperature bin 102 reaches 8MPa, the electromagnetic valve 6 is closed, and the pressurizing is stopped.
2) The working process of the piston in the pressurizing process is as follows: when the heat exchanger 3 pressurizes the high temperature bin 101 of the storage tank, the pressure of the high temperature bin 101 is higher than that of the low temperature bin 102, the piston 103 is extruded towards the low temperature bin 102 under the action of pressure difference, the outer surface of the piston 103 and the anti-slip saw teeth on the inner surface of the storage tank 1 rub in the forward direction, as shown in a local enlarged mode A of fig. 2, and the friction force is small at the moment. Meanwhile, the bottom of the piston protrudes to the side of the low-temperature bin 102 under the action of pressure difference, the chassis 106 moves to the side of the low-temperature bin 102 relative to the piston, and the brake pad 104 contracts under the linkage action of the connecting rod 105 and is in a loose state. When the pressure difference is greater than the critical value of 0.3MPa, the piston moves to the side of the low-temperature chamber 102.
2. Pressure and liquid level stabilization in the presence of reverse inertial forces in an overload state of an aircraft
When in overload, liquid in the low-temperature bin 102 presses the piston 103, the middle of the piston 103 bulges to enable the brake pad 104 to press the inner wall surface of the piston, meanwhile, the outer surface of the piston and anti-skid saw teeth on the inner surface of the storage tank are reversely rubbed, the friction force is increased, the purpose of preventing the piston from reversely moving is achieved, meanwhile, the possibility of inclination of the piston is reduced to a certain extent, and the overload pressure stabilizing effect is achieved.
The pretightening force can be adjusted in advance according to the magnitude of the overload force by the adjustable link mechanism 105.
When the heat exchanger 3 is under-pressure, namely when the pressure of the high-pressure sensor 9 on the heat exchanger 3 is lower than 8MPa, and when the temperature sensor 10 is higher than 50 ℃, the electromagnetic valve 6 is closed to stop pressurizing, the electromagnetic valve 7 is opened, the air is diffused through the overflow valve 5 (the back pressure is 6.5MPa, in a subcritical state), the diffused air is used for jetting and cooling the high-temperature pneumatic wall surface, the heat exchanger is cooled, and when the temperature is lower than 30 ℃, the electromagnetic valve 7 is closed, and the heat exchanger 3 starts to absorb heat and store pressure. The CO2 pressure increases from a subcritical temperature of 30 ℃ to a supercritical temperature of 35 ℃ at supercritical pressure by a factor of about 3. Namely the pressure accumulating capacity of the heat exchanger is about 20 MPa.
After the heat exchanger finishes pressure accumulation, the pressurizing electromagnetic valve 6 is opened, supercritical CO2 is supplemented to the high-temperature bin 101 of the storage tank 1, and the pressure of the storage tank is continuously increased to form a pressure stabilizing cycle.
And (3) heat source compensation: the heat exchanger 3 is internally provided with a heater, and when the pneumatic heat is low and the pressure of the storage tank is required to be supplemented, an onboard power supply is used for heat source compensation.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (9)
1. A pressure and fluid level stabilizing device for an aerospace vehicle, comprising: the storage box (1) is arranged on the aircraft and used for cooling electronic equipment and high-temperature wall surfaces on the aircraft, and a high-temperature bin (101) and a low-temperature bin (102) are arranged in the storage box (1); the high-temperature bin (101) and the low-temperature bin (102) store the same cooling working medium, and the periphery of the storage tank (1) is sequentially provided with: a storage tank low-pressure sensor (8), a check valve (11), a heat exchanger (3), a pressure relief electromagnetic valve (7), a pressure boosting electromagnetic valve (6) and a pressure reducing valve (4); one side of the heat exchanger (3) close to the low temperature end of the storage tank is connected with a check valve (11), and one side close to the high temperature end of the storage tank is connected with a pressure relief electromagnetic valve (7); the other end of the heat exchanger (3) is connected with a heat exchanger high pressure sensor (9) and a heat exchanger temperature sensor (10); the other end of the pressure relief electromagnetic valve (7) is connected with an overflow valve (5) matched with the pressure relief electromagnetic valve; the working medium of the high-temperature bin (101) is in a high-temperature and high-pressure state, and the cooling working medium of the low-temperature bin (102) is in a low-temperature and low-pressure state;
the method is characterized in that:
the heat exchanger (3) heats the cooling working medium in a low-temperature low-pressure state to a high-temperature high-pressure state by absorbing the aerodynamic heat of the aircraft:
when the control system judges that the pressure of the low-temperature bin (102) is reduced and needs to be boosted, the boosting electromagnetic valve (6) is opened, high-pressure gas in the heat exchanger (3) is conveyed to the high-temperature bin (101) of the storage box (1) through the boosting electromagnetic valve (6) and the pressure reducing valve (4), and then the pressure is transmitted to the low-temperature bin (102) through the high-temperature bin (101), so that the pressure and liquid level of the low-temperature bin (102) are ensured;
when the control system judges that working medium is required to be supplemented to the heat exchanger (3), the pressure relief electromagnetic valve (7) and the overflow valve (5) are opened to relieve pressure, and at the moment, the stored low-temperature working medium in the low-temperature bin (102) of the storage tank (1) is conveyed to the heat exchanger (3) through the check valve (11) so that the heat exchanger is changed from an under-pressure state to an accumulation state;
the storage tank (1) adopts an aluminum alloy lining, and carbon fiber materials are wound outside the storage tank, so that high pressure resistance and light weight are ensured; the storage tank (1) is internally provided with a piston (103) for separating a stored high-temperature working medium from a low-temperature working medium; the storage tank (1) comprises a double-layer shell (107), a piston (103), an adjustable connecting rod mechanism (105) and a brake pad (104), and triangular edges with opposite directions are arranged on the inner surface of the storage tank (1) and the outer surface of the piston (103).
2. The space vehicle pressure and liquid level stabilizing device according to claim 1, wherein: the piston (103) divides the storage tank (1) into a high temperature bin (101) and a low temperature bin (102), and the constant pressure control system is arranged as follows: when the pressure of the low-temperature bin is lower than the specified pressure, the pressurizing electromagnetic valve (6) is opened, and the cooling working medium is heated and expanded into the high-temperature bin (101) through the heat exchanger (3), so that the pressure of the high-temperature bin (101) and the pressure of the low-temperature bin are balanced; when the working medium of the low-temperature bin (102) extrudes the piston (103), the piston (103) bulges to drive the adjustable connecting rod mechanism (105) to move, the linkage brake pad (104) forms extrusion force on the side surface of the piston (103), and the friction force is increased by matching with the triangular edges, so that the piston is prevented from moving to the high-temperature bin.
3. An aerospace vehicle voltage and liquid level stabilizing method based on the aerospace vehicle voltage and liquid level stabilizing device according to any one of claims 1-2, which is characterized in that: the method comprises the following steps:
step one, when an aircraft takes off and enters an acceleration state, a heat exchanger (3) absorbs aerodynamic heat of the aircraft and transfers the aerodynamic heat to working media in the heat exchanger (3) so that the working media are in a high-temperature and high-pressure state; meanwhile, the storage tank (1) cools the aircraft, the pressure of the storage tank (1) is gradually reduced in the cooling process, and at the moment, the high-pressure gas of the heat exchanger (3) supplements the pressure to the storage tank (1) to ensure that the pressure of a low-temperature bin (102) of the storage tank (1) is unchanged;
and step two, when the aircraft is overloaded and a reverse inertia force occurs, the reverse inertia force is prevented from extruding the piston (103) to move reversely, so that the pressure of the low-temperature bin (102) of the storage tank (1) is further ensured to be unchanged.
4. A method of stabilizing a pressure and a liquid level of an aerospace vehicle according to claim 3, wherein: the first step ensures that the pressure of the low-temperature bin (102) of the storage tank (1) is unchanged, wherein the action process of the electromagnetic valve outside the storage tank (1) is as follows:
1) A cooling electromagnetic valve (12) of the storage tank is opened to provide cold energy for the aircraft, and at the moment, the low-temperature working medium of the low-temperature bin (102) of the storage tank enters a cooling system of the aircraft, and the pressure of the low-temperature bin (102) of the storage tank gradually drops;
2) When the control system judges that the low-pressure sensor (8) of the storage tank is lower than the specified pressure, a pressurizing electromagnetic valve (6) at the high-temperature end of the storage tank is opened, high-temperature and high-pressure working medium in the heat exchanger (3) is supplemented into a high-temperature bin (101) of the storage tank through the pressurizing electromagnetic valve (6) and a one-way pressure reducing valve (4), and then the pressure is transmitted to a low-temperature bin (102) through the high-temperature bin (101); when the pressure of the low-temperature bin (102) of the storage tank reaches the specified pressure, the pressurizing electromagnetic valve (6) at the high-temperature end of the storage tank is closed, and the pressurizing is stopped.
5. A method of stabilizing a pressure and a liquid level of an aerospace vehicle according to claim 3, wherein: the first step ensures that the pressure of the low-temperature bin (102) of the storage tank (1) is unchanged, wherein the action process of the piston (103) in the storage tank (1) is as follows:
1) When the low-temperature bin (102) is pressurized, the pressure of the high-temperature bin (101) is higher than that of the low-temperature bin (102);
the piston (103) is extruded towards the direction of the low-temperature bin (102) under the action of pressure difference; the outer surface of the piston (103) and the anti-skid saw tooth on the inner surface of the storage box (1) rub in the forward direction, and the friction force is small at the moment;
2) The bottom of the piston protrudes to the side of the low-temperature bin (102) under the action of pressure difference, the chassis (106) moves to the side of the low-temperature bin (102) relative to the piston, and the brake pad (104) contracts under the linkage action of the adjustable connecting rod mechanism (105) and is in a loose state;
3) When the pressure difference is larger than a critical value, the piston moves to the side of the low-temperature bin (102); when the pressure difference is larger than a critical value, namely in a non-extrusion state, the pressure difference required by the minimum thrust of the piston to move towards the low-temperature bin is generated.
6. The method for stabilizing the pressure and the liquid level of the aerospace vehicle according to claim 5, wherein the method comprises the following steps of:
the pretightening force of the piston (103) is adjusted in advance according to the magnitude of the overload force through the adjustable connecting rod mechanism (105).
7. A method of stabilizing a pressure and a liquid level of an aerospace vehicle according to claim 3, wherein: the specific process of the second step is as follows:
1) When the heat exchanger is under-pressure, namely when the pressure of a high-pressure sensor (9) on the heat exchanger (3) is lower than a specified pressure and when a temperature sensor (10) is higher than a set temperature, the pressurizing electromagnetic valve (6) is closed to stop pressurizing;
2) Opening a pressure relief electromagnetic valve (7), performing injection cooling on the high Wen Duanbi surface through an overflow valve (5), and simultaneously enabling a low-temperature working medium to enter a heat exchanger to cool the heat exchanger; the high-temperature end wall surface is the end surface of an outlet of the overflow valve (5);
3) When the temperature of the temperature sensor (10) is lower than a preset temperature, the pressure relief electromagnetic valve (7) is closed, and the heat exchanger (3) starts heat absorption and pressure accumulation.
8. The method for stabilizing the pressure and the liquid level of the aerospace vehicle according to claim 7, wherein the method comprises the following steps of:
after the heat exchanger (3) stores pressure, when the control system judges that the pressure of the low-temperature bin (102) of the storage tank (1) is reduced, the pressurizing electromagnetic valve (6) is opened, high-temperature and high-pressure is supplemented to the high-temperature bin (101) of the storage tank, and the pressure of the low-temperature bin (102) of the storage tank is continuously increased through the high-temperature bin (101) of the storage tank, so that a pressure stabilizing cycle is formed.
9. The method for stabilizing the pressure and the liquid level of the aerospace vehicle according to claim 8, wherein the method comprises the following steps of: an electric heater is arranged in the heat exchanger (3), and when the pneumatic heat is low and the pressure of the storage tank is required to be supplemented, an onboard power supply is used for heat source compensation.
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| RU2177070C2 (en) * | 2000-02-03 | 2001-12-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Spacecraft engine unit propellant tank pressurization system |
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| FR3042821B1 (en) * | 2015-10-26 | 2017-12-01 | Snecma | METHOD OF CONTROLLING PRESSURE WITHIN A FIRST ERGOL TANK OF FIRED ENGINE |
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|---|---|---|---|---|
| FR2063672A5 (en) * | 1969-10-27 | 1971-07-09 | Europ Propulsion | |
| JPH11173214A (en) * | 1997-12-11 | 1999-06-29 | Mitsubishi Heavy Ind Ltd | Burning type thrust generating device |
| RU2177070C2 (en) * | 2000-02-03 | 2001-12-20 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" им. С.П. Королева" | Spacecraft engine unit propellant tank pressurization system |
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