CN101907041B - Propane liquid gas micro propulsion device suitable for micro-nano satellite - Google Patents
Propane liquid gas micro propulsion device suitable for micro-nano satellite Download PDFInfo
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- CN101907041B CN101907041B CN 201010238400 CN201010238400A CN101907041B CN 101907041 B CN101907041 B CN 101907041B CN 201010238400 CN201010238400 CN 201010238400 CN 201010238400 A CN201010238400 A CN 201010238400A CN 101907041 B CN101907041 B CN 101907041B
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Abstract
The invention aims to provide a propane liquid gas micro propulsion device suitable for a micro-nano satellite. The device comprises an exhaust valve, a first propellant storage box, a second propellant storage box, a first heat-conducting module, a second heat-conducting module, a pressure reducer, a buffer tank, a safety valve, a thruster, a pressure sensor A, a pressure sensor B, a filter and a control circuit box. Propane serves as a propellant in the micro propulsion device, so the micro propulsion device is non-toxic and pollution-free; the micro propulsion device has the advantages of simple structure, low quality, low power consumption and high reliability; mounted on a mounting partition board, the micro propulsion device is convenient to be mounted and replaced; and because of no excessive relation and interference with other parts of the satellite, the micro propulsion device is convenient to be replaced and maintained.
Description
Technical field
The invention belongs to the little Push Technology of liquid gas field, is a kind of liquefied propane gas advancing means that is applicable to micro-nano satellite specifically.
Background technique
Manufacturing according to actual needs grapefruit satellite is a trend in the present age, and its purpose mainly is in order to save cost.Usually the satellite that with weight is l00kg～500kg is called moonlet, and weight is that the satellite of 10kg～100kg is called little satellite, receives satellite and the satellite below the l0kg is called.The following satellite of 1kg is called the skin satellite.The main feature of micro-nano satellite is development plan compact (cycle is short), shape is little, function is strong and cost is low.Closely during the last ten years, the high performance modern microsatellite of countries in the world successfully is applied to satellite can applicable almost every field, and more typical using scope is at aspects such as global communication, earth environment monitoring, military surveillance and military confrontations.In addition.The astronaut leaves the unit astrovehicle that Space laboratory or space shuttle carry out the space maneuvering flight, also a kind of moonlet at last.The cold air advancing means is a kind of advancing means commonly used, microsatellite can adopt cold air as the propellant agent of its advancing means, it is the significant development of the basic industry such as microelectronics, micromechanics, lightweight composite materials and ultraprecise processing that have benefited from developing rapidly, numerous difficult problems are broken through, so that advancing means is improving constantly aspect reliability, the practicability, substantially satisfied the whole requirement of microsatellite, also so that the application area of microsatellite constantly expand.
Traditionally, it is the cold gas micro propulsion device of nitrogen that the micro propulsion device of microsatellite is generally selected propellant agent, but for the less micro-nano satellite of quality volume, the restriction on the volume wants the restriction of specific mass more important.The density specific impulse of micro-nano satellite micro propulsion device (momentum of micro propulsion device per unit volume) is equally important with specific impulse.Than traditional nitrogen cold gas micro propulsion device, the propellant agent of liquid gas micro propulsion device stores with liquid form, from thruster, spray with gas form through gasification, therefore the propellant agent of liquid gas micro propulsion device has the advantage of the density higher than pressurized gas, can access higher density specific impulse.The propellant agent storage pressure of liquid gas micro propulsion device also will be lower than pressurized gas, and the Security of micro propulsion device improves greatly like this.For example, in the situation that some high pressure nitrogens can not satisfy particular requirement, liquid gas micro propulsion device can meet the demands, and needn't use more complicated and expensive hydrazine micro propulsion device.But liquid gas is the propellant agent of advancing means finishes the work owing to becoming gas through a gasification, therefore need to absorb amount of heat, if micro propulsion device thermal control measure is bad, then have the part propellant agent and spray from thruster with liquid form, can cause the reduction of micro propulsion device service behaviour and the waste of propellant agent.
Summary of the invention:
The object of the present invention is to provide a kind of micro propulsion device that is applicable to micro-nano satellite, be used for micro-nano satellite is carried out attitude control and track is kept and controlled, and for the requirement of micro-nano satellite to the low quality of advancing means, simple in structure, low power consumption, high reliability.The heat that the thermal source of propellant agent gasification can directly utilize the inside satellite heat-dissipating part to distribute, and therefore to select temperature requirements to satellite be not that very high propane is as the propellant agent of advancing means.
A kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite of the present invention comprises adding valve, the first propellant tank, the second propellant tank, the first heat conducting module, the second heat conducting module, decompressor, surge tank, safety valve, thruster, pressure transducer A, pressure transducer B, filter and control wiring box.
Be separately installed with the first heat conducting module and the second heat conducting module on the first propellant tank and the second propellant tank, the first heat conducting module and the second heat conducting module pass through pipeline connection.
The second heat conducting module is connected with safety valve by pipeline, and safety valve is connected with the tank four-way, and the tank four-way is connected with the first propellant tank, the second propellant tank and inflation threeway by pipeline, also is connected with pressure transducer A in the inflation threeway and adds valve.Add valve by unlatching, the liquid petroleum gas (liquid propane gas) propellant agent in the external world can be loaded in the first propellant tank and the second propellant tank, load to close after complete and add valve.Also can add valve by unlatching discharges propane propellant agent remaining in the first propellant tank, the second propellant tank.Pressure transducer A is used for the propane storage pressure in the first propellant tank and the second propellant tank is monitored, and when propellant pressure reaches design load, closes and adds valve, the propellant agent sand off.When opening the safety-valve, the liquid petroleum gas (liquid propane gas) propellant agent can flow out in the first propellant tank, the second propellant tank under pressure, and along with the variation of pressure, begins gasification, and enter successively in the first heat conducting module and the second heat conducting module.Described the first heat conducting module and the second heat conducting module indoor design have the U-shaped pipeline, not vaporized liquid petroleum gas (liquid propane gas) propellant agent flows in the U-shaped pipeline, absorb the heat that the first heat conducting module and the second heat conducting module are obtained by the inside satellite heat-dissipating part, not vaporized propane propellant agent is further gasified, form propane gas.
The first heat conducting module is connected with decompressor, surge tank, filter in turn by pipeline; Filter is connected with pressure transducer B by threeway A, and threeway A upward also is connected with the propelling four-way by pipeline.Propane propellant agent after most of gasification and the not vaporized propane propellant agent of fraction are entered in the decompressor by the first heat conducting module and reduce pressure, pressure drop process through decompressor, even whole propane propellant agents gasification, guarantee that thus propellant agent fully gasifies, so far the propellant agent gasification is finished.
Advance between two ports in the four-way and form the loop by pipeline, advancing on the four-way by supply air line connection thruster; Solenoid valve is housed on the thruster.Described loop is that thruster is supplied with the gaseous propane propellant agent as the propellant feed pipeline.Open the solenoid valve of the thruster that needs work, then the propane propellant agent can spray from thruster, thereby produces thrust.
The control wiring box is connected with safety valve, pressure transducer A, pressure transducer B and thruster by cable, be used for receiving the control signal that satellite sends so control safety valve and the control thruster on the opening or closing of solenoid valve, and to the job information of satellite feedback micro propulsion device.
The invention has the advantages that:
(1) propane liquid gas micro propulsion device of the present invention is simple in structure, and the device total quality is little, and has low cost, high reliability, low power consumption, pollution-free and safe advantage;
(2) propane liquid gas micro propulsion device of the present invention is designed with the installation dividing plate, is convenient to installation and the replacement of micro propulsion device, with other parts of satellite without significant correlation and interference.
Description of drawings
Fig. 1 is propane liquid gas micro propulsion device structure plan view of the present invention;
Fig. 2 is that propane liquid gas micro propulsion device of the present invention is installed mounting structure plan view on the dividing plate at Hexagon;
Fig. 3 is that propane liquid gas micro propulsion device of the present invention is installed mounting structure structure side view on the dividing plate at Hexagon.
Among the figure:
Embodiment:
A kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite of the present invention, mainly comprise and add valve 1, the first propellant tank 6, the second propellant tank 7, the first heat conducting module 8, the second heat conducting module 9, decompressor 10, surge tank 11, safety valve 5, thruster 18, pressure transducer A3, pressure transducer B13, filter 12 and control wiring box 19, as shown in Figure 1, above-mentioned parts are installed in and install on the dividing plate 20.The shape that dividing plate 20 is installed is identical with the satellite sectional shape of required installation micro propulsion device, does not have too much contact and interfere with other parts of satellite, be convenient to thus micro propulsion device installation, replace and repairing.The opposite side of described installation dividing plate 20 is installed control wiring box 19.
The first propellant tank 6 and the second propellant tank 7 are used for loading the propane propellant agent, the propane propellant agent is stored in the first propellant tank 6 and the second propellant tank 7 with liquid form, the pressure maximum that stores reaches 0.84MPa, filling propane propellant agent gross mass is 0.6kg, the work requirements in 1 year of micro propulsion device of the present invention can be satisfied, and the quality of propane propellant agent can be changed according to different mission requirementses.Be separately installed with the first heat conducting module 8 and the second heat conducting module 9 on the first propellant tank 6 and the second propellant tank 7, the first heat conducting module 8 and the second heat conducting module 9 have respectively a propellant agent entrance and a propellant agent outlet, and the propellant agent outlet of described the second heat conducting module 9 is passed through pipeline connection with the propellant agent entrance of the first heat conducting module 8.The first propellant tank 6 and the second propellant tank 7 are cylindrical tank, be convenient to fix at installation dividing plate 20, and Volume Loss are little.
The propellant agent entrance of the second heat conducting module 9 is connected with safety valve 5 by pipeline, safety valve 5 is connected with tank four-way 4, be connected with the first propellant tank 6, the second propellant tank 7 and inflation threeway 2 by pipeline on the tank four-way 4, also be connected with pressure transducer A3 in the inflation threeway 2 and add valve 1.After unlatching adds valve 1, extraneous liquid petroleum gas (liquid propane gas) propellant agent can be loaded in the first propellant tank 6 and the second propellant tank 7 by threeway 2 and tank four-way 4 successively, in the process of filling, pressure transducer A3 is used for the propane storage pressure in the first propellant tank 6 and the second propellant tank 7 is monitored, according to different mission requirementses, when propellant pressure reaches design load, close and add valve 1, the propellant agent sand off.In micro propulsion device using process of the present invention, add valve 1 and close; After using end, also can add valve 1 by unlatching propane propellant agent remaining in two propellant tanks is discharged.Safety valve 5 is used for making propane propellant agent and other line isolation of micro propulsion device in the propellant tank after the filling.The first heat conducting module 8 contacts with the radiator of the second heat conducting module 9 with satellite thermal control unit, obtains heat by the inside satellite heat-dissipating part.Because liquid propane propellant agent has certain thermal capacitance, heat can be stored, so the temperature of liquid petroleum gas (liquid propane gas) propellant agent can raise; Because the liquid petroleum gas (liquid propane gas) propellant receptacle exists in first propellant tank 6 and the second propellant tank 7 of elevated pressures, and external connecting pipe road pressure is vacuum, therefore when opening the safety-valve 5 the time, the liquid petroleum gas (liquid propane gas) propellant agent can be under pressure from the first propellant tank 6, the 7 interior outflows of the second propellant tank, and along with the variation of pressure, begin gasification, and enter successively the second heat conducting module 9 and the first heat conducting module 8 by safety valve 5.Described the first heat conducting module 8 and 9 indoor designs of the second heat conducting module have the U-shaped pipeline, not vaporized liquid petroleum gas (liquid propane gas) propellant agent flows in the U-shaped pipeline, absorb the heat on the first heat conducting module 8 and the second heat conducting module 9, not vaporized propane propellant agent is further gasified.
The propellant agent outlet of the first heat conducting module 8 is connected with decompressor 10, surge tank 11 and filter 12 in turn by pipeline, propane propellant agent after most of gasification and the not vaporized propane propellant agent of fraction are entered in the decompressor 10 by the first heat conducting module 8 and further reduce pressure, pressure drop process through decompressor 10, make whole propane propellant agent gasifications, guarantee that thus propellant agent fully gasifies, so far the propellant agent gasification is finished.Also can make the propane propellant pressure drop to the desired pressure of thruster 18 entrances from 0.84MPa by decompressor 10.Decompressor 10 post-decompression propane gas enter surge tank 11, make propellant pressure keep stable, guarantee that propellant agent can enter thruster 18 stably, and when micro propulsion device was worked, fluctuation can not appear in the pressure of propellant agent.Gasification and steadily after the propane propellant agent enter into filter 12 and filter, because thruster 18 throat diameters are minimum, even trickle impurity also can cause thruster 18 to stop up, therefore filter 12 is set to avoid existing impurity to stop up thruster 18 throats in the propane gas.
Connect a threeway A14 on the filter 12, be connected with pressure transducer B13 by threeway A14, and upper also being connected with by pipeline of threeway A14 advances four-way 17.Pressure transducer B13 is used for monitoring the pressure of propane propellant agent.Advance between two ports in the four-way 17 and form the loop by pipeline, be connected with at least one threeway B15 in the loop, this loop is the propellant feed pipeline.Advancing on the four-way 17 and all can connect a thruster 18 by supply air line 16 on the threeway B15.If need to when diverse location increases thruster 18, then in the propellant feed pipeline, increase threeway B15, connect thruster 18 at threeway B15 by supply air line 16; If need to be when same position increases thruster 18, the pipeline connecting parts that then connects with a plurality of ports at supply air line 16 such as threeway and four-way etc., thereby connects a plurality of thrusters 18.Propane propellant agent part after the gasification is by advancing four-way 17 to enter into and the supply air line 16 that advances four-way 17 to link to each other, another part is by advancing four-way 17 to enter into supply pipeline 16, enter into the supply air line 16 that links to each other with threeway B15 by the threeway B15 in the supply pipeline 16, finally all enter into corresponding thruster 18 by supply air line 16.On the thruster 18 solenoid valve is housed.
Advancing means is according to satellite 3 d pose regulation and control requirement, micro propulsion device need to be finished the control of satellite stages attitude and track is kept and controlled, determine thus the quantity of the thruster 18 that connects at supply air line, and determined that each thruster 18 is at the location layout of installing on the dividing plate 20.The inlet pressure of above-mentioned thruster 18 is relevant with its thrust requirement and size design, and thruster 18 thrusts that are designed to herein are 50mN, and throat dimension is 0.4mm, and divergence ratio is 100, and inlet pressure is designed to 0.2MPa.
Solenoid valve before work on assurance safety valve 5 and the thruster 18 cuts out, and prevents that propellant agent from flowing out naturally.
When end-of-job, at first close the solenoid valve of thruster 18, then closed safe valve 5, reason is to need to keep certain pressure before the solenoid valve of thruster 18, prevents to leak.
The below comes to come quantity and the location arrangements of thruster among the present invention are described further by an embodiment.
As shown in Figure 2, dividing plate 20 is installed is adopted hexagonal dividing plate, the propellant agent entrance that the first heat conducting module 8 and the second heat conducting module 9, the first heat conducting modules 8 are installed respectively on the first propellant tank 6 and the second propellant tank 7 is connected by pipeline with the propellant agent outlet of the second heat conducting module 9.
The propellant agent entrance of the second heat conducting module 9 is connected with safety valve 5 by pipeline, safety valve 5 is connected with tank four-way 4, be connected with the first propellant tank 6, the second propellant tank 7 and inflation threeway 2 by pipeline on the tank four-way 4, also be connected with pressure transducer A3 in the inflation threeway 2 and add valve 1.
The propellant agent outlet of the first heat conducting module 8 is connected with decompressor 10, surge tank 11 and filter 12 in turn by pipeline, and filter 12 is connected with pressure transducer B13 by threeway A14, and upper also being connected with by pipeline of threeway A14 advances four-way 17.
Advance between two ports in the four-way 17 and form the loop by pipeline, be connected with 5 threeway B15 in the loop, each threeway B15 is connected with thruster 18 by supply air line.If Hexagon is installed the interior angle place of dividing plate 20 and is respectively a, b, c, d, e, f, wherein a and d, b and e, c and f for this reason regular hexagon the diagonal angle of dividing plate 20 is installed, therefore will be arranged in a and d, b and e, c and f place at thruster 18, and respectively be provided with two thrusters 18 at a and d place, b and e, c and f place respectively arrange a thruster 18, and the thruster 18 at b and e and c and f place is separately positioned on the both sides that dividing plate is installed, as shown in Figure 3, make thus the propane micro propulsion device provide thrust and control moment for satellite along three axial directions of satellite orthogonal coordinate system.
Claims (6)
1. a propane liquid gas micro propulsion device that is applicable to micro-nano satellite comprises adding valve, propellant tank, decompressor, surge tank, safety valve, thruster; It is characterized in that: also comprise the first heat conducting module, the second heat conducting module, pressure transducer A, pressure transducer B, filter and control wiring box; And propellant tank is the first propellant tank, the second propellant tank; Above-mentioned parts are arranged in to be installed on the dividing plate;
Be separately installed with the first heat conducting module and the second heat conducting module on the first propellant tank and the second propellant tank, be connected by pipeline between the first heat conducting module and the second heat conducting module;
The second heat conducting module also is connected with safety valve by pipeline, safety valve is connected with the tank four-way, be communicated with the first propellant tank, the second propellant tank and inflation threeway by pipeline on the tank four-way, also be connected with pressure transducer A in the inflation threeway and add valve;
The first heat conducting module is connected with decompressor, surge tank, filter in turn by pipeline; Filter by threeway A and pressure transducer B be connected four-way to be connected;
Advance between two ports in the four-way and form the loop by pipeline, connect thruster by supply air line on the 4th port; Solenoid valve is housed on the thruster;
The control wiring box is connected with safety valve, pressure transducer A, pressure transducer B and thruster by cable, be used for receiving the control signal that satellite sends so control safety valve and the control thruster on the opening or closing of solenoid valve, and to the job information of satellite feedback micro propulsion device.
2. a kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite as claimed in claim 1, it is characterized in that: described the first propellant tank and the second propellant tank are cylindrical tank.
3. a kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite as claimed in claim 1, it is characterized in that: be connected with at least one threeway B in the described loop, threeway B connects thruster by supply air line.
4. a kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite as claimed in claim 1, it is characterized in that: filling liquid petroleum gas (liquid propane gas) propellant agent in described the first propellant tank and the second propellant tank, filling propane propellant agent gross mass is 0.6kg, and the pressure of storage is 0.84MPa.
5. a kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite as claimed in claim 1, it is characterized in that: described thruster thrust is 50mN, and throat dimension is 0.4mm, and divergence ratio is 100, and inlet pressure is designed to 0.2MPa.
6. a kind of propane liquid gas micro propulsion device that is applicable to micro-nano satellite as claimed in claim 1 is characterized in that: described the first heat conducting module and the second heat conducting module be inner to be the U-shaped pipeline.
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| CN 201010238400 CN101907041B (en) | 2010-07-23 | 2010-07-23 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
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| CN 201010238400 CN101907041B (en) | 2010-07-23 | 2010-07-23 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
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| CN101907041A CN101907041A (en) | 2010-12-08 |
| CN101907041B true CN101907041B (en) | 2013-04-03 |
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