CN101907040A - Nitrogen cold gas micro propulsion device adopting ring storage tank - Google Patents
Nitrogen cold gas micro propulsion device adopting ring storage tank Download PDFInfo
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- CN101907040A CN101907040A CN2010102383999A CN201010238399A CN101907040A CN 101907040 A CN101907040 A CN 101907040A CN 2010102383999 A CN2010102383999 A CN 2010102383999A CN 201010238399 A CN201010238399 A CN 201010238399A CN 101907040 A CN101907040 A CN 101907040A
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Abstract
The invention discloses a nitrogen cold gas micro propulsion device adopting a ring storage tank, comprising a propellant storage tank, a high-pressure charging valve, a high-pressure pressure reducer, a low-pressure pressure reducer, a high-pressure latching valve, a thruster, a high-pressure sensor and a filter. The micro propulsion device is used for attitude control on a micro satellite as well as maintenance and control on a track; nitrogen is used as a propellant, therefore, the nitrogen cold gas micro propulsion device has no toxicity and pollution; and the micro propulsion device has the advantages of simple structure, low quality, low power consumption and high reliability. The micro propulsion device is installed on an installation baffle, thereby being convenient to install and replace; and the micro propulsion device has no excessive connection and interference with other parts of the satellite, thereby being convenient to replace and repair.
Description
Technical field
The invention belongs to the little Push Technology of cold air field, relate to a kind of nitrogen cold gas micro propulsion device that is applicable to microsatellite, specifically is a kind of nitrogen cold gas micro propulsion device that adopts ring storage tank.
Background technique
The little propulsion system of cold air is meant the cold air propulsion system that is used for microsatellite, usually is that the satellite of 100kg～500kg is called moonlet with weight, 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.Microsatellite refers to the satellite of weight in 10kg～500kg scope.The main feature of microsatellite 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 propulsion system is a kind of propulsion system commonly used, microsatellite can adopt the propellant agent of cold air as its propulsion system, 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 propulsion system improve constantly aspect reliability, the practicability, substantially satisfy the whole requirement of microsatellite, also made the application area of microsatellite constantly expand.
Propulsion system is meant and is used for satellite or astrovehicle, under the instruction effect of control system, realizes the execution architecture of satellite orbit control and attitude control.An important technology of using in the propulsion system is a Push Technology, refers to that promptly any dependence energy makes the technology that propellant agent quickens of discharging.Press propulsion mode and divide, satellite propulsion system can be divided into bipropellant propulsion system, monopropellant propulsion system and electric propulsion system three major types substantially, and monopropellant propulsion system comprises two classes that produce chemical reaction and do not produce chemical reaction again.The propellant agent that participates in chemical reaction generally is that propellant agent passes through heating process and decomposes, and decomposition gas is sprayed by jet pipe, produces thrust.The propellant agent of this quasi-representative has anhydrous hydrazine and hydrogen peroxide etc.The propellant agent that does not participate in chemical reaction is meant these propellant agents, and it need not heat, and directly by the jet pipe ejection, can produce thrust.And the cold air propulsion system means that propulsion system does not have thermal source, discharges propellant gas by jet pipe and can produce thrust, and this propulsion system is compared and need not be heated with the propulsion system that thermal source is arranged, and problem such as does not have heat to return to soak, and is repeated and reliability is higher.
The working procedure of cold air propulsion system is that cold air is stored with high voltage style, decompressor drops to cold air pressure after the desired pressure, and gas is transported to jet pipe by solenoid valve, and its advantage is that safety, cost are low, response is fast, good reproducibility, and because system is simple the reliability height.Though jet pipe is in light weight, but owing to need to be equipped with gas cylinder (tank) and distribute transporting system, the weight of whole system is medium, in addition because need a large amount of gas cylinders to store propellant agent (gaseous state), the utilization ratio of system on volume is not high, the thrust output scope of typical cold air propulsion system is 5mN～250N, when exit area ratio is 100, nitrogen specific impulse excursion 45s～74s, the size that specifically depends on jet pipe (thruster) thrust, because the volume with thruster reduces, the loss of jet pipe will increase.
Summary of the invention:
The object of the present invention is to provide a kind of microsatellite that is used for to carry out the nitrogen cold gas micro propulsion device that attitude is controlled and track is kept and controlled; Micro propulsion device of the present invention adopts a ring gas cylinder as propellant tank, uses nitrogen to be propellant agent, nontoxic pollution-free; Micro propulsion device is simple in structure, and components and parts are less, can reduce the power consumption and the quality of system, improves reliability and Security, reduces production costs; The micro propulsion device integral installation is being installed on the dividing plate, is convenient to install and replaces, and does not have too much get in touch and interfere with other parts of satellite, is convenient to replace and repairs.
A kind of microsatellite nitrogen cold gas micro propulsion device of the present invention mainly comprises high pressure fill valve, ring propellant tank, high pressure fill valve, high pressure relief device, low pressure reducing valve, high pressure latching valve, thruster, high pressure sensor, filter and control wiring box.Above-mentioned parts are installed in to be installed on the dividing plate;
Be connected with high pressure fill valve on the propellant tank, by the propellant tank filling high pressure nitrogen of high pressure fill valve to propulsion system; Also be connected with threeway A on the propellant tank, be connected with high pressure sensor on the threeway A, the nitrogen pressure in the propellant tank can be monitored by high pressure sensor; Also be connected with high pressure latching valve, high pressure relief device, low pressure reducing valve and filter on the threeway A in turn, be connected by pipeline between high pressure latching valve, high pressure relief device, low pressure reducing valve and filter;
Filter is connected with threeway E by pipeline, and two ports of the residue of threeway E are connected with supply pipeline respectively, and the other end of supply pipeline respectively is connected with two and leads to, and leads to two to be connected with thruster by supply air line; Solenoid valve is housed on the thruster;
Be connected by cable between control wiring box and the high pressure sensor, high pressure latching valve and the thruster that need control, in order to power and transmission of control signals.The control wiring box can send control signal according to the relevant control command of satellite, opens the solenoid valve of the thruster that needs work.
The invention has the advantages that:
(1) micro propulsion device of the present invention is simple in structure, uses nitrogen as propellant agent, low cost, high reliability, low power consumption, pollution-free and safe;
(2) micro propulsion device integral installation of the present invention is being installed on the dividing plate, is convenient to install and replacement.
Description of drawings
Fig. 1 is a nitrogen cold gas micro propulsion device structure plan view of the present invention;
Fig. 2 is the mounting structure plan view of nitrogen cold gas micro propulsion device of the present invention on Hexagon installation dividing plate;
Fig. 3 is the mounting structure side view of nitrogen cold gas micro propulsion device of the present invention on Hexagon installation dividing plate.
Among the figure:
1-propellant tank 2-high pressure fill valve 3-high pressure sensor
4-high pressure latching valve 5-high pressure relief device 6-low pressure reducing valve
7-filter 8-threeway A 9-threeway B
10-threeway C 11-two logical 12-supply air lines
13-thruster 14-control wiring box 15-installs dividing plate
The 16-supply pipeline
Embodiment:
A kind of microsatellite nitrogen cold gas micro propulsion device of the present invention, mainly by propellant tank 1, high pressure fill valve 2, high pressure relief device 5, low pressure reducing valve 6, high pressure latching valve 4, thruster 13, high pressure sensor 3, filter 7, with control wiring box 14.As shown in Figure 1, above-mentioned parts are installed in to be installed on the dividing plate 15, is convenient to the installation of micro propulsion device and replacement, repairing.The shape of described installation dividing plate 15 is identical with the satellite sectional shape of required installation micro propulsion device.
Wherein propellant tank 1 is the ring tank, can maximum utilization be installed by the installing space of dividing plate 15, and help the barycenter of propulsion system integral body is adjusted on the medial axis that dividing plate 15 is installed.Be connected with high pressure fill valve 2 on the propellant tank 1, by the propellant tank 1 filling high pressure nitrogen of high pressure fill valve 2 to propulsion system.Also be connected with threeway A8 on the propellant tank 1, be connected with high pressure sensor 3 on the threeway A8, the nitrogen pressure in the propellant tank 1 can be monitored by high pressure sensor 3.Also be connected with high pressure latching valve 4, high pressure relief device 5, low pressure reducing valve 6 and filter 7 on the threeway A8 in turn, high pressure latching valve 4, high pressure relief device 5, low pressure reducing valve 6 and 7 of filters are connected by pipeline.High pressure latching valve 4 is used for making nitrogen propellant agent in the propellant tank 1 and the line isolation in the micro propulsion device of the present invention.Because the inlet pressure that the storage pressure of nitrogen requires far above thruster 13, therefore open high pressure latching valve 4, make the propellant agent that flows out in the propellant tank 1 enter high pressure relief device 5 and carry out the one-level decompression by high pressure latching valve 4, then enter low pressure reducing valve 6 and carry out second depressurized, make the pressure of nitrogen propellant agent drop to the inlet pressure value 0.25Mpa that thruster 13 requires from 20MPa, post-decompression propellant agent enters into filter 7 and filters, in order to avoid exist impurity to stop up thruster 13 throats in the nitrogen, what system adopted is high pure nitrogen, impurity is few, but because thruster 13 throat diameters are minimum, even trickle impurity also can cause thruster 13 to stop up, therefore adopt filter 7 to guarantee.
Filter 7 is connected with threeway B9 by pipeline, and two ports of the residue of threeway B9 are connected with an end of two supply pipelines 16 respectively, and the other end of two supply pipelines 16 respectively is connected with two and leads to 11, is connected with thruster 13 by supply air line 12 on two logical 11.If need when diverse location increases thruster 13, only need in supply pipeline 16, increase threeway C10, by supply air line 12 thruster 13 is connected with threeway C10 again; If need when same position increase thruster 13, can on supply pipeline 16, connect and have the pipe joint of a plurality of ports, thereby connect a plurality of thrusters 13.Propane propellant agent after the gasification enters into supply pipeline 16 by threeway B9, enters into supply air line 12 by the threeway C10 in the supply pipeline 16 and two logical 11, finally enters into corresponding thruster 13 by supply air line 12.On the thruster 13 solenoid valve is housed, opens the solenoid valve of the thruster 13 that needs work, then propane gas is known from experience therefrom ejection, thereby produces thrust.
Be connected by cable between control wiring box 14 and high pressure sensor 3, high pressure latching valve 4 and the thruster 13, in order to power supply and transmission of control signals.Control wiring box 14 can send control signal according to the relevant control command of satellite, opens the solenoid valve of the thruster 13 that needs work, and then nitrogen can therefrom spray, thereby produces thrust; Thruster 13 can be worked independently, also can a plurality of co-operation.
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 13 of connection on supply air line 12 thus, and determine that each thruster 13 is at the location layout of installing on the dividing plate 15.
The inlet pressure of above-mentioned thruster 13 is relevant with its thrust requirement and size design, and thruster 13 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.
At first the solenoid valve on assurance high pressure latching valve 4 and the thruster 13 cuts out before work, prevents that propellant agent from flowing out naturally.
When end-of-job, at first close the solenoid valve of thruster 13, then close high pressure latching valve 4, reason is to need to keep certain pressure before the solenoid valve of thruster 13, prevents leakage.
Come the quantity and the location arrangements of thruster among the present invention 13 are described further below by an embodiment.
As shown in Figure 2, dividing plate 15 is installed is adopted the Hexagon dividing plate, install on the dividing plate 15 annular propellant tank 1 is installed, make annular propellant tank 1 and dividing plate 15 concentrics are installed.
Be connected with high pressure fill valve 2 and threeway A8 on the propellant tank 1, be connected with high pressure sensor 3 on the threeway A8.Also be connected with high pressure latching valve 4, high pressure relief device 5, low pressure reducing valve 6 and filter 7 on the threeway A8 in turn, high pressure latching valve 4, high pressure relief device 5, low pressure reducing valve 6 and 7 of filters are connected by pipeline.
Filter 7 is connected with threeway B9 by pipeline, and two ports in addition of threeway B9 are connected with supply pipeline 16 respectively, and the other end of supply pipeline 16 respectively is connected with two and leads to 11, forms the supply air line 12 of micro propulsion device of the present invention thus.On supply pipeline 16, be respectively arranged with four threeway C10, two logical 11 with threeway C10 on respectively be connected with thruster 13 by supply air line 12.
Described high pressure fill valve, high pressure sensor 3, high pressure latching valve 4, high pressure relief device 5, low pressure reducing valve 6, filter 7 are arranged on the installation dividing plate 15 of annulus propellant tank 1 inner ring with control wiring box 14.Supply pipeline 16 is arranged on the installation dividing plate 15 of annulus propellant tank 1 outer ring.
If Hexagon is installed the interior angle place of dividing plate 15 and is respectively a, b, c, d, e, f, wherein a and d, b and e, c and f be the diagonal angle of regular hexagon installation dividing plate 15 for this reason, therefore will be arranged in a and d at thruster 13, b and e, c and f place, and respectively be provided with a pair of thruster 13 at c and f place, b and e, a and d place respectively are provided with a thruster 13, and the thruster 13 at b and e and a and d place is separately positioned on the both sides that dividing plate 15 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 (5)
1. a nitrogen cold gas micro propulsion device that adopts ring storage tank is characterized in that: comprise ring propellant tank, high pressure fill valve, high pressure relief device, low pressure reducing valve, high pressure latching valve, thruster, high pressure sensor, filter and control wiring box; Above-mentioned parts are installed in to be installed on the dividing plate;
Be connected with high pressure fill valve on the described ring propellant tank, load high pressure nitrogen to the ring propellant tank by high pressure fill valve; Also be connected with high pressure sensor on the ring propellant tank, be used for monitoring the nitrogen pressure in the ring propellant tank by threeway A; Also be connected with high pressure latching valve, high pressure relief device, low pressure reducing valve and filter by pipeline successively on the threeway A;
Filter is connected with threeway E by pipeline, and two ports of the residue of threeway E are connected with supply pipeline respectively, and the other end of supply pipeline respectively is connected with two and leads to, and leads to two to be connected with thruster by supply air line; Solenoid valve is housed on the thruster;
The control wiring box is connected by cable respectively with between high pressure sensor, high pressure latching valve and the thruster of needs control, in order to power and transmission of control signals; Described control wiring box sends control signal according to the satellite control command, and control needs the solenoid valve of the thruster of work.
2. a kind of according to claim 1 nitrogen cold gas micro propulsion device 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.
3. a kind of according to claim 1 nitrogen cold gas micro propulsion device is characterized in that: at least one threeway C is set in the described supply pipeline, and threeway C connects thruster by supply air line.
4. a kind of according to claim 1 nitrogen cold gas micro propulsion device is characterized in that: filling liquid nitrogen propellant agent in the described ring propellant tank, and filling liquid nitrogen propellant agent gross mass is 0.6kg, the pressure of storage is 0.84MPa.
5. a kind of according to claim 1 nitrogen cold gas micro propulsion device is characterized in that: described high pressure fill valve, high pressure sensor, high pressure latching valve, high pressure relief device, low pressure reducing valve, filter and control wiring box are arranged on the installation dividing plate of annulus propellant tank inner ring; Supply pipeline is arranged on the installation dividing plate of annulus propellant tank outer ring.
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201010238399 CN101907040B (en) | 2010-07-23 | 2010-07-23 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
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| Application Number | Priority Date | Filing Date | Title |
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| CN 201010238399 CN101907040B (en) | 2010-07-23 | 2010-07-23 | Nitrogen cold gas micro propulsion device adopting ring storage tank |
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| CN101907040A true CN101907040A (en) | 2010-12-08 |
| CN101907040B CN101907040B (en) | 2013-04-24 |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN105799954A (en) * | 2014-12-31 | 2016-07-27 | 上海新跃仪表厂 | Space-based modular aircraft for conducting decentralized deployment on micro-nano load and orbital transfer guidance method of modular aircraft |
| CN106121866A (en) * | 2016-08-18 | 2016-11-16 | 湖北三江航天红林探控有限公司 | Timesharing Ignition control algorithm based on the design of pressure self-stabilization and system |
| CN107097979A (en) * | 2017-03-30 | 2017-08-29 | 哈尔滨工业大学 | A kind of annular composite material tank structure |
| 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 |
| CN108190048A (en) * | 2017-12-05 | 2018-06-22 | 北京控制工程研究所 | A kind of micromodule butane propulsion system structure and propulsion method |
| CN109018444A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter power system |
| CN109515757A (en) * | 2018-10-18 | 2019-03-26 | 贵州航天林泉电机有限公司 | A kind of jet aircraft attitude-control device |
| 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 |
| CN110271693A (en) * | 2019-05-24 | 2019-09-24 | 深圳市魔方卫星科技有限公司 | A kind of integrated cold air propulsion system |
| CN111216926A (en) * | 2019-11-29 | 2020-06-02 | 天津航宇卓然科技有限公司 | Cold air propulsion system |
| CN111305978A (en) * | 2020-02-18 | 2020-06-19 | 哈尔滨工程大学 | Gas engine gas supply device with step gas supply pressure and control method thereof |
| 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 |
| CN113931817A (en) * | 2021-09-30 | 2022-01-14 | 北京控制工程研究所 | Two-stage pressure reduction device and pressure reduction method for electric propulsion system propellant |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN104260901B (en) * | 2014-09-11 | 2016-08-24 | 上海卫星工程研究所 | Modular bipropellant propulsion system |
| CN105799954A (en) * | 2014-12-31 | 2016-07-27 | 上海新跃仪表厂 | Space-based modular aircraft for conducting decentralized deployment on micro-nano load and orbital transfer guidance method of modular aircraft |
| CN105799954B (en) * | 2014-12-31 | 2018-06-05 | 上海新跃仪表厂 | Space-based disperses the modular aircraft for disposing micro-nano load and its becomes rail method of guidance |
| CN106121866A (en) * | 2016-08-18 | 2016-11-16 | 湖北三江航天红林探控有限公司 | Timesharing Ignition control algorithm based on the design of pressure self-stabilization and system |
| CN106121866B (en) * | 2016-08-18 | 2017-12-29 | 湖北三江航天红林探控有限公司 | Timesharing Ignition control algorithm and system based on the design of pressure self-stabilization |
| CN107097979A (en) * | 2017-03-30 | 2017-08-29 | 哈尔滨工业大学 | A kind of annular composite material tank structure |
| 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 |
| CN108190048A (en) * | 2017-12-05 | 2018-06-22 | 北京控制工程研究所 | A kind of micromodule butane propulsion system structure and propulsion method |
| CN108190048B (en) * | 2017-12-05 | 2020-04-10 | 北京控制工程研究所 | Miniature modular butane propulsion system structure and propulsion method |
| CN109018444A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter power system |
| CN109515757A (en) * | 2018-10-18 | 2019-03-26 | 贵州航天林泉电机有限公司 | A kind of jet aircraft attitude-control device |
| 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 |
| CN110271693A (en) * | 2019-05-24 | 2019-09-24 | 深圳市魔方卫星科技有限公司 | A kind of integrated cold air propulsion system |
| CN111216926A (en) * | 2019-11-29 | 2020-06-02 | 天津航宇卓然科技有限公司 | Cold air propulsion system |
| CN111216926B (en) * | 2019-11-29 | 2021-04-06 | 天津航宇卓然科技有限公司 | Cold air propulsion system |
| CN111305978A (en) * | 2020-02-18 | 2020-06-19 | 哈尔滨工程大学 | Gas engine gas supply device with step gas supply pressure and control method thereof |
| 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 |
| CN113931817A (en) * | 2021-09-30 | 2022-01-14 | 北京控制工程研究所 | Two-stage pressure reduction device and pressure reduction method for electric propulsion system propellant |
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