CN111622866A - Constant force spring type storage tank for liquid propellant - Google Patents
Constant force spring type storage tank for liquid propellant Download PDFInfo
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- CN111622866A CN111622866A CN202010414816.4A CN202010414816A CN111622866A CN 111622866 A CN111622866 A CN 111622866A CN 202010414816 A CN202010414816 A CN 202010414816A CN 111622866 A CN111622866 A CN 111622866A
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- piston
- constant force
- force spring
- box body
- liquid propellant
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- 239000003380 propellant Substances 0.000 title claims abstract description 30
- 239000007788 liquid Substances 0.000 title claims abstract description 24
- 238000007789 sealing Methods 0.000 claims abstract description 16
- 239000000463 material Substances 0.000 claims description 5
- 239000012530 fluid Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Devices (AREA)
Abstract
本发明属于液体工质电推进系统技术领域,提供了一种液体推进剂恒力弹簧式贮箱,包括箱体、弹簧支座、恒力弹簧、推杆、活塞、销轴、密封圈以及导向环。密封圈和导向环安装在活塞上,起密封和导向作用;推杆和活塞相连接,在恒力弹簧的弹力作用下,推杆和活塞将箱体中存储的液体推进剂挤入到供给管路。本发明可以保证液体推进剂在恒定压力下连续稳定的供给,并且体积小、重量轻、可靠性高,适用于液体工质的电推进系统。
The invention belongs to the technical field of liquid working fluid electric propulsion systems, and provides a liquid propellant constant force spring type storage tank, comprising a box body, a spring support, a constant force spring, a push rod, a piston, a pin shaft, a sealing ring and a guide ring. The sealing ring and guide ring are installed on the piston, which play the role of sealing and guiding; the push rod and the piston are connected, and under the elastic force of the constant force spring, the push rod and the piston squeeze the liquid propellant stored in the box into the supply pipe road. The invention can ensure the continuous and stable supply of the liquid propellant under constant pressure, has small volume, light weight and high reliability, and is suitable for the electric propulsion system of the liquid working medium.
Description
技术领域technical field
本发明属于液体工质电推进系统技术领域,涉及一种液体推进剂恒力弹簧式贮箱,用于液体推进剂在恒定压力下连续稳定的供给。The invention belongs to the technical field of liquid working medium electric propulsion systems, and relates to a liquid propellant constant-force spring-type storage tank, which is used for continuous and stable supply of liquid propellant under constant pressure.
背景技术Background technique
电推进技术具有高比冲、高控制精度、长寿命等特点,在卫星姿轨控、深空探测等任务中具有广阔的应用前景。推进剂稳定连续的供给是电推进系统的关键技术,在以往的液体工质电推进系统中,通常采用高压气体挤压式供给。但是这种供给方式需要携带高压气源以及一整套气压控制装置,会造成推进器重量、体积的急剧增加。Electric propulsion technology has the characteristics of high specific impulse, high control accuracy and long life, and has broad application prospects in missions such as satellite attitude and orbit control and deep space exploration. The stable and continuous supply of propellant is the key technology of electric propulsion system. In the previous liquid working medium electric propulsion system, high-pressure gas extrusion supply is usually used. However, this supply method needs to carry a high-pressure air source and a complete set of air pressure control devices, which will cause a sharp increase in the weight and volume of the propeller.
随着各国引力波探测的提出,微纳卫星成为航天技术的研究热点。在微纳卫星上,推进器受到体积和质量的限制,以往的高压气体挤压式供给方式显然无法满足要求。为此,各国都在研究新型的推进剂供给方式。With the introduction of gravitational wave detection in various countries, micro-nano satellites have become a research hotspot in aerospace technology. On micro-nano satellites, the thruster is limited by volume and mass, and the previous high-pressure gas extrusion supply method obviously cannot meet the requirements. To this end, countries are studying new ways of propellant supply.
发明内容SUMMARY OF THE INVENTION
本发明目的在于提供一种液体推进剂恒压弹簧式贮箱,把推进剂的贮存和供给集成在一起,有效的减少了推进器的体积和质量,解决了以往高压气体挤压式供给所造成的推进器体积和质量过大的问题,从而满足微纳卫星的应用需求。The purpose of the present invention is to provide a liquid propellant constant pressure spring type storage tank, which integrates the storage and supply of the propellant, effectively reduces the volume and mass of the propeller, and solves the problems caused by the extrusion type supply of high pressure gas in the past. The volume and mass of the thruster are too large, so as to meet the application requirements of micro-nano satellites.
本发明目的通过以下技术方案予以实现:The object of the present invention is achieved through the following technical solutions:
一种液体推进剂恒力弹簧式贮箱,包括弹簧支座1、恒力弹簧2、箱体3、活塞4、端盖5、推杆6、导向环7、密封圈8和销轴9。A liquid propellant constant force spring type storage tank, comprising a spring support 1, a
所述的箱体3为上下开口结构,箱体3底部的外围安装有弹簧支座1,箱体3底部的中心开有通孔10,作为推进剂加注口和出口;所述的活塞4安装在箱体3内,活塞4的外壁与箱体3的内壁相接触,且活塞4的外壁上设有导向槽和密封槽,用于安装导向环7和密封圈8,实现导向与密封,活塞4沿箱体3内壁上下滑动;所述的端盖5安装在箱体3的顶部,活塞4在箱体3和端盖5之间形成的内部空间内运动,活塞4底部与箱体3之间形成密闭空间,用于贮存液体推进剂;端盖5的中心设有通孔,用于安装推杆6;所述的推杆6,其底端与活塞4顶部连接,其顶端穿过端盖5,位于箱体3外部;所述的恒力弹簧2有多根,对称安装,恒力弹簧2的一端和推杆6相连接,另一端通过销轴9安装在弹簧支座1上;恒力弹簧2始终处于拉伸状态,提供恒定的拉力。The
所述箱体3、活塞4、导向环7和密封圈8的材料均为不与贮存的推进剂发生化学反应的材料。The materials of the
所述端盖5中心的通孔,比推杆6直径略大。The through hole in the center of the
本发明与现有的技术相比具有如下有益效果:Compared with the prior art, the present invention has the following beneficial effects:
(1)本发明通过整体结构能够实现液体推进剂的贮存和稳定连续的供给,有效保证电推进系统的可靠工作。(1) The present invention can realize the storage and stable and continuous supply of liquid propellant through the overall structure, and effectively ensure the reliable operation of the electric propulsion system.
(2)本发明把液体推进剂的贮存和供给集成在一起,有效减小了推进器的体积。(2) The present invention integrates the storage and supply of the liquid propellant, thereby effectively reducing the volume of the propeller.
(3)本发明利用恒力弹簧作为驱动源,可提供恒定的压力,省去了高压气源和气压控制装置,大大减少了推进器的质量,可应用于微小卫星上。(3) The present invention uses the constant force spring as the driving source, which can provide constant pressure, saves the high-pressure air source and the air pressure control device, greatly reduces the mass of the propeller, and can be applied to small satellites.
附图说明Description of drawings
图1是液体推进剂恒力弹簧式贮箱实施例的示意图。Figure 1 is a schematic diagram of an embodiment of a liquid propellant constant force spring tank.
图中:1弹簧支座;2恒力弹簧;3箱体;4活塞;5端盖;6推杆;7导向环;8密封圈;9销轴;10通孔。In the picture: 1 spring support; 2 constant force spring; 3 box body; 4 piston; 5 end cover; 6 push rod; 7 guide ring; 8 seal ring; 9 pin shaft; 10 through hole.
具体实施方式Detailed ways
下面将参照附图更详细地描述本公开的实例性实施例。虽然附图中显示了本公开的示例性实施例,然而应当理解,可以以各种形式实现本公开而不应该被这里阐述的实施例所限制。相反,提供这些实施例是为了能够更透彻的理解本公开,并且能够将本公开的范围完整的传达给本领域的技术人员。Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be more thoroughly understood, and will fully convey the scope of the present disclosure to those skilled in the art.
图1是本发明实施例提供的液体推进剂恒力弹簧式贮箱结构示意图。如图1所示,该液体推进剂恒力弹簧式贮箱包括:弹簧支座1、恒力弹簧2、箱体3、活塞4、端盖5、推杆6、导向环7、密封圈8以及销轴9;其中,端盖5安装在箱体3顶端,箱体3底部的中心开有通孔10,作为推进剂加注口和出口;推杆6的底端穿过端盖5中心的通孔,与活塞4上表面相连接,并且活塞4置于端盖5和箱体3形成的非密闭空间;液体推进剂贮存在活塞4和箱体3形成的密闭空间;活塞上4开有导向槽和密封槽,安装导向环7和密封圈8;弹簧支座1安装在箱体3底端两侧;恒力弹簧2的一端和推杆6相连接,并且另一端通过销轴9挂于弹簧支座1。FIG. 1 is a schematic structural diagram of a liquid propellant constant-force spring-type storage tank provided by an embodiment of the present invention. As shown in Figure 1, the liquid propellant constant force spring tank includes: spring support 1,
本实施例中箱体3和活塞4所采用材料为不锈钢。In this embodiment, the material used for the
本实施例中恒力弹簧2为4根。In this embodiment, there are four
本实施例中箱体3内推进剂贮存容积为50ml。In this embodiment, the propellant storage volume in the
本发明的具体工作过程为:The concrete working process of the present invention is:
加注阶段:将贮箱清洗干净,烘干;将推进剂加注装置和贮箱上的加注口连接,在加注压力的作用下,活塞4连同推杆6上移,恒力弹簧2被拉长;固定恒力弹簧2的位置;取下加注装置,密封贮箱加注口,完成加注。Filling stage: clean and dry the tank; connect the propellant filling device to the filling port on the tank, under the action of filling pressure, the
工作阶段:贮箱接到推进系统中,释放恒力弹簧2,在恒力弹簧2的作用下,活塞4连同推杆6被推动下移,将箱体3中存储的液体推进剂以恒定压力挤入到供给管路。Working stage: The storage tank is connected to the propulsion system, and the
以上所述实施例只是本发明较优选的具体实施方式,本领域的技术人员在本发明技术方案范围内的通常变化和替换都应包含在本发明的保护范围之内。The above-mentioned embodiments are only preferred specific embodiments of the present invention, and general changes and substitutions within the scope of the technical solutions of the present invention by those skilled in the art should be included within the protection scope of the present invention.
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN112124634A (en) * | 2020-09-07 | 2020-12-25 | 兰州空间技术物理研究所 | Micro flow storage and supply device for colloid propeller |
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CN109131943A (en) * | 2018-08-08 | 2019-01-04 | 上海新力动力设备研究所 | Piston for laser chemistry joint propeller drives charge constitution |
CN109455313A (en) * | 2018-11-15 | 2019-03-12 | 河北工业大学 | For space propultion from pressurized fuel case |
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2020
- 2020-05-15 CN CN202010414816.4A patent/CN111622866B/en active Active
Patent Citations (7)
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US3880326A (en) * | 1966-08-16 | 1975-04-29 | Thiokol Chemical Corp | Diaphragm structure for dispensing fluids |
EP2025907A2 (en) * | 2007-08-04 | 2009-02-18 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Rocket engine |
CN201348133Y (en) * | 2009-02-06 | 2009-11-18 | 华群 | Constant pressure container |
CN102507197A (en) * | 2011-09-29 | 2012-06-20 | 北京航空航天大学 | Solid lithium propelling agent constant temperature liquid state conveying device with pipeline blowing down function |
CN105156231A (en) * | 2015-09-10 | 2015-12-16 | 中国航天科技集团公司第四研究院第四十一研究所 | Gas self-pressurization hybrid rocket engine |
CN109131943A (en) * | 2018-08-08 | 2019-01-04 | 上海新力动力设备研究所 | Piston for laser chemistry joint propeller drives charge constitution |
CN109455313A (en) * | 2018-11-15 | 2019-03-12 | 河北工业大学 | For space propultion from pressurized fuel case |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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CN112124634A (en) * | 2020-09-07 | 2020-12-25 | 兰州空间技术物理研究所 | Micro flow storage and supply device for colloid propeller |
CN112124634B (en) * | 2020-09-07 | 2023-12-22 | 兰州空间技术物理研究所 | Micro-flow storage and supply device for colloid propeller |
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