CN113443175B - Structure of space liquid drop radiator - Google Patents
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- CN113443175B CN113443175B CN202110605268.8A CN202110605268A CN113443175B CN 113443175 B CN113443175 B CN 113443175B CN 202110605268 A CN202110605268 A CN 202110605268A CN 113443175 B CN113443175 B CN 113443175B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- H—ELECTRICITY
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- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20218—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant without phase change in electronic enclosures
- H05K7/20272—Accessories for moving fluid, for expanding fluid, for connecting fluid conduits, for distributing fluid, for removing gas or for preventing leakage, e.g. pumps, tanks or manifolds
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- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20218—Modifications to facilitate cooling, ventilating, or heating using a liquid coolant without phase change in electronic enclosures
- H05K7/20281—Thermal management, e.g. liquid flow control
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- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
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Abstract
The invention provides a structure of a space liquid drop radiator, which comprises a liquid drop emitter, a liquid conveying pipeline, a liquid drop receiver and a metal filament array, wherein the liquid drop receiver is connected with the liquid drop emitter through the liquid conveying pipeline, the metal filament array is arranged between the liquid drop emitter and the liquid drop receiver and arranged along the circumferential direction of the liquid conveying pipeline, a droplet spraying space is formed between the liquid conveying pipeline and the metal filament array, the liquid drop receiver is connected with a collecting and delivering system, the liquid is conveyed into the liquid drop emitter through the liquid conveying pipeline, the liquid is sprayed out from the liquid drop emitter to form liquid drops, the liquid drops are collected into the collecting and delivering system after passing through the droplet spraying space, the metal filament array and the liquid drops are charged bodies and have the same polarity of the charged charges, the invention utilizes electric field force to control the flight path of the liquid drops, and improves the capability of resisting the acceleration and the on-rail movement of a spacecraft of the liquid drop radiator, the method has the advantages of small system quality, high reliability and the like.
Description
Technical Field
The invention relates to the technical field of aerospace thermal control, in particular to a structure of a space liquid drop radiator.
Background
Prior art Droplet applicators were first specifically designed and described by Mattick et al (Mattick A.T. and Herzberg A., Liquid drop Radiators for Heat Rejection in Space, Energy to the 21st centre, Vol.1,1980, AIAA, New York,1980: 143-. Compared with the traditional panel type solid radiator, the liquid drop radiator adopts oil liquid which is not easy to volatilize under the vacuum environment as a heat carrier to absorb heat through the heat exchanger, then directional atomization and injection are carried out in the space to form a large number of oil liquid drops with small diameters and masses, the liquid drops are subjected to radiation cooling in the flying process by means of the huge number of the liquid drops and the corresponding huge radiation area, and finally the liquid drops after the radiation cooling are recovered through the recovery device and enter the heat exchanger again to absorb heat.
Such as the jet space radiator disclosed in RU2224199C2, which has the advantages of high efficiency and light weight of heat dissipation without heavy and bulky panels and heat conducting devices, and good reliability without being easily damaged in the case of impact of foreign objects such as meteor and small space debris. Although the single droplet beam has good directivity in the high vacuum and microgravity environment, the overall movement direction and flight speed of the droplet group ejected by the droplet radiator depend heavily on the processing precision and consistency of the emission nozzle, otherwise the droplet group has direction divergence, droplet impact and condensation, and the heat dissipation and recovery efficiency is affected, namely the size and the speed of the droplet completely depend on the lift, the flow rate and the design of an emitter small hole of the driving pump. The small holes are small, so that the flow resistance is high, and the requirement on the power of the pump is high. And the accuracy and consistency of the flight direction are also very strict on the processing level of the small holes. And the liquid drops fly freely in space under the action of inertia, and inevitably deviate from a recovery device when the spacecraft is accelerated and maneuvered in orbit, so that the liquid cannot be completely recovered, the liquid loss occurs and the interference force is generated on the spacecraft.
In addition, existing drop radiators rely primarily on a linear collector and a pump-driven auxiliary liquid film to capture the flying drops. Due to the small area of the collector, the motion condition of the liquid drops in the capturing process has great uncertainty, and mutual collision and splashing are easy to happen, so that the liquid is lost.
Further, as the liquid droplet radiator for heat dissipation in space proposed by Mattick A.T. and Herzberg A. in International conference on energy conversion, proceedings published by the American society for aerospace and aviation in 1980, at page 143-.
Therefore, in order to overcome the technical deficiencies, it is necessary to provide an improved droplet radiator, which makes the flight of the droplets more stable and controllable, and the recovery of the droplets more reliable and efficient, thereby improving the engineering feasibility of the droplet radiator and accelerating the space application and popularization of the droplet radiator.
Disclosure of Invention
In view of the deficiencies in the prior art, it is an object of the present invention to provide a structure for a spatial drop radiator.
The structure of the space liquid drop radiator provided by the invention comprises a liquid drop emitter, a liquid conveying pipeline, a liquid drop receiver and a metal filament array;
the liquid drop receiver is connected with the liquid drop emitter through a liquid conveying pipeline;
the metal filament array is arranged between the liquid drop emitter and the liquid drop receiver and arranged along the circumferential direction of the liquid conveying pipeline, and a drop spraying space is formed between the liquid conveying pipeline and the metal filament array;
the liquid drop receiver is connected with a collecting and delivering system, the liquid is conveyed into the liquid drop emitter through the liquid conveying pipeline, and the liquid is sprayed out of the liquid drop emitter to form liquid drops, passes through a liquid drop spraying space and is finally collected into the collecting and delivering system;
wherein, the metal filament array and the liquid drop are charged bodies and have the same polarity of charge.
Preferably, the droplet emitter comprises a first drive pump, a heat source heat exchanger and an emitter housing;
the emitter shell is provided with an emitting hole array, an inlet of the first driving pump is connected with an outlet of the liquid conveying pipeline, and an outlet of the first driving pump is sprayed out of the emitting hole array after passing through the heat source heat exchanger.
Preferably, the array of emission holes is arranged along the circumference of the liquid conveying pipeline;
the emitting holes of the emitting hole array are annularly arranged, and outlets of the emitting holes point to the center of an inner spherical surface of the liquid drop receiver.
Preferably, the inner side surface of the liquid drop receiver is provided with a main line capillary channel and a circumferential capillary channel which are arranged in a crossed manner, wherein the main line capillary channel is a straight channel along the radial direction of the liquid conveying pipeline and is arranged in the circumferential direction of the liquid conveying pipeline, the circumferential capillary channel is a discontinuous annular channel along the radial direction perpendicular to the liquid conveying pipeline and is arranged in the circumferential direction of the liquid conveying pipeline, and the main line capillary channel is connected with the circumferential capillary channel;
the number of the trunk capillary channels is multiple, and every two adjacent trunk capillary channels are arranged at intervals;
the number of the circumferential capillary channels is multiple, and every two adjacent circumferential capillary channels are arranged at intervals.
Preferably, the trunk capillary channels and the circumferential capillary channels form a channel array together, the outer surface of the droplet receiver is spherical, the channel array covers the whole inner side of the spherical surface, the region for receiving the droplets is plated with a continuous metal film, and the inner side of the spherical surface of the droplet receiver is made of a light flexible material.
Preferably, the liquid is liquid metal gallium, liquid metal lithium or silicon oil.
Preferably, the inner side surface of the liquid drop receiver is provided with a collection hole array which is connected with the collection and delivery system, the collection and delivery system is provided with a second driving pump, and the liquid drops in the collection and delivery system are delivered into the liquid delivery pipeline through the second driving pump.
Preferably, the metal filament array comprises a plurality of metal filaments which are uniformly arranged along the circumferential direction of the liquid conveying pipeline;
one end of the metal filament array is electrically connected with the liquid drop emitter, and the other end of the metal filament array is connected with the metal film on the inner side surface of the liquid drop receiver in an insulation mode.
Preferably, in operation, the droplet emitter and the array of metal filaments are each supplied with a positive high voltage, the droplet emitter charging the emitted droplets with a positive charge and the droplet emitter supplying a negative voltage to the metal film on the inside surface of the droplet receiver;
alternatively, a negative high voltage is applied to both the droplet emitter and the metal filament array, the droplet emitter charges the emitted droplet with a negative charge, and a positive voltage is applied to the metal film on the inside surface of the droplet receiver.
Preferably, the liquid conveying pipeline is a pipeline with a telescopic length;
the liquid drop emitter and the liquid drop receiver are both supported by a truss.
Compared with the prior art, the invention has the following beneficial effects:
1. the liquid drop radiator of the invention radiates and radiates heat in the flying process of liquid drops between the emitter and the receiver, has the characteristics of small system mass, high reliability and the like, and is an important option for radiating high-power spacecrafts such as nuclear power airships, space solar power stations and the like. The flight path of the liquid drop is controlled by using the electric field force, the loss of the liquid drop is reduced on the premise of not obviously increasing the system quality, and the resistance of the liquid drop radiator to the acceleration and the on-orbit maneuvering of the spacecraft is improved.
2. The invention accelerates the liquid drop by using the electric field force, has lower flow velocity at the outlet of the emitter, and is beneficial to reducing the power and the lift of the first driving pump.
3. The invention reduces the number of the emitting holes on the emitter, and reduces the impact density of the liquid drops on the surface of the receiver and the possible liquid collision and splashing through the expanding type liquid drop flying path and the large-area spherical receiver.
4. According to the invention, the densely distributed capillary channel array is arranged on the surface of the receiver, so that the received liquid is transported to the receiver terminal by utilizing the capillary force of the liquid, and the liquid transportation difficulty on the receiver is reduced.
5. The invention utilizes the metal wire to surround the flying space of the liquid drop to form a Faraday cage, thereby blocking the adverse effect of solar wind and ionized layer plasma on the liquid drop in the space environment and inhibiting the liquid drop from escaping to the outside in the flying process.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic diagram of a system configuration of a droplet emitter;
FIG. 2 is a schematic view of the interconnection of the droplet emitter, emitter and liquid delivery conduit with the array of metal filaments;
FIG. 3 is a schematic diagram of the inner near-center region of the spherical surface of the receiver;
fig. 4 is a schematic structural view of one application configuration of the liquid droplet radiator of the invention in combination with the various sections of a spacecraft.
The figures show that:
Drop receiver 3 firing aperture array 11
Collecting and delivery system 4 trunk capillary channel 31
Load chamber 6 collection hole array 33
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In the traditional design of a liquid drop radiator, liquid drops are subjected to pressure of a driving pump and restriction of a small hole, so that an outflow liquid beam is broken through flow instability of the liquid drops to form a liquid drop string, and the liquid drops radiate and radiate heat to a space while making uniform-speed linear motion in the space. Through the direction arrangement of a plurality of emitters, the flight directions of the droplet groups are generally parallel to each other or are converged continuously, so that the space number density of the droplet groups is basically unchanged or is increased continuously in the flight process, and a higher difficulty requirement is provided for one side of a receiver.
Example 1:
in order to realize the large heat dissipation of the high-power spacecraft and avoid bringing huge system mass, the invention provides a structure of a space liquid drop radiator, which comprises a liquid drop emitter 1, a liquid conveying pipeline 2, a liquid drop receiver 3 and a metal filament array 5, the liquid drop receiver 3 is connected with the liquid drop emitter 1 through a liquid conveying pipeline 2, the metal filament array 5 is arranged between the liquid drop emitter 1 and the liquid drop receiver 3 and arranged along the circumferential direction of the liquid conveying pipeline 2, a droplet spraying space is formed between the liquid conveying pipeline 2 and the metal filament array 5, the droplet receiver 3 is connected with a collecting and delivering system 4, the liquid is conveyed to the liquid drop emitter 1 through the liquid conveying pipeline 2, and the liquid is sprayed out of the liquid drop emitter 1 to form liquid drops, and the liquid drops pass through the liquid drop spraying space and are finally collected in the collection and outward conveying system 4. In practice, the droplet emitter 1 is small in size and can be considered approximately as a point relative to the overall emitter system, located approximately at the center of the sphere of the droplet receiver 3.
Specifically, an electric field is arranged between the liquid drop emitter 1 and the liquid drop receiver 3, the flying of the liquid drops is controlled and accelerated by the electric field force, the metal filament array 5 and the liquid drops are all charged bodies and have the same charged polarity, and are influenced by the mutual repulsion effect of the same charges, and the flying of the liquid drop group between the liquid drop emitter 1 and the liquid drop receiver 3 forms a conical diffusion shape and is finally received by the spherical surface of the liquid drop receiver 3 with a large area. In the present invention, a high voltage is applied to the metal filament array 5, and the electric polarity of the metal filament array is the same as that of the liquid droplets. The electric field force action of the metal filaments is utilized to limit charged liquid drops from flying away from the control area after diverging in the flying direction.
When the liquid drop receiver works, the liquid drop emitter 1 and the metal filament array 5 apply positive high voltage, the liquid drop emitter 1 charges the emitted liquid drops with positive electric quantity, and applies negative voltage to a metal film on the inner side surface of the liquid drop receiver 3; alternatively, the droplet emitter 1 and the metal filament array 5 are applied with a negative high voltage, the droplet emitter 1 charges the emitted droplets with a negative electric charge, and a positive voltage is applied to the metal film provided on the inner side surface of the droplet receiver 3. A metal filament array 5 is arranged at the outer boundary of the radiator, high voltage with the same polarity as the charge of the liquid drop is applied, and the liquid drop is prevented from deviating and flying and is prevented from being interfered and influenced by external plasma by the electric field and Faraday cage effect of the high voltage.
Under the action of an electric field force, on one hand, the liquid drops accelerate to fly to the liquid drop receiver 3, on the other hand, like electric charges repel between the liquid drops and adjacent liquid drops, so that the movement of the liquid drop group is dispersed in the normal direction, the small section of the emission hole array 11 on the liquid drop emitter 1 is expanded to a spherical surface with a large area on the liquid drop receiver 3, the liquid drops are radiated and cooled in the flying process, and the liquid drops are in contact with a metal film on the liquid drop receiver 3 to realize electric neutralization. Then the collecting and delivering system 4 sucks the liquid recovered on the spherical surface through the collecting hole array 33 at the center of the spherical surface, and the liquid is pressurized by a second driving pump and then conveyed to the heat source heat exchanger from the liquid conveying pipeline 2 to perform heat exchange circulation again.
Further, the liquid drop emitter 1 comprises a first driving pump, a heat source heat exchanger and an emitter shell, wherein an emitting hole array 11 is arranged on the emitter shell, an inlet of the first driving pump is connected with an outlet of the liquid conveying pipeline 2, an outlet of the first driving pump absorbs heat through the heat source heat exchanger and then is ejected out of the emitting hole array 11, the emitting hole array 11 is arranged along the circumferential direction of the liquid conveying pipeline 2, emitting holes of the emitting hole array 11 are arranged in an annular mode, and outlets of the emitting holes point to the center of an inner spherical surface of the liquid drop receiver 3.
Specifically, the liquid drop receiver 3 is made of a lightweight flexible material, and the inner side surface of the liquid drop receiver 3 is provided with a trunk capillary channel 31 and a circumferential capillary channel 32 which are arranged in a crossed manner, wherein the trunk capillary channel 31 is a straight channel along the radial direction of the liquid conveying pipeline 2 and is arranged in the circumferential direction of the liquid conveying pipeline 2, the circumferential capillary channel 32 is a discontinuous annular channel along the radial direction perpendicular to the liquid conveying pipeline 2 and is arranged in the circumferential direction of the liquid conveying pipeline 2, the trunk capillary channel 31 is connected with the circumferential capillary channel 32, the trunk capillary channel 31 is multiple in number and is arranged at intervals between every two adjacent trunk capillary channels 31, and the circumferential capillary channel 32 is multiple in number and is arranged at intervals between every two adjacent circumferential capillary channels 32.
The spherical surface of the liquid drop receiver 3 utilizes the capillary channel on the spherical surface to converge and transport the received liquid to the center of the spherical surface, the inner side surface of the liquid drop receiver 3 is provided with a collecting hole array 33, the collecting hole array 33 is connected with the collecting and delivering system 4, the collecting hole array 33 comprises a plurality of collecting holes, the liquid enters the collecting and delivering system 4 through the collecting holes at the center of the spherical surface, the collecting and delivering system 4 is internally provided with a second driving pump, and the liquid drops in the collecting and delivering system 4 are delivered into the liquid delivery pipeline 2 through the second driving pump. After being pressurized by a second driving pump, the liquid is sent back to the heat source heat exchanger from the liquid conveying pipeline 2 to absorb heat again.
Specifically, the trunk capillary channels 31 and the circumferential capillary channels 32 together form a channel array covering the entire area inside the spherical surface of the droplet receiver 3 except near the center, the outer surface of the droplet receiver 3 is spherical, and the channel array covers the entire inside of the spherical surface and the area receiving the droplets is plated with a continuous metal film of high conductivity. The droplet receiver 3 is approximately bowl-shaped with a circumferentially symmetrical profile and the range of the cone angle of the array of metal filaments 5 is typically less than 40 deg. depending on the requirements of the application. The expansion type liquid drop flying path is adopted, the space quantity density of the liquid drops is continuously reduced in the flying process, and the impact of the liquid drops on the spherical surface of the liquid drop receiver 3 is reduced.
The invention makes the surface of the liquid drop receiver 3 into a large-area spherical surface to adapt to the expansion type flying dispersion of the liquid drop group and the vertical landing of the liquid drop, and simultaneously utilizes the surface tension of the liquid and the main line capillary channel 31 and the circumferential capillary channel 32 arranged on the surface of the liquid drop receiver 3 to carry out liquid transportation, thereby reducing the impact and the splashing of the liquid drop to the liquid drop receiver 3 to the maximum extent.
The metal filament array 5 comprises a plurality of metal filaments which are uniformly arranged along the circumferential direction of the liquid conveying pipeline 2, one end of the metal filament array 5 is electrically connected with the liquid drop emitter 1, and the other end of the metal filament array 5 is in insulation connection with a metal film on the inner side surface of the liquid drop receiver 3.
Example 2:
this embodiment is a preferred embodiment of embodiment 1.
In this embodiment, since the liquid droplets are driven by the electric field force, the liquid droplet emitter 1 only needs to atomize the liquid, and the power consumption can be greatly reduced. The driving effect of the electric field force on the droplets is exemplified by typical methyl silicone oil droplets with a radius of 25 μm. The mass of the liquid is about 6.28 x 10-11kg, the liquid drop formed in the microgravity environment is generally spherical, the radius of the liquid drop is R, and the dielectric constant of the liquid is epsilon 0 The methyl silicone oil is 2.65, the surface tension coefficient of the liquid is 0.02N/m, the maximum critical charge quantity which can be borne on the liquid drop and can keep the liquid drop from cracking is about
Referring to the results of general droplet charging experiments, one million times of the critical value is taken as the charge amount of the droplet, which is about 7.3 × 10 -14 C. When the distance between the bottom surface of the emitter 1 and the metal film on the spherical surface of the droplet receiver 3 is 20m and the voltage difference between the bottom surface of the emitter and the metal film is 1000V, the stress on the droplet at this time is about 3.65X 10 -12 N, the liquid drop can obtain 0.058m/s 2 Average acceleration of (2). The full flight time is about 26 seconds, which provides sufficient cooling time for the droplets. The speed of the liquid drop reaching the spherical surface of the liquid drop receiver 3 is only about 1.5m/s, and the spherical surface of the liquid drop receiver 3 adopts flexible materials, so that the impact and possible splashing on the surface of the liquid drop receiver 3 can be effectively reduced. Because each liquid drop has the same polarity, the adjacent liquid drops have repulsion action, so that the liquid drop group forms a continuously divergent expansion shape and is just suitable for a liquid drop receiver 3 with a large area.
Charged droplets may be affected by the earth's magnetic field when the spacecraft is in low orbit on earth. Taking the larger value of the earth magnetic field intensity as 6 x 10 -5 T, the flying speed of the spacecraft is 7800m/s, and the charged liquid can be calculatedThe maximum magnetic force to which the droplet is subjected is approximately 3.42X 10 -14 N, two orders of magnitude less than the electric field force, so the effect of the earth's magnetic field on the flight of charged droplets is negligible. Assuming that the temperature of the droplets is reduced by 30 ℃ during flight, taking the specific heat of the methylsilicone oil as 2.4 KJ/kg. K, the heat dissipation amount provided is about 4.53X 10 -6 J. Assuming a spacecraft system is required to dissipate 2000KW of large heat, a droplet emitter is required to emit 4.4 x 10 droplets per second 11 The mass flow rate of each droplet is about 27.6 kg/s. Corresponding to this number of drops, the drop emitter 1 consumes about 0.32C of charge per second, corresponding to a current intensity of the cable connecting the drop emitter 1 and the drop receiver 3 of only 0.32A, a driving power of only 320W, which is within an engineering acceptable range. Throughout the transmission and reception of the droplets, the net charge of the emitter system is neutral. The charged liquid drops are under the action of electric field force and earth magnetic field force, momentum is transferred to the liquid drop receiver 3 at the liquid drop receiver 3, cables between the liquid drop emitter 1 and the liquid drop receiver 3 form an open loop, the action of the force is also under the action of the earth magnetic field force, the action of the force is mutually counteracted on the system level, and the flying speed and the attitude control of the spacecraft cannot be influenced.
The droplet emitter 1 generates tiny droplets by means of piezoelectric oscillation, only system back pressure is needed, and a special driving pump is not needed. The orifices of the droplet emitter 1 are evenly distributed to form an array of emission apertures 11, integral with the electrodes for charging the droplets, as shown in figure 2. The spherical surface of the liquid drop receiver 3 is unfolded in an auxiliary mode of integrating light flexible materials. The spherical structure of the drop receiver 3, although large in size and area, has a very small mass, and the advantage of light weight of the drop radiator can be maintained. The liquid conveying pipeline 2 is respectively connected with the liquid drop emitter 1 and the liquid drop receiver 3, so that the liquid drop emitter 1 and the liquid drop receiver 3 need to be combined with other structures, such as a truss and the like, and the liquid drop emitter 1 and the liquid drop receiver 3 are supported by the truss and are used as stress parts for connecting and supporting besides liquid conveying. In view of the space requirements for launching the spacecraft, the liquid conveying pipeline 2 should be made as a length-adjustable part.
In the history of research on droplet radiators, methods for controlling the movement of droplets by using electric field force have been abandoned, one reason is that charged droplets with the same polarity can repel each other, the flight direction of droplet groups is diverged to cause loss, and a single droplet is broken into a plurality of smaller droplets by too high charge amount. Another reason is the presence of solar wind particles and large amounts of plasma in the ionosphere of the cosmos and earth orbits, which are likely to cause droplets and transmitter/receivers to charge and discharge. In order to solve the problems, the invention adopts the measures that the metal filament array 5 is arranged between the spherical surfaces of the liquid drop emitter 1 and the liquid drop receiver 3, the space for flying and transporting liquid drops is divided into two parts with the external space, a Faraday cage is formed, and the passing and the mutual influence of the internal electromagnetic field and the external electromagnetic field are isolated. The purpose of the measure is to resist the interference of external solar wind or plasma in the earth ionized layer to the charged liquid drop, and on the other hand, apply high voltage with the same polarity as the charged liquid drop on the metal wire, and prevent a few liquid drops with deviated flight directions from flying away from the inner space of the Faraday cage by the repulsion action of electric field force, thereby realizing the high-efficiency recovery of the liquid drops. As shown in fig. 2, a thin wire may be in communication with the electrode on the droplet emitter 1, reducing the complexity of powering the system.
In the high vacuum environment of the universe, although general liquid can be rapidly volatilized, a few liquids with extremely low vapor pressure can still keep a liquid state in space. For the situation that the heat dissipation temperature is higher, the liquid can adopt liquid metal with extremely low vapor pressure at the working temperature, such as gallium, lithium and the like; if the heat dissipation temperature is low, DC705 silicon oil and the like can be considered as heat exchange working media. These liquids generally have a large surface tension coefficient and tend to form spherical droplets in a microgravity state. In addition, these liquids are hydrophilic to most solid surfaces and can still adhere to solid surfaces even under vacuum. Thus, the inner side of the spherical surface of the drop receiver 3 of the drop radiator is provided with a trunk capillary channel 31 and a circumferential capillary channel 32, as shown in fig. 3. By providing the collection hole array 33 at the center of the spherical surface, the liquid near the center of the spherical surface is absorbed by the second driving pump in the collection and delivery system 4, the height of the liquid level at this position is changed, and the liquid transportation on the spherical surface is realized by the adsorption force of the solid surface to the liquid and the capillary force of the capillary channel. The cooling liquid pressurized by the pump is sent back to the heat source heat exchanger again through the liquid conveying pipeline 2 to absorb heat.
An example of a specific integration of a droplet radiator with a spacecraft in the present invention is shown in figure 4. Assuming that the spacecraft uses a space nuclear reactor as a heat source for thermoelectric conversion, the reactor forms a conical non-nuclear radiation protection zone at the rear by using a shielding wall. The reactor of the spacecraft and the corresponding thermoelectric converter are therefore arranged in the front as a power bay 7 of smaller cross-sectional area, to which the droplet radiator is connected by its conical outer shape. The energy cabin 7 transmits waste heat generated by the thermoelectric conversion device to the emitter of the droplet radiator through the fluid loop of the liquid conveying pipeline 2 and the heat source heat exchanger, and receives low-temperature liquid returned by the droplet radiator. The load cabin 6 of the spacecraft is mainly arranged behind the liquid drop radiator liquid drop receiver 3 and can be provided with high-power electric loads such as a space-based radar or an electric thruster 8.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A structure of a space liquid drop radiator is characterized by comprising a liquid drop emitter (1), a liquid conveying pipeline (2), a liquid drop receiver (3) and a metal filament array (5);
the liquid drop receiver (3) is connected with the liquid drop emitter (1) through a liquid conveying pipeline (2);
the metal filament array (5) is arranged between the liquid drop emitter (1) and the liquid drop receiver (3) and arranged along the circumferential direction of the liquid conveying pipeline (2), and a drop spraying space is formed between the liquid conveying pipeline (2) and the metal filament array (5);
the liquid drop receiver (3) is connected with a collecting and delivering system (4), liquid is conveyed into the liquid drop emitter (1) through the liquid conveying pipeline (2), and the liquid is sprayed out of the liquid drop emitter (1) to form liquid drops, the liquid drops pass through a liquid drop spraying space and are finally collected into the collecting and delivering system (4);
wherein, the metal filament array (5) and the liquid drop are charged bodies and have the same polarity of charge.
2. The structure of a spatial droplet radiator according to claim 1, characterized in that the droplet emitter (1) comprises a first drive pump, a heat source heat exchanger and an emitter housing;
the emitter shell is provided with an emitting hole array (11), an inlet of the first driving pump is connected with an outlet of the liquid conveying pipeline (2), and an outlet of the first driving pump is sprayed out of the emitting hole array (11) after passing through the heat source heat exchanger.
3. The structure of a spatial droplet radiator according to claim 2, characterised in that the array of emission apertures (11) is arranged along the circumference of the liquid conveying pipe (2);
the emitting holes of the emitting hole array (11) are annularly arranged, and the outlets of the emitting holes point to the center of the inner spherical surface of the liquid drop receiver (3).
4. A structure of a spatial droplet radiator according to claim 1, characterized in that the inner side surface of the droplet receiver (3) is provided with crosswise arranged trunk capillary channels (31) and circumferential capillary channels (32), wherein the trunk capillary channels (31) are straight channels in the radial direction of the liquid transport pipe (2) and arranged in the circumferential direction of the liquid transport pipe (2), the circumferential capillary channels (32) are discontinuous annular channels in the radial direction perpendicular to the liquid transport pipe (2) and arranged in the circumferential direction of the liquid transport pipe (2), the trunk capillary channels (31) connecting the circumferential capillary channels (32);
the number of the trunk line capillary channels (31) is multiple, and every two adjacent trunk line capillary channels (31) are arranged at intervals;
the number of the circumferential capillary channels (32) is multiple, and every two adjacent circumferential capillary channels (32) are arranged at intervals.
5. A spatial droplet radiator structure according to claim 4, characterised in that the trunk capillary channels (31) and the circumferential capillary channels (32) together form a channel array, the outer surface of the droplet receiver (3) is spherical, the channel array covers the entire inner side of the sphere and the droplet receiving area is coated with a continuous metal film, and the inner side of the sphere of the droplet receiver (3) is made of a light weight flexible material.
6. The structure of a spatial droplet radiator according to claim 1, characterised in that the liquid is liquid metal gallium, liquid metal lithium or silicone oil.
7. A space droplet radiator structure according to claim 1, characterized in that the inside surface of the droplet receiver (3) is provided with an array of collecting holes (33), the array of collecting holes (33) connecting the collecting and feeding system (4), a second driven pump being provided in the collecting and feeding system (4), through which second driven pump the droplets in the collecting and feeding system (4) are fed into the liquid conveying pipe (2).
8. A space droplet radiator structure according to claim 1, characterized in that the metal filament array (5) comprises a plurality of metal filaments, which are arranged uniformly in the circumferential direction of the liquid conveying pipe (2);
one end of the metal filament array (5) is electrically connected with the liquid drop emitter (1), and the other end of the metal filament array (5) is connected with a metal film on the inner side surface of the liquid drop receiver (3) in an insulation mode.
9. A spatial droplet radiator arrangement according to claim 1, characterised in that, in operation, the droplet emitter (1) and the array of metal filaments (5) each apply a positive high voltage, the droplet emitter (1) charging the emitted droplets with a positive charge and applying a negative voltage to the metal film provided on the inside surface of the droplet receiver (3);
or, the liquid drop emitter (1) and the metal filament array (5) apply negative high voltage, the liquid drop emitter (1) charges the emitted liquid drop with negative electric quantity, and applies positive voltage to the metal film on the inner side surface of the liquid drop receiver (3).
10. The structure of a spatial droplet radiator according to claim 1, characterised in that the liquid feed line (2) is a length-scalable line;
the liquid drop emitter (1) and the liquid drop receiver (3) are supported by a truss.
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