CN101907041A - 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
- Publication number
- CN101907041A CN101907041A CN2010102384008A CN201010238400A CN101907041A CN 101907041 A CN101907041 A CN 101907041A CN 2010102384008 A CN2010102384008 A CN 2010102384008A CN 201010238400 A CN201010238400 A CN 201010238400A CN 101907041 A CN101907041 A CN 101907041A
- Authority
- CN
- China
- Prior art keywords
- micro
- propellant
- propulsion device
- heat conducting
- tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Filling Or Discharging Of Gas Storage Vessels (AREA)
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 grapefruit satellite according to actual needs is a trend in the present age, and its purpose mainly is in order to save cost.Usually the satellite that with weight is 100kg~500kg is called moonlet, and weight is that the satellite of 10kg~100kg is called little satellite, receives satellite and the satellite below the 10kg is called.The following satellite of 1kg is called the skin satellite.The main feature of micro-nano satellite is a development plan compactness (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 can a kind of at last moonlet.The cold air advancing means is a kind of advancing means commonly used, microsatellite can adopt the propellant agent of cold air as 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 obtain breaking through, make advancing means improve constantly aspect reliability, the practicability, substantially satisfy the whole requirement of microsatellite, also made 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 littler micro-nano satellite of quality volume, the qualification on the volume wants the qualification 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, can not satisfy at some high pressure nitrogens under the situation of particular requirement, liquid gas micro propulsion device can meet the demands, and needn't use complicated and expensive more 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 a large amount of heats, if micro propulsion device thermal control measure is bad, then have the part propellant agent and spray from thruster, can cause the reduction of micro propulsion device service behaviour and the waste of propellant agent with liquid form.
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 at 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 be distributed, and therefore to select temperature requirements to satellite for use be not the very high propane propellant agent as 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, first propellant tank, second propellant tank, first heat conducting module, 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 first heat conducting module and second heat conducting module on first propellant tank and second propellant tank, first heat conducting module and second heat conducting module pass through pipeline connection.
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 first propellant tank, second propellant tank and inflation threeway by pipeline, also is connected with pressure transducer B 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 first propellant tank and second propellant tank, filling need be closed after finishing and be added valve.Also can add valve by unlatching discharges propane propellant agent remaining in first propellant tank, second propellant tank.Pressure transducer A is used for the propane storage pressure in first propellant tank and 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 first propellant tank, second propellant tank under pressure, and along with the variation of pressure, begins gasification, and enter successively in first heat conducting module and second heat conducting module.Described 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 first heat conducting module and second heat conducting module are obtained by the inside satellite heat-dissipating part, not vaporized propane propellant agent is further gasified, form propane gas.
First heat conducting module is connected with decompressor, surge tank, filter in turn by pipeline; Filter is connected with pressure transducer A 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 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, advancing on the four-way by supply air line connection thruster by pipeline; 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, design has the installation dividing plate, is convenient to the installation and the replacement of micro propulsion device, does not have significant correlation and interference with other parts of satellite.
Description of drawings
Fig. 1 is a propane liquid gas micro propulsion device structure plan view of the present invention;
Fig. 2 installs mounting structure plan view on the dividing plate for propane liquid gas micro propulsion device of the present invention at Hexagon;
Fig. 3 installs mounting structure structure side view on the dividing plate for propane liquid gas micro propulsion device of the present invention at Hexagon.
Among the figure:
1-adds valve 2-inflation threeway 3-pressure transducer A 4-tank four-way
The 5-safety valve 6-first propellant tank 7-second propellant tank 8-first heat conducting module
The 9-second heat conducting module 10-decompressor 11-surge tank 12-filter
13-pressure transducer B 14-threeway A 15-threeway B 16-supply air line
17-advances four-way 18-thruster 19-control wiring box 20-that dividing plate is installed
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, first propellant tank 6, second propellant tank 7, first heat conducting module 8, 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 get in touch and interfere with other parts of satellite, be convenient to thus micro propulsion device installation, replace and repairing.The opposite side installation and control circuit box 19 of described installation dividing plate 20.
The propellant agent inlet of 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 first propellant tank 6, 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 first propellant tank 6 and 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 first propellant tank 6 and 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 propane propellant agent remaining in two propellant tanks is discharged by unlatching.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.First heat conducting module 8 contacts with the radiator of 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 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 flow out in first propellant tank 6, second propellant tank 7 under pressure, and along with the variation of pressure, begin gasification, and enter second heat conducting module 9 and first heat conducting module 8 successively by safety valve 5.Described first heat conducting module 8 and 9 indoor designs of 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 first heat conducting module 8 and second heat conducting module 9, not vaporized propane propellant agent is further gasified.
The propellant agent outlet of 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 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 inlets by decompressor 10 from 0.84MPa.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.Propane propellant agent after gasification is also steady enters into filter 12 and filters, 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, and threeway A14 upward also is connected with propelling four-way 17 by pipeline by threeway A14.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 on the threeway B15 by supply air line 16.If need when diverse location increases thruster 18, then in the propellant feed pipeline, increase threeway B15, on threeway B15, connect thruster 18 by supply air line 16; If need when same position increases thruster 18, then on supply air line 16, connect the pipeline connecting parts that has a plurality of ports,, thereby connect a plurality of thrusters 18 as threeway and four-way etc.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 be finished each stage attitude control of satellite and track is kept and controlled, determine the quantity of the thruster 18 that on supply air line, connects thus, 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 leakage.
Come below to come the 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 the Hexagon dividing plate, the propellant agent inlet that first heat conducting module 8 and second heat conducting module, 9, the first heat conducting modules 8 are installed respectively on first propellant tank 6 and second propellant tank 7 is connected by pipeline with the propellant agent outlet of second heat conducting module 9.
The propellant agent inlet of 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 first propellant tank 6, second propellant tank 7 and inflation threeway 2 by pipeline on the tank four-way 4, also be connected with pressure transducer B13 in the inflation threeway 2 and add valve 1.
The propellant agent outlet of 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 A3 by threeway A14, and threeway A14 upward also is connected with propelling four-way 17 by pipeline.
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 are provided with 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 the propane micro propulsion device provide thrust and control moment for satellite thus 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 is characterized in that: comprise adding valve, first propellant tank, second propellant tank, first heat conducting module, second heat conducting module, decompressor, surge tank, safety valve, thruster, pressure transducer A, pressure transducer B, filter and control wiring box; Above-mentioned parts are arranged in to be installed on the dividing plate, and connects by pipeline between the parts that are connected;
Be separately installed with first heat conducting module and second heat conducting module on first propellant tank and second propellant tank, be connected by pipeline between first heat conducting module and second heat conducting module;
Second heat conducting module also is connected with safety valve by pipeline, safety valve is connected with the tank four-way, be communicated with first propellant tank, second propellant tank and inflation threeway by pipeline on the tank four-way, also be connected with pressure transducer B in the inflation threeway and add valve;
First heat conducting module is connected with decompressor, surge tank, filter in turn by pipeline; Filter is connected with the propelling four-way with pressure transducer A by threeway A;
Advance between two ports in the four-way and form the loop, connect thruster by supply air line on the 4th port by pipeline; 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 according to claim 1 propane liquid gas micro propulsion device that is applicable to micro-nano satellite is characterized in that: described first propellant tank and second propellant tank are cylindrical tank.
3. a kind of according to claim 1 propane liquid gas micro propulsion device that is applicable to micro-nano satellite 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 according to claim 1 propane liquid gas micro propulsion device that is applicable to micro-nano satellite, it is characterized in that: filling liquid petroleum gas (liquid propane gas) propellant agent in described first propellant tank and second propellant tank, filling propane propellant agent gross mass is 0.6kg, and the pressure of storage is 0.84MPa.
5. a kind of according to claim 1 propane liquid gas micro propulsion device that is applicable to micro-nano satellite 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 according to claim 1 propane liquid gas micro propulsion device that is applicable to micro-nano satellite is characterized in that: described first heat conducting module and second heat conducting module are inner to be the U-shaped pipeline.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 201010238400 CN101907041B (en) | 2010-07-23 | 2010-07-23 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 201010238400 CN101907041B (en) | 2010-07-23 | 2010-07-23 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
Publications (2)
Publication Number | Publication Date |
---|---|
CN101907041A true CN101907041A (en) | 2010-12-08 |
CN101907041B CN101907041B (en) | 2013-04-03 |
Family
ID=43262594
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN 201010238400 Expired - Fee Related CN101907041B (en) | 2010-07-23 | 2010-07-23 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN101907041B (en) |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102358437A (en) * | 2011-08-08 | 2012-02-22 | 北京控制工程研究所 | Layout method for 10 N thrusters of high orbit satellite platform |
CN103471756A (en) * | 2013-09-05 | 2013-12-25 | 兰州空间技术物理研究所 | Ground measurement method for electric propulsion thrust |
CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
CN105863881A (en) * | 2016-04-06 | 2016-08-17 | 北京航空航天大学 | Miniature thrust generation device capable of being subjected to fuel charging repeatedly and operation method thereof |
CN106184823A (en) * | 2016-07-06 | 2016-12-07 | 浙江大学 | A kind of autonomous vaporization management method and liquefied ammonia micromass culture system |
CN106564623A (en) * | 2016-09-30 | 2017-04-19 | 上海空间推进研究所 | System and method for liquefied gas constant-pressure propulsion of small satellite |
CN107187618A (en) * | 2017-05-27 | 2017-09-22 | 上海航天控制技术研究所 | Gas propellant control system and control method |
CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
CN107514320A (en) * | 2017-07-10 | 2017-12-26 | 北京控制工程研究所 | A kind of micromass culture modular structure based on high pressure frontier technology |
CN108928505A (en) * | 2018-06-28 | 2018-12-04 | 上海卫星工程研究所 | The satellite powered phase method for exhausting controlled using satellite and the rocket pull-off plug signal |
CN109441748A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of thrust integrated system for small-sized hall thruster |
CN109823573A (en) * | 2019-01-22 | 2019-05-31 | 南京航空航天大学 | A kind of propelling integrated solar thermal propulsion system of accumulation of heat-power generation- |
CN110332060A (en) * | 2019-03-22 | 2019-10-15 | 北京蓝箭空间科技有限公司 | Liquid oxygen methane rocket and liquid oxygen methane Rocket tank fall pressure type pressurized design method |
CN110395410A (en) * | 2019-07-04 | 2019-11-01 | 南京理工大学 | Rail control all-in-one micro cold air propulsion system |
CN110562496A (en) * | 2019-08-21 | 2019-12-13 | 上海航天控制技术研究所 | integrated satellite propulsion system |
CN111114834A (en) * | 2019-12-17 | 2020-05-08 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
CN112407337A (en) * | 2020-11-23 | 2021-02-26 | 北京微动航科技术有限公司 | Propulsion system of satellite simulator and satellite simulator |
CN112918705A (en) * | 2021-03-12 | 2021-06-08 | 深圳航天东方红卫星有限公司 | Thermal control system and method of integrated propulsion subsystem |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3807657A (en) * | 1972-01-31 | 1974-04-30 | Rca Corp | Dual thrust level monopropellant spacecraft propulsion system |
DE19623017C1 (en) * | 1996-06-08 | 1998-01-02 | Daimler Benz Aerospace Ag | Propellant tank for corrosive fluids for driving space vehicle |
CN1206671A (en) * | 1997-07-25 | 1999-02-03 | 航空发动机的结构和研究公司 | Compact single propelling agent unit prepelling system for small artificial satellite |
CN101607604A (en) * | 2009-07-02 | 2009-12-23 | 哈尔滨工业大学 | Satellite attitude control and heat control integrated executive mechanism and control method thereof |
-
2010
- 2010-07-23 CN CN 201010238400 patent/CN101907041B/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3807657A (en) * | 1972-01-31 | 1974-04-30 | Rca Corp | Dual thrust level monopropellant spacecraft propulsion system |
DE19623017C1 (en) * | 1996-06-08 | 1998-01-02 | Daimler Benz Aerospace Ag | Propellant tank for corrosive fluids for driving space vehicle |
CN1206671A (en) * | 1997-07-25 | 1999-02-03 | 航空发动机的结构和研究公司 | Compact single propelling agent unit prepelling system for small artificial satellite |
CN101607604A (en) * | 2009-07-02 | 2009-12-23 | 哈尔滨工业大学 | Satellite attitude control and heat control integrated executive mechanism and control method thereof |
Non-Patent Citations (5)
Title |
---|
唐铖等: "小型航天器液化气推进系统的数值模拟", 《清华大学学报(自然科学版)》, vol. 47, no. 5, 15 May 2007 (2007-05-15), pages 730 - 733 * |
李军: "液化气在小卫星推进系统中的应用", 《火箭推进》, vol. 28, no. 4, 15 August 2002 (2002-08-15), pages 58 - 63 * |
潘科炎: "小卫星的推进系统", 《航天控制》, no. 2, 30 June 1996 (1996-06-30), pages 47 - 56 * |
马彦峰等: "液化气体推进剂在微小卫星推进系统中的应用", 《空间控制技术与应用》, vol. 34, no. 2, 15 April 2008 (2008-04-15), pages 59 - 64 * |
魏青等: "微小卫星液化气推进技术", 《上海航天》, no. 5, 25 October 2003 (2003-10-25), pages 46 - 50 * |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102358437A (en) * | 2011-08-08 | 2012-02-22 | 北京控制工程研究所 | Layout method for 10 N thrusters of high orbit satellite platform |
CN102358437B (en) * | 2011-08-08 | 2013-11-20 | 北京控制工程研究所 | Layout method for 10 N thrusters of high orbit satellite platform |
CN103471756A (en) * | 2013-09-05 | 2013-12-25 | 兰州空间技术物理研究所 | Ground measurement method for electric propulsion thrust |
CN103471756B (en) * | 2013-09-05 | 2015-07-29 | 兰州空间技术物理研究所 | A kind of ground survey method of electric propulsion thrust |
CN104828262B (en) * | 2015-04-30 | 2017-05-03 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
CN104828262A (en) * | 2015-04-30 | 2015-08-12 | 北京控制工程研究所 | Low-pressure liquefied gas thrust generating method for spacecraft |
CN105863881A (en) * | 2016-04-06 | 2016-08-17 | 北京航空航天大学 | Miniature thrust generation device capable of being subjected to fuel charging repeatedly and operation method thereof |
CN105863881B (en) * | 2016-04-06 | 2017-05-10 | 北京航空航天大学 | Miniature thrust generation device capable of being subjected to fuel charging repeatedly and operation method thereof |
CN106184823A (en) * | 2016-07-06 | 2016-12-07 | 浙江大学 | A kind of autonomous vaporization management method and liquefied ammonia micromass culture system |
CN106184823B (en) * | 2016-07-06 | 2018-05-01 | 浙江大学 | A kind of autonomous vaporization management method and liquefied ammonia micromass culture system |
CN106564623A (en) * | 2016-09-30 | 2017-04-19 | 上海空间推进研究所 | System and method for liquefied gas constant-pressure propulsion of small satellite |
CN106564623B (en) * | 2016-09-30 | 2019-05-17 | 上海空间推进研究所 | Grapefruit satellite liquefied gas constant pressure propulsion system and method |
CN107323694A (en) * | 2017-05-18 | 2017-11-07 | 上海卫星工程研究所 | Modular satellite booster cabin |
CN107187618A (en) * | 2017-05-27 | 2017-09-22 | 上海航天控制技术研究所 | Gas propellant control system and control method |
CN107187618B (en) * | 2017-05-27 | 2019-08-16 | 上海航天控制技术研究所 | Gas propellant control system and control method |
CN107514320B (en) * | 2017-07-10 | 2019-05-24 | 北京控制工程研究所 | A kind of micromass culture modular structure based on high pressure frontier technology |
CN107514320A (en) * | 2017-07-10 | 2017-12-26 | 北京控制工程研究所 | A kind of micromass culture modular structure based on high pressure frontier technology |
CN108928505A (en) * | 2018-06-28 | 2018-12-04 | 上海卫星工程研究所 | The satellite powered phase method for exhausting controlled using satellite and the rocket pull-off plug signal |
CN109441748A (en) * | 2018-11-02 | 2019-03-08 | 北京航空航天大学 | A kind of thrust integrated system for small-sized hall thruster |
CN109823573A (en) * | 2019-01-22 | 2019-05-31 | 南京航空航天大学 | A kind of propelling integrated solar thermal propulsion system of accumulation of heat-power generation- |
CN109823573B (en) * | 2019-01-22 | 2022-04-26 | 南京航空航天大学 | Heat storage-power generation-propulsion integrated solar thermal propulsion system |
CN110332060A (en) * | 2019-03-22 | 2019-10-15 | 北京蓝箭空间科技有限公司 | Liquid oxygen methane rocket and liquid oxygen methane Rocket tank fall pressure type pressurized design method |
CN110332060B (en) * | 2019-03-22 | 2020-10-16 | 蓝箭航天空间科技股份有限公司 | Liquid oxymethane rocket and liquid oxymethane rocket storage tank pressure-drop type pressurization design method |
CN110395410A (en) * | 2019-07-04 | 2019-11-01 | 南京理工大学 | Rail control all-in-one micro cold air propulsion system |
CN110562496A (en) * | 2019-08-21 | 2019-12-13 | 上海航天控制技术研究所 | integrated satellite propulsion system |
CN111114834A (en) * | 2019-12-17 | 2020-05-08 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
CN111114834B (en) * | 2019-12-17 | 2021-05-04 | 西安航天动力研究所 | Light side wall suspension vertical force transmission rack and primary engine |
CN112407337A (en) * | 2020-11-23 | 2021-02-26 | 北京微动航科技术有限公司 | Propulsion system of satellite simulator and satellite simulator |
CN112918705A (en) * | 2021-03-12 | 2021-06-08 | 深圳航天东方红卫星有限公司 | Thermal control system and method of integrated propulsion subsystem |
Also Published As
Publication number | Publication date |
---|---|
CN101907041B (en) | 2013-04-03 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN101907041B (en) | Propane liquid gas micro propulsion device suitable for micro-nano satellite | |
CN101907040B (en) | Nitrogen cold gas micro propulsion device adopting ring storage tank | |
CN101907039B (en) | Nitrogen cold air micro-propeller adopting three cylindrical propelling agent storage boxes | |
CN203010197U (en) | Skid-mounted liquefied natural gas automobile refueling device | |
CN101566524B (en) | Propellant supply equipment for electric propulsion engine test | |
CN104828262A (en) | Low-pressure liquefied gas thrust generating method for spacecraft | |
CN114291300B (en) | Ground-moon shuttle aircraft propulsion system | |
RU2445503C1 (en) | Test bench for testing power plants with fuel cryogenic components | |
CN114275194B (en) | Self-generating pressurization system suitable for multi-station storage tank pressurization of nuclear carrier | |
CN101943082A (en) | Heating gasification device for liquefied gas micro-propulsion system | |
CN203190024U (en) | Filling machine of liquefied natural gas vehicle | |
CN209145736U (en) | Blowing adapter for cryogenic liquid engine | |
Hammock Jr et al. | Apollo experience report: Descent propulsion system | |
Tsohas et al. | Progress in technology demonstration for a small hybrid launch vehicle | |
Champion, Jr et al. | X-34 main propulsion system design and operation | |
CN221171784U (en) | Skid-mounted hydrogen pressure regulating system of hydrogen adding station | |
Norquist | External tank for the Space Shuttle main propulsion system | |
US20240151358A1 (en) | Integrated cryogenic hydrogen tank systems and methods for operating the same | |
Yang III | Development trend and integrated design of liquid launch vehicle | |
RU2775518C1 (en) | Propulsion unit for liquid-propellant rockets with hydrogen and methane filling invariant fuel tanks with batch layout | |
CN217029124U (en) | Precooling device for liquid rocket engine and liquid carrier rocket | |
US12031686B2 (en) | Device and method for storing and supplying fluid fuel | |
Rozycki et al. | Development of the ground fluid servicing system for the DC-X vehicle | |
McCleskey et al. | High-Payoff Space Transportation Design Approach with a Technology Integration Strategy | |
Robertson et al. | Portable test platform for student liquid rocket engine development |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
C17 | Cessation of patent right | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130403 Termination date: 20130723 |