CN104443437B - A kind of piezoelectric type microthruster - Google Patents
A kind of piezoelectric type microthruster Download PDFInfo
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- CN104443437B CN104443437B CN201410746564.XA CN201410746564A CN104443437B CN 104443437 B CN104443437 B CN 104443437B CN 201410746564 A CN201410746564 A CN 201410746564A CN 104443437 B CN104443437 B CN 104443437B
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Abstract
The invention provides a kind of piezoelectric type microthruster, include admission port (1), shell (2), power interface (3), filter (4), reseting spring leaf (5), spool (6), piezoelectric stack (7), pad spring (8), valve seat (9), seal ring (10), adjustment ring (11), pedestal (12), nozzle (13).In non-energising situation, the surface of spool (6) and the intimate surface of valve seat (9) and adjustment ring (11) are fitted, and thruster is in closed condition; In energising situation, due to the deformation of piezoelectric stack (7), spool (6) will produce displacement, and the surface of spool (6) is separated with the surface of valve seat (9) and adjustment ring (11), thruster is opened jet, produces thrust.Sealing element in the present invention, as spool (6), valve seat (9) and adjustment ring (11) are metallic material, is sealed into metal sealing therefore in the present invention.Piezoelectric type microthruster response time is short, thrust continuously adjustabe, low in energy consumption, the life-span is long, microsatellite and guided missile precise orbit determination can be met to the strict demand of micromass culture system, and quality is light, volume is little, for microsatellite saves more quality and volumetric spaces.
Description
Technical field
The invention belongs to spacecraft propulsion system technical field, particularly a kind of piezoelectric type microthruster.
Background technology
Existing microthruster all adopts Electromagnetic Drive, and its principle of work is as follows: when input voltage, and magnet coil produces application force, attracts valve body, away from valve seat, open gas flow path, gas enters from admission port, flow through fixing gas flow path, finally from nozzle ejection, realize progradation; When power cut-off, the application force of magnet coil disappears, and valve body gets back to valve seat under the screen resilience effect of spring, and close gas flow path, progradation terminates.In existing microthruster, the effect of electromagnetic valve is as bolt, for opening and closing gas flow path, the size of this gas flow path and path are changeless, therefore when stream is opened, in unit time, the flow of gas is fixing, thus the thrust produced in the unit time is also fixing.And existing microthruster is in stable state progradation, because gas flow path is in open mode always, therefore magnet coil needs to continue energising to attract valve body, causes power consumption larger.With rubber seal between the valve body of existing microthruster and valve seat, prevent from occurring Leakage Gas when switch cuts out.Because the elastic strength of rubber is little, therefore in sealing situation, rubber can produce larger deformation, spool and valve seat is caused to be not easy to be separated, namely when the switch is opened, first the rubber deformation will experienced on valve seat and spool reverts to the stage of zero, then could realize being separated of spool and valve seat, produce gas flow, therefore the response time of switch is long.In addition, data show that electromagnetic valve switch is on average only 100,000 ~ 200,000 times service life.Described in summary, existing microthruster Problems existing mainly contains: thrust is non-adjustable, response time is long, power supply power consumption is larger, the life-span is shorter, is difficult to the demand meeting microsatellite.
Summary of the invention
Due to the fast development of microsatellite (10 ~ 500kg), more and more higher to the performance requriements of microthruster, particularly very harsh requirement is proposed to its power consumption, response characteristic, life-span etc.The object of the invention is long for the microthruster response time of Electromagnetic Drive, that thrust is unadjustable, power consumption is high, the life-span is short deficiency, there is provided a kind of driving type piezoelectric actuator microthruster, to meet microsatellite and guided missile precise orbit determination to the strict demand of micromass culture system.
In order to solve the problems of the technologies described above, the invention provides a kind of piezoelectric type microthruster, comprising: admission port, filter, Piexoelectric actuator, adjustment ring, valve seat, pedestal, seal ring and nozzle; Be coaxial configuration with upper-part and all wrapped up by same shell; Shell there is the power interface being provided with piezoelectric stack electrode, for accessing input voltage.
Described Piexoelectric actuator comprises piezoelectric stack, T-shaped spool, reseting spring leaf, pad spring; Piezoelectric stack is cylindrical shape, in the middle of the base being clamped in T-shaped spool and pad spring; The base of T-shaped spool is at inlet end, and pad spring is at jet end; Reseting spring leaf is positioned at valve core base opposite side, plays a supportive role; Pad spring and reseting spring leaf center have circular hole; T-shaped spool is made up of the core body of base and protrusion, and core body passes from piezoelectric stack center cavity and pad spring center circular hole, and when voltage is zero, fit in the surface of core body head and adjustment ring and valve seat, forms sealing; T-shaped center spool axis place is cavity, and cavity one end is closed, and one end open, oral area is towards inlet end, and core body sidewall has several aperture and cavity connects.
In existing thruster, between valve seat and spool, all adopt rubber seal, and the parts in the present invention for sealing, the making material as spool, valve seat and adjustment ring is metal, and what therefore the present invention adopted is metal sealing.
Described reseting spring leaf and pad spring all adopt double-deck series connection disc spring design.
In the present invention, thruster switch is realized by the move under influence of spool at piezoelectric stack and spring system (i.e. reseting spring leaf and pad spring), common individual layer disc spring or coil spring cannot provide enough large application force to promote valve core movement, therefore the reseting spring leaf in the present invention and pad spring all adopt the design plan of two disc spring series connection, strengthen the application force of spring system, thruster switch successfully can be opened or close.
Described T-shaped spool core body is designed to truncated conical shape near valve seat one end portion, and the angle in its round platform between axial plane bus is between 25 ° to 60 °.In the present invention, the round platform design of poppet head can amplify the restoring force of reseting spring leaf, is conducive to fitting tightly between spool and adjustment ring.
It is that density is lower than 4.5kg/m that described admission port, shell, spool, valve seat and adjustment ring make material
3, tensile strength such as, higher than the light-weight metal of 600MPa, titanium alloy TC 4.
It is the metal of strength under shock higher than 306J/m, good toughness that described filter, reseting spring leaf and pad spring make material, as bryllium bronze.The advantage of piezoelectric type microthruster of the present invention is:
(1) response is fast.The switch of this thruster is realized by the separation between metal surface and laminating.In existing thruster, rubber seal is adopted between valve seat and spool, because the elastic strength of rubber is very little compared to metal, so under identical stress condition, the strain ratio metal of rubber is much larger, causes spool and valve seat to be not easy to be separated, namely when spool is lifted off a seat, first the rubber deformation will experienced on valve seat and spool reverts to the stage of zero, then could realize being separated of spool and valve seat, produces gas flow; And what adopt in the present invention is metal sealing, relative rubber, the distortion of metal is almost negligible, therefore once spool setting in motion, without the need to experiencing the process that Metal Deformation recovers, can directly realize being separated, produce gas flow, so speed of response of the present invention is faster, response time is between 0.1 ~ 2ms, and general solenoid valve fastest response is between 10 ~ 20ms, therefore piezoelectric type thruster can realize pulsed operation process fast.
(2) good airproof performance.For the parts of air seal in the present invention, the material as spool, valve seat and adjustment ring adopts metallic material, and the rubber that metal uses in the existing microthruster of fine limit work rear surface roughness arithmetic mean deviation ratio is little, and therefore the sealing property of metal is better; In addition, the bilayer series connection disc spring design of reseting spring leaf and pad spring increases application force, and the design of the round platform of spool can amplify the restoring force of reseting spring leaf further, when angle such as, in round platform between axial plane bus is between 25 ° to 60 °, the restoring force that reseting spring leaf can be provided amplifies 1.1 to 1.93 times, thus make to fit tightly between spool and adjustment ring, ensure good sealing property; And the making material of reseting spring leaf and pad spring is that strength under shock is high, the metal of good toughness, also can not break under the application force of 2000 ~ 4000N.
(3) adjustable thrust.The feature that the present invention utilizes the deflection of piezoelectric stack to be directly proportional to input voltage size, can realize the function being adjusted thruster thrust size by regulating voltage.When input voltage changes, the longitudinal travel of piezoelectric stack will change, thus change the displacement of spool, and then change the size of gas flow path, the flow of propelling gas in the final change unit time, thus realize the continuously adjustabe of 0 ~ 10mN thrust, to meet microsatellite and guided missile precise orbit determination to the requirement of micromass culture system.And electromagnetic valve only plays the effect of switch, cannot change uninterrupted, the thrust adopting its thruster as actuator to produce is fixed value.
(4) low in energy consumption.Utilize the deformation of piezoelectric stack to the characteristic of change of voltage sensitivity, the present invention's power when transient working is very low, is about between 1.0 ~ 2.0W; Utilize piezoelectric stack in electric principle, be equal to the characteristic of electric capacity, in stable state progradation, electric current in circuit is zero, therefore its power when steady operation is 0W, do not consume energy, can by the Power supply that saves to other energy-consuming parts of satellite, and electromagnetic valve thruster is when steady operation, power consumption average out to about 4W.
(5) long service life.Electromagnetic valve switch average out in service life 100,000 ~ 200,000 times, and piezoelectric type switch on average reaches 1,000,000 times service life.
(6) the making material of admission port, shell, spool, valve seat and adjustment ring in piezoelectric type microthruster of the present invention is light-weight metal, such as titanium alloy TC 4, alleviate angle of rake quality, and structure is simple, volume is little, can be microsatellite and save more quality and volumetric spaces.
In a word, replace the piezoelectric type thruster of electromagnetic component development of new with piezoelectric stack, significant to micromass culture technical development.
Accompanying drawing explanation
Fig. 1 is piezoelectric type microthruster inner structure cutaway view of the present invention
Fig. 2 is piezoelectric type microthruster stereoscopic schematic diagram of the present invention
Fig. 3 is the schematic diagram of middle filtrator of the present invention
Fig. 4 is Intermediate gasket spring stereoscopic schematic diagram of the present invention
Fig. 5 is spool stereoscopic schematic diagram in the present invention
Fig. 6 is reseting spring leaf stereoscopic schematic diagram in the present invention
Fig. 7 is spool principle of work schematic diagram in the present invention
Fig. 8 is the gas flow path schematic diagram of piezoelectric type microthruster in the present invention
Detailed description of the invention
Below in conjunction with principle of work and accompanying drawing, piezoelectric type microthruster of the present invention is described further.It should be noted that at this, the explanation for these embodiments understands the present invention for helping, but does not form limitation of the invention.
This Piexoelectric actuator utilizes piezoelectric stack under electric field action, produce the characteristic of deformation, and the effect in conjunction with reseting spring leaf and pad spring promotes T-shaped valve core movement, realizes the on-off action of thruster.The principle of work of piezoelectric type microthruster of the present invention is: under given voltage, piezoelectric stack axially will increase miniature scale along microthruster, promote spool to move to admission port direction, and pressed home spring leaf and pad spring make it that deformation occur, now poppet head is separated with valve base surface with adjustment ring, form gas flow path, from the gas that admission port is come in, flow through filter, valve core inside cavity, via the aperture on spool sidewall, flow into the gap between spool and adjustment ring, spray finally by jet pipe; When voltage is zero, piezoelectric stack will recover original length, and spool will move to nozzle direction under the effect of reseting spring leaf, and poppet head and adjustment ring and valve base surface are fitted, and realize sealing, close gas flow.Therefore under pulse power effect, the micrometric displacement that piezoelectric stack produces changes with impulse form, spool sway is driven: when spool moves to admission port direction under reseting spring leaf and the combined action of pad spring, then gas circuit is opened, air-flow sprays, otherwise spool and adjustment ring and valve seat are close together, gas circuit disconnection, jet stopping, thus the switch control rule realizing microthruster.
Details are as follows for each component working principle:
(1) piezoelectric stack principle of work
Piezoelectric stack is made up of multi-disc piezoceramic, and circuit is connected in parallel, and the voltage namely on every sheet pottery is identical.Be insulating glass between ceramic plate, inner adhesion without adhesiver annex is made by solid state sintering technique.Due to the axis direction that direction of polarization is along piezoelectric stack, therefore the longitudinal travel of piezoelectric stack is equivalent to the summation of all ceramic plate axial displacements.
Definition δ (unit: rice) is the longitudinal thickness size of every sheet piezoceramic; N is the sheet number of the piezoceramic comprised in piezoceramic; L (unit: rice) is the length of piezoelectric stack; D (unit: rice/volt) is one of piezoelectric coefficients of piezoceramic, it reflects the piezoelectric properties of material; Above four parameters are known parameters; V (unit: volt) is input voltage; Δ δ (unit: rice) is the axial deflection of monolithic piezoelectric ceramic; Δ l (unit: rice) is the axial total deformation of piezoelectric stack.
n＝l/δ(1)
Δδ＝dV(2)
As can be seen from (3) formula, when given input voltage, piezoelectric stack will produce axial deformation, and spool is moved to admission port direction, and make retracing spring and pad spring generation deformation, and the axial deflection Δ l of piezoelectric stack changes with the change of voltage.
(2) spool principle of work
1. thruster closed condition
When thruster cuts out, definition F
10, F
20, F
30(unit: newton) is respectively pad initial tension of spring, conical surface seal predetermincd tension, retracing spring predetermincd tension; x
10, x
30(unit: rice) is respectively pad spring pre compressed magnitude, retracing spring pre compressed magnitude; k
1, k
3(unit: Newton/meter) is respectively the rigidity of pad spring and retracing spring.Following condition is met between predetermincd tension:
F
10+F
20＝F
30(4)
F
10＝k
1x
10(5)
F
30＝k
3x
30(6)
Comprehensively (4), (5), (6) Shi Ke get
F
20＝k
3x
30-k
1x
10(7)
2. thruster open mode
When thruster is opened, definition F
1, F
3(unit: newton) is respectively pad spring stress, retracing spring stress; x
1, x
3(unit: rice) is the amount of compression of pad spring, retracing spring respectively; Δ l (unit: rice) is the total deformation of piezoelectric stack.Following condition is met between each parameter:
F
1＝F
3(8)
F
1＝k
1x
1(9)
F
3＝k
3x
3(10)
x
10+x
30＝x
1+x
3-Δl(11)
Comprehensively (8), (9), (10), (11), can obtain
Therefore, when thruster is opened, spool displacement is
From (14) formula, the axial displacement l produced by piezoelectric stack accurately can calculate the displacement x of spool.
(3) jet pipe principle of work
The inertial forces F (unit: newton) of thruster is calculated by following formula:
In formula,
(unit: Kilograms Per Second) is mass-flow rate of propellant, the gas constant that R (unit: joule/mole * degree Kelvin) is propellant, T
c(DEG C) is nozzle throat gas flow temperature, and γ is propellant specific heat ratio.When voltage changes, piezoelectric stack produces different longitudinal travels, thus cause between spool from adjustment ring, producing different apertures, mass-flow rate of propellant is changed, from (15) formula, when flow changes, the application force of corresponding thruster also changes, and also namely can adjust the size of thruster thrust by changing voltage.
As shown in Figure 1, a kind of piezoelectric type microthruster, it includes admission port 1, shell 2, power interface 3, filter 4, reseting spring leaf 5, spool 6, piezoelectric stack 7, pad spring 8, valve seat 9, seal ring 10, adjustment ring 11, pedestal 12, nozzle 13.Thruster stereoscopic figure as shown in Figure 2.
It is light-weight metal that admission port 1, shell 2, spool 6, valve seat 9 and adjustment ring 11 make material, and the present embodiment adopts titanium alloy TC 4, less to ensure the quality of whole thruster; Filter 4, reseting spring leaf 5 and pad spring 8 make the metal that material is good toughness, and the present embodiment adopts bryllium bronze, and this material can not be damaged under the restoring force effect of 2000 ~ 4000N; Power interface 3, pedestal 12 are corrosion-resistant steel manufacture; Seal ring 10 material is rubber.
Piezoelectric type microthruster integral structure of the present invention is cylinder.In FIG, microthruster right-hand member outshot is admission port 1, and its internal diameter is 1.00mm, and external diameter is 4.00mm; Shell 2 diameter is 27.20mm, and on side wall of outer shell, outwardly position is power interface 3, and interface 3 is threaded with the contact conductor base of piezoelectric stack 7, and centre is provided with two apertures for accessing power supply;
Filter 4 is for having the disk of flange, and its front elevation as shown in Figure 3.Described Fiber Diameter is 21.00mm, and thickness is 1.75mm, and thickness of flange is 1.00mm, is highly 1.25mm, and in the circular scope that circle centre position diameter is 5.00mm, be uniformly distributed 67 diameters is the aperture of 0.05mm.Filter 4 is used for filtering the gas of coming in from admission port, and it is adjacent with admission port, is placed on the left of admission port, and is communicated with the inlet channel of spool 6.
The structure of reseting spring leaf 5 as shown in Figure 6, the disk by two with flange is formed, and two disks are concentric structure, and disc centre place has diameter to be the circular hole of 4.00mm, connect with the short cylinder that internal diameter is 4.00mm, external diameter is 5.00mm, length is 1.00mm between two disks, for inserting wherein by spool 6, roundel external diameter is 17.90mm, and thickness is 1.25mm, big disk external diameter is 19.00mm, thickness is 1.25mm, and flange height is 2.00mm, and thickness is 1.00mm.The left side flange of reseting spring leaf 5 is just in time inserted in the interior edge of filter 4 flange, and right side connects with the base of spool 6.
Spool 6 is designed to T-shaped, and structure as shown in Figure 5.Its base is discoid, and external diameter is 20.00mm, and thickness is 2.75mm, and flange height is 1.25mm, and thickness is 1.05mm, and on the left of reseting spring leaf 5, the flange of big disk is just in time inserted in the interior edge of this base flange; The cylinder inlet channel internal diameter that base circle centre position protrudes to inlet end is 1.50mm, and external diameter is 4.00mm, and this cylinder inserts the center hole of reseting spring leaf 5; The left side of valve core base contacts with piezoelectric stack 7, plays a supportive role; To the hollow cylinder that jet end protrudes on valve core base, hollow internal diameter is 1.50mm, this part is made up of cylinder and round platform, high order end is external diameter is 2.92mm, length is the cylinder of 1.38mm, next is upper base diameter is 3.20mm, diameter of going to the bottom is 5.00mm, length is the round platform of 4.06mm, and the angle of round platform bus and central axis is 25 °.This cylinder jointly realizes metal sealing with adjustment ring 11 together with round platform.Be thirdly external diameter be 5.00mm, length is the cylinder of 4.00mm, and 8 apertures that this cylinder post jamb is evenly arranged, for being communicated with internal gas runner, air-flow can be flowed out from the inlet channel of spool 6, thus enter in the gap of spool 6 and pad spring 9 and adjustment ring 11.Thirdly for diameter be 5.40mm, length is that the annulus of 1.50mm is protruding, the inwall of it and pad spring fits tightly, and for preventing gas from flowing to inlet end, and plays a supportive role to pad spring.The annulus projection left side is external diameter is 5.00mm, length is the cylinder of 14.72mm, and its right side place has the annular arrangement that a diameter is 6.90mm, length is 2.00mm protruding, and its outer wall and the internal diameter of piezoelectric stack fit tightly.
Piezoelectric stack 7 is cylinder type, internal diameter 6.90mm, external diameter 16.00mm, when voltage is zero, length is 20.00mm, and the hollow parts of cylinder inserts spool 6, internal diameter and spool 6 are close to fixing, and cylinder right side is connected with spool 6 base, and left side contacts with pad spring 8.
The lateral plan of pad spring 8 as shown in Figure 4.These parts are hollow structure, be external diameter 6.90mm from right to left respectively, internal diameter 5.40mm, length is the thin circular cylinder of 3.60mm, for inserting spool left end head; Next is external diameter 18.00mm, internal diameter 5.40mm, thickness are the disk of 0.90mm; The cylinder parameter connected with on the left of disk is external diameter 10mm, internal diameter 5.40mm, length are 1.00mm; And then left for upper base diameter 15.00mm, diameter 18.00 of going to the bottom, highly be the round platform of 1.20mm, round platform upper bottom surface has a diameter 14.60mm, is highly the cylindrical concave of 1.01mm.It is middle with piezoelectric stack 7 that described pad spring 8 is positioned at valve seat 9, spool 6 inserts its hollow parts, on the inwall of its thin circular cylinder and spool hollow cylinder, chime rings fits tightly, its disk right side contacts with piezoelectric stack 7, piezo stack is piled up to the effect of fixed pedestal, carrying out metal sealing to spool 6 and adjustment ring 11 together with reseting spring leaf 5 provides application force.Its round platform sidewall contacts with valve seat 9, and being interacted by the metal conical surface produces predetermincd tension, prevents Leakage Gas.Form cylindric cavity between round platform concave surface and valve seat 9, the air-flow flowed out from spool 6 afterbody aperture can be stored in cavity, can to the buffer action of air-flow.When valve core movement, this concave surface will to jet end motion, will fit tightly to be formed with valve seat 9 to seal, and prevents gas from flowing into.
Seal ring 10 is arranged between adjustment ring 11 and valve seat 9, for preventing adjustment ring 11 and valve seat 9 screw-threaded engagement imprecision gas leakage.
Adjustment ring 11 is fixed on valve seat 9, and the nose shape of its inner chamber and spool 6 closely agrees with, to realize metal sealing.
Jet pipe 13 is arranged on pedestal 12, and the gas of coming in from admission port 1 sprays through jet pipe 13, realizes propulsion functions.
Concrete progradation is: under pulse power effect, piezoelectric stack 7 produces axial micrometric displacement, drives spool 6 to inlet end motion, adjustment ring 11 is separated with spool 6 under the combined action of reseting spring leaf 5 and pad spring 8, produce gas flow path, principle of work as shown in Figure 7.Figure 8 shows that the partial enlargement image of gas flow path: air-flow flows into thruster body by admission port 1, filter through filter 4, flow in spool 6, the gap between adjustment ring 11 and spool 6 is flowed into from spool 6 head aperture, spray finally by by jet pipe 13, produce thrust, thus realize the switch control rule of microthruster.
Table 1 provides voltage when being fixed as 250V below, the stable state thrust that under various inlet mouth pressure, nozzle pressure and ambient temperature, piezoelectric type thruster of the present invention produces.
Table 1 voltage is certain, the thrust magnitude under different pressures and temperature conditions
| Inlet pressure, × 10 5Pa | Ambient temperature, DEG C | Nozzle pressure, Pa | Stable state thrust, mN |
| 1.0 | 25 | 1.1 | 2.39 |
| 1.0 | 25 | 0.97 | 2.43 |
| 1.5 | 24 | 2.0 | 1.83 |
| 1.5 | 24 | 1.2 | 1.78 |
| 1.5 | 24 | 1.0 | 5.73 |
| 2.0 | 24 | 1.0 | 5.62 |
| 4.0 | 24 | 1.0 | 8.53 |
| 5.0 | 23 | Air environment | 3.15 |
| 5.0 | 25 | Air environment | 0.65 |
| 5.0 | 25 | 2.1 | 8.41 |
| 5.0 | 25 | 1.0 | 10.17 |
Data as can be seen from table 1, piezoelectric type thruster of the present invention can provide the thrust within the scope of 0 ~ 10mN.
Table 2 for ambient temperature be 25 DEG C, when nozzle pressure is 1.1Pa, the stable state thrust that under different voltage and inlet pressure condition, piezoelectric type thruster of the present invention produces.
Table 2 temperature and nozzle pressure are certain, the thrust magnitude under different voltage, various inlet mouth pressure condition
Data as can be seen from table 2, by changing voltage, piezoelectric type thruster of the present invention can realize the adjustment of thrust size within the scope of 0 ~ 10mN.
In above-mentioned experiment, the response time average out to 1.5ms of piezoelectric type thruster can be recorded.
Claims (5)
1. a piezoelectric type microthruster, is characterized in that: it comprises admission port (1), filter (4), Piexoelectric actuator, adjustment ring (11), valve seat (9), pedestal (12), seal ring (10) and nozzle (13); Be coaxial configuration with upper-part and all wrapped up by same shell (2); Shell (2) there is the power interface being provided with piezoelectric stack (7) electrode, for accessing input voltage;
Described Piexoelectric actuator comprises piezoelectric stack (7), T-shaped spool (6), reseting spring leaf (5), pad spring (8); Piezoelectric stack (7) is cylindrical shape, and the base and the pad spring (8) that are clamped in T-shaped spool (6) are middle; The base of T-shaped spool (6) is at inlet end, and pad spring (8) is at jet end; Reseting spring leaf (5) is positioned at valve core base opposite side, plays a supportive role; Pad spring (8) and reseting spring leaf (5) center have circular hole; T-shaped spool (6) is made up of the core body of base and protrusion, core body passes from piezoelectric stack (7) center cavity and pad spring (8) center hole, when voltage is zero, fitting in the surface of its head and adjustment ring (11) and valve seat (9), forms sealing; T-shaped spool (6), valve seat (9) and adjustment ring (11) are metallic material, described in be sealed into metal sealing; T-shaped spool (6) central axis place is cavity, and cavity one end is closed, and one end open, oral area is towards inlet end, and core body sidewall has several aperture and cavity connects.
2. piezoelectric type microthruster according to claim 1, is characterized in that: described reseting spring leaf and pad spring all adopt double-deck series connection disc spring design.
3. piezoelectric type microthruster according to claim 1, it is characterized in that: described T-shaped spool (6) core body is designed to truncated conical shape near valve seat (9) one end portion, and the angle in its round platform between axial plane bus is between 25 ° to 60 °.
4. piezoelectric type microthruster according to claim 1, is characterized in that: it is that density is lower than 4.5kg/m that described admission port, shell, T-shaped spool, valve seat and adjustment ring make material
3, tensile strength is higher than the light-weight metal of 600MPa.
5. piezoelectric type microthruster according to claim 1, is characterized in that: it is the metal of strength under shock higher than 306J/m that described filter, reseting spring leaf and pad spring make material.
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| CN106763991B (en) * | 2016-11-22 | 2020-04-24 | 上海空间推进研究所 | Miniature electromagnetic type proportional flow control valve |
| CN107554817B (en) * | 2017-07-11 | 2020-02-14 | 西北工业大学 | Satellite composite formation method |
| CN112780443B (en) * | 2021-03-02 | 2022-03-01 | 北京航空航天大学 | Adjusting mechanism of piezoelectric ceramic micro-motion pintle injector |
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| CN100549647C (en) * | 2008-02-22 | 2009-10-14 | 哈尔滨工业大学 | Be applied to the dry damping device of electric propulsion device microthrust measuring system |
| CN102022299B (en) * | 2010-12-07 | 2012-01-25 | 中国人民解放军国防科学技术大学 | Laser microthruster |
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