CN105423001A - Capillary tube applied to monopropellant thruster - Google Patents
Capillary tube applied to monopropellant thruster Download PDFInfo
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- CN105423001A CN105423001A CN201510849328.5A CN201510849328A CN105423001A CN 105423001 A CN105423001 A CN 105423001A CN 201510849328 A CN201510849328 A CN 201510849328A CN 105423001 A CN105423001 A CN 105423001A
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- arc section
- straight length
- capillary tube
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L9/00—Rigid pipes
Abstract
The invention relates to a capillary tube applied to a monopropellant thruster and belongs to the technical field of monopropellant thrusters. The outer diameter of the capillary tube ranges from 0.2 mm to 0.7 mm and the wall thickness ranges from 0.05 mm to 0.3 mm. The capillary tube comprises a left straight tube segment, a first arc segment, a second arc segment, a left transition straight tube segment, a third arc segment, a right transition straight tube segment, a fourth arc segment, a fifth arc segment and a right straight tube segment. By the adoption of the capillary tube, the flow resistance of the monopropellant thruster can be controlled precisely by selecting the total length of the capillary tube before the capillary tube is bent, so that the thrust of the monopropellant thruster is controlled precisely; and the thermal resistance of the capillary tube is increased, the amount of heat conducted to the upstream position from a hot end component when the monopropellant thruster is ignited is lowered, and the work safety of the monopropellant thruster is improved.
Description
Technical field
The present invention relates to a kind of capillary tube being applied to single constituent element thruster, particularly relate to a kind of 360 ° of ultrafine-hair tubules being applied to single constituent element thruster, belong to single constituent element thruster technical field, described capillary tube external diameter is 0.2mm ~ 0.7mm, and wall thickness is 0.05mm ~ 0.3mm.
Background technique
Single constituent element thruster is one of main power unit of current astrovehicle rail control, and application area is very extensive.Along with the lifting of Spacecraft Control required precision and the development trend of self microminaturization, require that single constituent element thruster realizes microminaturization, thrust magnitude is even lower than 200mN.The element that single constituent element thruster adopts capillary tube to control as flow conveying and pressure drop usually, the effect of capillary tube in thruster is the circulation passage as flow, propellant agent is carried to firing chamber from upstream, simultaneously doublely do flow transfer passage and pressure drop controlling component, be usually arranged in the less framework of internal diameter size (axial installing space only has 20mm usually).
When single constituent element thruster thrust magnitude is 200mN, if adopt existing capillary tube, there is following shortcoming:
(1) capillary inner diameter is very little, and manufacturing error is very large, is difficult to satisfied accurate control overflow;
(2) because capillary pipe length and frame size deviation are very large, coupling is difficult to.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, proposes a kind of the ultrafine-hair tubule and the forming method thereof that are applied to unit thruster.
Technical solution of the present invention is:
A kind of capillary tube being applied to single constituent element thruster, this capillary tube is formed by a straight tube bending, and this capillary tube comprises left straight length, the first arc section, the second arc section, left transition straight length, three-arc section, right transition straight length, the 4th arc section, the 5th arc section and right straight length;
Left straight length, the first arc section, the second arc section, left transition straight length, three-arc section, right transition straight length, the 4th arc section, the 5th arc section and right straight length are linked in sequence successively and seamlessly transit;
With the mid point at left straight length and right straightway interval for true origin, defining direction, left straight length place is x-axis, and postive direction to the right; Y-axis postive direction upwards; Z-axis is determined according to left hand rule;
Left straight length is positioned at-x-axis line on; First arc section is positioned on (-x+y) face; Second arc section is positioned on (-x+z) face; Left transition straight length is parallel with y, and is positioned on (+y+z) face; Three-arc section one end is positioned on (+y+z) face, and the other end is positioned on (+y-z) face; Right transition straight length is parallel with y, and is positioned on (+y-z) face; 4th arc section is positioned on (-x-z) face; 5th arc section is positioned on (+x+y) face; Right straight length is positioned at+x-axis line on.
Described capillary tube external diameter is of a size of 0.2mm ~ 0.7mm, and wall thickness is 0.05mm ~ 0.3mm.
Described left straight length and the first arc section tangent, first arc section and the second arc section tangent, second arc section and left transition straight length tangent, left transition straight length and three-arc section tangent, three-arc section and right transition straight length tangent, right transition straight length and the 4th arc section tangent, the 4th arc section and the 5th arc section tangent, the 5th arc section and right straight length tangent.
Left straight length and right straight length conllinear, and vertical with left transition straight length, three-arc section, right transition straight length, left straight length and right flow development length are a.
First arc section, the second arc section, the 4th arc section and the 5th arc section are 1/4 circular arc, and its radius is r.
Left transition straight length and right transition flow development length are r.
Three-arc section radius is 2r, is semi-circle.
Before capillary tube is bending, overall length is S=2a+ (4 π+2) r, and after bending, capillary pipe length L=2a+2r, S determine according to flow resistance requirement and capillary inner diameter, L determines according to single constituent element thruster frame size, according to S and L, solve and obtain capillary form size
The present invention's beneficial effect is compared with prior art:
(1) adopt capillary tube of the present invention, while meeting frame size requirement, the internal diameter size of capillary tube can be increased as far as possible, reduce difficulty of processing and foozle;
(2) adopt capillary tube of the present invention, before can being bent by selection, capillary tube total length accurately controls the flow resistance of single constituent element thruster, thus accurately controls the thrust of single constituent element thruster;
(3) adopt the present invention, the length of bending postcapillary can be finely tuned, and can adapt to the deviation of frame size, meet the matching performance of capillary pipe length and frame size;
(4) adopt the present invention, the structural stress of bending postcapillary is little, can adapt to the environment that difference variation is larger;
(5) adopt capillary tube of the present invention, increase the thermal resistance of capillary tube, reduce hot-end component when single constituent element thruster is lighted a fire and, toward the heat conduction amount of upstream, improve the job security of single constituent element thruster.
Accompanying drawing explanation
Fig. 1 is 360 ° of ultrafine-hair tubule perspective view;
Fig. 2 is 360 ° of ultrafine-hair capillary structure schematic diagram.
Embodiment
A kind of capillary tube being applied to single constituent element thruster, this capillary tube is formed by a straight tube bending 360 °, comprises left straight length 1, first arc section 2, second arc section 3, left transition straight length 4, three-arc section 5, right transition straight length 6, the 4th arc section 7, the 5th arc section 8 and right straight length 9;
Left straight length 1, first arc section 2, second arc section 3, left transition straight length 4, three-arc section 5, right transition straight length 6, the 4th arc section 7, the 5th arc section 8 and right straight length 9 are linked in sequence successively and seamlessly transit, and caliber and wall thickness completely the same;
This capillary tube external diameter is of a size of 0.2mm ~ 0.7mm, and wall thickness is 0.05mm ~ 0.3mm;
Before capillary tube is bending, overall length is S=2a+ (4 π+2) r, capillary pipe length L=2a+2r after bending, determines S size, determine L size according to single constituent element thruster frame size according to flow resistance requirement and capillary inner diameter;
According to S and L size, solve and obtain capillary form size a and r,
Left straight length 1 and right straight length 9 conllinear, and vertical with left transition straight length 4, three-arc section 5, right transition straight length 6, left straight length 1 and right straight length 9 length are a;
Left straight length 1 and the first arc section 2 tangent, first arc section 2 and the second arc section 3 tangent, second arc section 3 is tangent with left transition straight length 4, left transition straight length 4 and three-arc section 5 tangent, three-arc section 5 is tangent with right transition straight length 6, right transition straight length 6 and the 4th arc section 7 tangent, the 4th arc section 7 and the 5th arc section 8 tangent, the 5th arc section 8 is tangent with right straight length 9;
First arc section 2, second arc section 3, the 4th arc section 7 and the 5th arc section 8 radius are r, are 1/4 circular arc;
Left transition straight length 4 and right transition straight length 6 length are r;
Three-arc section 5 radius is 2r, is semi-circle;
With the mid point at left straight length 1 and right straightway 9 interval for true origin, defining direction, left straight length 1 place is x-axis, and postive direction to the right; Y-axis postive direction upwards; Z-axis is determined according to left hand rule;
Left straight length 1 is positioned at-x-axis line on; First arc section 2 is positioned on (-x+y) face; Second arc section 3 is positioned on (-x+z) face; Left transition straight length 4 is parallel with y, and is positioned on (+y+z) face; Three-arc section 5 one end is positioned on (+y+z) face, and the other end is positioned on (+y-z) face; Right transition straight length 6 is parallel with y, and is positioned on (+y-z) face; 4th arc section 7 is positioned on (-x-z) face; 5th arc section 8 is positioned on (+x+y) face; Right straight length 9 is positioned at+x-axis line on.
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is further described in detail.
Embodiment
Require and single constituent element thruster frame size according to flow resistance, determine S=45.12mm, L=20mm; According to S and L size, solve and obtain capillary form size a=8mm and r=2mm.
As shown in Figure 1, be applied to a ultrafine-hair tubule for single constituent element thruster, this capillary tube comprises left straight length 1, first arc section 2, second arc section 3, left transition straight length 4, three-arc section 5, right transition straight length 6, the 4th arc section 7, the 5th arc section 8 and right straight length 9 by bending the forming of a straight tube (overall length 45.12mm);
As shown in Figure 1, left straight length 1, first arc section 2, second arc section 3, left transition straight length 4, three-arc section 5, right transition straight length 6, the 4th arc section 7, the 5th arc section 8 and right straight length 9 are linked in sequence successively and seamlessly transit, and caliber and wall thickness completely the same;
As shown in Figure 1, this capillary tube external diameter is of a size of 0.14mm, and wall thickness is 0.23mm;
As shown in Figure 2, left straight length 1 and right straight length 9 conllinear, and vertical with left transition straight length 4, three-arc section 5, right transition straight length 6, left straight length 1 and right straight length 9 length are 8mm;
As shown in Figure 2, left straight length 1 and the first arc section 2 tangent, first arc section 2 and the second arc section 3 tangent, second arc section 3 is tangent with left transition straight length 4, left transition straight length 4 and three-arc section 5 tangent, three-arc section 5 is tangent with right transition straight length 6, right transition straight length 6 and the 4th arc section 7 tangent, 4th arc section 7 and the 5th arc section 8 tangent, the 5th arc section 8 is tangent with right straight length 9;
As shown in Figure 2, the first arc section 2, second arc section 3, the 4th arc section 7 and the 5th arc section 8 radius are 2mm, are 1/4 circular arc;
As shown in Figure 2, left transition straight length 4 and right transition straight length 6 length are 2mm;
As shown in Figure 2, three-arc section 5 radius is 4mm, is semi-circle;
As shown in Figure 1, with the mid point at left straight length 1 and right straightway 9 interval for true origin, defining direction, left straight length 1 place is x-axis, and postive direction to the right; Y-axis postive direction upwards; Z-axis is determined according to left hand rule;
As shown in Figure 1, left straight length 1 be positioned at-x-axis line on; First arc section 2 is positioned on (-x+y) face; Second arc section 3 is positioned on (-x+z) face; Left transition straight length 4 is parallel with y, and is positioned on (+y+z) face; Three-arc section 5 one end is positioned on (+y+z) face, and the other end is positioned on (+y-z) face; Right transition straight length 6 is parallel with y, and is positioned on (+y-z) face; 4th arc section 7 is positioned on (-x-z) face; 5th arc section 8 is positioned on (+x+y) face; Right straight length 9 is positioned at+x-axis line on.
Claims (8)
1. one kind is applied to the capillary tube of single constituent element thruster, it is characterized in that: this capillary tube is formed by a straight tube bending, this capillary tube comprises left straight length (1), the first arc section (2), the second arc section (3), left transition straight length (4), three-arc section (5), right transition straight length (6), the 4th arc section (7), the 5th arc section (8) and right straight length (9);
Left straight length (1), the first arc section (2), the second arc section (3), left transition straight length (4), three-arc section (5), right transition straight length (6), the 4th arc section (7), the 5th arc section (8) and right straight length (9) are linked in sequence successively and seamlessly transit;
With the mid point at left straight length (1) and right straightway (9) interval for true origin, defining left straight length (1) direction, place is x-axis, and postive direction to the right; Y-axis postive direction upwards; Z-axis is determined according to left hand rule;
Left straight length (1) is positioned at-x-axis line on; First arc section (2) is positioned on (-x+y) face; Second arc section (3) is positioned on (-x+z) face; Left transition straight length (4) is parallel with y, and is positioned on (+y+z) face; Three-arc section (5) one end is positioned on (+y+z) face, and the other end is positioned on (+y-z) face; Right transition straight length (6) is parallel with y, and is positioned on (+y-z) face; 4th arc section (7) is positioned on (-x-z) face; 5th arc section (8) is positioned on (+x+y) face; Right straight length (9) is positioned at+x-axis line on.
2. a kind of capillary tube being applied to single constituent element thruster according to claim 1, it is characterized in that: described capillary tube external diameter is of a size of 0.2mm ~ 0.7mm, wall thickness is 0.05mm ~ 0.3mm.
3. a kind of capillary tube being applied to single constituent element thruster according to claim 1, it is characterized in that: described left straight length (1) is tangent with the first arc section (2), first arc section (2) is tangent with the second arc section (3), second arc section (3) is tangent with left transition straight length (4), left transition straight length (4) is tangent with three-arc section (5), three-arc section (5) is tangent with right transition straight length (6), right transition straight length (6) is tangent with the 4th arc section (7), 4th arc section (7) is tangent with the 5th arc section (8), 5th arc section (8) is tangent with right straight length (9).
4. a kind of capillary tube being applied to single constituent element thruster according to claim 1, it is characterized in that: left straight length (1) and right straight length (9) conllinear, and vertical with left transition straight length (4), three-arc section (5), right transition straight length (6), left straight length (1) and right straight length (9) length are a.
5. a kind of capillary tube being applied to single constituent element thruster according to claim 1, it is characterized in that: the first arc section (2), the second arc section (3), the 4th arc section (7) and the 5th arc section (8) are 1/4 circular arc, and its radius is r.
6. a kind of capillary tube being applied to single constituent element thruster according to claim 1, is characterized in that: left transition straight length (4) and right transition straight length (6) length are r.
7., according to the arbitrary described a kind of capillary tube being applied to single constituent element thruster of claim 1-6, it is characterized in that: three-arc section (5) radius is 2r, is semi-circle.
8. a kind of capillary tube being applied to single constituent element thruster according to claim 7, it is characterized in that: before capillary tube is bending, overall length is S=2a+ (4 π+2) r, capillary pipe length L=2a+2r after bending, S requires according to flow resistance and capillary inner diameter is determined, L determines according to single constituent element thruster frame size, according to S and L, solve and obtain capillary form size
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510849328.5A CN105423001B (en) | 2015-11-27 | 2015-11-27 | A kind of capillary applied to single group member thruster |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510849328.5A CN105423001B (en) | 2015-11-27 | 2015-11-27 | A kind of capillary applied to single group member thruster |
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| CN105423001A true CN105423001A (en) | 2016-03-23 |
| CN105423001B CN105423001B (en) | 2017-07-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105927423A (en) * | 2016-04-20 | 2016-09-07 | 北京控制工程研究所 | Jetting structure used for single-component catalytic decomposition thruster and assembling method of jetting structure |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03265780A (en) * | 1990-03-15 | 1991-11-26 | Tlv Co Ltd | Fluid transfer device |
| US20040245406A1 (en) * | 2003-06-06 | 2004-12-09 | Guiheen James V. | Micropump-based microthruster |
| CN101858374A (en) * | 2010-05-21 | 2010-10-13 | 北京理工大学 | Design method of serial-connection laminar flow capillary |
| US20140145036A1 (en) * | 2012-11-28 | 2014-05-29 | Mitsubishi Heavy Industries, Ltd. | Orbit attitude control device, and method of controlling orbit attitude |
| CN104089112A (en) * | 2014-06-27 | 2014-10-08 | 北京控制工程研究所 | Flexible pipeline of electric propulsion system thrust vector adjustment mechanism |
| 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 |
-
2015
- 2015-11-27 CN CN201510849328.5A patent/CN105423001B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03265780A (en) * | 1990-03-15 | 1991-11-26 | Tlv Co Ltd | Fluid transfer device |
| US20040245406A1 (en) * | 2003-06-06 | 2004-12-09 | Guiheen James V. | Micropump-based microthruster |
| CN101858374A (en) * | 2010-05-21 | 2010-10-13 | 北京理工大学 | Design method of serial-connection laminar flow capillary |
| US20140145036A1 (en) * | 2012-11-28 | 2014-05-29 | Mitsubishi Heavy Industries, Ltd. | Orbit attitude control device, and method of controlling orbit attitude |
| CN104089112A (en) * | 2014-06-27 | 2014-10-08 | 北京控制工程研究所 | Flexible pipeline of electric propulsion system thrust vector adjustment mechanism |
| 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 |
Non-Patent Citations (1)
| Title |
|---|
| 陈君: "单组元推力器毛细管两相流影响分析", 《中国空间科学技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105927423A (en) * | 2016-04-20 | 2016-09-07 | 北京控制工程研究所 | Jetting structure used for single-component catalytic decomposition thruster and assembling method of jetting structure |
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| CN105423001B (en) | 2017-07-28 |
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