CN114084378B - Microwave heating water propulsion system and propulsion control method - Google Patents
Microwave heating water propulsion system and propulsion control method Download PDFInfo
- Publication number
- CN114084378B CN114084378B CN202111355846.3A CN202111355846A CN114084378B CN 114084378 B CN114084378 B CN 114084378B CN 202111355846 A CN202111355846 A CN 202111355846A CN 114084378 B CN114084378 B CN 114084378B
- Authority
- CN
- China
- Prior art keywords
- subsystem
- microwave heating
- temperature
- pressure
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000008236 heating water Substances 0.000 title claims abstract description 17
- 238000010438 heat treatment Methods 0.000 claims abstract description 119
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 101
- 239000003380 propellant Substances 0.000 claims abstract description 48
- 230000033228 biological regulation Effects 0.000 claims abstract description 12
- 239000007921 spray Substances 0.000 claims description 19
- 230000001276 controlling effect Effects 0.000 claims description 16
- 239000007788 liquid Substances 0.000 claims description 10
- 238000005507 spraying Methods 0.000 claims description 4
- 230000003750 conditioning effect Effects 0.000 claims description 3
- 230000008602 contraction Effects 0.000 claims description 3
- 239000012774 insulation material Substances 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 8
- 238000011161 development Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 14
- 238000004364 calculation method Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 description 4
- 229910001416 lithium ion Inorganic materials 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000009123 feedback regulation Effects 0.000 description 2
- 239000001307 helium Substances 0.000 description 2
- 229910052734 helium Inorganic materials 0.000 description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000008033 biological extinction Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005672 electromagnetic field Effects 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 201000009240 nasopharyngitis Diseases 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000003595 spectral effect Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000001988 toxicity Effects 0.000 description 1
- 231100000419 toxicity Toxicity 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Classifications
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Constitution Of High-Frequency Heating (AREA)
Abstract
The application relates to a microwave heating water propulsion system and a propulsion control method. The system comprises: a propellant supply subsystem, a microwave heating subsystem, a thrust chamber subsystem, a temperature regulation subsystem, a power supply subsystem and a control subsystem. The system adopts water as a propellant, a propellant supply subsystem fills water working medium into a microwave heating subsystem, the microwave heating subsystem converts electric energy into microwaves, the microwaves reach larger pressure and temperature in a microwave heating mode, finally high-temperature steam is sent into a thrust chamber subsystem, and the injected high-pressure superheated steam is sprayed out after being accelerated to a preset speed, so that a propelling task is completed. The system takes water as a propulsion working medium, and obtains energy through microwave heating, so that the microwave heating water propulsion system has the advantages of small volume, low cost, safety, reliability, short development period, cleanness, no pollution and the like.
Description
Technical Field
The application relates to the technical field of propulsion systems, in particular to a microwave heating water propulsion system and a propulsion control method.
Background
The micro-nano satellite represented by the cube star has the advantages of small volume, low cost, short development period and the like, and has been rapidly developed in the fields of the space-based internet, scientific experiments, earth observation and the like in recent years. However, due to the limitation of volume and cost, the existing various cubes are not provided with a propulsion system, the tasks of autonomous orbit adjustment, resistance compensation, off-orbit control and the like cannot be realized, the use efficiency of the micro-nano satellite is greatly limited, and the used micro-nano satellite can only continuously float in space to become space garbage due to the fact that off-orbit control cannot be carried out, and the safety of a spacecraft and a space station is seriously threatened.
Conventional propulsion means, such as cold air propulsion, have relatively low specific impulse; chemical propulsion, complex structure, great technical difficulty and toxicity of propellant; electric propulsion, small thrust, large volume, etc., and none of these propulsion systems are suitable for use in microsatellites.
Disclosure of Invention
In view of the foregoing, it is desirable to provide a microwave-heated water propulsion system and propulsion control method.
A microwave-heated water propulsion system, the system comprising: a propellant supply subsystem, a microwave heating subsystem, a thrust chamber subsystem, a temperature regulation subsystem, a power supply subsystem and a control subsystem.
The propellant supply subsystem is used for storing liquid water working medium and controlling the propellant supply subsystem to load a preset amount of water working medium into the microwave heating subsystem according to preset requirements.
The microwave heating subsystem is used for converting electric energy into microwaves, heating water working media loaded from the propellant supply subsystem by utilizing the microwaves, and sending high-pressure superheated steam into the thrust chamber subsystem when the temperature or the pressure reaches a preset value.
And the thrust chamber subsystem is used for accelerating the injected high-pressure superheated steam to a preset speed and then spraying the high-pressure superheated steam to finish the propelling task.
The temperature regulating subsystem is used for detecting the temperature and the pressure in the propellant supply subsystem and transmitting the temperature and the pressure to the control subsystem, and controlling the heating resistor according to the instruction of the control subsystem so as to enable the water working medium to be kept as a liquid water working medium with a certain temperature in a space low-temperature and low-pressure environment.
The control subsystem is used for carrying out feedback regulation on the system according to signals fed back by the preset requirements, the propellant supply subsystem, the temperature regulation subsystem and the microwave heating subsystem.
The power subsystem is used for providing power for the propellant supply subsystem, the microwave heating subsystem, the thrust chamber subsystem, the temperature regulation subsystem and the control subsystem.
The propulsion control method is applied to the microwave heating water propulsion system for propulsion control, and comprises the following steps:
and acquiring an attitude adjustment instruction, and calculating the flow of the required water working medium and the preset temperature or the preset pressure of the high-pressure superheated steam according to the attitude adjustment instruction.
And sending an electromagnetic valve opening command, and opening a second electromagnetic valve in the propellant supply subsystem through a control circuit, wherein water working medium in the propellant supply subsystem is injected into the microwave heating subsystem through the second electromagnetic valve.
And when the filling amount of the water working medium reaches a preset value, closing the second electromagnetic valve.
And starting microwave heating, and collecting the temperature and pressure of the microwave heating subsystem in real time.
When the temperature of the high-pressure superheated steam reaches a preset temperature, a control circuit is used for opening a first electromagnetic valve in the microwave heating subsystem and a reversing valve of the thrust chamber subsystem, and the high-pressure superheated steam is injected into the scaling spray pipe after passing through the first electromagnetic valve and the reversing valve to complete the propelling task.
The system for microwave heating water propulsion and propulsion control method comprises: a propellant supply subsystem, a microwave heating subsystem, a thrust chamber subsystem, a temperature regulation subsystem, a power supply subsystem and a control subsystem. The system adopts water as a propellant, a propellant supply subsystem fills water working medium into a microwave heating subsystem, the microwave heating subsystem converts electric energy into microwaves, the microwaves reach larger pressure and temperature in a microwave heating mode, finally high-temperature high-pressure steam is sent into a thrust chamber subsystem, and the injected high-pressure superheated steam is sprayed out after being accelerated to a preset speed, so that a propelling task is completed. The system takes water as a propulsion working medium, and obtains energy through microwave heating, so that the microwave heating water propulsion system has the advantages of small volume, low cost, safety, reliability, short development period, cleanness, no pollution and the like.
Drawings
FIG. 1 is a block diagram of a microwave-heated water propulsion system in accordance with one embodiment;
FIG. 2 is a schematic diagram of a two-dimensional structure of a microwave-heated water propulsion system according to another embodiment;
FIG. 3 is a schematic diagram of another embodiment of a micro-nano satellite configuration using a microwave heated water propulsion system;
FIG. 4 is a schematic view of a three-dimensional structural layout of a microwave-heated water propulsion system according to another embodiment;
FIG. 5 is a diagram of a nozzle shape in one embodiment;
fig. 6 is a flow chart of a propulsion control method according to an embodiment.
Detailed Description
The present application will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.
In one embodiment, as shown in FIG. 1, a microwave-heated water propulsion system is provided, the system comprising: for propellant supply subsystem 10, microwave heating subsystem 20, thrust chamber subsystem 30, temperature conditioning subsystem 40, power subsystem 50, and control subsystem 60.
Propellant supply subsystem 10 is used for storing liquid water working media and controlling the propellant supply subsystem to load a predetermined amount of water working media into microwave heating subsystem 20 through control subsystem 40 according to predetermined requirements.
The microwave heating subsystem 20 is used for converting electric energy into microwaves, heating the water working medium loaded from the propellant supply subsystem 10 by the microwaves, and sending high-pressure superheated steam into the thrust chamber subsystem 30 when the temperature or pressure reaches a preset value.
The thrust chamber subsystem 30 is used for accelerating the injected high-pressure superheated steam to a preset speed and then spraying the high-pressure superheated steam to complete the propelling task.
The temperature adjusting subsystem 40 is used for detecting the temperature and the pressure in the propellant supplying subsystem 10, transmitting the detected temperature and pressure to the control subsystem 60, and controlling the heating resistor according to the instruction of the control subsystem 60 so as to keep the water working medium as a liquid water working medium with a certain temperature in the environment of space with low temperature and low pressure.
The control subsystem 60 is used for feedback regulation of the system according to the predetermined requirements, the signals fed back by the propellant supply subsystem 10, the temperature regulation subsystem 20 and the microwave heating subsystem 30.
The power subsystem 50 is used to provide power to the propellant supply subsystem 10, the microwave heating subsystem 20, the thrust chamber subsystem 40, the temperature conditioning subsystem 30, and the control subsystem 60.
In the above-mentioned microwave heating water propulsion system, the system includes: a propellant supply subsystem, a microwave heating subsystem, a thrust chamber subsystem, a temperature regulation subsystem, a power supply subsystem and a control subsystem. The system adopts water as a propellant, a propellant supply subsystem fills water working medium into a microwave heating subsystem, the microwave heating subsystem converts electric energy into microwaves, the microwaves reach larger pressure and temperature in a microwave heating mode, finally high-temperature high-pressure steam is sent into a thrust chamber subsystem, and the injected high-pressure superheated steam is sprayed out after being accelerated to a preset speed, so that a propelling task is completed. The system takes water as a propulsion working medium, and obtains energy through microwave heating, so that the microwave heating water propulsion system has the advantages of small volume, low cost, safety, reliability, short development period, cleanness, no pollution and the like.
In one embodiment, a microwave heating subsystem includes: the microwave heating device comprises a microwave heating cavity, a transformer, a magnetron, a waveguide, a first temperature sensor, a first pressure sensor and a first electromagnetic valve; the microwave heating cavity is made of heat-insulating materials and is used for heating the hydraulic medium loaded by the propellant supply subsystem; the first temperature sensor and the first pressure sensor are respectively used for detecting the temperature and the pressure in the microwave heating cavity and sending the detected temperature and pressure values in the heating cavity to the control subsystem.
A first solenoid valve for controlling the injection of high pressure superheated steam into the thrust chamber subsystem or stopping; the on-off control of the first electromagnetic valve is that the control subsystem compares the acquired internal temperature of the heating cavity or internal pressure of the heating cavity with a preset value, and when the internal temperature of the heating cavity or the internal pressure of the heating cavity reaches the preset value, the first electromagnetic valve is opened, and high-pressure superheated steam is sprayed into the thrust chamber subsystem; otherwise, closing the first electromagnetic valve; the voltage provided by the power subsystem is increased through a transformer, the high voltage generates microwaves through a magnetron, and the microwaves are transmitted to a microwave heating cavity through a waveguide; the microwave heating cavity heats the loaded hydraulic medium, the first temperature sensor and the first pressure sensor transmit the detected temperature and pressure inside the microwave heating cavity to the control subsystem, and when the preset condition is met, the control subsystem sends a command to open the first electromagnetic valve, and high-pressure superheated steam is sent into the thrust chamber; when the predetermined condition is not satisfied, the control subsystem issues an instruction to close the solenoid valve.
Specifically, as shown in fig. 2, the microwave heating water propulsion system is an extremely critical part of the whole propulsion system, and is used for providing energy for water working media to heat the water working media, so that the gas can obtain larger thrust after passing through the Laval nozzle. The microwave heating subsystem is composed of a microwave heating cavity, a magnetron, a waveguide, a temperature sensor, a pressure sensor, a metal fan and the like. The water flowing from the flexible water storage bag is heated to extremely high temperature, when the temperature (or pressure) reaches a preset value, the electromagnetic valve is opened, and high-pressure superheated steam is sent into the thrust chamber, so that the work task of the whole subsystem is completed. The electric energy required by the whole microwave cavity is provided by a storage battery, the voltage is increased through a transformer, the high voltage generates microwaves through a magnetron, and finally the microwaves are transmitted to the microwave cavity through a waveguide. The metal fan is used for stirring the working medium in the microwave cavity, so that the working medium can be sufficiently and uniformly heated. In the whole heating process, the pressure is particularly high, so that obvious real gas effect is shown, gas is dissociated or even ionized under the condition of particularly high temperature to become a mixture of ideal gas, so that a pressure sensor and a temperature sensor are adopted to detect the state in a microwave cavity simultaneously, information is transmitted to a spaceborne computer, and the heating time is accurately regulated and controlled through accurate calculation and comprehensive analysis of the spaceborne computer.
In one embodiment, the propellant supply subsystem includes a pressurized canister, a flexible reservoir, and a second solenoid valve; the pressurizing tank is made of heat insulation materials and is used for storing high-pressure gas for pressurizing the system; the flexible water storage bag is used for storing liquid hydraulic medium; the second electromagnetic valve is used for controlling the water working medium to flow into the microwave heating subsystem; when the water working medium is required to be loaded to the microwave heating subsystem, the control subsystem sends out an instruction to control the second electromagnetic valve to be opened, and the high-pressure gas in the pressurizing tank extrudes the water working medium in the flexible water storage bag to flow into the microwave heating subsystem through the second electromagnetic valve; when the water passing through the electromagnetic valve reaches a preset value, the control subsystem sends out an instruction again to control the second electromagnetic valve to be closed.
Specifically, the propellant supply subsystem uses high pressure helium stored in a pressurized canister as a pressurized gas source. The pressurizing tank is made of heat insulating material, and the water working medium is stored in liquid state in the flexible water storing bag inside the pressurizing tank.
When water injection working media are needed to be added, the satellite-borne computer of the control subsystem sends out instructions, the second electromagnetic valve switch is opened through the control circuit, and high-pressure helium in the pressurizing tank extrudes water in the flexible water storage bag to flow out through the electromagnetic valve. When the water passing through the electromagnetic valve reaches a required value, the on-board computer sends out an instruction through the control circuit, and the second electromagnetic valve is closed.
The temperature in the flexible water storage bag is controlled to be about 300K through a resistance wire arranged in the flexible water storage bag. The second temperature sensor feeds water temperature back to the spaceborne computer through real-time measurement, and the second temperature sensor is matched with the heating controller to complete heat preservation of water in the flexible water storage bag so as to ensure continuous and stable operation of the propellant supply system.
In one embodiment, the temperature regulation subsystem includes a second temperature sensor, a heating controller, and a heating resistor; the second temperature sensor and the heating resistor are both arranged in the flexible water storage bag, and the second temperature sensor is used for measuring the temperature of the water working medium in the flexible water storage bag and transmitting the detected value to the control subsystem; the heating controller is used for controlling the heating resistor to heat the water working medium in the flexible water storage bag according to the instruction sent by the control subsystem.
Specifically, the temperature regulation subsystem is used for maintaining the temperature in the flexible water storage bag, and water is prevented from icing in the environment of space low temperature and low pressure, so that the normal working efficiency of the system is ensured. In the running process of the whole system, the second temperature sensor can detect the water temperature in the flexible water storage bag in real time, transmits data to a signal acquisition card of the control subsystem, and feeds information back to the heating controller through calculation processing of the on-board computer. According to the feedback of the spaceborne computer, the heating controller can perform heating or cooling treatment on the flexible water storage bag, so that the water temperature in the flexible water storage bag is controlled at a certain level, and adverse conditions such as freezing of water are avoided.
In one embodiment, the thrust chamber subsystem includes a convergent-divergent nozzle and a diverter valve; the control end of the reversing valve is connected with the control subsystem and is used for controlling the high-pressure superheated steam flowing out of the microwave heating subsystem to flow into the scaling spray pipe; the convergent-divergent nozzle consists of a convergent section of the front half section of the nozzle, a throat in the middle and an divergent nozzle of the end section.
Specifically, in the last ring of the thrust generated by the propulsion system, the task of the spray pipe is to continuously accelerate the water vapor in the high-temperature state in the microwave heating cavity to a speed of more than 1500m/s for spraying. Preferably, a convergent-divergent nozzle is the most suitable nozzle type.
The convergent-divergent nozzle consists of a convergent section of the front half section, a throat in the middle and an divergent section of the end section. The high-pressure superheated steam starts to flow under the condition that the initial speed is extremely low in the contraction section of the spray pipe, reaches the local sound velocity when reaching the throat, continuously accelerates the flow (when the flow velocity exceeds the local sound velocity) in the expansion section through the throat, and then is sprayed out. The whole process is assumed that the gas performs performance estimation and calculation under a one-dimensional steady-state flow state to design the spray pipe.
The performance of a convergent nozzle is primarily dependent on the nozzle pinch ratio and pinch curve. The gas flow is ensured to flow stably and to accelerate under the condition of limited volume during the contraction process. Several approaches to the experiment include the wiener method, the quintic curve, the cubic curve, the shift axis wiener method, etc. Through design analysis, the axis-shifting dimension method has the advantages of uniform overall distribution, uniform velocity field after the spray pipe, flexible control of curve shape through axis-shifting quantity, and the like, and is the best choice of the shrinkage surface.
The nozzle throat is the beginning of the supersonic flow and the flow parameter of the nozzle throat is the beginning of the supersonic section of the working medium. Here, an approximation solution is required for the throat flow field, and the Kliegel method is preferably used, and the result is reliable except for the portion near the wall.
The nozzle design of the expansion section needs to be careful to maintain the stability of the air flow under the high Mach number state, and an axisymmetric circular cross-section surface is adopted. When hypersonic air flow is sprayed out of the section of the outlet, the hypersonic air flow is kept straight and uniform as much as possible, so that the expansion section spray pipe is divided into an initial expansion section and a extinction section. In the initial expansion section, the curved surface of the nozzle is gradually expanded outwards, and the airflow in the section is expanded outwards to accelerate and generate a series of expansion waves. In the wave elimination band, the slope of the wall surface is gradually reduced, the air flow expands inwards and generates compression waves to counteract the expansion waves generated before, and finally, the flat and uniform supersonic air flow is formed at the outlet.
In one embodiment, the convergent-divergent nozzle is a Laval nozzle.
The thrust chamber subsystem mainly comprises a Laval nozzle and a reversing valve, and heated gas enters the nozzles in different directions through the reversing valve to complete different required propelling tasks after passing through the first electromagnetic valve, so that the micro-nano satellite is ensured to have higher gesture control precision.
In one embodiment, the power subsystem includes a solar windsurfing board and a battery; the storage battery is used for storing electric energy from the solar sailboard.
Specifically, the solar sailboard is a folding solar sailboard commonly used for commercial micro-nano satellites.
The maximum output power of a single-sided solar cell array can be expressed as:
P mppt ＝(N s ·V mppt -V d )·(N p ·A·J mppt )
wherein P is mppt Represents the maximum output power of the single-sided solar cell array; n (N) s Representing the series number of the battery pieces; n (N) p Representing the parallel number of the battery pieces; v (V) mppt Representing the maximum power point voltage of the single-chip battery, V d Representing a reverse diode drop; a represents the area of a single battery piece; j (J) mppt Representing the maximum power point current areal density. From this calculation, the power of the solar sailboard is about 448 watts, and the maximum power supply is 112 watts by multiplying the power by the usual conversion efficiency of 25%.
Because of the instability of solar energy, 18650 lithium ion batteries are used in the present application for energy storage and energy supply for better energy utilization. The 18650 lithium ion battery is used as the most widely used storage battery, has the advantages of high specific energy, low cost, stable power supply and the like, and the storage battery system formed by combining the storage batteries is suitable for the low-cost satellite field.
Preferably, the lithium ion battery is of the type BPI-18650-3S16P-11.1V, and can output 500 watts of power at maximum.
In one embodiment, the control subsystem comprises a spaceborne computer, a control circuit and a signal acquisition card; the control circuit and the signal acquisition card are connected with the satellite-borne computer; the signal acquisition card is connected with the first temperature sensor, the first pressure sensor and the second temperature sensor; the control circuit is connected with the first electromagnetic valve, the second electromagnetic valve, the reversing valve, the magnetron and the heating controller.
The microwave heating water propulsion system is applied to a 12U satellite, the micro-nano satellite structure layout of the microwave heating water propulsion system is shown in fig. 3, and the three-dimensional structure layout schematic diagram of the microwave heating water propulsion system is shown in fig. 4. The whole microwave heating water propulsion system approximately occupies 8U of volume, wherein the propellant supply system occupies 2U, the microwave heating system occupies 2U, the thrust chamber system occupies 2U, and the final power supply system approximately occupies 1.5U.
In one illustrative embodiment, an idealized parameter calculation is performed on the system, without regard to various losses due to drag, heat transfer, etc. The high pressure superheated steam is considered as ideal gas, satisfying the ideal gas equation pv= RgT. The following calculations are all performed under the assumption that the single water consumption m=20g, and the temperature of the liquid water in the flexible water storage bladder is t0=300k.
Firstly, the total area of the solar sailboards is not particularly limited, and a group of sailboards is generally allowed to be folded for 2-5 times, and the folded area is equivalent to the area of one side of a satellite.
Assume the total area is: s=2×2×3×0.06=0.72 square meters, the solar radiation power at a track 600km from the earth surface is approximately 1400 w/square meter, assuming that the conversion efficiency of the solar sailboard is 25%, the power supply of the solar sailboard can be obtained as follows: w=s×0.25×1400=252W.
The lithium ion battery BPI-18650-3S16P-11.1V. A power of about 500w, an alternating voltage of 11.1v may be provided when the propulsion system is in operation.
The total efficiency of the microwave heating cavity is:
substituting parameters and calculating the total efficiency n 0 About 0.7.
And then by the formula
Suppose C v =1.57 kj/(kg x K), t=1000k gives a heating time of t=62.8s.
The microwave heating cavity is the microwave resonant cavity. The microwave resonant cavity is designed by adopting a rectangular resonant cavity, and the design principle is that the designed resonant cavity has as many oscillation modes as possible, so that the resonant cavities can obtain a relatively uniform energy distribution state after being overlapped. The wavelength and the desired oscillation mode are determined first and then the size of such rectangular resonant cavity is calculated.
In the examples, a 2450MHz magnetron was used, having a wavelength of 12.24cm and a spectral range Δf=10 MHz. Assuming that the side lengths of the resonant cavity along the x, y and z directions are a, b, l and m, n and p are the standing wave numbers of electromagnetic waves in the length-width-height directions of the resonant cavity, respectively, various possible combinations of (m, n and p) represent the distribution of the electromagnetic field.
The speed of light is set to c, represented by the formula:
the number of the modes meeting the calculation requirement and the corresponding resonant frequencies can be obtained through calculation, and the mode is selected most from the modes, so that the frequency interval is more uniform, and the combination of heating uniformity is improved; the resonant mode distribution should be relatively uniform with approximately the same resonant frequency on both sides of the center frequency; the mode numbers are preferably even and odd, and the field distribution is more uniform by using the complementation of the mode numbers, so that the proper resonant cavity size is obtained. And programming and calculating to obtain: within the framework of 1U, there are at most 3 different modes and parity complements. Finally, a rectangular cavity with a=8.63 cm, b=8.63 cm and c=8.72 cm was chosen, with a volume of approximately 650ml.
Secondly, the design of the shape of the spray pipe adopts a Laval spray pipe due to the requirement of the propeller on the performance of high specific impulse. The design of the nozzle mainly comprises a throat, namely the area A of the critical section cr Cross-sectional area A of the outlet 2 The length and the shape of the curve can obtain better acceleration benefit. Setting the section area A of the throat part according to the principle of controlling the volume of the spray pipe and increasing the jet speed of the spray pipe as much as possible cr ＝0.283mm 2 And the pressure of the outlet section, the area A of the outlet section being obtained by the pressure ratio of the outlet section to the critical section 2 About 20mm 2 . The inlet/outlet cross-sectional area was determined to be 18.01mm from the area of the critical cross-section that has been obtained by the ideal pinch ratio 2 . The length L1 of the contracted section is 3mm as found by the empirical formula. The length of the expansion part has no certain standard, if the expansion part is selected to be too short, the airflow expands too fast and is easy to leadDisturbance increases internal friction loss; if too long a choice is made, the friction losses of the air flow with the wall surface increase, which is also disadvantageous. From the designed tip angle ψ=10°
According to the formula:
the length L2 of the expansion section was determined to be 23.97mm. FIG. 5 is a nozzle shape result programmed by a shift algorithm. The speed designed by the method is 8% higher than that of a common spray pipe.
And finally, calculating the jet speed, the thrust generated by the single jet pipe and the obtained momentum. First, the ideal gas state equation pv= RgT. Setting a microwave heating system to heat the superheated steam to 1000K and 14.19MPa, wherein the specific volume of the superheated steam at the inlet of the spray pipeThe specific heat ratio was about 1.3, rg= 461.5J/(kg×k), and the critical pressure ratio was 0.546. According to the formula of adiabatic flow, we can obtain the following result by programming:
TABLE 1 jet pipe gas parameters
The flow obtained was 3.94g/s, the thrust of the single nozzle was 7.1N, the jet time was 5.07s, the momentum provided was 36.0N x s, and the specific impulse was 180s. Therefore, the setting of the parameters is reasonable, the jet speed is higher than that of the common cold air propulsion, the thrust is larger, and the satellite can be provided with larger specific impulse.
In one embodiment, as shown in fig. 6, there is provided a propulsion control method applied to the above-mentioned microwave-heated water propulsion system for propulsion control, the method including the steps of:
step S100: and acquiring an attitude adjustment instruction, and calculating the flow of the required water working medium and the preset temperature or the preset pressure of the high-pressure superheated steam according to the attitude adjustment instruction.
Step S200: and sending an electromagnetic valve opening command, and opening a second electromagnetic valve in the propellant supply subsystem through a control circuit, wherein water working medium in the propellant supply subsystem is injected into the microwave heating subsystem through the second electromagnetic valve.
Step S300: and when the filling amount of the water working medium reaches a preset value, closing the second electromagnetic valve.
Step S400: and starting microwave heating, and collecting the temperature and pressure of the microwave heating subsystem in real time.
Step S500: when the temperature of the high-pressure superheated steam reaches a preset temperature, a control circuit is used for opening a first electromagnetic valve in the microwave heating subsystem and a reversing valve of the thrust chamber subsystem, and the high-pressure superheated steam is injected into the scaling spray pipe after passing through the first electromagnetic valve and the reversing valve, so that the propelling task is completed.
In one embodiment, the method further comprises: according to the received temperature of the water working medium in the flexible water storage bag in the propellant supply subsystem, when the temperature reaches a preset value for starting heating, a command is sent to the heating controller, and the heating resistor is controlled to heat the water working medium.
It should be understood that, although the steps in the flowchart of fig. 6 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not strictly limited to the order of execution unless explicitly recited herein, and the steps may be executed in other orders. Moreover, at least some of the steps in fig. 6 may include multiple sub-steps or stages that are not necessarily performed at the same time, but may be performed at different times, nor do the order in which the sub-steps or stages are performed necessarily performed in sequence, but may be performed alternately or alternately with at least a portion of the sub-steps or stages of other steps or other steps.
The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The above examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.
Claims (10)
1. A microwave-heated water propulsion system, the system comprising: a propellant supply subsystem, a microwave heating subsystem, a thrust chamber subsystem, a temperature regulation subsystem, a power supply subsystem and a control subsystem;
the propellant supply subsystem is used for storing liquid water working media and controlling the propellant supply subsystem to load a preset amount of water working media into the microwave heating subsystem through the control subsystem according to preset requirements;
the microwave heating subsystem is used for converting electric energy into microwaves, heating water working media loaded from the propellant supply subsystem by utilizing the microwaves, and sending high-pressure superheated steam into the thrust chamber subsystem when the temperature or the pressure reaches a preset value;
the thrust chamber subsystem is used for accelerating the injected high-pressure superheated steam to a preset speed and then spraying out to complete a propelling task;
the temperature regulating subsystem is used for detecting the temperature and the pressure in the propellant supply subsystem and transmitting the temperature and the pressure to the control subsystem, and controlling the heating resistor according to the instruction of the control subsystem so as to enable the water working medium to be kept as a liquid water working medium with a certain temperature in a space low-temperature and low-pressure environment;
the control subsystem is used for controlling and feedback-regulating the system according to signals fed back by the preset requirements, the propellant supply subsystem, the temperature regulation subsystem and the microwave heating subsystem; when the water working medium is required to be loaded to the microwave heating subsystem, the control subsystem sends out an instruction, the propellant supply subsystem is controlled to add the water working medium to the microwave heating subsystem, when the added water working medium reaches a preset value, the control subsystem sends out an instruction again, the propellant supply subsystem is controlled to stop filling, and then the control subsystem controls the microwave heating subsystem to start heating the water working medium;
the power subsystem is used for providing power for the propellant supply subsystem, the microwave heating subsystem, the thrust chamber subsystem, the temperature regulation subsystem and the control subsystem.
2. The system of claim 1, wherein the microwave heating subsystem comprises: the microwave heating device comprises a microwave heating cavity, a transformer, a magnetron, a waveguide, a first temperature sensor, a first pressure sensor and a first electromagnetic valve;
the microwave heating cavity is made of a heat insulation material and is used for heating the hydraulic medium loaded by the propellant supply subsystem;
the first temperature sensor and the first pressure sensor are respectively used for detecting the temperature and the pressure in the microwave heating cavity and sending the detected temperature and pressure values in the heating cavity to the control subsystem;
the first electromagnetic valve is used for controlling the high-pressure superheated steam to be sprayed into the thrust chamber subsystem or stopped; the on-off control of the first electromagnetic valve is that the control subsystem compares the acquired internal temperature of the heating cavity or internal pressure of the heating cavity with a preset value, and when the internal temperature of the heating cavity or the internal pressure of the heating cavity reaches the preset value, the first electromagnetic valve is opened, and high-pressure superheated steam is sprayed into the thrust chamber subsystem; otherwise, closing the first electromagnetic valve;
the voltage provided by the power subsystem is increased through a transformer, the high voltage generates microwaves through a magnetron, and the microwaves are transmitted to a microwave heating cavity through a waveguide; the microwave heating cavity heats the loaded hydraulic medium, the first temperature sensor and the first pressure sensor transmit the detected temperature and pressure inside the microwave heating cavity to the control subsystem, and when the preset condition is met, the control subsystem sends a command to open the first electromagnetic valve, and high-pressure superheated steam is sent into the thrust chamber; when the predetermined condition is not satisfied, the control subsystem issues an instruction to close the solenoid valve.
3. The system of claim 1, wherein the propellant supply subsystem comprises a pressurized canister, a flexible water reservoir, and a second solenoid valve;
the pressurizing tank is made of heat insulation materials and is used for storing high-pressure gas for system pre-pressurization; the flexible water storage bag is used for storing liquid hydraulic medium; the second electromagnetic valve is used for controlling the water working medium to flow into the microwave heating subsystem;
when water working media need to be loaded to the microwave heating subsystem, the control subsystem sends out instructions to control the second electromagnetic valve to be opened, and high-pressure gas in the pressurizing tank extrudes the water working media in the flexible water storage bag to flow into the microwave heating subsystem through the second electromagnetic valve; when the water passing through the electromagnetic valve reaches a preset value, the control subsystem sends out an instruction again to control the second electromagnetic valve to be closed.
4. The system of claim 3, wherein the temperature conditioning subsystem comprises a second temperature sensor, a heating controller, and a heating resistor;
the second temperature sensor and the heating resistor are both arranged in the flexible water storage bag, and the second temperature sensor is used for measuring the temperature of the water working medium in the flexible water storage bag and transmitting the detected value to the control subsystem;
the heating controller is used for controlling the heating resistor to heat the water working medium in the flexible water storage bag according to the instruction sent by the control subsystem.
5. The system of claim 1, wherein the thrust chamber subsystem comprises a convergent-divergent nozzle and a diverter valve,
the control end of the reversing valve is connected with the control subsystem and is used for controlling high-pressure superheated steam flowing out of the microwave heating subsystem to flow into the scaling spray pipe;
the scaling spray pipe consists of a contraction section of the front half section of the spray pipe, a throat part in the middle and an expansion spray pipe of the tail section.
6. The system of claim 5, wherein the convergent-divergent nozzle is a laval nozzle.
7. The system of claim 1, wherein the power subsystem comprises a solar windsurfing board and a battery; the storage battery is used for storing electric energy from the solar sailboard.
8. The system of any one of claims 1-7, wherein the control subsystem comprises an on-board computer, a control circuit, and a signal acquisition card; the control circuit and the signal acquisition card are connected with the satellite-borne computer;
the signal acquisition card is connected with the first temperature sensor, the first pressure sensor and the second temperature sensor; the control circuit is connected with the first electromagnetic valve, the second electromagnetic valve, the reversing valve, the magnetron and the heating controller.
9. A propulsion control method applied to the microwave-heated water propulsion system of claim 8 for propulsion control, the method comprising:
acquiring an attitude adjustment instruction, and calculating the flow of a required water working medium and the preset temperature or preset pressure of high-pressure superheated steam according to the attitude adjustment instruction;
a solenoid valve opening instruction is sent out, a second solenoid valve in the propellant supply subsystem is opened through a control circuit, and water working medium in the propellant supply subsystem is injected into the microwave heating subsystem through the second solenoid valve;
when the filling amount of the water working medium reaches a preset value, closing the second electromagnetic valve;
starting microwave heating, and collecting the temperature and pressure of a microwave heating subsystem in real time;
when the temperature of the high-pressure superheated steam reaches a preset temperature, a control circuit is used for opening a first electromagnetic valve in the microwave heating subsystem and a reversing valve of the thrust chamber subsystem, and the high-pressure superheated steam is injected into the scaling spray pipe after passing through the first electromagnetic valve and the reversing valve to complete the propelling task.
10. The method according to claim 9, wherein the method further comprises:
according to the received temperature of the water working medium in the flexible water storage bag in the propellant supply subsystem, when the temperature reaches a preset value for starting heating, a command is sent to the heating controller, and the heating resistor is controlled to heat the water working medium.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111355846.3A CN114084378B (en) | 2021-11-16 | 2021-11-16 | Microwave heating water propulsion system and propulsion control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111355846.3A CN114084378B (en) | 2021-11-16 | 2021-11-16 | Microwave heating water propulsion system and propulsion control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114084378A CN114084378A (en) | 2022-02-25 |
| CN114084378B true CN114084378B (en) | 2023-09-26 |
Family
ID=80300955
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111355846.3A Active CN114084378B (en) | 2021-11-16 | 2021-11-16 | Microwave heating water propulsion system and propulsion control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114084378B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114810427B (en) * | 2022-03-31 | 2023-06-16 | 北京控制工程研究所 | High-energy green liquid propeller ignition device and method for microwave excited plasma |
| CN115750137A (en) * | 2022-12-12 | 2023-03-07 | 厦门大学 | Water propeller and satellite used in space environment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6301876B1 (en) * | 1998-09-23 | 2001-10-16 | Mainstream Engineering Corporation | Noble gas storage and flow control system for ion propulsion |
| US7247953B1 (en) * | 2006-07-06 | 2007-07-24 | Stanley Schmulewitz | Solar energy conversion and transmission system |
| US9242747B1 (en) * | 2011-11-18 | 2016-01-26 | Cu Aerospace, Llc | Space thruster using robust microcavity discharge and advanced propellants |
| CN107975462A (en) * | 2016-10-21 | 2018-05-01 | 南京理工大学 | Electric heating microthruster |
| CN110469474A (en) * | 2019-09-04 | 2019-11-19 | 北京航空航天大学 | A kind of radio frequency plasma source for microsatellite |
| CN111502940A (en) * | 2020-04-29 | 2020-08-07 | 武汉大学 | Microwave air plasma water vapor injection pushing device |
| CN113404621A (en) * | 2021-06-19 | 2021-09-17 | 西北工业大学 | Solid-liquid mixed engine and method for Mars ascending aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017085746A1 (en) * | 2015-11-18 | 2017-05-26 | Jsw Steel Limited | A microwave electrothermal thruster adapted for in-space electrothermal propulsion |
| US10910198B2 (en) * | 2019-03-12 | 2021-02-02 | Momentus Inc. | Spacecraft propulsion devices and systems with microwave excitation |
-
2021
- 2021-11-16 CN CN202111355846.3A patent/CN114084378B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6301876B1 (en) * | 1998-09-23 | 2001-10-16 | Mainstream Engineering Corporation | Noble gas storage and flow control system for ion propulsion |
| US7247953B1 (en) * | 2006-07-06 | 2007-07-24 | Stanley Schmulewitz | Solar energy conversion and transmission system |
| US9242747B1 (en) * | 2011-11-18 | 2016-01-26 | Cu Aerospace, Llc | Space thruster using robust microcavity discharge and advanced propellants |
| CN107975462A (en) * | 2016-10-21 | 2018-05-01 | 南京理工大学 | Electric heating microthruster |
| CN110469474A (en) * | 2019-09-04 | 2019-11-19 | 北京航空航天大学 | A kind of radio frequency plasma source for microsatellite |
| CN111502940A (en) * | 2020-04-29 | 2020-08-07 | 武汉大学 | Microwave air plasma water vapor injection pushing device |
| CN113404621A (en) * | 2021-06-19 | 2021-09-17 | 西北工业大学 | Solid-liquid mixed engine and method for Mars ascending aircraft |
Non-Patent Citations (1)
| Title |
|---|
| AQT-D: Demonstration of the Water Resistojet Propulsion System by the ISS-Deployed CubeSat.33rd Annual AIAA/USU Conference on Small Satellites.2019,1-5. * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114084378A (en) | 2022-02-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114084378B (en) | Microwave heating water propulsion system and propulsion control method | |
| Bao et al. | Dynamic characteristics of combustion mode transitions in a strut-based scramjet combustor model | |
| US8381528B2 (en) | Ramjet superheater | |
| Dıaz | An overview of the VASIMR engine: High power space propulsion with RF plasma generation and heating | |
| Gebhart et al. | Optimization of fusion pellet launch velocity in an electrothermal mass accelerator | |
| Gao et al. | A review of the vaporizing liquid microthruster technology | |
| Tani et al. | Aerodynamic characteristics of the combined cycle engine in an ejector jet mode | |
| Knowlen et al. | Ram accelerator performance modeling | |
| Mulki et al. | Study of Microwave Electrothermal Propulsion System | |
| Freitas et al. | Experimental and analytical study of the cold flow inside a ramjet test engine | |
| Blinov et al. | Gas dynamic model of electrothermal thrusters of small spacecraft and possibility of applying microwave heating of a working | |
| Yildiz et al. | Global Energy Transfer Model of a Microwave Electrothermal Thruster Operating With Helium Propellant at 2.45-GHz Frequency | |
| Biswas et al. | Use of ammonia as a propellant in a 17.8-GHz microwave electrothermal thruster | |
| Su et al. | The dynamic model of the high-thrust orbital maneuvering engine with storable propellant | |
| Sun et al. | Design, development, and performance of an ammonia self-managed vaporization propulsion system for micro-nano satellites | |
| Abaimov et al. | A 17.8-GHz microwave elec-trothermal thruster for CubeSats and small satellites | |
| Benford et al. | Propulsion of small launch vehicles using high-power millimeter waves | |
| Keefer et al. | A re-examination of the laser-supported combustion wave | |
| Bidabadi et al. | A novel analytical model of a MEMS vaporizing liquid micro thruster | |
| Sun et al. | Propulsion Technology | |
| CN113864062B (en) | Solid ramjet wall surface cooling system and method with ejector | |
| Squire et al. | Investigation of a light gas helicon plasma source for the VASIMR space propulsion system | |
| Katsurayama et al. | Analitical Study on Flight Performance of an Air-Breathing RP Laser Launcher | |
| Petro et al. | A flight demonstration of plasma rocket propulsion | |
| Böhrk et al. | Flexible piloted Mars missions using the TIHTUS engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |