CN101445160A - Micro liquid fuel propulsion system used in micro-nano satellite - Google Patents
Micro liquid fuel propulsion system used in micro-nano satellite Download PDFInfo
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- CN101445160A CN101445160A CNA2008102202801A CN200810220280A CN101445160A CN 101445160 A CN101445160 A CN 101445160A CN A2008102202801 A CNA2008102202801 A CN A2008102202801A CN 200810220280 A CN200810220280 A CN 200810220280A CN 101445160 A CN101445160 A CN 101445160A
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Abstract
The invention discloses a micro liquid fuel propulsion system used in a micro-nano satellite. The micro liquid fuel propulsion system comprises a pressurized gas generator, a micro propeller and a fuel storage tank for supplying liquid fuel to the micro propeller, the pressurized gas generator is used for inflating and pressurizing the fuel storage tank; the inside of the fuel storage tank is comparted by a diaphragm into a liquid storage part for storing the liquid fuel and a gas storage part which is communicated with the pressurized gas generator by a gas transmission pipeline, and two ends of the gas transmission pipeline are provided with a pressure sensor and a gas charge-discharge valve respectively; the liquid storage part is communicated with the micro propeller by a liquid transmission pipeline, and two ends of the liquid transmission pipeline near the liquid storage part are provided with a liquid fuel charge-discharge valve and a safety valve respectively; and the liquid transmission pipeline is further sequentially provided with a diaphragm valve, a filter and an solenoid valve. The micro liquid fuel propulsion system avoids the disadvantage of a clumsy structure of a high pressure cylinder which is used in the traditional liquid fuel satellite propulsion system for pressurizing the fuel, and can meet the requirements of the micro-nano satellite for small size, light weight and low energy consumption.
Description
Technical field
The present invention relates to satellite propulsion system, particularly relate to a kind of micro liquid fuel propulsion system that is applicable to micro-nano satellite.
Background technology
Microsatellite has that volume is little, in light weight, with high content of technology, the lead time is short, the low advantages such as (tens million of yuans) of development cost, is the new focus of space technology development in recent years.Many microsatellites can be formed the formation flight satellite, are with a wide range of applications at aspects such as earth observation, three-dimensional imaging, accurate location, atmospheric exploration, celestial observation and geophysical explorations.Microsatellite can also center on the flight of space station or other space vehicles as following satellite, and it is observed, detects service.These microsatellites all need good attitude control and track adjustment capability.In the middle of the evolution of small satellite technology, other parts of satellite generally can adopt micro-processing technologies such as MEMS carry out microization more easily, and traditional liquid fuel satellite propulsion system adopts high pressure nitrogen or helium tank that fuel is pressurizeed, and the propulsion system of this principle is directly carried out the micro-miniaturisation not a duck soup.And propulsion system is bigger at the shared proportion of satellite generally, and is about about 30%, and this ratio is higher in the middle of micro-nano satellite.Therefore, it is little to possess a volume, and light weight, the propulsion system that performance is high are the keys of this class micro-nano satellite successful Application.
Mainly adopted the blue gas propulsion system at present a lot of microsatellites, followed for No. seven small satellite to use liquefied ammonia as propellant as divine boat.The blue gas propulsion system has advantages of simple structure and simple, but with blue gas as propellant itself, it can not have very high chemical power like that as simple fraction chemical liquid fuel (as high concentration hydrogen peroxide, hydrazine etc.), improves specific impulse thereby can discharge chemical heat in propelling unit.Therefore, be necessary to develop the miniature propulsion system of performance-oriented liquid fuel to promote the development and application of microsatellite.
Summary of the invention
The objective of the invention is to overcome in the miniature propulsion system of prior art with blue gas as propellant itself, thereby can not have very high chemical power as simple fraction chemical liquid fuel, can't satisfy the power demand of propulsion system, a kind of micro liquid fuel propulsion system structure of novelty is provided, and this system can satisfy the requirement that the micro-nano satellite volume is little, in light weight, energy consumption is low.
For realizing above purpose, the present invention has taked following technical scheme: a kind of micro liquid fuel propulsion system that is used for micro-nano satellite, include pressurization gas producer, microdriver, for microdriver provides the fuel tank of liquid fuel, described pressurization gas producer is used for described fuel tank plenum; Be separated into the liquid storage part of storage of liquids fuel in this fuel tank by barrier film, and by the gas storage part that gas line is communicated with described pressurization gas producer, be provided with pressure sensor at these gas line two ends and gas adds/valve; Described liquid storage part is communicated with described microdriver by liquid-transport pipe-line, is provided with liquid fuel and adds/valve and safety valve on the liquid-transport pipe-line two ends near the liquid storage part, also is provided with diaphragm valve, filter and electromagnetic valve on this liquid-transport pipe-line successively.
The principle of work of pressurization gas producer is to use microheater that pharmaceutical chemicals is added thermolysis and produces gas, it is communicated with fuel tank by gas line, fuel tank is played the effect of plenum, a part of liquid in fuel tank is consumed, after pressure reduces, the pressurization gas producer produces gas, makes the pressure recovery predetermined value; Fuel tank can be for spherical or cylindrical, the centre is divided into two halves by a lax and whippy barrier film, barrier film one side stock solution fluid fuel, and opposite side is communicated with the pressurization gas producer, the pressed gas that the pressurization gas producer produces is pressed into propelling unit with required liquid fuel; The fuel tank pressure inside can be detected by pressure sensor, and the quantity of pressurization gas producer and microdriver can be single or multiple according to the concrete needs of micro-nano satellite.
On the described liquid-transport pipe-line, be provided with restrictor between described filter and the electromagnetic valve.When needs change microdriver thrust size, can realize by the size of regulating flow that is provided with of restrictor.
Described pressurization gas producer is a plurality of, and is communicated with described gas line respectively.The pressurization gas producer is a plurality of, can be the fuel tank supercharging simultaneously, and a plurality of pressurization gas producers are respectively shared a part of pharmaceutical chemicals powder, only need very little heating power just can be heated to dissociation temperature; Redundant design increases system reliability, and when a pressurization gas producer lost efficacy, the normal pressurization gas producer of other situation still can make system's supercharging.
Poured carbon dioxide in the gas storage part in described fuel tank in advance.Charge into the carbon dioxide of certain pressure in the gas storage part in fuel tank in advance, help to reduce the interior drug dosage of pressurization gas producer.
Described pressurization gas producer comprises leakproof tank and top cover, be provided with the powder charge bucket in this leakproof tank, be filled with volatile pharmaceutical chemicals in the powder charge bucket, and be used for temperature booster, decompose generation gas after this volatile pharmaceutical chemicals is heated described volatile pharmaceutical chemicals heating.The basic functional principle of pressurization gas producer is that temperature booster heats volatile pharmaceutical chemicals, and pharmaceutical chemicals is heated temperature build-up and promptly decomposes generation gas after to a certain degree.
Be folded with adiabatic sealing block between described temperature booster and the described top cover, the sealing piece is the middle cylinder that has through hole, be equipped with lead screw in through hole, the shell of this lead screw and temperature booster is integrally welded, stretches out in lead screw on the part of top cover to be provided with clamp nut; The power lead of described temperature booster and thermocouple wire pass described top cover by through hole, described temperature booster near the powder charge bucket and with volatile pharmaceutical chemicals closed contact.Temperature booster is put in the middle of the leakproof tank, need power lead to be drawn out to external container, but guarantee the air-tightness of container again, therefore between temperature booster and top cover, accompany not only a thermal insulation but also sealable adiabatic sealing block, this thermal insulation sealing block can be polytetrafluoroethylene and makes, can anti-200 to 300 degrees centigrade high temperature, by lead screw and nut temperature booster, adiabatic sealing block and top cover are closely linked, like this, the power lead of temperature booster and thermocouple wire make a call in top cover that two apertures are drawn and the air-tightness that do not influence leakproof tank has reached the leak free effect.
On described adiabatic sealing block and end face that described top cover contacts, also have the seal groove that is used to settle seal ring.Seal ring the further sealing effectiveness that has guaranteed in the leakproof tank is set.
The composition of described volatile pharmaceutical chemicals comprises NH
4HCO
3NH
4HCO
3Decompose when being heated to 80 ℃ of left and right sides and produce carbon dioxide, ammonia G﹠W.
On the inwall of described leakproof tank, be provided with the porous diatomite layer.Because NH
4HCO
3Solid itself has certain volatility, volatility is stronger after particularly being heated, work has after a period of time on the inwall that the sub-fraction solid condenses in leakproof tank, in order to improve the degree of utilization of ammonium bicarbonate, by one deck porous diatomite layer is set, this layer becomes acid loaded article through the treatment process of dipping acid solution (as phosphoric acid etc.), oven dry, makes the NH that volatilizes
4HCO
3With acid diatom earth the acid-base neutralization reaction taking place promptly emits CO
2Pressurization gas; Another effect of diatomite layer is to play certain adiabatic heat-insulation effect, reduces heat dissipation, thereby reduces the micro-nano satellite energy consumption.
On the bottom of described powder charge bucket or sidewall, be installed on spring.Because NH4HCO3 all becomes gas and water after decomposing, decompose no residue, the volatile pharmaceutical chemicals of being close to temperature booster decomposes disappearance at first, if do not take certain measure that remaining medicine and temperature booster are in contact with one another, causes heat conduction bad, heat dissipation is serious, for the bottom at the powder charge bucket is mounted with spring, after the volatile pharmaceutical chemicals of contact heater decomposes disappearance, under the elastic force effect of spring, the powder charge bucket is continued and the temperature booster closed contact remaining medicine by jack-up; Spring is installed on bottom and the sidewall and helps shortening the length of gas generator on the other hand, thereby reduces system bulk and weight.
The present invention compared with prior art, have following advantage: this miniature propulsion system has been broken away from traditional liquid fuel satellite propulsion system and has been adopted high-pressure gas bottle that fuel is pressurizeed, the defective of structure heaviness, be specially adapted in the middle of the micro-nano satellite, various aspects of performance is better than the miniature propulsion system of blue gas; This system can satisfy the requirement that the micro-nano satellite volume is little, in light weight, energy consumption is low.
Description of drawings
Fig. 1 is for forming scheme drawing for micro liquid fuel propulsion system of the present invention;
Fig. 2 is a pressurization gas producer inner structure scheme drawing;
Description of reference numerals: 1, the pressurization gas producer, 2, pressure sensor, 3, gas adds/valve, 12, microdriver, 4, fuel tank, 41, gas storage part, 42, the liquid storage part, 5, barrier film, 6, liquid fuel adds/valve, 7, safety valve, 8, diaphragm valve, 9, filter, 10, restrictor, 11, electromagnetic valve, 13, gas line, 14, liquid-transport pipe-line, 101, top cover, 102, leakproof tank, 103, the porous diatomite layer, 104, lead screw, 1041, shell, 105, clamp nut, 106, power lead, 107, thermocouple wire, 108, adiabatic sealing block, 1081, seal groove, 109, temperature booster, 110, spring, 111, the powder charge bucket, 112, volatile pharmaceutical chemicals, 118, through hole, 1012, the coping screw hole, 1021, the container screw hole, 1022, settle the seal groove of seal ring, 1081, seal groove.
The specific embodiment
Below in conjunction with the drawings and specific embodiments content of the present invention is described in further details.
Embodiment:
See also shown in Figure 1, the miniature propulsion system of liquid fuel of the present invention mainly comprises: pressurization gas producer 1, microdriver 12, for microdriver 12 provides the fuel tank 4 of liquid fuel, and pressurization gas producer 1 is used for fuel tank 4 plenums; Be separated into the liquid storage part 42 of storage of liquids fuel in this fuel tank 4 by barrier film 5, and the gas storage part 41 that is communicated with pressurization gas producer 1 by gas line 13, for reducing the drug dosage in the pressurization gas producer, in the gas storage part 41 of fuel tank 4, poured carbon dioxide in advance, the effect of barrier film 5 is that liquid fuel and pressurization gas are separated, can make liquid not carry bubble secretly under the weightlessness of space state discharges smoothly, be provided with pressure sensor 2 at these gas line 13 two ends and gas adds/valve 3, pressure signal imports control circuit into and controls 1 heating of pressurization gas producer and produces gas, pressure increases thereupon, can on the control circuit of system, set a certain force value, after the liquid fuel in the diaphragm type fuel tank 4 is consumed a part, the pressure of being sensed fuel tank 4 by pressure sensor 2 reduces, and by the break-make of pressure controller according to the electric heater power supply of the big or small control gaseous producer of pressure signal, be specially: when system's internal pressure during less than setting value, heater power source is connected, the pressurization gas producer begins to decompose generation gas, and intrasystem pressure is raise; When pressure surpassed setting value, control circuit disconnected the power supply of temperature booster, stops to heat aerogenesis, keeps setting pressure, can make fuel tank 4 keep certain pressure thus, and like this, fuel tank 4 also can be microdriver 12 constant voltages supply liquid fuel; Liquid storage part 42 is communicated with microdriver 12 by liquid-transport pipe-line 14, adding/valve 6 and safety valve 7, also be provided with diaphragm valve 8, filter 9 and electromagnetic valve 11 on this liquid-transport pipe-line 14 successively near being provided with liquid fuel on liquid-transport pipe-line 14 two ends of liquid storage part 42.
Further, the size of thrust for a change is on the liquid-transport pipe-line 14, be provided with restrictor 10 between filter 9 and the electromagnetic valve 11.
For increasing system reliability, pressurization gas producer 1 can be provided with a plurality of, and is communicated with gas line 13 respectively.
Pressurization gas producer 1 comprises leakproof tank 102, be provided with top cover 101 at leakproof tank 102 opening parts, be provided with powder charge bucket 111 in this leakproof tank 102, be filled with volatile pharmaceutical chemicals 112 in the powder charge bucket 111, and being used for temperature booster 109 to 112 heating of volatile pharmaceutical chemicals, this volatile pharmaceutical chemicals 112 back that is heated is decomposed and is produced gas.
Be folded with adiabatic sealing block 108 between temperature booster 109 and the top cover 101, sealing piece 108 is the middle cylinder that has through hole 118, in through hole 118, be equipped with lead screw 104, this lead screw 104 is integrally welded with the shell 1041 of temperature booster 109, stretches out in lead screw 104 on the part of top cover 101 to be provided with clamp nut 105; The power lead 106 and the thermocouple wire 107 of temperature booster 109 pass top cover 101 by through hole 118, with extraneous power supply power taking, temperature booster 109 near powder charge buckets 111 and with volatile pharmaceutical chemicals 112 closed contacts, guaranteed to make full use of the heat energy of temperature booster 109, easier volatilization after making volatile pharmaceutical chemicals 112 be heated also has the seal groove 1081 or 1022 that is used to settle seal ring on adiabatic sealing block 108 and end face that top cover 101 contacts.
The composition of volatile pharmaceutical chemicals 112 comprises NH in the present embodiment
4HCO
3, also can be other pharmaceutical chemicalss certainly, have the heating back characteristic of volatilization easily as long as guarantee it; The principle of work of pressurization gas producer just is to use microheater that pharmaceutical chemicals (as ammonium bicarbonate) is added thermolysis and produces gas.Reaction formula is:
After guaranteeing that volatile pharmaceutical chemicals 112 reaction volatilizations that powder charge bucket 111 the superiors contacts with temperature booster 109 finish, remaining medicine energy better contact with temperature booster 109 and be heated, and is installed on spring 110 on the bottom of powder charge bucket 111 and sidewall; Because the NH that buys
4HCO
3Be generally soft white powder, so can be when packing powder charge bucket 111 into NH
4HCO
3Powder 112 is pressed tight, can make full use of the space of powder charge bucket 111 like this, can load more medicine, reduces the volume of pressurization gas producer 1; And the stress that tight volatile pharmaceutical chemicals stands up to spring 110 is unlikely to make in the middle of the volatile up to one's neck at the very start pharmaceutical chemicals 112 of temperature booster 109.
For making full use of the remaining solid on the inwall that condenses in leakproof tank after ammonium bicarbonate reacts, on the inwall of leakproof tank 102, be provided with porous diatomite layer 103, it can continue to discharge CO with ammonium bicarbonate generation neutralization reaction
2Pressurization gas.
Offering coping screw hole 1012 on top cover 101, offer container screw hole 1021 on leakproof tank 102, works in coordination top cover 101 and container 102 usefulness screws is locked in this two-screw hole.
Microdriver can be the micro liquid fuel rocket engine in the present embodiment, or the miniature electrical heating type propelling unit of making of MEMS technology, as the liquid vaporation-type microdriver (VLM) of chip type etc.
Above-listed detailed description is at the specifying of possible embodiments of the present invention, and this embodiment is not in order to limiting claim of the present invention, and the equivalence that all the present invention of disengaging do is implemented or change, all should be contained in the claim of this case.
Claims (10)
1, a kind of micro liquid fuel propulsion system that is used for micro-nano satellite, it is characterized in that: include pressurization gas producer (1), microdriver (12), be the fuel tank (4) that microdriver (12) provides liquid fuel, described pressurization gas producer (1) is used for described fuel tank (4) plenum; Be separated into the liquid storage part (42) of storage of liquids fuel in this fuel tank (4) by barrier film (5), and the gas storage part (41) that is communicated with described pressurization gas producer (1) by gas line (13), be provided with pressure sensor (2) at this gas line (13) two ends and gas adds/valve (3); Described liquid storage part (42) is communicated with described microdriver (12) by liquid-transport pipe-line (14), on liquid-transport pipe-line (14) two ends, be provided with liquid fuel and add/valve (6) and safety valve (7), also be provided with diaphragm valve (8), filter (9) and electromagnetic valve (11) on this liquid-transport pipe-line (14) successively near liquid storage part (42).
2, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 1 is characterized in that: go up at described liquid-transport pipe-line (14), be provided with restrictor (10) between described filter (9) and the electromagnetic valve (11).
3, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 2 is characterized in that: described pressurization gas producer (1) is a plurality of, and is communicated with described gas line (13) respectively.
4, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 3 is characterized in that: poured carbon dioxide in advance in the gas storage part (41) of described fuel tank (4).
5, as arbitrary described micro liquid fuel propulsion system that is used for micro-nano satellite in the claim 1 to 4, it is characterized in that: described pressurization gas producer (1) comprises leakproof tank (102) and top cover (101), be provided with powder charge bucket (111) in this leakproof tank (102), be filled with volatile pharmaceutical chemicals (112) in the powder charge bucket (111), and being used for temperature booster (109) to described volatile pharmaceutical chemicals (112) heating, this volatile pharmaceutical chemicals (112) back that is heated is decomposed and is produced gas.
6, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 5, it is characterized in that: be folded with adiabatic sealing block (108) between described temperature booster (109) and the described top cover (101), sealing piece (108) has the cylinder of through hole (118) for the centre, in through hole (118), be equipped with lead screw (104), the shell (1041) of this lead screw (104) and temperature booster (109) is integrally welded, stretches out in lead screw (104) on the part of top cover (101) to be provided with clamp nut (105); The power lead (106) and the thermocouple wire (107) of described temperature booster (109) pass described top cover (101) by through hole (118), described temperature booster (109) near powder charge bucket (111) and with volatile pharmaceutical chemicals (112) closed contact.
7, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 6 is characterized in that: also have the seal groove (1081) that is used to settle seal ring on described adiabatic sealing block (108) and end face that described top cover (101) contacts.
8, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 7 is characterized in that: the composition of described volatile pharmaceutical chemicals (112) comprises NH
4HCO
3
9, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 8 is characterized in that: be provided with porous diatomite layer (103) on the inwall of described leakproof tank (102).
10, the micro liquid fuel propulsion system that is used for micro-nano satellite as claimed in claim 9 is characterized in that: be installed on spring (110) on the bottom of described powder charge bucket (111) and sidewall.
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| CNA2008102202801A CN101445160A (en) | 2008-12-23 | 2008-12-23 | Micro liquid fuel propulsion system used in micro-nano satellite |
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| CNA2008102202801A CN101445160A (en) | 2008-12-23 | 2008-12-23 | Micro liquid fuel propulsion system used in micro-nano satellite |
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| CN107860446A (en) * | 2017-12-08 | 2018-03-30 | 上海悟道机电设备有限公司 | The equipment that a kind of flow is weighed |
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| CN109455313A (en) * | 2018-11-15 | 2019-03-12 | 河北工业大学 | For space propultion from pressurized fuel case |
| CN109552668A (en) * | 2018-11-23 | 2019-04-02 | 北京精密机电控制设备研究所 | A kind of array arm load propeller change propulsive control system |
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| CN110697082A (en) * | 2019-09-03 | 2020-01-17 | 陕西蓝箭航天技术有限公司 | Attitude control power system |
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