CN112078831B - Mu N thruster based on flowmeter and use method - Google Patents
Mu N thruster based on flowmeter and use method Download PDFInfo
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- 229920002432 poly(vinyl methyl ether) polymer Polymers 0.000 claims 1
- 230000008569 process Effects 0.000 abstract description 7
- 239000007789 gas Substances 0.000 description 95
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 23
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- 229910052757 nitrogen Inorganic materials 0.000 description 9
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- 239000001273 butane Substances 0.000 description 2
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- IJDNQMDRQITEOD-UHFFFAOYSA-N n-butane Chemical compound CCCC IJDNQMDRQITEOD-UHFFFAOYSA-N 0.000 description 2
- OFBQJSOFQDEBGM-UHFFFAOYSA-N n-pentane Natural products CCCCC OFBQJSOFQDEBGM-UHFFFAOYSA-N 0.000 description 2
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- 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
- B64G1/244—Spacecraft control systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The application relates to the technical field of micro thrusters, in particular to a mu N thruster based on a flowmeter and a use method, wherein the mu N thruster based on the flowmeter comprises: gas cylinder, flowmeter, buffer chamber and controller, wherein: the gas cylinder is connected with the flowmeter, and the flowmeter is connected with the buffer chamber; the controller is respectively and electrically connected with the gas cylinder, the flowmeter and the buffer chamber and is respectively used for controlling the pressure in the gas cylinder, controlling the flowmeter to set the flow and controlling the temperature of the buffer chamber; the end of the buffer chamber is provided with a nozzle for injecting gas. The micro-bovine-level thrust adjusting device is simple in structure and convenient to use, can provide accurate adjustable micro-bovine-level thrust, can not vibrate in the process of adjusting and setting flow, can not enable output flow values to fluctuate, provides a stable working environment for gas flow, ensures stability of the thrust, can continuously adjust the flow with high precision, and greatly prolongs the service life of the thruster.
Description
Technical Field
The application relates to the technical field of micro thrusters, in particular to a mu N thruster based on a flowmeter and a using method.
Background
The micro thruster has wide application prospect in the fields of attitude adjustment, orbit determination and the like of microsatellites. The micro-thruster can generally provide thrust of mu N level, and can be divided into two main categories according to the working principle of a micro-propulsion system: the electronic type thruster uses the accelerating motion of plasma gas in electromagnetic field as power, and the thrust range of the electronic type thruster is above N level.
Most of the existing gas thrusters adopt cold air thrusters, such as SNAP-1 satellites developed by SSTL company are equipped with the cold air thrusters for the first time, butane is adopted as propulsion gas, the generated thrust range is 45 mN-120 mN, and the total impulse is up to 22.3Ns. But butane is adopted as the propulsion gas, so that the cost is high, the size of the existing thruster is closely related to the internal air pressure, vibration can be generated in the pressure regulating process, the output pressure continuously fluctuates in a central value area, the stability is not enough, and the generated thrust is not accurate enough.
Disclosure of Invention
The utility model provides a mu N thruster based on flowmeter and a use method thereof, which aims to solve the problems that the thruster in the related art generates unstable thrust and cannot be accurately adjusted.
To achieve the above object, the present application provides a flow meter-based μn thruster, including: gas cylinder, flowmeter, buffer chamber and controller, wherein: the gas cylinder is connected with the flowmeter, and the flowmeter is connected with the buffer chamber; the controller is respectively and electrically connected with the gas cylinder, the flowmeter and the buffer chamber and is respectively used for controlling the pressure in the gas cylinder, controlling the flowmeter to set the flow and controlling the temperature of the buffer chamber; the end of the buffer chamber is provided with a nozzle for injecting gas.
Further, a self-locking valve and a pressure reducing valve are sequentially connected between the gas cylinder and the flowmeter, and the controller is connected with the self-locking valve through a solenoid valve driving circuit.
Further, the controller is connected with the gas cylinder through a pressure control system.
Further, the controller is connected with the buffer chamber through a temperature control system.
Further, a heating wire is arranged above the buffer chamber and is connected with the controller through a heating system.
Further, the pressure of the gas is regulated to be 0.3-0.5MPa by the controller, the self-locking valve and the pressure reducing valve.
The application also provides a method for using the mu N thruster based on the flowmeter, which comprises the following steps: (1) The controller receives a ground setting instruction, calculates required thrust data and obtains an initially set flow value Qset and a temperature value Tset; (2) The adjusting controller is used for setting the flow of the flowmeter according to the initially set flow value Qset and adjusting the temperature of the buffer chamber through the temperature control system according to the initially set temperature value Tset; (3) After receiving a starting instruction, the controller opens the self-locking valve through the electromagnetic valve driving circuit to enable the gas in the gas cylinder to flow into the flowmeter; (4) The pressure of the gas entering the flowmeter is kept between 0.3 and 0.5MPa through the adjustment of the pressure reducing valve and the pressure control system; (5) The flow rate of the gas entering the buffer chamber is controlled by the flow meter, so that the flow rate of the gas entering the buffer chamber can be always controlled within the range of the initially set flow rate value Qset; (6) After the gas enters the buffer chamber, the controller adjusts the heating wire to heat the buffer chamber through the heating system, so that the temperature of the buffer chamber is always controlled within the range of an initial set temperature value Tset; (7) The gas molecules move thermally in the buffer chamber and exchange heat with the wall of the buffer chamber, so that the kinetic energy of the gas molecules is improved, and the gas molecules are ejected from the nozzle at the end part of the buffer chamber to obtain the required thrust.
The mu N thruster based on the flowmeter and the use method have the following beneficial effects:
the mu N thruster based on the flowmeter provided by the application adopts a conventional gas molecular thermal motion mode to generate thrust, is simple in structure and convenient to use, can provide accurate and adjustable micro-cow-level thrust, reduces the use cost, ensures that the pressure is stably maintained between 0.3 and 0.5MPa in the gas flowing process through the regulating controller, is irrelevant to the inlet pressure in the gas flow output in the working range, does not generate vibration or fluctuation in the output flow value in the process of regulating the set flow, provides stable working environment for gas flow, ensures the stability of the thrust, ensures that the generated thrust is accurately and continuously regulated by setting the flow of the gas entering a buffer chamber through the flowmeter, does not need redundant easy-to-block parts such as plug holes, and greatly prolongs the service life of the thruster.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the application and to provide a further understanding of the application with regard to the other features, objects and advantages of the application. The drawings of the illustrative embodiments of the present application and their descriptions are for the purpose of illustrating the present application and are not to be construed as unduly limiting the present application. In the drawings:
FIG. 1 is a schematic diagram of a flow meter-based μN thruster provided in accordance with an embodiment of the present application;
in the figure: the device comprises a 1-gas cylinder, a 2-flowmeter, a 3-buffer chamber, a 4-controller, a 41-pressure control module, a 42-pressure zeroing module, a 43-temperature control module, a 44-temperature zeroing module, a 45-A/D converter, a 46-PID control module, a 47-electromagnetic valve driving circuit, a 48-heating driving circuit, a 5-nozzle, a 6-self-locking valve, a 7-pressure reducing valve and an 8-heating wire.
Description of the embodiments
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
As shown in fig. 1, a flow meter-based μn thruster provided in an embodiment of the present application includes: gas cylinder 1, flowmeter 2, buffer chamber 3 and controller 4, wherein: the gas cylinder 1 is connected with the flowmeter 2, and the flowmeter 2 is connected with the buffer chamber 3; the controller 4 is respectively and electrically connected with the gas cylinder 1, the flowmeter 2 and the buffer chamber 3 and is respectively used for controlling the pressure in the gas cylinder 1, controlling the flowmeter 2 to set the flow and controlling the temperature of the buffer chamber 3; the end of the buffer chamber 3 is provided with a spout 5 for injecting gas.
Specifically, the existing thruster technology generally adopts a pressure reducing valve to regulate pressure for output, then adopts a plug hole control module to control micro-flow, but can generate vibration in the pressure regulating process, so that the application range is greatly limited, and adopts the plug hole control module to control micro-flow. The mu N thruster provided by the embodiment of the invention adopts the flowmeter to regulate and control the gas flow, the required pressure range of the flowmeter is wider, the output flow can not vibrate or fluctuate in the process of regulating the output flow, and the accuracy and the stability of the thrust are greatly improved. The embodiment of the invention mainly adopts a mode of thermal movement of conventional gas molecules to generate thrust, and continuously and highly precisely adjusts the output flow of the gas by controlling the pressure and the temperature of the conventional gas, so that the conventional gas molecules perform thermal movement, and stable thrust is generated by spraying. The gas cylinder 1 is mainly used for storing gas, generated gas generating thrust is filled into the gas cylinder 1 for storage, and the gas in the subsequent gas cylinder 1 continuously flows into the buffer chamber 3. The flow meter 2 is mainly used for setting the flow rate of the gas according to the required thrust, controlling the flow rate of the gas entering the buffer chamber 3, keeping the flow rate of the gas entering the buffer chamber 3 within an initial set Qset range, providing stable gas for the buffer chamber 3, and calculating the ventilation time and the volume of the gas through the flow meter 2. The buffer chamber 3 is mainly used for the accumulation of gas, which undergoes thermal movement in the buffer chamber 3 and is then ejected through the nozzle 5 and generates the required thrust. The controller 4 is mainly used for integrated control, is respectively connected with the gas cylinder 1, the flowmeter 2 and the buffer chamber 3 through a control circuit, and is used for controlling the working environment of gas in the gas flowing process. The nozzle 5 is elongated, so that irregular collision of gas molecules can be reduced, and gas can be rapidly ejected. In the embodiment of the invention, the gas cylinder 1 is preferably a stainless steel gas cylinder, the gas stored in the gas cylinder 1 is preferably nitrogen, the flow meter 2 preferably controls the flow of the gas by adopting a capillary heat transfer temperature difference heat method, and the nozzle 5 is preferably a nozzle with an slender and straight structure.
Further, a self-locking valve 6 and a pressure reducing valve 7 are sequentially connected between the gas cylinder 1 and the flowmeter 2, and the controller 4 is connected with the self-locking valve 6 through a solenoid valve driving circuit 47. Because the flowmeter 2 and the self-locking valve 6 have the characteristic of slow air leakage, under the condition of no work, the self-locking valve 6 is controlled to close an air source to prevent air leakage, and the self-locking valve 6 has the characteristic of magnetic retention, can operate without power consumption under the stable state of a switch, and greatly reduces the power consumption. In the embodiment of the invention, the electromagnetic valve driving circuit 47 is a conventional valve control circuit, the self-locking valve 6 is a high-pressure self-locking valve, the controller 4 is connected with the self-locking valve 6 through the electromagnetic valve driving circuit 47, and the opening and closing of the gas circulation in the gas cylinder 1 can be realized through the self-locking valve 6. The pressure reducing valve 7 is arranged on the flow pipeline between the self-locking valve 6 and the flowmeter 2 and is used for reducing pressure of high-pressure gas flowing out of the gas cylinder 1, and adjusting the pressure range of the gas entering the flowmeter 2, so that the gas can stably enter the flowmeter 2.
Further, the controller 4 is connected to the gas cylinder 1 through a pressure control system. The controller 4 controls the pressure of the gas in the gas cylinder 1 through a pressure control system, the pressure control system mainly comprises a pressure control module 41, a pressure zeroing module 42 and an A/D converter 45, the controller 4 controls the pressure of the gas in the gas cylinder 1 through the pressure control module 41, the pressure zeroing module 42 controls the pressure gauge to be zeroed, and the pressure signal and the digital control signal are converted through the A/D converter 45.
Further, the controller 4 is connected to the buffer chamber 3 through a temperature control system. The controller 4 controls the temperature in the buffer chamber 3 through a temperature control system, the temperature control system mainly comprises a temperature control module 43, a temperature zeroing module 44 and an A/D converter 45, the controller 4 controls the temperature in the buffer chamber 3 through the temperature control module 43, the temperature zeroing module 44 controls the temperature meter to be zeroed, and the temperature signal and the digital control signal are converted through the A/D converter 45.
Further, a heating wire 8 is arranged above the buffer chamber 3, and the heating wire 8 is connected with the controller 4 through a heating system. The controller 4 is internally provided with a PID control module 46, and the PID control module 46 is connected with the heating wire 8 through a heating driving circuit 48 and is used for performing closed-loop PID control on the temperature in the buffer chamber 3 so as to enable the temperature in the buffer chamber 3 to be in a constant-temperature environment. In the working process, as the gas continuously enters the buffer chamber 3 to generate heat exchange, the temperature in the buffer chamber 3 can be changed, the controller 4 can obtain the temperature in the buffer chamber 3 in real time through a temperature control system, compares the temperature with an initial set temperature value Tset, then performs error calculation, and according to the error calculation result, the PID control module 46 in the controller 4 adjusts the heating power of the heating wire 8 through the heating driving circuit 48, so that the temperature in the buffer chamber 3 is always kept within the set temperature value Tset.
Further, the pressure of the gas is regulated to be 0.3-0.5MPa by the controller 4 through the gas cylinder 1, the self-locking valve 6 and the pressure reducing valve 7. In the process of gas flow ejection, the pressure of the gas is maintained between 0.3 and 0.5MPa, so that the gas can be ejected stably.
The application also provides a method for using the mu N thruster based on the flowmeter, which comprises the following steps: (1) The controller 4 receives a ground setting instruction, calculates required thrust data and obtains an initially set flow value Qset and a temperature value Tset; (2) An adjustment controller 4 for setting the flow rate of the flowmeter according to the initially set flow rate value Qset and adjusting the temperature of the buffer chamber 3 by the temperature control system according to the initially set temperature value Tset; (3) After receiving the starting-up instruction, the controller 4 opens the self-locking valve 6 through the electromagnetic valve driving circuit 47, so that the gas in the gas cylinder 1 flows into the flowmeter 2; (4) The pressure of the gas entering the flowmeter is kept between 0.3 and 0.5MPa through the adjustment of the pressure reducing valve 7 and the pressure control system; (5) The flow rate of the gas entering is regulated and controlled through the flowmeter 2, so that the flow rate of the gas entering the buffer chamber 3 is always controlled within the range of the flow rate value Qset which is originally set, and the ventilation time and the volume of the gas are set and calculated; (6) After the gas enters the buffer chamber 3, the controller 4 adjusts the heating wire 8 to heat the buffer chamber 3 through the heating system, so that the temperature of the buffer chamber 3 is always controlled within the range of an initial set temperature value Tset, and the temperature converted into Kelvin is set; (7) The gas molecules thermally move in the buffer chamber 3 and exchange heat with the wall of the buffer chamber 3, the kinetic energy of the gas molecules is improved, and the gas molecules are ejected from the nozzle 5 at the end part of the buffer chamber 3 to obtain a required thrust, wherein the thrust can be calculated according to the formula f=p×v×m×s/(r×tj×t), wherein P represents atmospheric pressure, V represents the volume of gas under 1mL, M represents the molar mass of gas, S represents the root mean square velocity of gas, R represents the molar mass of gas, tj represents kelvin temperature, and t represents time.
The following specifically describes an embodiment of the present invention, taking nitrogen gas to obtain a thrust of 1. Mu.N as an example:
(1) The known gas atmospheric pressure p=101325 Pa, the molar mass m=28×10 of nitrogen -3 g/mol, molar gas constant r= 8.314J/(mol·k), controller 4 receives a ground setting instruction, and obtains an initially set flow value 1/60SCCM and a temperature value of 20 ℃ by calculating thrust data f=1μn and formula f=pvms/(r×tj×t);
(2) The controller 4 is regulated, the initial flow of the flowmeter 2 is set to be 1/60SCCM, and the initial temperature of the buffer chamber 3 is set to be 20 ℃;
(3) Opening the self-locking valve 6 to enable the nitrogen in the gas cylinder 1 to flow into the flowmeter 2;
(4) The pressure of the nitrogen entering the flowmeter 2 is kept between 0.3 and 0.5MPa through the adjustment of the pressure reducing valve 7 and the pressure control system;
(5) The flow rate of the nitrogen gas entering the buffer chamber 3 is always kept at 1/60SCCM by regulating and controlling the flow rate of the nitrogen gas entering the buffer chamber 3 through the flowmeter 2, and the ventilation time t=60 s of the nitrogen gas and the volume v=1×10 of the nitrogen gas are set -7 L；
(6) After nitrogen enters the buffer chamber 3, the controller 4 adjusts the heating wire 8 to heat the buffer chamber 3 through the heating system, so that the temperature of the buffer chamber 3 is always kept at 20 ℃, and the temperature converted into Kelvin temperature Tj=290K is set;
(7) The nitrogen molecules thermally move in the buffer chamber 3 and exchange heat with the wall of the buffer chamber 3, the kinetic energy of the nitrogen molecules is improved, the nitrogen molecules are ejected from the nozzle 5 at the end part of the buffer chamber 3 to obtain the required thrust, and the data are substituted into the formula according to the formula f=p×v×m×s/(r×tj×t):
therefore, the thrust generated by 1ml of nitrogen within 1min is calculated to be 1 mu N, and the thrust value is obtained to be 1 mu N, so by adopting the mu N thruster based on the flowmeter and the application method provided by the embodiment of the invention, through controlling the molecular flow and the temperature of gas and combining the law of conservation of energy, the thruster can generate tiny micro-bovine-level thrust which can be accurately adjusted, and the micro-bovine-level thruster has wide application prospect.
The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the same, but rather, various modifications and variations may be made by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.
Claims (4)
1. A flow meter based μn thruster comprising: gas cylinder, flowmeter, buffer chamber and controller, wherein:
the gas cylinder is connected with the flowmeter, and the flowmeter is connected with the buffer chamber;
the controller is respectively and electrically connected with the gas cylinder, the flowmeter and the buffer chamber and is respectively used for controlling the pressure in the gas cylinder, controlling the flowmeter to set the flow and controlling the temperature of the buffer chamber;
the flowmeter is used for setting the flow rate of the gas according to the required thrust, controlling the flow rate of the gas entering the buffer chamber, keeping the flow rate of the gas entering the buffer chamber within an initial set Qset range, providing stable gas for the buffer chamber, and calculating the ventilation time and the volume of the gas through the flowmeter;
the end part of the buffer chamber is provided with a nozzle for jetting gas;
the controller is connected with the gas cylinder through a pressure control system, the controller controls the pressure of the gas in the gas cylinder through the pressure control system, the pressure control system comprises a pressure control module, a pressure zeroing module and an A/D converter, the controller controls the pressure of the gas in the gas cylinder through the pressure control module, controls and adjusts the pressure gauge to return to zero through the pressure zeroing module, and converts a pressure signal and a digital control signal through the A/D converter;
the controller is connected with the buffer chamber through a temperature control system, the temperature in the buffer chamber is controlled by the controller through the temperature control system, the temperature control system comprises a temperature control module, a temperature zeroing module and an A/D converter, the temperature in the buffer chamber is controlled by the controller through the temperature control module, the temperature meter is controlled and adjusted to be zero through the temperature zeroing module, and the temperature signal and the digital control signal are converted through the A/D converter;
a heating wire is arranged above the buffer chamber and is connected with the controller through a heating system;
the controller is internally provided with a PID control module, the PID control module is connected with the heating wire through a heating driving circuit and used for carrying out closed-loop PID control on the temperature in the buffer chamber, the controller can obtain the temperature in the buffer chamber in real time through a temperature control system and compare with an initial set temperature value Tset, then error calculation is carried out, and according to an error calculation result, the PID control module in the controller adjusts the heating power of the heating wire through the heating driving circuit, so that the temperature in the buffer chamber is always kept in the set temperature value Tset range.
2. The flowmeter-based μn thruster of claim 1, wherein a latching valve and a pressure reducing valve are connected in sequence between the gas cylinder and the flowmeter, and the controller is connected with the latching valve through a solenoid valve driving circuit.
3. The flowmeter-based μn thruster of claim 2, wherein the pressure of the gas is adjusted by the controller to be between 0.3 MPa and 0.5MPa by the gas cylinder, the latching valve, and the pressure reducing valve.
4. A method of using the flowmeter-based μn thruster of any one of claims 1-3, comprising the steps of:
(1) The controller receives a ground setting instruction, and calculates thrust data F and a formula F=PVMs/(RTj) t to obtain an initial set flow value Qset and a temperature value Tset, wherein P represents atmospheric pressure, V represents a gas volume under 1mL, M represents gas molar mass, S represents gas root mean square speed, R represents gas molar mass, tj represents Kelvin temperature, and t represents time;
(2) The adjusting controller is used for setting the flow of the flowmeter according to the initially set flow value Qset and adjusting the temperature of the buffer chamber through the temperature control system according to the initially set temperature value Tset;
(3) After receiving a starting instruction, the controller opens the self-locking valve through the electromagnetic valve driving circuit to enable the gas in the gas cylinder to flow into the flowmeter;
(4) The pressure of the gas entering the flowmeter is kept between 0.3 and 0.5MPa through the adjustment of the pressure reducing valve and the pressure control system;
(5) The flow rate of the gas entering the buffer chamber is controlled by the flow meter, so that the flow rate of the gas entering the buffer chamber can be always controlled within the range of the initially set flow rate value Qset;
(6) After the gas enters the buffer chamber, the controller adjusts the heating wire to heat the buffer chamber through the heating system, so that the temperature of the buffer chamber is always controlled within the range of an initial set temperature value Tset;
(7) The gas molecules move thermally in the buffer chamber and exchange heat with the wall of the buffer chamber, so that the kinetic energy of the gas molecules is improved, and the gas molecules are ejected from the nozzle at the end part of the buffer chamber to obtain the required thrust.
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