CN104791136B - Solid micro-thruster array structure is used in a kind of test - Google Patents
Solid micro-thruster array structure is used in a kind of test Download PDFInfo
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Abstract
Solid micro-thruster array structure is used in a kind of test, including firing circuit layer, ignition charge layer, firing chamber layers and orifice layer, its firing circuit layer is at the bottom, the array of the M row N row for being made up of M*N firing circuit, wherein M and N is positive integer and M and N is all not less than 2, the top of firing circuit layer is ignition charge layer, ignition charge layer includes M*N igniting coyote hole, each corresponding firing circuit of igniting coyote hole, equipped with gunpowder in igniting coyote hole, the top of ignition charge layer is firing chamber layers, firing chamber layers includes M*N combustor, the corresponding igniting coyote hole of each combustor, equipped with solid propellant in combustor, the top of firing chamber layers is orifice layer, orifice layer includes M*N jet pipe, the corresponding combustor of each jet pipe.Present invention can apply to solid micro-thruster array development, the little critical dimension propelling of microthruster, micro-scale gas flow, microfluidic, control system etc. are studied.
Description
Technical field
The present invention relates to a kind of solid micro-thruster array structure, can be applicable to solid micro-thruster array development, study for the little critical dimension propelling of microthruster, micro-scale gas flow, microfluidic, control system etc., it is possible to be substantially reduced development cost, lead time etc..
Background technology
In recent years, along with the development of the technology such as micro-nano, microelectronics, micro-nano satellite just becomes one of most active research direction of space industry with a kind of completely new concept, brand-new design philosophy.Micro-nano satellite have the lead time short, investment with operation costs are low, risk is little, motility high, make it can with list star inexpensively be rapidly completed multinomial space mission, can complete, with the networking of many stars or formation flight mode, the space tasks that large satellite is difficult to be competent at again.
Along with the development of the every support technology of micro-nano satellite, it just converts from flight validation to innovation and application.Within 2013, Spaceworks company of the U.S. has issued " micro-nano satellite market prediction ", it is predicted that the year two thousand twenty, and the annual requirement of 1～50kg micro-nano satellite is reached as high as 188 by the whole world.As the platform technology micromass culture technology that micro-nano satellite is important, the application extension of micro-nano satellite there is important effect.Solid micro-thruster array has high integration, low in energy consumption, microthrust, micro-momentum, lightweight, volume is little, simple in construction, without the advantage such as movable part, installation form be flexible, it it is a kind of propulsion system having superior application prospect, it is capable of high accuracy control, it is possible to meet the micro-nano satellite requirement to propulsion system.
Current domestic and international each research institution be concentrated mainly on to the structural design of small-scale thruster array, performance test, simulation analysis, single thruster the aspect such as thrust test research on, although the U.S. proposes the concept of megacell, but does not have the research of the aspects such as the test of relative thrust device array performance and fire trial in existing document.Present stage array structure disadvantageously, can not quickly realize, adopt silica-based MEMS technology to process, be unfavorable for testing on a large scale.And firing circuit adopts the mode that each thruster individually controls, and is unfavorable for realizing popularization.
Summary of the invention
Present invention solves the technical problem that and be: overcome the deficiencies in the prior art, provide a kind of test solid micro-thruster array structure, by adopting the ranks addressing system respectively of igniting resistance series diode, can effectively realize the extension of array, also the Rapid Implementation of solid micro-thruster array it is beneficial to, it is simple to carry out large-scale associated verification test.
The technical solution of the present invention is: a kind of test solid micro-thruster array structure, including firing circuit layer, ignition charge layer, firing chamber layers and orifice layer, its firing circuit layer is at the bottom, the array of the M row N row for being made up of M*N firing circuit, wherein M and N is positive integer and M and N is all not less than 2, the top of firing circuit layer is ignition charge layer, ignition charge layer includes M*N igniting coyote hole, each corresponding firing circuit of igniting coyote hole, equipped with gunpowder in igniting coyote hole, the top of ignition charge layer is firing chamber layers, firing chamber layers includes M*N combustor, the corresponding igniting coyote hole of each combustor, equipped with solid propellant in combustor, the top of firing chamber layers is orifice layer, orifice layer includes M*N jet pipe, the corresponding combustor of each jet pipe.
Described gunpowder includes 50% black powder, 22.8% potassium chlorate, 27.2% red phosphorus.Described solid propellant is HTPB-86# propellant.
Described firing circuit includes a heating resistor and a diode, one end of heating resistor is connected with the positive pole of diode, the other end of heating resistor connects is expert in addressed line, row addressing alignment is connected with positive source, the negative pole of diode is connected in row addressed line, and row addressing alignment is connected with power cathode.
Described firing circuit layer, ignition charge layer, between firing chamber layers and orifice layer, pass through adhering with epoxy resin.Described igniting coyote hole adopts cylindrical structure.The diameter of described cylindrical structure is 1mm, is highly 0.5mm.
Described combustor adopts cylindrical structure.The diameter of described cylindrical structure is 1mm, is highly 1mm, and the spacing of two adjacent column bodies is 2mm.Described jet pipe is straight tube.
Present invention advantage compared with prior art is in that: the test solid micro-thruster array structure of the present invention, it is possible to realize the addressing of quick ranks, it is possible to realize the extensive extension of array, it is simple to carry out large-scale associated verification test.Igniting resistance and diode adopt commercial device, and array can quickly realize, and reduce lead time and cost.By adopting the ignition charge configured voluntarily, ignition success rate is high, and firing power is low.Propellant adopts granule powder charge, and combustion face is big, it is possible to increase efficiency of combustion.Array thruster combustor yardstick of the present invention is 1mm, if adopting the Chip-R of more small package, or directly it is used without the resistance of encapsulation, smaller size of array can be realized prepare, and can be used in carrying out combustor is the series of experiments such as the propellant development test of 0.5～1mm thruster array, ignition charge development test, ignition success rate development test, Micro-thrust test, and the kinetics of combustion research etc. for the researchs such as the microfluidic of solid micro-thruster, micro-combustion, micro-heat transfer and propellant has important impetus.
Accompanying drawing explanation
Fig. 1 is the theory of constitution figure of solid micro-thruster array structure of the present invention；
Fig. 2 is the array firing circuit schematic diagram of firing circuit layer of the present invention.
Detailed description of the invention
As it is shown in figure 1, be the theory of constitution figure of solid micro-thruster array structure of the present invention, including firing circuit layer, ignition charge layer, firing chamber layers and orifice layer.In Fig. 1,1 is firing circuit layer, and 2 is ignition charge layer, and 3 is firing chamber layers, and 4 is orifice layer, and 5 is heating resistor, and 6 is diode.Array firing circuit is at the bottom, and ignition charge layer is arranged on firing circuit upper strata, and ignition charge is loaded in ignition charge layer, and firing chamber layers is arranged on ignition charge layer upper strata, and propellant is loaded in firing chamber layers, and orifice layer is installed to firing chamber layers upper strata.All each layers all adopt epoxide-resin glue to be attached.Each igniting resistance corresponding ignition charge layer, firing chamber layers, an orifice layer, each layer all adopts array arrangement.
Solid micro-thruster array of the present invention adopts the firing circuit of ranks addressing, is determined the accurate location of each igniting unit by the form of ranks coordinate.Each igniting unit adopts the form of heating element heater and Diode series, and array scale is designed as M × N, forms the firing circuit of M row, N row altogether, and M and N is all higher than being equal to 2.(this general scale is to be the bigger the better, it does not have be strict with.) one end of heating resistor is connected with the positive pole of diode, the other end of heating resistor connects is expert in addressed line, and row addressing alignment is connected with positive source, and the negative pole of diode is connected in row addressed line, and row address alignment and are connected with power cathode.
The solid micro-thruster array adopting this form possesses good autgmentability, it is possible to carry out Expansion according to demand.Circuit substrate adopts epoxy resin, uses pcb board processing technology to prepare firing circuit.Heating element heater and diode all adopt paster packing forms heating element heater, it is possible to be positioned in the combustor of 0.5～1mm diameter, specifically as shown in Figure 2.
Firing circuit adopts business PCB to make, igniting resistance and be unidirectionally controlled diode and be commercial device, combustor and igniting coyote hole and orifice layer etc. all adopt high accuracy machining process, can quickly realize, and cost can be reduced, easily form fairly large array, can be used for testing concordance, performance reproducibility experiment.
Thickness and the single thruster momentum of combustor are directly related, it is possible to be determined according to thruster momentum, propellant density and estimation specific impulse.
In order to improve ignition success rate, and reduce firing power.By substantial amounts of test, present invention obtains the gunpowder component proportioning of a kind of the best, including 50% black powder, 22.8% potassium chlorate, 27.2% red phosphorus.
In order to ensure thrust effect, HTPB-86# propellant chosen by the solid propellant of the present invention.
The each layer of array adopts high strength epoxy resin to carry out bonding, uniformly puts glue by what precise glue dispensing machine realized resin glue, and thickness is 50 μm, solidified by external world's pressure between each layer, adopting array prepared by this technology, final thruster combustor is 0.5～1mm, and spacing is 1～2mm.
Adopting the material that epoxy resin is prepared as thruster structure, adopt the mach mode of high accuracy to realize the processing of thrust chamber structure, for simplifying thruster structure, jet pipe adopts straight tube form, and thrust coefficient is reduced to 1.
Adopt high accuracy beveller, it is achieved particle type medicament molding, propellant grain particle diameter is 150 μm～200 μm, and ignition charge grain diameter is 50～100 μm.
Embodiment
The solid micro-thruster structure of the present invention mainly includes firing circuit layer, ignition charge layer, firing chamber layers and orifice layer.Thruster array scale is 10 × 10 (10 row, 10 row), 100 × 100 (100 row, 100 row).
1 solid micro-thruster array structure
(1) micro-thruster array firing circuit
Firing circuit includes designing for two-layer, and upper strata is resistance, and lower floor is diode, it is attached by line and alignment, each heating resistor one end is connected with a diode cathode, and the other end of heating resistor is connected on line, and the negative pole of diode is connected on alignment；Line and alignment are respectively distributed in different surface-mounted integrated circuits, are independent of each other.For distinguishing and stand alone type firing circuit, here this kind of firing circuit is called array firing circuit.
(2) microthruster thrust chamber
Micro-thruster array thrust chamber is divided into two-layer, respectively ignition charge layer and firing chamber layers, for the storage of ignition charge and propellant, adopts epoxide resin material.Table 1 lists the physical property of epoxide resin material.
The performance of table 1 epoxide resin material
On firing chamber layers, each chamber diameter is 1mm, and combustor height is 1mm, and adjacent combustor spacing is 2mm, thrust chamber becomes ranks to arrange, the number of thrust chamber number and heating resistor and position consistency, for the array of 10 × 10, possessing every a line thrust chamber number is 10, and row thrust chamber number is 10.On ignition charge layer, each igniting chamber diameter is 1mm, and igniting coyote hole height is 0.5mm.
(3) orifice layer
Jet pipe adopts straight tube, and jet size is 0.4mm, is highly 0.3mm.Adjacent lance spacing is 2mm, and jet pipe becomes ranks to arrange, the number of jet pipe number and heating resistor and position consistency, and for the array of 10 × 10, possessing every a line jet pipe number is 10, and row jet pipe number is 10.
(4) propellant and ignition charge select
Ignition charge, based on black powder, adds part potassium chlorate, red phosphorus etc., and particle diameter is the particles powder charge of 50 μm～100 μm.Propellant adopts HTPB-86# propellant, and particle diameter is 150 μm～200 μm.
If required igniter quantity is mig, according to the empirical equation that put-put system obtains:
mig=0.95 (VgAbSpLp)0.32
In formula, VgFor free volume；AbFor burning area；SpFor breathing area (cm2)；LpFor grain length.
HTPB-86# propellant density pgr=1.76g/cm-3, thruster charging quality is 1mg, charge volume Vp:
In formula, mpFor charging quality.
Propellant mean diameter is 0.075mm, it is known that individual particle volume:
Propellant grain number:
The combustion model of propellant thinks that all of granule burns simultaneously, then combustion face is represented by:
It is computed obtaining: mig=0.0128mg.
2 techniques and preparation method
(1) firing circuit preparation method
On manufacturing, this firing circuit adopts chip mounter to carry out machine welding, welds diode and resistance, (top layer welding kesistance, backing weld diode) and then composition firing circuit array on thruster array firing circuit.Respectively being connected with 10 resistance on line R1～R10, each resistance is each connected with diode, and diode is connected on alignment C1～C10.
Thruster combustor spacing distance is 2mm, and therefore between igniting resistance center, spacing is 2mm, and firing circuit is designed according to the method for Fig. 2.Igniting resistance needs moment formation focus to light a fire, therefore the resistance of igniting resistance is significantly larger than wire, conductive line resistance values is relevant with igniting unit position, is 0.094 Europe for 100 × 100 arrays maximum value in measure traverse line, and therefore single thruster firing power loss rate is 4.7%.Heating resistor adopts the Chip-R of ROHM company, adopts 0201 encapsulation, and resistance is 2 Europe, and resistance error is 1%, can reach more than 2W through test instantaneous power, it is possible to meet the requirement of microthruster array.Diode adopts Schottky diode Rb520s-30.
(2) prepared by thrust chamber
Using precise machine machining to carry out capillary processing, error is less than 0.45%.
(3) propellant preparation method
A () grinds.Ignition charge, propellant all adopt granule powder charge, adopt High-precision instrument to carry out medicament grinding.
B () sieves.The ignition charge ground uses high-accuracy pulp classifier to sieve, and selects required particle diameter by the sieve of different meshes, and equipment uses.This test propellant particle diameter is the granule between 100 μm～200 μm；Ignition charge selects two kinds of particle diameters to be 50 μm～100 μm.
C () weighs.The high-accuracy balance adopting precision to be 0.1mg carries out the weighing of explosive payload, it is difficult to owing to carrying out the weighing of single thruster, therefore the quality weighed before and after array powder charge tries to achieve total charge, then passes through the method averaged and calculates the average explosive payload of each thruster.
(4) thruster array complete machine method for packing
Limitation due to technique, thruster cannot be integrally machined, it is therefore desirable to after each parts are processed respectively, adopts technique for sticking technology to carry out thruster encapsulation, and the reliability encapsulated directly determines service behaviour and the ignition success rate etc. of thruster, there is vital effect.
The number of plies that the present invention is packaged totally four layers.Firing circuit layer, ignition charge layer, firing chamber layers, orifice layer.Each layer is attached by high strength epoxy.After encapsulation, vacuum shelf dryer is deposited use carried out above in 24 hours.
3 fire trial checkings
10 × 10 array principle prototypes and 100 × 100 array principle prototypes that use designed Iganition control system and preparation carry out compbined test, demonstrate the feasibility etc. of the reliability of lighter, array making packaging technology.0.72W, 0.98W, 1.28W, 1.62W, 2W, 2.65W, 2.88W is selected to carry out igniting response analysis and correlation test.With 10 × 10 arrays for object of study, 75 thrusters of powder charge, each 15 thruster of power situation point, ignition charge is only loaded during test, this igniting resistance can the minimum ignition power of successful ignition be 0.72W after tested, can the 100% successful peak power got angry being 2.65W, when power is more than 3.38W, ignition success rate be 0%, and test result is as shown in table 2.
Table 2 fire trial
Table 2 is that the igniting resistance firing power selected is when being 0.72W～2.65W, it is possible to constant ignition, the time not fused.And the matching having carried out ignition charge and igniting resistance is verified.When firing power is 0.72W～2.65W, it is possible to realize the reliable ignition of 100%, ignition success rate is high, lights a fire low in energy consumption.
Igniting response time is defined as to be initially powered up generating heat from resistance and produces the time of thrust to thruster.Responding time test by thrust testboard bay, firing command is as the triggering of data collecting system, and when firing command sends, it is as shown in table 3 that thrust data acquisition system proceeds by data acquisition.
Table 3 is lighted a fire response test result
Table 3 tests thruster array igniting reliability test, and tests igniting response time.The igniting resistance and the ignition charge that adopt the design possess shorter igniting response time, it is possible to realize rapid-ignition.
The content not being described in detail in description of the present invention belongs to the known technology of those skilled in the art.
Claims (7)
1. solid micro-thruster array structure is used in a test, it is characterized in that including: firing circuit layer, ignition charge layer, firing chamber layers and orifice layer, its firing circuit layer is at the bottom, the array of the M row N row for being made up of M*N firing circuit, wherein M and N is positive integer and M and N is all not less than 2, the top of firing circuit layer is ignition charge layer, ignition charge layer includes M*N igniting coyote hole, each corresponding firing circuit of igniting coyote hole, equipped with gunpowder in igniting coyote hole, the top of ignition charge layer is firing chamber layers, firing chamber layers includes M*N combustor, the corresponding igniting coyote hole of each combustor, equipped with solid propellant in combustor, the top of firing chamber layers is orifice layer, orifice layer includes M*N jet pipe, the corresponding combustor of each jet pipe；Described gunpowder includes 50% black powder, 22.8% potassium chlorate, 27.2% red phosphorus, described solid propellant is HTPB-86# propellant, and described firing circuit includes a heating resistor and a diode, and one end of heating resistor is connected with the positive pole of diode, the other end of heating resistor connects is expert in addressed line, row addressed line is connected with positive source, and the negative pole of diode is connected in row addressed line, and row addressed line is connected with power cathode.
2. a kind of test solid micro-thruster array structure according to claim 1, it is characterised in that: described firing circuit layer, ignition charge layer, between firing chamber layers and orifice layer, pass through adhering with epoxy resin.
3. a kind of test solid micro-thruster array structure according to claim 1, it is characterised in that: described igniting coyote hole adopts cylindrical structure.
4. a kind of test solid micro-thruster array structure according to claim 3, it is characterised in that: the diameter of described cylindrical structure is 1mm, is highly 0.5mm.
5. a kind of test solid micro-thruster array structure according to claim 1, it is characterised in that: described combustor adopts cylindrical structure.
6. a kind of test solid micro-thruster array structure according to claim 5, it is characterised in that: the diameter of described cylindrical structure is 1mm, is highly 1mm, and the spacing of two adjacent column bodies is 2mm.
7. a kind of test solid micro-thruster array structure according to claim 1, it is characterised in that: described jet pipe is straight tube.
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| CN105422316B (en) * | 2015-11-30 | 2018-04-17 | 中国电子科技集团公司第四十八研究所 | A kind of solid micro-thruster firing circuit and preparation method thereof |
| CN105927423B (en) * | 2016-04-20 | 2017-08-29 | 北京控制工程研究所 | A kind of spray structure and its assembly method for single group member catalytic decomposition thruster |
| CN107264840A (en) * | 2017-06-05 | 2017-10-20 | 南京理工大学 | A kind of micro five-dimensional cathode arc thruster |
| CN110145412B (en) * | 2019-05-27 | 2020-11-03 | 北京理工大学 | Gate type solid rocket engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN101943148A (en) * | 2010-07-27 | 2011-01-12 | 北京航空航天大学 | Circuit for pulse plasma thruster |
| CN102022224A (en) * | 2010-09-08 | 2011-04-20 | 北京理工大学 | Ignition system for large-scale solid micro-thruster array |
| CN201916075U (en) * | 2010-12-23 | 2011-08-03 | 西北工业大学 | Experiment device for full-scale spray pipe thermal structure of solid-propellant rocket engine |
-
2015
- 2015-03-11 CN CN201510107038.3A patent/CN104791136B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN101943148A (en) * | 2010-07-27 | 2011-01-12 | 北京航空航天大学 | Circuit for pulse plasma thruster |
| CN102022224A (en) * | 2010-09-08 | 2011-04-20 | 北京理工大学 | Ignition system for large-scale solid micro-thruster array |
| CN201916075U (en) * | 2010-12-23 | 2011-08-03 | 西北工业大学 | Experiment device for full-scale spray pipe thermal structure of solid-propellant rocket engine |
Non-Patent Citations (1)
| Title |
|---|
| MEMS数字固体微推进器的制备与性能研究;王成玲;《中国优秀硕士学位论文》;20140731;论文第2-3章，附图2.1（a）、附图3.15、图5.3 * |
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