CN102417040B - Novel super-light and highly effective space particle radiator system - Google Patents

Abstract

An ultra-light and high-efficiency space particle radiator method based on solid-liquid two-phase flow mixing and heat exchange separation, including: mixing and heat exchange of solid particles and liquid fluid; separation of solid-liquid two-phase mixed flow and drying of solid particles; Jetting of solid particles; radiation heat dissipation of solid particles in outer space; collection of solid particles. The invention utilizes hybrid heat exchange to enhance the heat exchange in the middle, and uses solid particles to radiate heat dissipation, thus overcoming the inability of existing space radiators to meet the heat dissipation requirements when they are applied to large-structure spacecraft and strong-power space energy systems. On the basis of this, it effectively reduces the problem of the quality of the space radiator, and at the same time eliminates the damage and pollution of the surrounding space environment during radiation heat dissipation, as well as the working time problem caused by evaporation loss, and improves the predictability and stability of control. , expanding the scope of application.

Description

A new ultra-light and high-efficiency space particle radiator system

technical field

The invention relates to an ultra-light and high-efficiency space particle radiator system based on solid-liquid two-phase flow mixing and heat exchange separation applied to a space thermal control system, which is used to integrate a large amount of waste heat generated by a large-structure spacecraft and a space energy power system On the basis of effectively reducing the mass of the radiator, it can be efficiently discharged into space.

Background technique

The thermal control technology of the spacecraft is mainly to control the heat exchange process inside the spacecraft and between the interior and the external space environment, so that the thermal state (temperature, humidity, etc.) inside the spacecraft is within the required range, ensuring that the astronauts and equipment can work normally Work. In the microgravity environment of space, the heat generated by the instruments and equipment inside the spacecraft and the astronauts is transferred to the space radiator through the thermal control loop, and finally radiated into space by radiation. As the main device for heat exchange between the spacecraft and the space environment, the space radiator usually accounts for about 50% to 60% of the mass of the entire thermal control system.

In recent years, with the rapid development of large spacecraft and space stations, their power consumption will increase, which will inevitably lead to an increase in their thermal power consumption, making traditional thermal control technologies face new challenges and difficult to adapt to new development of. According to literature records, the existing space development plan chooses to use large-scale power supply systems such as isotope power (its power supply is above 10kw), solar power (its power supply is above 100kw) and nuclear thermal power (its power supply is above 100kw) , to provide energy for large spacecraft, they are mainly intended to be used in IR monitoring spacecraft, space radar stations, space chemical laser platforms and space weapon platforms, and their power consumption is mostly in the range of 10kw to 100kw. The Liberty space station consumes more power. The power consumption of the proposed first phase of the project is 100kw, and the power consumption of the second phase of the project is 300kw. However, the energy conversion efficiency of these space platforms or space stations is extremely low, usually less than 10%, and a large amount of energy must be converted into heat dissipation, which must be discharged into space. If the existing space radiator technology is simply used, it will inevitably lead to a very large space radiator. In addition, the power to drive the flow of the heat carrier in the thermal control loop is also limited. Therefore, under the condition of satisfying the thermal control capability and strength, it is very important to design an efficient space radiator for the lightweight design of the spacecraft thermal control system.

As far as the design technology currently applied to space heat radiators is concerned, it mainly includes passive structural radiators that directly use the surface of the spacecraft structure itself; heat pipe radiators that utilize the high thermal conductivity of heat pipes; body-mounted radiators; expandable radiators and some new radiator types. In the design of existing space heat radiators, the most used ones are composed of a series of heat pipes and pipe warp structures, and the refrigerant flows in the pipe warp structures. The requirement for these tubes is that they be strong enough to minimize the penetration of microfluidics; in addition, the transmission of fluids over long distances is also a must. And if the design technology of this relatively heavy heat pipe circulating flow radiator is applied to future large-structure space spacecraft and space energy power systems, the launch quality and occupied space will be greatly increased, and the cost required The cost is also very large. Although the droplet radiator and the liquid film radiator, which are currently in the experimental stage, have great advantages in quality, they are inferior in terms of working time, pollution to the surrounding space environment, and evaporation loss of the work flow. There are certain problems. Therefore, it is necessary to research and develop new space radiators with lighter weight, smaller footprint, higher efficiency, lower cost, stronger anti-interference and no pollution to the surrounding space environment.

For all space systems, heat dissipation in space is a key problem. From space vehicles, geostationary satellites, space stations to moon or planetary bases, etc., their heat dissipation problems will directly affect the safety of these system equipment. , high efficiency and reliability. For these devices, if there is no suitable working temperature, that is, a comfortable working environment, the working efficiency of these devices in space will be reduced or even completely scrapped, becoming cosmic garbage. Therefore, the research and development of advanced space heat radiators is an effective means for various systems in space to work better.

In view of the importance and necessity of thermal control systems for space vehicles, satellites, space stations and other space equipment, in order to effectively improve heat exchange efficiency and reduce manufacturing costs on the basis of reducing the quality of the overall space thermal control system, and to develop large structures for the future To make necessary technical reserves for space equipment and deep space exploration equipment, it is urgent to conduct detailed and in-depth research on ultra-light and high-efficiency space heat radiators, and develop advanced thermal control technologies for space system equipment.

Contents of the invention

According to one aspect of the present invention, there is provided a heat radiation device, which is characterized in that it comprises: a particle injector for launching particles into space; a particle collector for collecting the particles emitted by the particle injector; an exchanger for exchanging heat with the particles.

According to another aspect of the present invention, there is provided a heat radiation method, which is characterized in that it comprises: using a particle injector to launch particles into space; using a particle collector to collect the particles emitted by the particle injector; using a heat exchanger A heat exchange of the particles is performed.

Description of drawings

FIG. 1 is a schematic diagram of a space particle radiator according to an embodiment of the present invention.

Fig. 2 is a working flow chart of the space particle radiator according to one embodiment of the present invention.

Fig. 3 is a schematic structural diagram of a space particle radiator according to an embodiment of the present invention.

Figure number:

101 Particle collector 102 Solid-liquid two-phase mixed heat exchanger

103 Solid-liquid two-phase fluid pump 104 Solid-liquid two-phase cyclone separator

105 particle injector 106 spacecraft space system

201 Particle collection 202 Intermediate mixing heat transfer

203 Solid-liquid fluid transmission 204 Solid-liquid cyclone separation

205 Particle Jetting 206 Workflow Absorbs Waste Heat

301 Radiator System Hybrid

302 Radiator mixed heat exchange 303 Separation

304 Absorption of waste heat 305 Radiator system hybrid

306 Radiator mixed heat exchange 307 Separation and drying

308 Particle Collection 309 Radiation Heat Dissipation

310 Jet of Particles

Detailed ways:

An object of the present invention is to overcome the deficiencies in the existing space radiator structure design technology in terms of heat dissipation rate in large-structure spacecraft and space energy power systems, occupying space volume, cost and environmental pollution to the surrounding space. A new set of ultra-light and high-efficiency space particle radiator system based on solid-liquid two-phase flow mixing and heat exchange separation in space environment. The system can effectively reduce the quality of the radiator system and reduce the pollution to the surrounding environment while efficiently radiating waste heat, and expands its application range, which is simple and easy to implement.

According to one aspect of the present invention, an ultra-light and high-efficiency space particle radiator system based on solid-liquid two-phase flow mixing and heat exchange separation is provided, wherein:

The space particle radiator system includes a solid-liquid two-phase mixed heat exchanger, a solid-liquid two-phase cyclone separator, a particle injector, a particle collector, a solid-liquid two-phase fluid pump and pipelines.

First, as shown in Figure 1, in the entire space system including the space particle radiator system according to an embodiment of the present invention, the hot side work flow will take away the waste heat generated by the space system, and at the exit of the particle collector (101) The solid particles enter the solid-liquid two-phase hybrid heat exchanger (102) under the driving action of the working flow, and conduct heat conduction and convection heat transfer under the action of the hybrid heat exchanger (102). Function, so that the temperature of the particles and the temperature of the working flow FC50 (fluorocarbon polymer) increase and decrease accordingly. After that, the solid-liquid two-phase flow that has undergone mixed heat exchange treatment is sent to the solid-liquid two-phase fluid pump (103), so that the solid-liquid two-phase flow reaches a certain pressure value, and enters the solid-liquid two-phase cyclone separator (104). , through a series of conversion and separation operations and drying operations in the solid-liquid two-phase cyclone separator (104), the corresponding particles and fluids are finally separated. Finally, send the separated working fluid FC50 (fluorocarbon polymer) back to the space system (106), absorb the waste heat generated by the space system during work, and continue to circulate; send the separated particles directly into the particle In the injector (105), the particles are ejected into the space according to the pre-designed trajectory by combining the kinetic energy of the particle itself and the effect of the particle injector (105). The carried heat is dissipated. After the particles fly a certain distance in the outer space according to the predetermined flight trajectory, they will be collected by the particle collector (101) with rotating centrifugal force, and the collected particles will be mixed with the circulating workflow to continue the previous working steps. As shown in Figure 1.

According to the above-mentioned novel space particle radiator system of the present invention, compared with traditional heat pipe type space radiators, etc., it can meet more practical application requirements, including:

- It is capable of dissipating a large amount of waste heat in space with a small radiator mass;

- It can be easily transported, installed and retracted in a limited space;

-It can work effectively, stably and continuously for a long time under the condition of using very little power. All these essential characteristics will be represented by 5 parameters, which are: the radiation heat dissipation per unit mass of the radiator, the radiation heat dissipation area per unit mass of the radiator, the radiation heat dissipation per unit area of the radiator, and the radiation heat dissipation per unit radiation heat dissipation. Radiation heat dissipation per unit mass of radiator under power consumption and unit temperature difference;

- The space occupied by this new type of space particle radiator will be very small when the spacecraft is launched and unfolded in outer space, which can reduce the risk factor of being collided by micrometeoroids.

The requirements for the solid particles in the above-mentioned new space particle radiator system are essentially different from those of the droplet radiators that are in the experimental stage, and can effectively overcome the problems caused by the droplets in practical applications. A lot of inconveniences.

The material of the solid particle is carbon fiber compound material, which ensures the light weight and non-sticky property of the solid particle; at the same time, because the existing industrial manufacturing technology has met the technical requirements in the manufacture of small particle size particles, it can meet the Manufacture solid particles with a particle size of 100 μm to 300 μm, so that the solid particles have uniformity and consistency. In this way, the trajectory of the solid particles injected into the space by the injection device can be well predicted, so that the operation is simplified and the radiation heat dissipation is maximized. Moreover, when solid particles fly in space for radiation and heat dissipation, they are not volatile, so they will not cause pollution to the surrounding space environment and spacecraft.

The intermediate heat exchanger components in the above-mentioned new space particle radiator system can adopt a hybrid heat exchanger design, thereby improving the heat exchange efficiency of the intermediate cold and hot fluids, and can effectively reduce the quality of the intermediate heat exchanger. It is the design based on this basic structure that ensures that the mass of the entire space radiator system can be greatly reduced, while still maintaining the reliability and stability of large radiation heat dissipation and heat exchange.

The connection mode between the particle ejector and the solid-liquid cyclone separator in the above-mentioned new space particle radiator system is different from the droplet space radiator, but adopts a direct connection method to make it a whole, which is convenient for particle Pass and squirt.

The specific operations in the ultra-light and high-efficiency space particle radiator system according to the present invention which have these characteristics and are based on the mixing and heat exchange separation of solid-liquid two-phase flow include:

-Mixing and heat exchange of solid particles and working fluid

After the solid particles of the present invention are collected by the particle collector, they are directly merged with the working fluid (301) (305), and under the action of the working fluid, the solid particles are driven to flow in the pipeline to form a flow of solid-liquid mixture.

The intermediate heat exchange equipment of the present invention adopts a direct contact heat exchanger—a hybrid heat exchanger. This is a device in which hot and cold fluids are in direct contact for heat exchange. The cold fluid here is a solid particle fluid, and the hot fluid is FC50 (fluorocarbon polymer), and they exchange heat through this hybrid heat exchanger (302) (306). Due to the uniformity and consistency of the solid particles in particle size, quality, etc., and due to the restrictions on the material used to make the particles, when the solid particles flow in the liquid, they will not form a film on the surface of the particles to affect the heat transfer effect, and because The non-viscosity of the particle material makes the heat transfer of solid particles in the hybrid heat exchanger stable and uniform.

-Separation of solid-liquid two-phase mixed flow and drying of solid particles

On the basis of the solid-liquid two-phase flow mixed fluid obtained in the mixing of the solid particles and the working fluid and the heat exchange step, the solid-liquid separation is carried out by using the multi-stage cyclone separation technology, and the solid particles are dried after the separation treatment (307), the liquid carried on the surface of the solid particle is omitted, so that there will be no pollution of the space environment and corrosion of the spacecraft due to the evaporation loss of the liquid after the solid particle enters the space. The separated working fluid (303) is directly sent back to the spacecraft system, and continues to circulate to absorb waste heat generated by the spacecraft system (304).

- solid particle jetting

Since the solid particles directly enter the particle spraying equipment after being separated, and the solid particles have a certain momentum, the solid particles obtained in the separation of the solid-liquid two-phase mixed flow and the drying steps of the solid particles enter the spraying equipment. Afterwards, the device can meet the ejection requirements of the particles in terms of speed, pressure, etc., and eject them into space through the particle ejector (308). At the same time, due to the consistency of the particle size and the uniformity of the material, it is possible to accurately predict the flight trajectory of the particles in space, thereby ensuring the effective recovery of solid particles. And the radiative heat dissipation of solid particles during spaceflight is maximized.

- Radiation heat dissipation of solid particles in outer space

Since the solid particles in this new type of space particle radiator fly in the entire outer space, the solid particles do not exist alone, but a particle system composed of multiple particles, so there are also interactions between the particles caused by mutual radiation. Mutual absorption, scattering; and mutual interference of particle radiation fields. Therefore, after the solid particles obtained in the solid particle spraying step are sprayed into the outer space from the spraying device, radiation heat is dissipated (309). Moreover, according to the exit velocity, force and particle injection direction, the solid particles are injected into a local sparse particle system, so that each particle is not affected by adjacent particles.

Solid particles fly in outer space according to the predetermined flight trajectory, and radiate heat during the flight. According to an embodiment of the present invention, the solid particles are hollow spherical, with a particle size ranging from 100 μm to 300 μm, and the material is selected from carbon fiber compound materials. Because the radiation heat dissipation capacity of solid particles has a great relationship with the shape, particle size, surface area, absorptivity of surface materials, emissivity, spectral wavelength and other attribute parameters of solid particles, so through the determination of the particle size and material of the above solid particles, It also determines the radiation cooling capacity of solid particles. And the solid particle system is locally sparse, which maximizes the radiation heat dissipation of a single particle, which means the maximum radiation heat dissipation of the overall particle system.

- Collection of solid particles

In the step of radiating heat dissipation of the solid particles in the outer space, the solid particles perform radiation heat dissipation in the outer space (309), and after flying for a certain distance according to a predetermined trajectory, the solid particles are recovered by the particle collector (310). Since the particles still have a certain speed during the flight, but the speed is relatively small, such as 10-50m/s, so in order to prevent the particle splash loss caused by the solid particles when they encounter the collector, the particle collector passes through the collector. The centrifugal force generated by the rotation of the surface makes the particles be affected by the centrifugal force when they contact the wall of the collector, and flow inward along the wall with a certain speed, which can effectively mix the solid particles and the liquid fluid.

According to one aspect of the present invention, an ultra-light and high-efficiency space particle radiator system based on the mixing and heat exchange separation of solid-liquid two-phase flow in a space environment is proposed. A hybrid heat exchanger is a device in which hot and cold fluids are in direct contact with each other for heat exchange. The mixed fluid usually used is a mixed fluid of gas and liquid with low vaporization pressure, which is easy to separate after heat exchange. This kind of heat exchanger has the advantages of simple design, easy realization, and high heat transfer efficiency, and has been widely used in In the heat conduction cooling of chemical industry, metallurgy and other industries, especially in the application of water cooling tower. However, in the actual space radiator system, most of the heat exchangers or intermediate heat exchangers used are partition wall heat exchangers. , there are many problems in heat transfer efficiency. Based on the recognition that the solid particle flow has the characteristics of light weight, non-volatility and uniformity, in one embodiment of the present invention, the solid particle and the space radiator are combined to achieve outstanding technical effect; but on the other hand, this combination is not a simple combination of traditional structures, but is based on the reconstruction of the entire space radiator, using solid particles as the refrigerant in the entire radiator system—the source of radiation heat dissipation, thereby It realizes the effect of light weight and no pollution to the space environment, and utilizes the high efficiency and stability of the hybrid heat exchanger, and sets it as the intermediate heat exchanger of the entire space radiator system. The fluids are solid particles and the liquid that absorbs waste heat respectively, where direct contact heat conduction and convective heat exchange (202) are performed, so that in this heat transfer process, the surface temperature of the solid particles has uniformity, consistency and stability . Furthermore, the pressure of the solid-liquid mixed fluid is adjusted (203) through the solid-liquid two-phase fluid pump, so that the solid-liquid mixed flow meets the system performance index requirements. Send the solid-liquid mixed flow that reaches the pressure index value into the solid-liquid two-phase cyclone separator, and perform the corresponding solid-liquid separation operation (204). After the solid-liquid two-phase cyclone separator completes the solid-liquid separation, the solid-liquid Particles also need to be dried to a certain extent to ensure that the surface of the solid particles does not stick to the workflow. The separated work flow is returned to the spacecraft structure to continue absorbing waste heat cycle work (206). Afterwards, since the separator and the particle injector are directly connected, the solid particles will directly enter the particle injector under certain momentum and pressure conditions, and be sprayed into the outer space for radiation heat dissipation (205). Because the particles have good consistency and uniformity in particle size and shape, the trajectory of the particles in the outer space is easy to calculate and predict, and it is accurate, so that the particles are stable and reliable in the process of collection (201), reducing losses due to particle splashing during collection.

It should be noted that the solid particle material of the ultra-light and efficient space particle radiator system based on solid-liquid two-phase flow mixing and heat exchange separation is made of light-weight carbon fiber composite material, and the particle size is required to be small, about 100 μm to 300 μm. It guarantees a certain absorption rate, emissivity and good non-mucus property. Such solid particles can achieve the characteristics of accelerated radiation heat dissipation and minimize the problem of cyclic workflow being carried away.

The advantages of the present invention compared with the prior art include:

1. The present invention adopts the working mode of solid-liquid two-phase mixed heat transfer, solid-liquid two-phase swirl separation and particle space radiation heat dissipation, and utilizes the high efficiency of solid-liquid two-phase mixed convective heat transfer and space particle radiation heat dissipation and the particle Lightweight, to meet the requirements of future large-structure space spacecraft and space energy power systems, on the basis of ensuring that they have a large heat removal capacity, the mass of the space radiator can be greatly and effectively reduced.

2. The present invention is easy to realize the transportation in a narrow space, has good installation and shrinkability in the space, and the system has strong anti-interference ability to the external environment, stable and reliable operation, and can be used in the case of using little electric energy. Under, long-term continuous work.

3. The intermediate heat exchange method of the present invention is mixed heat exchange of solid-liquid two-phase flow. Since this heat exchange method is direct contact between two media, it has good thermal conductivity and convective heat transfer, and has good heat transfer performance. heat effect. And it is easy to realize and simple to operate.

4. The radiation heat dissipation medium of the present invention is a solid particle. Because it is through the radiation heat dissipation of the particles, there is no loss of liquid evaporation, and the pollution or corrosion of the surrounding space environment and spacecraft structure due to liquid evaporation.

5. The radiation medium used in the present invention-solid particles have consistency and uniformity in particle size, so they have good predictability and accuracy on the running track, and can maximize the radiation heat dissipation rate of particles in outer space .

6. The solid-liquid separator and particle injector used in the present invention are directly socketed together, which ensures the consistency of particle force and velocity.

An important aspect of the present invention is to use solid particles as the radiation medium for radiation heat dissipation, use carbon compound materials to manufacture solid particles, and effectively combine the light-weight solid particles with solid-liquid mixing heat exchange, through efficient solid-liquid Mix heat exchange, so that solid particles will take away more waste heat. The solid-liquid mixture is effectively separated by solid-liquid two-phase cyclone separation, directly enters the particle injector, and is ejected by the particle injector into the outer space for efficient radiation heat dissipation. It is precisely because of the high efficiency of solid-liquid mixed heat exchange, the uniformity and consistency of solid particles and the high emissivity of materials that ensure that while reducing the overall radiator quality, it can dissipate more waste heat and reduce the collection time. In the case of solid particles, the loss caused by the inability to accurately judge the trajectory of the solid particles. At the same time, since the solid particles do not have evaporative properties, the surrounding space environment and spacecraft are avoided from being polluted and corroded. The working steps according to an embodiment of the present invention include:

(1) Mixing and heat exchange of solid particles and liquid fluid

In this embodiment, the material of the solid particles is carbon compound, and the liquid fluid is FC50 (fluorocarbon polymer). By utilizing the high efficiency of the mixed heat exchange of the solid-liquid completely uniform contact type, before spraying the solid particles into the outer space, Make as much heat exchange as possible between solid particles and liquid fluid.

(2) Separation of solid-liquid two-phase mixed flow and drying of solid particles

After the solid particles and the liquid fluid are mixed and exchanged for heat, the solid particles need to be separated from the solid and liquid before they can be used. The present invention utilizes the combined mode of cyclone separation and filtration to effectively separate the solid-liquid mixture, and then carry out corresponding treatment on the solid particles so that the surface of the solid particles does not carry liquid. At the same time, the particles will have a certain kinetic energy.

(3) Jetting of solid particles

The solid particles obtained in steps (1) and (2) are directly fed into the particle injector, and the particles are injected into the outer space according to the predetermined speed and method in combination with the principle of the injector.

(4) Radiation heat dissipation of solid particles in outer space

Obtained from step (3), after the solid particles are sprayed into the outer space through the injector, they fly according to the predetermined flight trajectory, and the heat carried by the particles is discharged to the outer space by applying the principle of radiation heat dissipation.

(5) Collection of solid particles

After the solid particles fly a certain distance in the outer space according to the predetermined trajectory, the particle collector is used to collect and process them. The use of rotating centrifugal force effectively prevents the loss of particle splashing.

Claims (10)

1. Thermal radiation equipment, characterized in that it comprises: A particle injector (105) for emitting particles into space; a particle collector (101) for collecting particles emitted by the particle injector (105); A solid-liquid two-phase mixed heat exchanger (102), used for heat exchange between the working flow and the particles; The solid-liquid two-phase separator (104), which is directly connected with the particle injector to form a whole, is used to separate the working flow and the particles. 2. The heat radiation device according to claim 1, characterized in that: The solid-liquid two-phase mixed heat exchanger (102) makes the particles collected by the particle collector (101) and the working fluid from the working system (106) merge at the outlet of the particle collector (101), and the particles Driven by the working fluid, it flows into the hybrid heat exchanger, so that the particles and the working fluid can exchange heat. 3. The heat radiation device according to claim 2, characterized in that: The solid-liquid two-phase separator (104) is also used for drying the particles. 4. The heat radiation device according to claim 3, further comprising: The solid-liquid two-phase fluid pump (103) arranged downstream of the solid-liquid two-phase hybrid heat exchanger (102) is used to make the solid-liquid two-phase flow reach a certain pressure value. 5. The heat radiation device according to claim 4, characterized in that: The particle collector (101) has a rotating centrifugal force and collects the particles by centrifugal action, The particle injector (105) is used to inject particles into space according to a pre-designed trajectory, so that the particles dissipate heat through radiation. 6. A heat radiation method, characterized in that comprising: Emit particles into space with a particle injector (105); collecting particles emitted by said particle injector (105) with a particle collector (101); Carrying out the heat exchange of the particles with a solid-liquid two-phase mixed heat exchanger (102); The solid-liquid mixture is separated by a solid-liquid two-phase separator (104). 7. The heat radiation method according to claim 6, characterized in that: Use the solid-liquid two-phase mixed heat exchanger (102) to make the particles collected by the particle collector (101) and the working fluid from the working system (106) merge at the outlet of the particle collector (101), and the particles It flows under the driving action of the working fluid and enters the hybrid heat exchanger to make the particles and the working fluid exchange heat. 8. The thermal radiation method according to claim 7, further comprising: A solid-liquid two-phase separator (104) is used to separate the particles from the working fluid and to dry the particles. 9. The thermal radiation method according to claim 8, further comprising: A solid-liquid two-phase fluid pump (103) arranged downstream of the heat exchanger (102) is used to make the solid-liquid two-phase flow reach a certain pressure value. 10. The heat radiation method according to claim 9, characterized in that: Using the particle collector (101) to collect the particles by centrifugal force, The particle injector (105) is used to inject particles into space according to a pre-designed trajectory, so that the particles dissipate heat through radiation.