CN115946876A - Running method of micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster - Google Patents
Running method of micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster Download PDFInfo
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- 239000010437 gem Substances 0.000 claims abstract description 52
- 229910001751 gemstone Inorganic materials 0.000 claims abstract description 52
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- 238000007789 sealing Methods 0.000 claims abstract description 41
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Abstract
The invention provides an operation method of a micro-Newton-level gem-based double-gas-volume variable-thrust closed-loop cold air thruster.A working medium gas inlet, a primary gas volume, a connecting channel, a secondary gas volume and a working medium gas outlet are sequentially arranged in a soft magnetic material shell, and the working medium gas outlet is provided with a Laval nozzle main body; the Laval nozzle body is provided with a valve assembly at a working medium inlet of the narrow throat, the valve assembly comprises a valve and a restoring elastic element, the restoring force of the restoring elastic element controls the working medium gas inlet to be communicated or sealed, and the restoring force of the restoring elastic element synchronously controls the valve assembly to be communicated or sealed with the connecting channel and the Laval nozzle body; the outer wall of the soft magnetic material shell is provided with a driving electromagnetic coil driving valve assembly to generate movement in different directions, and meanwhile, the sealing force of the valve is controlled by the elastic force of the recovery elastic element. The running method of the micro-Newton-grade precious stone-based double-0 gas-capacity variable-thrust closed-loop cold air thruster realizes continuous precision control and continuous stable output of thrust.
Description
The application is a divisional application of the invention patent application with the application number of 2022103826198;
application date of the original application: 2022-04-13;
application No. of the original application: 2022103826198;
the name of the original application: a micro-Newton grade gem-based double-air-volume variable-thrust closed-loop cold air thruster and an operation method thereof.
Technical Field
The invention relates to the field of thrusters in precision machinery and aerospace propulsion technologies, in particular to an operation method of a micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster.
Background
The propeller is an important power device in the aerospace technology, and when the propeller works, the working substance is sprayed out of the spray pipe at a high speed, and the back flush of the propeller and a carrier thereof is provided with a driving force through the sprayed substance. Propulsion systems used in spaces are classified into cold air propulsion, chemical propulsion and electric propulsion according to the working principle. For short term use, the effective specific impulse of a cold gas propulsion system is greater than the electric propulsion when the total impulse required for satellite control is small. For the micro satellite, the propulsion system is mainly used for satellite orbit keeping and attitude control, the required thrust is small, and the working time is short, so that the cold air propulsion system is preferred to be used as the space propulsion system of the micro satellite on the premise that the loading space and the total mass requirement are met.
The cold air propulsion system comprises a working medium storage box, a pressure reducer, an electric control valve, a spray pipe and a driving circuit; some are also equipped with pressure or flow sensors. The working medium flows out from the air source, is decompressed by the decompressor and is sprayed out through the electric control valve and the spray pipe to form thrust. Wherein, the electric control valve adopts a block valve, and the propeller works in a continuous on/off or pulse state; the on-time of the electrically controlled shut-off valve determines the duration and the magnitude of the impulse of each propulsion process. The cold air micro thruster is a core component of the cold air micro propulsion system.
In the cold air micro thruster in the prior art, a nozzle seat is mostly made of metal or alloy materials; the one-way valve mostly uses a traditional proportional control valve or an electromagnetic proportional valve, and the valve head is mostly made of organic matters or metal materials; no buffer gas or only one buffer gas container, single sealing mode, and multiple shunt or thermal micro-flow chips for monitoring flow; most are either open-loop control or closed-loop control of a single parameter. .
The prior art cold air propeller has the following problems:
1. the metal and alloy material nozzle seat has relatively large thermal expansion coefficient, the spray pipe can expand/contract and deform in a space environment with temperature difference up to hundreds of K, particularly the diameter of the throat can change obviously, and the change is unfavorable for a high-precision micro-Newton cold air thruster and can directly influence the thrust accuracy of the thruster.
2. Common valve head and disk seat (nozzle seat) are the soft seal of organic matter and metal generally, and fatigue deformation can appear in the organic matter valve head after long-time work, leads to the valve stroke change, leads to the flow to appear the deviation, probably leads to the valve even can't be sealed totally, takes place to leak gas.
3. The other metal and metal hard seal can solve the fatigue deformation of the soft seal to a certain extent, but the metal collision loss is larger, especially for the pulse electromagnetic valve, the loss to the metal valve head and the valve seat/nozzle seat can be larger, the service life of the cold air thruster is shortened, the long-term working stability of the cold air thruster is influenced, and the thrust noise is increased.
4. The conventional micro-Newton stage cold air thruster has no preceding stage buffer air volume or only single-stage air volume, and airflow cannot form uniform and stable distribution, so that the pressure distribution is uneven, the thrust stability is poor, and the thrust noise is large.
5. The single-air-volume cold air thruster generally places an air volume in front of a self-locking valve, and working medium gas flows into a spray pipe through a one-way valve after being uniformly distributed through the air volume to generate thrust. If the one-way valve fails due to factors such as fatigue deformation or working loss, the air volume completely loses the buffer function when air leakage occurs.
6. The thermal flowmeter needs to heat local gas, and has certain disturbance to the stable flow of the gas.
7. The split-flow meter needs to consume a small part of gas and has disturbance on the stable flow of the gas.
8. Parameters such as temperature and flow are controlled in an open loop mode, accurate regulation and control of the thruster cannot be achieved, and thrust accuracy and thrust noise are affected.
Therefore, how to solve the problems of the precision control of the thrust and the continuous and stable output of the thrust in the micro-Newton-grade variable-thrust cold air micro-thruster is a technical problem to be solved urgently by those skilled in the art.
Disclosure of Invention
The invention aims to: aiming at the problems of insufficient thrust precision control and difficulty in sustaining stable thrust output in the prior art, the operation method of the micro-Newton-level gem-based double-gas-volume variable-thrust closed-loop cold air thruster is provided.
Therefore, the above purpose of the invention is realized by the following technical scheme:
a running method of a micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster is characterized by comprising the following steps of: in the thruster, a working medium gas inlet, a primary gas capacitor, a connecting channel, a secondary gas capacitor and a working medium gas outlet are sequentially arranged in a soft magnetic material shell, and the working medium gas outlet is provided with a Laval nozzle main body;
the Laval nozzle body is provided with a valve assembly at a working medium inlet of the narrow throat, the valve assembly comprises a valve and a restoring elastic element, and the restoring force of the restoring elastic element synchronously controls the communication or sealing of the valve assembly to the connecting channel and the Laval nozzle body;
the outer wall of the soft magnetic material shell is provided with a driving electromagnetic coil driving valve assembly to move upwards, and meanwhile, the sealing force of the valve is controlled by the elastic force of a return elastic element;
the laval nozzle body is a nozzle base made of a jewel, a jewel valve head is arranged at the front end of the valve and abuts against a working medium gas inlet of the laval nozzle body to realize sealing, one end of a return elastic element at the rear end of the valve elastically props against the working medium gas inlet, the other end props against a valve component to prop against a connecting channel tightly,
the running steps of the thruster are as follows:
s1, connecting a thruster to a stable gas source, and receiving a flow set value Qset and a temperature set value Tset;
s2, setting working parameters of the electromagnetic coil and a temperature control module according to Qset and Tset, working the thruster, magnetizing the valve, overcoming elastic force and pressure difference force to lift upwards under the action of electromagnetic force, and releasing sealing, wherein the working parameters of the electromagnetic coil are expressed by a relational expression (1) between the working parameters of the electromagnetic coil and an actual flow value: qreal = k1 × D, wherein Qreal is an actual flow value, D is an electromagnetic coil working parameter, and k1 is a calibration coefficient;
s3, the working medium gas firstly enters a primary gas capacitor for buffering, and the inlet pressure of the gas inlet is obtained by a primary gas capacitor pressure sensor;
s4, the working medium gas enters a secondary gas volume from the gas inlet to be buffered, the outlet pressure of the gas inlet is obtained through a secondary gas volume pressure sensor, and the pressure difference delta p is obtained through calculation; a secondary gas capacity temperature sensor obtains the temperature Treal of the working medium gas;
s5, when the real temperature Treal of the working medium gas is less than Tset, the temperature control module works by heating coils to heat the working medium gas to the Tset, and is switched on and off in real time according to the temperature indication Treal of the secondary gas capacity temperature sensor to maintain the stable working temperature of the working medium gas and realize closed-loop control of the temperature; when the real temperature Treal of the working medium gas is greater than Tset, the temperature control module is closed, only the temperature indication Treal of the secondary gas-capacitor temperature sensor is recorded, and the relation between the flow and the thrust is corrected through the real temperature Treal of the working medium gas;
s6, measuring the relation between the pressure difference delta p and the actual flow value, wherein the relation is as follows (2): qreal = k2 Δ p, where Qreal is the actual flow value, Δ p is the measured pressure difference, k2 is the calibration coefficient 2, i.e. for correcting the conductance of the vent hole, to obtain the actual flow value Qreal, if Qreal is inconsistent with Qset, the solenoid coil adjusts its working parameters to make Qreal tend to Qset, maintains the stability and accuracy of the working medium gas flow, and implements the closed-loop control of the flow;
and S7, controlling the flow and the temperature of the working medium gas, then feeding the working medium gas into the gem spray pipe, accelerating the working medium gas and then spraying the working medium gas out to obtain the required thrust.
While adopting the above technical solutions, the present invention can also adopt or combine the following technical solutions:
as a preferred technical scheme of the invention: the valve is T-shaped, the cross rod of the valve is clamped on one side of the connecting channel facing to the first-stage gas container, the piston of the connecting channel seat moves, the valve cross rod tightly pushes the connecting channel, the jewel valve head tightly pushes the laval nozzle main body to seal the first-stage gas container and the second-stage gas container, and the jewel valve head is communicated with the first-stage gas container and the second-stage gas container when the valve cross rod leaves the connecting channel.
As a preferred technical scheme of the invention: the valve comprises a jewel valve head, a valve core and a valve core shell, wherein the valve core shell is sleeved outside the valve core and the jewel valve head, and the jewel valve head is adhered to the valve core;
or the ruby valve head is a ruby valve head.
As a preferred technical scheme of the invention: the Laval nozzle body sets up recess installation disk seat sealing washer with soft magnetic material shell link, and the casing is established with soft magnetic material shell overcoat to Laval nozzle body, and the casing is being close to working medium gas inlet one side and soft magnetic material shell fixed connection in order to chucking Laval nozzle body and soft magnetic material shell, realizes sealing through the disk seat sealing washer.
As a preferred technical scheme of the invention: be equipped with the control by temperature change module, the control by temperature change module sets up between soft magnetic material shell and casing, and is located the circumference outside of second grade gas capacity.
As a preferred technical scheme of the invention: the temperature control module sets up second grade gas capacity temperature sensor in interface channel week side, through second grade gas capacity temperature sensor monitoring real-time temperature and adjust temperature control module power simultaneously to the gaseous temperature of working medium in the closed-loop control second grade gas capacity.
As a preferred technical scheme of the invention: the primary gas volume is provided with a primary gas volume pressure sensor, the secondary gas volume is provided with a secondary gas volume pressure sensor, the primary gas volume front end pressure p1 and the secondary gas volume foremost end pressure p2 are respectively measured by the secondary gas volume pressure sensor, the pressure difference delta p is obtained, after the delta p is judged to be approximate to the pressure difference between the two sides of the gas inlet, the theoretical approximate flow value is obtained through calculation, the working parameters of the electromagnetic pulse valve are adjusted in real time, and therefore closed-loop control of the flow is achieved.
As a preferred technical scheme of the invention: the electromagnetic coil is wound in a coil framework outside the rear end of the soft magnetic material shell, and the outer side of the electromagnetic coil is limited to be dislocated through the shell to drive the electromagnetic coil to drive the valve component to move towards the working medium gas inlet direction.
As a preferred technical scheme of the invention: the return elastic element is a tension spring, one end of the return elastic element is fixed on the valve core, the other end of the return elastic element is installed at the rear end of the soft magnetic material shell, the solenoid coil is driven to drive the valve and overcome the elastic force of the return elastic element to lift, the working medium gas outlet and the connecting channel are opened, the gas channel of the first-stage gas capacitor and the second-stage gas capacitor is opened, the solenoid coil is closed, and the valve is tightly pressed by the tension force of the tension spring to realize sealing.
The running method of the micro-Newton-level gem-based double-gas-volume variable-thrust closed-loop cold air thruster drives the valve and the return elastic element to move upwards by utilizing the working parameters of the pulse electric signal of the regulating electromagnetic coil, regulates and controls the working medium gas output of the gas inlet of the first-level gas volume and the working medium gas outlet in real time, realizes the continuous and variable regulation of the working medium gas flow, and provides hardware conditions for realizing the continuous and stable output thrust of the cold air thruster; the valve T-shaped design and the middle waist design of the soft magnetic material shell are utilized to match with the return elastic element to divide the gas volume into a primary gas volume and a secondary gas volume, so that a foundation is provided for closed-loop control of working medium gas flow, a theoretical approximate flow value can be realized by matching with the primary gas volume pressure sensor and the secondary gas volume pressure sensor, the front-end gas supply is controlled through negative feedback of the gas outlet end, constant flow control of a working medium gas outlet is realized through adjusting the electromagnetic coil, and real-time high-precision control of the thrust of the cold air thruster can be realized. The separation design of the first-stage air volume and the second-stage air volume provides double insurance for avoiding air leakage of the air volumes, ensures high sealing performance of the thruster, improves the continuous uniformity and continuous stability of airflow by matching with air pressure monitoring and flow control in the two-stage air volumes, realizes continuous and stable thrust of the cold air thruster, and reduces thrust noise; the hard seal combination of the gem nozzle base and the gem valve head effectively overcomes the thermal expansion and cold contraction influence on the nozzle base and the valve head caused by extreme high and low temperatures in the space, effectively solves the abrasion problem in the long-term working process of the traditional valve head and valve seat, and realizes the continuous output precision and stability of the thrust.
According to the running method of the micro-Newtonian-grade gem-based double-air-volume variable-thrust closed-loop cold air thruster, the double-gem hard seal formed by the sapphire material nozzle tube seat and the ruby material valve head is utilized, the continuous and stable sealing effect and the service life are effectively improved, and particularly, the thermal expansion coefficient of the gem material is lower than that of metal and alloy materials, so that the thruster is more suitable for working in the space working environment with larger temperature difference, the stability of the nozzle structure is ensured, and the stability and the accuracy of the thruster are ensured; by adopting the two-stage gas capacity, the gas working medium can be effectively buffered, the uniformity of the gas working medium is ensured, and the stability and the accuracy of the thrust of the thruster are ensured; the pressure sensors respectively arranged in the two-stage gas capacitors can be used for monitoring the pressure difference between the two gas capacitors in real time, namely the pressure difference at two ends of the gas inlet, so that the working flow of the thruster is obtained, the two-stage gas capacitors can be used for adjusting the working parameters of the electromagnetic pulse signals in real time according to the flow, the closed-loop control on the flow is completed, and the stability and the accuracy of the flow are ensured; the temperature control module realizes the accurate control of the temperature of the secondary gas capacitor, namely the outlet working medium gas, and the real-time feedback signal of the temperature sensor is used for completing the closed-loop control of the gas in the secondary gas capacitor, so that the stability of the temperature of the working medium gas is ensured, and the thrust value can be corrected through a theoretical formula through the actual temperature even if the temperature of the working medium gas is higher than the working temperature, and the actual thrust value is obtained.
Drawings
FIG. 1 is a schematic structural diagram of a thruster adopted by an operation method of a micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster of the invention;
in the drawings: the device comprises a gem spray pipe seat 1, an outlet temperature sensor 2, a shell 3, a gem valve head 4, a valve seat sealing O ring 5, a valve core shell 6, a valve core 7, a temperature control module 8, a secondary gas capacitor 9, a secondary gas capacitor pressure sensor 10, a secondary gas capacitor temperature sensor 11, a connecting channel 12, a primary gas capacitor pressure sensor 13, an electromagnetic coil 14, a primary gas capacitor 15, a return elastic element 16, a soft magnetic material shell 17, a lead 18 and a working medium gas inlet 19; and a working medium gas outlet 20.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention relates to an operation method of a micro-Newton-level gem-based double-gas-volume variable-thrust closed-loop cold air thruster.A working medium gas inlet 19, a primary gas volume 15, a connecting channel 12, a secondary gas volume 9 and a working medium gas outlet 20 are sequentially arranged in a soft magnetic material shell 17 in the used thruster, and the working medium gas outlet 20 is provided with a Laval nozzle main body 1; a valve assembly is arranged at a working medium inlet of the narrow throat of the Laval nozzle body 1, the valve assembly comprises a valve and a restoring elastic element 16, and the restoring force of the restoring elastic element 16 synchronously controls the communication or sealing of the valve assembly on the connecting channel 12 and the Laval nozzle body;
the outer wall of the soft magnetic material shell 17 is provided with an electromagnetic coil 14 for driving the valve assembly to move in different directions, and meanwhile, the sealing force of the valve is controlled by the elastic force of the return elastic element 16; laval nozzle body 1 is the nozzle seat of precious stone material, and the valve front end sets up the working medium gas inlet that the precious stone valve head supported Laval nozzle body 1 and realizes sealing, and the valve rear end is replied 16 one end elasticity of elastic component and is tightly pushed up working medium gas inlet 19, and the tight valve module in other end top is with tight connecting channel 12 in top.
The valve is T-shaped, the cross rod of the valve is clamped on one side, facing the first-stage gas container 15, of the connecting channel 12, the piston moves on the connecting channel 12, the jewel valve head 4 tightly pushes the Laval nozzle main body 1 to seal the first-stage gas container and the second-stage gas container when the valve cross rod tightly pushes the connecting channel 12, and the jewel valve head 4 is communicated with the first-stage gas container and the second-stage gas container when the valve cross rod leaves the connecting channel 12.
The valve comprises a jewel valve head 4, a valve core 7 and a valve core shell 6, wherein the valve core shell 6 is sleeved outside the valve core 7 and the jewel valve head 4, and the jewel valve head 4 is adhered to the valve core 7; the ruby valve head 4 is a ruby valve head.
The connection end of the Laval nozzle body 1 and the soft magnetic material shell 17 is provided with a groove for installing a valve seat sealing ring 5, the Laval nozzle body 1 and the soft magnetic material shell 17 are sleeved with a shell 3, one side of the shell 3 close to a working medium gas inlet is fixedly connected with the soft magnetic material shell 17 so as to clamp the Laval nozzle body 1 and the soft magnetic material shell 17, and sealing is realized through the valve seat sealing ring.
Be equipped with temperature control module 8, temperature control module 8 sets up between soft magnetic material shell 17 and casing 3, and is located the circumference outside of second grade gas capacity.
The primary air volume 15 is provided with a primary air volume pressure sensor 13, the secondary air volume 9 is provided with a secondary air volume pressure sensor 10 which respectively measures the front end pressure p1 of the primary air volume 13 and the most front end pressure p2 of the secondary air volume 10 and obtains a pressure difference delta p, after the delta p is judged to be approximate to the pressure difference of the two sides of the connecting channel 12, a theoretical approximate flow value is obtained through calculation of Q = K2 delta p, and the working parameters of the electromagnetic pulse valve are adjusted in real time, so that closed-loop control of the flow is achieved.
The driving electromagnetic coil 14 is wound in a coil framework outside the rear end of the soft magnetic material shell 17, the outer side of the driving electromagnetic coil is limited to be dislocated by the shell 3, and the driving electromagnetic coil 14 drives the valve component to move towards the direction of the working medium gas inlet.
The return elastic element 16 is a tension spring, drives the electromagnetic coil 14 to drive the valve and overcomes the elastic force of the return elastic element 16 to lift, opens the working medium gas outlet 20 and the connecting channel, and opens the gas channel of the primary gas container 15 and the secondary gas container 9.
When the temperature of the gas working medium is lower than the working requirement temperature, the temperature closed-loop control is realized through the temperature sensor 11 arranged in the secondary gas container 9, and the quick and accurate adjustment of the temperature of the working medium gas is realized. And when the temperature of the gas working medium is higher than the working required temperature, correcting the relation between the flow and the thrust through the temperature of the secondary gas capacity temperature sensor 11.
The flow calibration and closed-loop control are realized through the pressure sensors 10 and 13 in the front-stage gas container 9 and the rear-stage gas container 15, so that the high accuracy of the working medium gas flow is achieved.
The continuous variable adjustment of the flow is realized by adjusting the working parameters of the electromagnetic coil, so that the continuous variable adjustment of the thrust is realized.
The thruster realizes closed-loop control of temperature and flow, effectively ensures the stability of working medium gas temperature and the stability of flow output, further realizes the stability and the quick closed-loop regulation of thrust output, effectively reduces the thrust noise and ensures the long-term working stability.
The double-stage gas capacity ensures the uniformity and stability of the airflow, provides a measuring and calibrating space for closed-loop control of the flow, can enhance the sealing effect and effectively reduce the thrust noise.
The T-shaped valve is sealed in two stages, and even if one stage of air volume leaks gas and fails, the one stage of air volume still exists to realize the sealing and buffering functions, so that the gas leakage is prevented.
The hard seal combination of the gem spray pipe seat 1 and the gem valve head 4 effectively overcomes the thermal expansion and cold contraction influence on the spray pipe seat and the valve head caused by extreme high and low temperature in the space, can effectively reduce the impulse valve impact loss, improves the thrust output precision and stability, and prolongs the service life.
According to the micro-Newton-level gem-based variable-thrust closed-loop cold air thruster, the valve is driven and the elastic element is restored to move upwards by utilizing the working parameters of the pulse electrical signals of the electromagnetic coil, the working medium gas output of the gas inlet of the primary air volume and the working medium gas outlet 20 is regulated and controlled in real time, the continuous and variable regulation of the working medium gas flow is realized, and the hardware condition is provided for realizing the thrust continuously and stably output by the cold air thruster; in the invention, the valve T-shaped design and the waist design in the middle of the soft magnetic material shell 17 are utilized, the return elastic element is matched to divide the air volume into a primary air volume and a secondary air volume, a foundation is provided for closed-loop control of working medium gas flow, the theoretical approximate flow value can be realized by matching the primary air volume pressure sensor 13 and the secondary air volume pressure sensor 10, the front-end air supply is controlled through air outlet end negative feedback, the constant flow control of the working medium gas outlet is realized by adjusting the electromagnetic coil, and the real-time high-precision control of the thrust of the cold air thruster can be realized. The design of the separation of the first-stage air volume and the second-stage air volume ensures high sealing performance of the thruster by adopting double insurance for avoiding air leakage of the air volumes, improves the continuous uniformity and the continuous stability of airflow by matching with air pressure monitoring and flow control in the two-stage air volumes, realizes continuous and stable thrust of the cold air thruster, and reduces thrust noise; the hard seal combination of the gem nozzle base and the gem valve head effectively overcomes the thermal expansion and cold contraction influence on the nozzle base and the valve head caused by extreme high and low temperatures in the space, and provides hardware conditions for continuous output precision and stability of the thrust.
Example 1
As shown in figure 1, in the operation method of the micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster, a section of shallow groove is arranged on the contact surface of a shell 3 and a Laval nozzle main body 1, an outlet temperature sensor 2 is arranged in the groove, the outlet temperature at the front end is monitored, and the micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster is fixed on the shell 3 in an adhesion mode. The interior of the Laval nozzle body 1 is hollow, the rear end of the Laval nozzle body is double-arc-shaped, the front end of the Laval nozzle body is conical and expanded, and the Laval nozzle body is of a Laval nozzle structure. The valve seat sealing ring 5 is positioned in a groove at the front end of the soft magnetic material shell 17 and at the rear end of the sapphire nozzle seat, and sealing between the Laval nozzle body 1 and the soft magnetic material shell 17 is guaranteed. The temperature control module 8 is wound in a coil framework outside the front end of the soft magnetic material shell 17, and the other side of the temperature control module is limited in the shell 3 by the shell 3 to prevent falling off and is used for controlling the temperature of working medium gas in the secondary gas container. The secondary gas capacity pressure sensor 10 and the secondary gas capacity temperature sensor 11 are arranged at the rear end of the secondary gas capacity 9 and at the front end of the connecting channel 12 through pipe joints welded in empty grooves of the soft magnetic material shell 17, sealing of the pipe joints is guaranteed by using sealing glue, and the secondary gas capacity pressure sensor and the secondary gas capacity temperature sensor are respectively used for monitoring the temperature of working medium gas in the secondary gas capacity 9 and the outlet pressure of the connecting channel 12. The primary air volume pressure sensor is arranged at the front end of the primary air volume 15 and at the rear end of the connecting channel 12 through a pipe joint welded in a hollow groove of a soft magnetic material shell 17, sealing of the pipe joint is guaranteed by using a sealant, and the primary air volume pressure sensor is used for monitoring the inlet pressure of the connecting channel 12. The driving solenoid 14 is wound in a bobbin pointed outside the rear end of the soft magnetic material housing 17, and the other side is restrained by the housing 3 within the housing 3 against falling off for generating a force for driving the valve assembly to move upward. The valve component comprises ruby valve head 4, case 7, case shell 6 and reply elastic element 16, ruby valve head 4 is connected with case 7 through the mode of adhesion, and case shell 6 cover is outside ruby valve head 4 and case 7, plays the guard action, and the valve front end supports in 1 rear end of laval spray tube main part through ruby valve head 4, and the rear end supports in 15 front ends of one-level gas capacity in soft magnetic material shell 17 through case shell 6, forms the doublestage and seals. The restoring elastic element 16 is mounted on the valve core 7 at the front end and mounted on the soft magnetic material shell 17 at the rear end for generating the sealing force and restoring force of the valve. On the structure of the soft magnetic material shell 17, 4 connecting channels 12 are uniformly arranged between the primary air volume 15 and the secondary air volume 9. The shell 3 is connected with the soft magnetic material shell 17 through a sealant and a rear end screw, and the outlet temperature sensor 2, the temperature control module 8, the secondary air volume pressure sensor 10, the secondary air volume temperature sensor 11, the primary air volume pressure sensor 13 and a lead 18 of the driving electromagnetic coil 14 extend to the outside of the rear end of the soft magnetic material shell 17 through a shallow groove in the shell 3 and a through hole in the soft magnetic material shell 17.
The temperature control module 8 controls the temperature of the working medium gas in the secondary gas capacitor 9 through the soft magnetic material shell 17, monitors the real-time temperature through the secondary gas capacitor temperature sensor 11 and adjusts the power of the temperature control module 8 at the same time, and the closed-loop control of the temperature of the working medium gas in the secondary gas capacitor 9 is realized.
Under the non-working state, due to the action of the return elastic element, the valve core shell 6 is abutted against the front end of the primary gas capacitor 15 in the soft magnetic material shell 17, the connecting channel 12 cannot work, the ruby valve core 4 is abutted against the rear end of the Laval nozzle main body 1, and the gas working medium cannot be ejected to form thrust, so that the double-cutoff state is realized. When the electromagnetic coil 14 is electrified in a working state, the ruby valve head 4, the valve core 7 and the valve core shell 6 overcome the elastic force of the return elastic element 16 to lift, the gas channels of the first-stage gas capacitor 15 and the second-stage gas capacitor 9 are opened, the gas working medium in the second-stage gas capacitor is sprayed out from the Laval nozzle main body 1 to form thrust, and then the working medium gas in the first-stage gas capacitor is supplemented to the second-stage gas capacitor 9 through the connecting channel 12.
Under the stable working state, due to the pressure difference between the secondary gas container 9 and the working environment, the gas working medium can be sprayed out through the Laval nozzle main body 1, and the gas pressure in the secondary gas container 9 is reduced along with the spraying. Because the gas pressure in the secondary gas container 9 is reduced, a pressure difference is formed between the primary gas container 15 and the secondary gas container 9, the working medium gas in the primary gas container 15 is supplemented to the secondary gas container 9 through the connecting channel 12, the supplementary flow rate and the flow rate sprayed out through the Laval nozzle body 1 are in a series relation, and the numerical value is equal. The pressure p1 at the front end of the primary air volume 13, namely the rear end of the connecting channel 12, and the pressure p2 at the front end of the secondary air volume 10, namely the front end of the connecting channel 12 can be respectively measured through the primary air volume pressure sensor 13 and the secondary air volume pressure sensor 10, a pressure difference deltap is obtained, and after the deltap is considered to be approximate to the pressure difference between the two sides of the connecting channel 12, a theoretical approximate flow value can be obtained through calculation of Q = K2 deltap. Because the air paths of the whole set of cold air propulsion system are connected in series, the flow entering the first-stage air volume 15 and the second-stage air volume 10 is completely consistent with the flow in the working environment, a high-precision flow calibrator can be used at the front end to supply air, the flow is used as the standard flow to calibrate the relation between the pressure difference delta p at the two ends of the connecting channel 12 and the flow, and a calibrated flow relation formula is obtained. The duty ratio of the electromagnetic pulse valve is adjusted in real time by measuring the flow value corresponding to the pressure difference through the primary gas capacity pressure sensor 13 and the secondary gas capacity pressure sensor 10, so that the closed-loop control of the flow is realized.
The laval nozzle body 1 is made of sapphire, the ruby valve head 4 is made of ruby, the shell 3 and the soft magnetic material shell 17 are made of stainless steel, and the valve core shell 6 and the valve core 7 are made of soft magnetic alloy materials. The Laval nozzle body 1 adopts a laser processing to form a Laval nozzle structure with a hollow interior, so that the processing precision of small holes and front and back linear and nonlinear structures is ensured. The ruby valve head 4 adopts the technology of dry etching assisted laser processing. The shell 3, the soft magnetic material shell 17 and the valve core shell 6 are all processed by precision machining, so that the installation axis and the thrust axis of the thruster are in the same straight line, and the thrust precision is improved.
The operation method of the thruster of the present invention will be described below.
When the driving electromagnetic coil 14 does not work, the valve is pressed on the Laval nozzle body 1 and the soft magnetic material shell 17 by means of the elastic force of the return elastic element 16, and double-stage sealing is formed. When the thruster works, the driving electromagnetic coil 14 is applied with a certain electric signal to magnetize the valve core 7 and generate axial suction force to the valve core 7. When the suction force is larger than the elastic force of the return elastic element 16, the valve is lifted upwards, the double-stage sealing is released, the working medium gas is throttled from the secondary gas container 9 through the Laval nozzle main body 1 and then expanded and sprayed out to form thrust, and meanwhile, the working medium gas in the primary gas container 15 supplements the working medium gas to the secondary gas container 9 through the connecting channel 12. The driving signal in the thruster is a pulse signal, so that the thruster is in a pulse jet working mode, and the valve controls the ejection of a gas working medium through continuous switching action. The gas working medium flow can be controlled by adjusting the duty ratio of the working pulse signal of the driving electromagnetic coil 14, so that the continuous adjustment of the flow and the continuous adjustment of the thrust are realized. In the working process of the thruster, the temperature control module 8 adjusts the temperature of the working medium gas in the secondary gas capacitor 9 in real time according to the feedback temperature of the secondary gas capacitor temperature sensor 10 to form closed-loop control of the temperature of the working medium gas, so that the stability of the temperature of the sprayed working medium gas is ensured, and the stability of the thrust is ensured. The secondary air volume pressure sensor 11 and the primary air volume pressure sensor measure the pressure difference at two ends of the connecting channel 12 when the thruster works in real time and convert the pressure difference into real-time flow, the real-time flow value is fed back to the front end control system, and the system adjusts the duty ratio of a pulse driving signal according to the feedback, so that the flow is adjusted, and the closed-loop control of the flow is realized.
The flow calibration control process and the method for operating a cold gas thruster of the present invention will be further described below.
Firstly, the method comprises the following steps: flow calibration:
1. giving working parameters of the electromagnetic coil 14, opening the temperature control module 8 and removing the sealing of the T-shaped valve;
2. supplying gas to the thruster through a gas inlet, installing a standard mass flowmeter on a pipeline before the working medium gas enters the thrust, and taking the indication of the standard mass flowmeter as a standard flow value;
3. recording pressure readings of the secondary air volume pressure sensor 10 and the primary air volume pressure sensor 13 under the working state and obtaining a pressure difference delta p; recording the temperature readings of the secondary gas-capacitor temperature sensor 11 in the working state;
4. if the temperature indication of the secondary gas capacity temperature sensor 11 is lower than the working requirement temperature, the heating electromagnetic coil works, and the temperature of the gas working medium is maintained at the working requirement temperature in the whole calibration working period. And if the temperature indication number of the secondary gas capacity temperature sensor 11 is greater than the temperature required by work, the temperature control module 7 stops working, and the relationship between the flow and the thrust is corrected by using the gas working medium temperature data acquired by the secondary gas capacity temperature sensor 11 to obtain a corrected thrust value.
5. Repeating the operation process to obtain the standard flow, the pressure difference delta p and the working medium gas temperature corresponding to the working parameters of the plurality of groups of electromagnetic coils 14;
6. fitting the working parameters of the electromagnetic coil 14 with the data of the standard flow to obtain a relational expression (1) of the working parameters and the standard flow value: q = k1 × D, wherein Q is a standard flow value, D is an electromagnetic coil working parameter, and k1 is a calibration coefficient 1, and then fitting is performed on the pressure difference Δ p and the standard flow value data to obtain a relation (2) of the pressure difference Δ p and the standard flow value: q = k2 Δ p, where Q is the standard flow value, Δ p is the measured pressure difference, and k2 is the calibration factor 2. Establishing the relation among the pressure difference delta p, the standard flow value and the working parameter of the electromagnetic coil 14 through the relations (1) and (2) to obtain a flow calibration formula: d = k2 Δ p/k1 as a transfer function for closed-loop control of the flow;
7. after calibration is finished, the power supply is turned off, and the T-shaped valve returns the resilience force of the elastic element to realize sealing;
the operation method of the cold air thruster comprises the following operation steps:
s1, connecting a thruster to a stable gas source, and receiving a flow set value Qset and a temperature set value Tset;
s2, setting working parameters of the electromagnetic coil and a temperature control module according to Qset and Tset, working the thruster, magnetizing the valve, overcoming elastic force and differential pressure to lift upwards under the action of electromagnetic force, and releasing sealing, wherein the working parameters of the electromagnetic coil pass through a relational expression (1) of the working parameters of the electromagnetic coil and a standard flow value: q = k1 × D (where Q is a standard flow value, D is an operating parameter of the solenoid, and k1 is a calibration coefficient 1;
s3, the working medium gas firstly enters a primary gas capacitor for buffering, and the inlet pressure of the gas inlet is obtained by a primary gas capacitor pressure sensor;
s4, the working medium gas enters a secondary gas volume from the gas inlet to be buffered, the outlet pressure of the gas inlet is obtained through a secondary gas volume pressure sensor, and the pressure difference delta p is obtained through calculation; a secondary gas capacity temperature sensor obtains the temperature Treal of the working medium gas;
and S5, when the temperature Treal of the working medium gas is less than Tset, the heating coil of the temperature control module works to heat the working medium gas to the Tset, and the temperature control module is switched on and off in real time according to the temperature Treal of the working medium gas of the secondary gas-capacitor temperature sensor to maintain the stable working temperature of the working medium gas and realize closed-loop control of the temperature. When the working medium gas temperature Treal is greater than Tset, the temperature control module is closed, only the working medium gas temperature Treal of the secondary gas-capacitor temperature sensor is recorded, and the relation between the flow and the thrust is corrected through the working medium gas temperature Treal;
s6, measuring the relation (2) between the pressure difference delta p and the standard flow rate value: q = k2 Δ p, wherein Q is a standard flow value, Δ p is a measurement pressure difference, k2 is a calibration coefficient 2, and an actual flow value Qreal is obtained by substituting Δ p as the measurement pressure difference into the relational expression (2), if Qreal is inconsistent with Qset, the solenoid coil adjusts working parameters thereof to make Qreal tend to Qset, so that the stability and accuracy of the gas flow of the working medium are maintained, and the closed-loop control of the flow is realized;
and S7, controlling the flow and the temperature of the working medium gas, then feeding the working medium gas into the gem spray pipe, accelerating the working medium gas and then spraying the working medium gas out to obtain the required thrust. The above-described embodiments are intended to illustrate the present invention, but not to limit the present invention, and any modifications, equivalents, improvements, etc. made within the spirit of the present invention and the scope of the claims fall within the scope of the present invention.
Claims (9)
1. A running method of a micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster is characterized by comprising the following steps of: in the thruster, a working medium gas inlet, a primary gas capacitor, a connecting channel, a secondary gas capacitor and a working medium gas outlet are sequentially arranged in a soft magnetic material shell, and the working medium gas outlet is provided with a Laval nozzle main body;
the Laval nozzle body is provided with a valve assembly at a working medium inlet of the narrow throat, the valve assembly comprises a valve and a restoring elastic element, and the restoring force of the restoring elastic element synchronously controls the communication or sealing of the valve assembly to the connecting channel and the Laval nozzle body;
the outer wall of the soft magnetic material shell is provided with a driving electromagnetic coil driving valve assembly to move upwards, and meanwhile, the elastic force of the return elastic element is used for controlling the sealing force of the valve;
the laval nozzle body is a nozzle base made of a jewel, a jewel valve head is arranged at the front end of the valve and abuts against a working medium gas inlet of the laval nozzle body to realize sealing, one end of a return elastic element at the rear end of the valve elastically props against the working medium gas inlet, the other end of the return elastic element props against a valve component to prop against a connecting channel,
the thruster comprises the following operation steps:
s1, a thruster is connected to a stable air source and receives a flow set value Qset and a temperature set value Tset;
s2, setting working parameters of the electromagnetic coil and a temperature control module according to Qset and Tset, working the thruster, magnetizing the valve, overcoming elastic force and pressure difference force to lift upwards under the action of electromagnetic force, and releasing sealing, wherein the working parameters of the electromagnetic coil are expressed by a relational expression (1) between the working parameters of the electromagnetic coil and an actual flow value: qreal = k1 × D, wherein Qreal is an actual flow value, D is an electromagnetic coil working parameter, and k1 is a calibration coefficient;
s3, the working medium gas firstly enters a primary gas capacitor for buffering, and the inlet pressure of the gas inlet is obtained by a primary gas capacitor pressure sensor;
s4, the working medium gas enters a secondary gas volume from the gas inlet to be buffered, the outlet pressure of the gas inlet is obtained by a secondary gas volume pressure sensor, and the pressure difference delta p is obtained through calculation; a secondary gas capacity temperature sensor obtains the temperature Treal of the working medium gas;
s5, when the real temperature Treal of the working medium gas is less than Tset, the heating coil of the temperature control module works to heat the working medium gas to the Tset, and the temperature control module is switched on and off in real time according to the temperature indication Treal of the secondary gas capacity temperature sensor to maintain the stable working temperature of the working medium gas and realize closed-loop control of the temperature; when the real temperature Treal of the working medium gas is greater than Tset, the temperature control module is closed, only the temperature indication Treal of the secondary gas capacity temperature sensor is recorded, and the relation between the flow and the thrust is corrected through the real temperature Treal of the working medium gas;
s6, through the relation (2) of the measured pressure difference delta p and the actual flow rate value: qreal = k2 Δ p, where Qreal is the actual flow value, Δ p is the measured pressure difference, k2 is the calibration coefficient 2, i.e. for correcting the conductance of the vent hole, to obtain the actual flow value Qreal, if Qreal is inconsistent with Qset, the solenoid coil adjusts its working parameters to make Qreal tend to Qset, maintains the stability and accuracy of the working medium gas flow, and implements the closed-loop control of the flow;
and S7, the working medium gas enters the gem spray pipe after flow and temperature control, and is sprayed out after acceleration to obtain the required thrust.
2. The operation method of the micro-Newton-based double-air-volume variable-thrust closed-loop cold air thruster of claim 1, wherein: the valve is T-shaped, the cross rod of the valve is clamped on one side of the connecting channel facing to the first-stage gas container, the connecting channel performs piston motion, the valve cross rod tightly pushes the connecting channel, the jewel valve head tightly pushes the laval nozzle main body to seal the first-stage gas container and the second-stage gas container, and the jewel valve head is communicated with the first-stage gas container and the second-stage gas container when the valve cross rod leaves the connecting channel.
3. The operation method of the micro-Newton-based double-air-volume variable-thrust closed-loop cold air thruster of claim 1, wherein: the valve comprises a jewel valve head, a valve core and a valve core shell, wherein the valve core shell is sleeved outside the valve core and the jewel valve head, and the jewel valve head is adhered to the valve core;
wherein, ruby valve head chooses for use ruby valve head.
4. The operation method of the micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster, according to claim 1, is characterized in that: the Laval nozzle body sets up recess installation disk seat sealing washer with soft magnetic material shell link, and the casing is established with soft magnetic material shell overcoat to Laval nozzle body, and the casing is being close to working medium gas inlet one side and soft magnetic material shell fixed connection in order to chucking Laval nozzle body and soft magnetic material shell, realizes sealing through the disk seat sealing washer.
5. The operation method of the micro-Newton-based double-air-volume variable-thrust closed-loop cold air thruster of claim 4, wherein: be equipped with the control by temperature change module, the control by temperature change module sets up between soft magnetic material shell and casing, and is located the circumference outside of second grade gas capacity.
6. The operation method of the micro-Newton-level Gem-based double-air-volume variable-thrust closed-loop cold air thruster, according to claim 5, is characterized in that: the temperature control module sets up second grade gas capacity temperature sensor in interface channel week side, through second grade gas capacity temperature sensor monitoring real-time temperature and adjust temperature control module power simultaneously to the gaseous temperature of working medium in the closed-loop control second grade gas capacity.
7. The operation method of the micro-Newton-level gem-based double-air-volume variable-thrust closed-loop cold air thruster, according to claim 1, is characterized in that: the primary air volume is provided with a primary air volume pressure sensor, the secondary air volume is provided with a secondary air volume pressure sensor, the primary air volume front end pressure p1 and the secondary air volume front end pressure p2 are respectively measured, the pressure difference delta p is obtained, after the delta p is judged to be approximate to the pressure difference between the two sides of the air inlet, the theoretical approximate flow value is obtained through calculation according to the formula Q = c × delta p, the working parameters of the electromagnetic pulse valve are adjusted in real time, and therefore closed-loop control of the flow is achieved.
8. The operation method of the micro-Newton-based double-air-volume variable-thrust closed-loop cold air thruster of claim 4, wherein: the electromagnetic coil is wound in a coil framework arranged outside the rear end of the soft magnetic material shell, and the outer side of the electromagnetic coil is limited to be dislocated through the shell to drive the electromagnetic coil to drive the valve component to move towards the working medium gas inlet.
9. The operation method of the micro-Newton-based double-air-volume variable-thrust closed-loop cold air thruster of claim 8, wherein: the return elastic element is a tension spring, one end of the return elastic element is fixed on the valve core, the other end of the return elastic element is installed at the rear end of the soft magnetic material shell, the solenoid coil is driven to drive the valve and overcome elastic lifting of the return elastic element, the working medium gas outlet and the connecting channel are opened, the gas channel of the primary gas container and the gas channel of the secondary gas container are opened, the solenoid coil is closed, and the valve is tightly pressed by the tension force of the tension spring to realize sealing.
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| CN202211017117.1A CN115946876A (en) | 2022-04-13 | 2022-04-13 | Running method of micro-Newton-level gem-based double-gas-capacity variable-thrust closed-loop cold air thruster |
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| US5519991A (en) * | 1994-08-30 | 1996-05-28 | Olin Corporation | Increased efficiency arcjet thruster |
| JP3652940B2 (en) * | 1999-10-29 | 2005-05-25 | 三菱重工業株式会社 | Floating poppet valve device |
| CN106134389B (en) * | 2008-05-30 | 2012-10-31 | 上海空间推进研究所 | The cold air thruster of microminiature satellite |
| CN101963111A (en) * | 2010-09-28 | 2011-02-02 | 北京航空航天大学 | Sample machine on basis of principle of nitrous oxide mono-component thruster and use method thereof |
| US8707675B2 (en) * | 2011-01-20 | 2014-04-29 | Honeywell International Inc. | Pressure assisted direct drive proportional hot-gas thruster |
| CN104005923B (en) * | 2014-05-14 | 2017-12-15 | 中国人民解放军国防科学技术大学 | A kind of solar heat thruster |
| FR3021301B1 (en) * | 2014-05-21 | 2017-12-29 | Snecma | MOTOR FOR SPACE ENGINE, AND SPACE ENGINE COMPRISING SUCH AN ENGINE |
| WO2017023383A1 (en) * | 2015-05-05 | 2017-02-09 | Digital Solid State Propulsion, Inc. | Liquid fueled pulsed plasma thruster |
| CN106369207A (en) * | 2016-08-30 | 2017-02-01 | 兰州空间技术物理研究所 | Micro flow proportional control valve |
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