CN109725359A - Space debris detection device based on thin film type solar battery array - Google Patents
Space debris detection device based on thin film type solar battery array Download PDFInfo
- Publication number
- CN109725359A CN109725359A CN201811558293.XA CN201811558293A CN109725359A CN 109725359 A CN109725359 A CN 109725359A CN 201811558293 A CN201811558293 A CN 201811558293A CN 109725359 A CN109725359 A CN 109725359A
- Authority
- CN
- China
- Prior art keywords
- array
- thin
- layer
- space
- film
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Photovoltaic Devices (AREA)
- Photometry And Measurement Of Optical Pulse Characteristics (AREA)
Abstract
The invention discloses a kind of space debris detection devices based on thin film type solar battery array, including with open-topped detection shell, first layer thin-film solar cells array, second layer thin-film solar cells array and piezoelectric effect detection layers, wherein, first layer array is formed by the single solar battery cell of plating latticed array on thin polymer film respectively with second layer array, and the solar battery cell of two layers of array is respectively to the sun photaesthesia of different-waveband, and first layer solar cell array can be penetrated to the sunlight of the second layer (i.e. bottom) solar cell array sensitivity.Space debris detection device of the invention, structure is simple, and manufacturing cost is low, and the detection of space junk easy to accomplish, can obtain size, speed, direction and the qualitative data of space junk.
Description
Technical field
The invention belongs to space debris environment detection technology fields, and in particular to a kind of sky of rich model solar cell array
Between fragment detection device.
Background technique
In the space environment, " space junk " (also known as space trash) is that mankind's solar-system operation is abandoned in the discarded of space
Object is the primary pollution source of space environment.Since emitting first man made earth satellite from nineteen fifty-seven, space junk sum is
More than 4,000 ten thousand, gross mass has reached millions of kilograms, and the space junk that ground-based telescope and radar can observe increases every year on average
About 200 are increased, the space junk greater than 10 centimetres has been over 9200 now.Space junk is mainly distributed on 2000 public affairs
In low orbit area below, they constitute a serious threat to the spacecraft of terrestrial space.
Space junk size range include micron order, grade, Centimeter Level or even meter level, wherein Centimeter Level and its more than
Space junk be mainly carrier rocket Upper Stage, task end spacecraft, work when abandon object, unexpectedly disintegrate it is broken
Piece, aluminum oxide residue, sodium k particle etc.；Grade space junk is mainly spacecraft surface flakes, sputtering object, three
Al 2 O residue, sodium k particle, micrometeroroid, unexpected disintegration fragment etc.；Micron-sized space debris mainly includes that peeling is broken
Piece, sputtering object, aluminum oxide dust, micrometeroroid etc..
Space junk greater than 10 centimetres will lead to the damage of spacecraft destructiveness, due to that can pass through ground telescope at present
Or radar measuring its track, the strategy that early warning can be taken to evade are effectively prevented its injury；Centimeter Level space junk can also be with
Cause spacecraft thoroughly to damage, there is no practicable safeguard procedures at present, unique method be on Spacecraft guidance and control and operation,
Trying to reduce makes spacefarer and spacecraft that the risk of mortality damage occur；Grade space junk can result in spacecraft surface
Generation hits hole or even bulkhead is made to perforate, and impact site is different, and the degree of harm also has very big difference.
Currently, needing to design the detection device of different space junks for the position of space exploration fragment, wherein empty
Between fragment detection device according to hit detecting sensor difference can be divided into piezo-electric type detector, semi-conductor type detector, ionization
Type detector etc..
Piezo-electric type detector, as sensor, mainly there is polyvinylidene fluoride (PVDF) biography using high performance piezoelectric material
Sensor and piezoelectric ceramics (PZT) sensor.Wherein, PVDF detector is common detection means, and detection principle is to utilize
The piezoelectric effect of PVDF thin film can generate one not under impact force effect that is, when space dust high velocity impact PVDF thin film
Reversible crater, while charge signal is generated on two electrodes of film.Measuring circuit analyzes the charge signal can
With information such as the speed and qualities that obtains powder dust particle, it is suitable as the detection sensor of micro space debris and micrometeroroid.
The working principle of semi-conductor type detector is to aoxidize out one layer of very thin titanium dioxide on high purity silicon (Si) chip
Silicon (SiO2), then in silica (SiO2) one layer of aluminium film is plated on film, silicon, silicon dioxide film and aluminium film form a capacity plate antenna
Device, frequently referred to MOS semiconductor transducer.It is fabricated to space dust detector with mos sensor, referred to as semi-conductor type detects
Device.When detector work, bias voltage is provided to capacitor by external circuit.It is worn when space dust collides with sensor
When crossing aluminium film and silicon dioxide film, capacitor, which will discharge, generates electric current, an electric signal is generated in external circuit, by this
The information of micro space debris or micrometeroroid can be obtained in the analysis of signal.
Hitting ionization detector, the most commonly used is plasma-type detectors, the basic principle is that working as micro space debris
When colliding with the proof gold target center of detector, huge kinetic energy generates plasma cloud；It, can be with by the measurement of plasma
Obtain the quality of space junk, speed and at grading information.
In addition, solar cell for space use belongs to a kind of semi-conductor type detector, mainly there are silicon solar cell, unijunction GaAs too
Positive electricity pond, three-junction gallium arsenide solar battery and multijunction gallium arsenide solar cell etc..
Since silicon and unijunction gallium arsenide solar cell can only absorb the sunlight of special spectrum range, transfer efficiency is not
It is high.Therefore, being prepared into multijunction solar cell with III-V race material of different band gap widths allows it respectively selectively to absorb and turn
That changes solar spectrum is different from domain, to increase substantially the photoelectric conversion efficiency of solar cell.
Three-junction gallium arsenide solar battery is the major cell primitive of current space solar battery array, it by top battery, in
Battery and bottom battery composition, using tri- pn-junctions vertically contacted of GaInP2, GaAs, Ge to respectively to the sun can be carried out photoelectricity turn
It changes.The light of 300nm~660nm, 660nm~900nm, 900nm~1800nm wave band is absorbed respectively, three sub- batteries are logical
Tunnel junctions series connection is crossed, photoelectric conversion efficiency can reach 40% or more 28% or so.Pass through the GaAs sun more tied
Battery series connection, available better photoelectric conversion efficiency.
Since response wave band of the different thin-film solar cells to solar spectrum is different, and too by impact from space debris
Positive cell piece can not then provide effective photoelectric current.Therefore, it can use the upper layer and lower layer sun electricity with different spectral responses
Chi Zhen realizes the detection to the speed of the particulates such as space junk, direction and size.
Summary of the invention
Based on this, goal of the invention of the invention is to provide a kind of space junk spy based on thin film type solar battery array
Device is surveyed, which the principle of different-waveband sun photaesthesia, which is arranged, two layers using different thin film solar cells has one
The space thin-film solar cells of set a distance, every layer of thin-film solar cells are latticed array, broken by every layer of upper space
Piece hit caused by solar battery cell damage position and photoelectric effect mutate time come judge space junk size,
Speed and incident angle finally recycle traditional piezoelectric principle to realize the detection of the quality of fragment.
In addition, another object of the present invention is to provide a kind of sides for carrying out space debris detection using above-mentioned detection device
Method, this method is easy to operate and the detection easy to accomplish to space junk direction and quality.
Present invention employs the following technical solutions:
Space debris detection device based on thin film type solar battery array, including with open-topped detection shell,
First layer thin-film solar cells array, second layer thin-film solar cells array and piezoelectric effect detection layers, wherein first
Layer film solar battery array is arranged at the top opening position of detection shell, and second layer thin-film solar cells array is set
It sets in the detection intracorporal middle position of shell, piezoelectric effect detection layers are located at the detection intracorporal bottom of shell, wherein the first layer film is too
It is positive can cell array and second layer thin-film solar cells array respectively by thin polymer film plating latticed array it is single
Solar battery cell forms, and the solar battery cell of two layers of array is respectively to the sun photaesthesia of different-waveband, and right
The sunlight of the second layer (i.e. bottom) solar cell array sensitivity can penetrate first layer solar cell array.
Wherein, thin polymer film is for polyimides, polyfluorinated ethylene membrane, polyurethane film etc. or with these films
For the derivative film of matrix.
Wherein, the coating material of thin-film solar cells array is respectively GaInP2, GaAs, Ge or or Si, respectively correspond
Sensitive sunlight wave band be 300nm~660nm, 660nm~900nm, 900nm~1800nm, 400nm~1100nm.
Wherein, single thin film solar cell cell size is 1cm × 1cm or smaller, single thin film solar battery
Area is big for 1m × 1m or more, and specific size is depending on design.
Wherein, the spacing of first layer thin-film solar cells array and second layer thin-film solar cells array is 100mm-
1000mm。
Wherein, piezoelectric effect detection layers use polyvinylidene fluoride (PVDF) sensor or piezoelectric ceramics (PZT) sensor.
The method for carrying out space debris detection using above-mentioned probe unit, comprising the following steps:
1) after impact from space debris passes through first layer thin-film solar cells array, a certain sun electricity thereon will be penetrated
Pool unit obtains the time that space junk passes through, being set as t1 according to the time that solar battery cell photoelectric effect mutates,
According to the position that it mutates, the in-orbit position passed through of space junk is obtained, (X1, Y1) is set as；
2) when space junk further passs through second layer thin-film solar cells array, t2 and (X2, Y2) are similarly obtained,
The then speed of space junk are as follows:
3) ruler of space junk is obtained according to the numerical value of battery unit photoelectric properties mutational lesions in every layer of solar battery array
Very little size, the area of space junk is less than the area of solar battery cell, if the area of a certain solar battery cell is S1, function
Rate is W1, after impact from space debris passes through, chugging W2, then the size S2 of space junk are as follows:
S2=S1 × (W1-W2)/W1；
4) first layer thin-film solar cells array and second layer thin-film solar cells array are punctured by space junk
Position obtains the crash direction [(X1, Y1, Z2), (X2, Y2, Z1)] of space junk；
5) it after space junk passes through second layer thin-film solar cells array, will strike in piezoelectric effect detection layers, root
According to the piezoelectric signal generated is hit, the quality for hitting space junk is obtained.
Solar cell type space debris detection device of the invention, structure is simple, and manufacturing cost is low, and space easy to accomplish
The detection of fragment can obtain size, speed, direction and the qualitative data of space junk.
Detailed description of the invention
Fig. 1 is the first layer film sun in the space debris detection device of the invention based on thin film type solar battery array
The structural schematic diagram of cell array.
Fig. 2 carries out the schematic diagram of space debris detection using detection device of the invention.
Fig. 3 is that first layer thin-film solar cells array of the invention passes through the position view after space junk.
Fig. 4 is that second layer thin-film solar cells array of the invention passes through the position view after space junk.
Specific embodiment
Below in conjunction with attached drawing, invention is further described in detail, but this is only exemplary, it is no intended to this
The protection scope of invention carries out any restrictions.The invention patent is further described with reference to the accompanying drawing.
Fig. 1 shows the first layer film in the space debris detection device of the invention based on thin film type solar battery array
The structural schematic diagram of solar cell array.Wherein, first layer thin film solar battery array column are on 1m × 1m Kapton
The array that n × n single solar battery cells are arranged and are formed, the size of single solar battery cell is 1cm × 1cm,
Due to GaInP2, GaAs, Ge film layer respectively to 300nm~660nm, 660nm~900nm, 900nm~1800nm wave band light into
Row absorbs, and therefore, we can choose GaInP2Battery and Ge battery utilize it respectively as the battery of upper and lower two groups of cell arrays
The direction positioning and detection to space junk are realized to the difference of spectral response.Fig. 2 is participated in, Fig. 2, which is shown, utilizes the present invention
Detection device carry out space debris detection schematic diagram.Space junk based on thin film type solar battery array of the invention is visited
Device is surveyed, including with open-topped detection shell, first layer thin-film solar cells array, second layer thin film solar electricity
Pond array and piezoelectric effect detection layers, wherein first layer thin-film solar cells array, which is arranged at the top of detection shell, to be opened
At mouth position, the setting of second layer thin-film solar cells array is in the detection intracorporal middle position of shell, piezoelectric effect detection layers position
In the detection intracorporal bottom of shell, wherein first layer thin-film solar cells array and second layer thin-film solar cells array point
It is not formed by the single solar battery cell of plating latticed array on thin polymer film, and the solar battery of two layers of array
Unit can wear the sunlight of the second layer (i.e. bottom) solar cell array sensitivity respectively to the sun photaesthesia of different-waveband
Saturating first layer solar cell array.
Wherein, the bottom unijunction Ge battery is usually to make base area, N-shaped Ge emission layer and N-shaped GaInP or GaAs by p-type Ge substrate
Etc. Window layers composition.Using MOCVD epitaxy technology, using the p-type Ge in (100) face 9 ° of (111) face partially as epitaxial growth substrate,
It is passed through H2 and PH3 at high temperature first, surface preparation, in favor of the inhibition of epitaxial nucleation and antiphase domain, 10 is carried out to substrate
After minute, it is cooled to the growth temperature of N-shaped GaInP, then low temperature slow growth n-GaInP Window layer grows GaAs contact layer,
Complete the epitaxial growth of the bottom entire unijunction Ge battery.
In (100) face (111) face 9 partiallyoN-shaped Ge substrate on use 650 DEG C 1 μm of growth thickness of n- first
In0.01Ga0.99As buffer layer keeps growth temperature constant later, V/III=180, growth rateGrowth
In group is divided into 0.49 Ga0.51In0.49P material, to prepare GaInP battery.
Similarly, it can according to need the array for carrying out thin-film solar cells in different base using above-mentioned preparation method
Design, specific as follows:
First, thin-film solar cells can use polyimides etc. for substrate, and thin-film solar cells material can divide
It Wei not GaInP2, GaAs, Ge etc., corresponding sensitivity sunlight wave band is 300nm~660nm, 660nm~900nm,
900nm~1800nm.Single thin film solar cell unit can be 1cm × 1cm or smaller, single thin film solar battery
Area can be 1m × 1m, and specific size is depending on design.
Second, the distance of double-layer films solar battery can choose depending on design such as 50cm, the numerical value such as 100cm.
Third, piezoelectric effect detection layers can be sensed using polyvinylidene fluoride (PVDF) sensor, piezoelectric ceramics (PZT)
Device etc., by ground simulation test, the impact from space debris piezoelectric effect detection layers for obtaining different quality friction speed are corresponding
Piezoelectric signal is compared with the signal of space exploration, the quality of the space junk of available in-orbit shock.Specific space is broken
The detection process of piece impact probing device is as follows:
1) after impact from space debris passes through first layer thin-film solar cells array, a certain sun electricity thereon will be penetrated
Pool unit, such as Fig. 3 obtain the time that space junk passes through according to the time that solar battery cell photoelectric effect mutates, if
The in-orbit position passed through of space junk is obtained, (X1, Y1) is set as according to the position that it mutates for t1；
2) when space junk further passs through second layer thin-film solar cells array, such as Fig. 4, similarly obtain t2 and
(X2, Y2), the then speed of space junk are as follows:
3) ruler of space junk is obtained according to the numerical value of battery unit photoelectric properties mutational lesions in every layer of solar battery array
Very little size, the area of space junk is less than the area of solar battery cell, if the area of a certain solar battery cell is S1, function
Rate is W1, after impact from space debris passes through, chugging W2, then the size S2 of space junk are as follows:
S2=S1 × (W1-W2)/W1；
4) first layer thin-film solar cells array and second layer thin-film solar cells array are punctured by space junk
Position obtains the crash direction [(X1, Y1, Z2), (X2, Y2, Z1)] of space junk；
5) it after space junk passes through second layer thin-film solar cells array, will strike in piezoelectric effect detection layers, root
According to the piezoelectric signal generated is hit, the quality for hitting space junk is obtained.
Although giving detailed description and explanation to the specific embodiment of the invention patent above, it should be noted that
Be, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to above embodiment, produced by
Function still covered without departing from specification and attached drawing spirit when, should all be within the scope of protection of the patent of the invention.
Claims (7)
1. the space debris detection device based on thin film type solar battery array, including with open-topped detection shell,
Thin film solar battery array, second layer thin-film solar cells array and piezoelectric effect detection layers, wherein first layer
Thin-film solar cells array is arranged at the top opening position of detection shell, the setting of second layer thin-film solar cells array
In the detection intracorporal middle position of shell, piezoelectric effect detection layers are located at the detection intracorporal bottom of shell, wherein the first layer film sun
Can cell array and second layer thin-film solar cells array respectively by thin polymer film plating latticed array it is single too
It is positive can battery unit form, and the solar battery cell of two layers of array is respectively to the sun photaesthesia of different-waveband, and to the
The sunlight of two layers of (i.e. bottom) solar cell array sensitivity can penetrate first layer solar cell array.
2. space debris detection device as described in claim 1, wherein thin polymer film is polyimides, perfluoroethylene third
Alkene film, polyurethane film or using these films as the derivative film of matrix.
3. space debris detection device as described in claim 1, wherein the coating material of thin-film solar cells array is distinguished
For GaInP2, GaAs, Ge or Si, corresponding sensitivity sunlight wave band is 300nm~660nm, 660nm~900nm,
900nm~1800nm, 400nm~1100nm.
4. space debris detection device as described in claim 1, wherein single thin film solar cell cell size be 1cm ×
1cm is smaller, and the area of single thin film solar battery is big for 1m × 1m or more.
5. space debris detection device as described in claim 1, wherein first layer thin-film solar cells array and the second layer
The spacing of thin-film solar cells array is 10cm~50cm.
6. space debris detection device according to any one of claims 1-4, wherein piezoelectric effect detection layers, which use, gathers inclined two
Vinyl fluoride (PVDF) sensor or piezoelectric ceramics (PZT) sensor.
7. the method for carrying out space debris detection using detection device described in any one of claims 1-6, comprising the following steps:
1) after impact from space debris passes through first layer thin-film solar cells array, a certain solar cell list thereon will be penetrated
Member obtains the time that space junk passes through, being set as t1 according to the time that solar battery cell photoelectric effect mutates, according to
Its position to mutate obtains the in-orbit position passed through of space junk, is set as (X1, Y1)；
2) when space junk further passs through second layer thin-film solar cells array, t2 and (X2, Y2) are similarly obtained, then it is empty
Between fragment speed are as follows:
3) size for obtaining space junk according to the numerical value of battery unit photoelectric properties mutational lesions in every layer of solar battery array is big
Small, the area of space junk is less than the area of solar battery cell, if the area of a certain solar battery cell is S1, power is
W1, after impact from space debris passes through, chugging W2, then the size S2 of space junk are as follows:
S2=S1 × (W1-W2)/W1；
4) puncture the position of first layer thin-film solar cells array and second layer thin-film solar cells array by space junk,
Obtain the crash direction [(X1, Y1, Z2), (X2, Y2, Z1)] of space junk；
5) it after space junk passes through second layer thin-film solar cells array, will strike in piezoelectric effect detection layers, according to hitting
The piezoelectric signal for hitting generation obtains the quality for hitting space junk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811558293.XA CN109725359B (en) | 2018-12-19 | 2018-12-19 | Space debris detection device based on thin film type solar cell array |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811558293.XA CN109725359B (en) | 2018-12-19 | 2018-12-19 | Space debris detection device based on thin film type solar cell array |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109725359A true CN109725359A (en) | 2019-05-07 |
| CN109725359B CN109725359B (en) | 2021-01-15 |
Family
ID=66297654
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811558293.XA Active CN109725359B (en) | 2018-12-19 | 2018-12-19 | Space debris detection device based on thin film type solar cell array |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109725359B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112304349A (en) * | 2020-09-24 | 2021-02-02 | 航天东方红卫星有限公司 | Space debris detection device and method |
| CN116294959A (en) * | 2023-05-11 | 2023-06-23 | 合肥皖科智能技术有限公司 | Battery bulge on-line monitoring system and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130176049A1 (en) * | 2012-01-10 | 2013-07-11 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Solar generator |
| DE102012112080B3 (en) * | 2012-12-11 | 2014-03-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Solar generator for e.g. spacecraft, has light source and light sensors connected to evaluation unit to determine disorder of total reflection properties of internal reflection layer due to collision with space object |
| CN108459351A (en) * | 2018-03-29 | 2018-08-28 | 北京卫星环境工程研究所 | Resistive type space debris detection device and detection method |
-
2018
- 2018-12-19 CN CN201811558293.XA patent/CN109725359B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130176049A1 (en) * | 2012-01-10 | 2013-07-11 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Solar generator |
| DE102012112080B3 (en) * | 2012-12-11 | 2014-03-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Solar generator for e.g. spacecraft, has light source and light sensors connected to evaluation unit to determine disorder of total reflection properties of internal reflection layer due to collision with space object |
| CN108459351A (en) * | 2018-03-29 | 2018-08-28 | 北京卫星环境工程研究所 | Resistive type space debris detection device and detection method |
Non-Patent Citations (1)
| Title |
|---|
| WALDEMAR BAUER 等: "Development of in-situ Space Debris Detector", 《ADVANCES IN SPACE RESEARCH》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112304349A (en) * | 2020-09-24 | 2021-02-02 | 航天东方红卫星有限公司 | Space debris detection device and method |
| CN116294959A (en) * | 2023-05-11 | 2023-06-23 | 合肥皖科智能技术有限公司 | Battery bulge on-line monitoring system and method |
| CN116294959B (en) * | 2023-05-11 | 2024-01-09 | 合肥皖科智能技术有限公司 | Battery bulge on-line monitoring system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109725359B (en) | 2021-01-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Storey et al. | Timing of hot spot—related volcanism and the breakup of Madagascar and India | |
| CN109725359A (en) | Space debris detection device based on thin film type solar battery array | |
| CN105633215A (en) | Method for optimizing thickness of baffle layer of blocking impurity band detector | |
| CN108459351B (en) | Resistive type space debris detection device and detection method | |
| CN109524430B (en) | Four-quadrant photoelectric detection chip of multi-pixel integrated InGaAs avalanche diode | |
| CN100414721C (en) | Double-colour indium-gallium-arsenide infrared detector and producing method and application thereof | |
| Meriwether Jr et al. | Nighttime thermospheric winds over Sondre Stromfjord, Greenland | |
| CN103247637B (en) | Infrared Detectors and preparation method thereof | |
| CN101814545B (en) | InAs/GaSb superlattice infrared photoelectric detector for HPT (Hydrogenated Propylene Tetramer) structure | |
| US20190187307A1 (en) | High efficiency 3d nanostructured neutron detectors | |
| Kok et al. | Fabrication of 3D silicon sensors | |
| CN103247638B (en) | Infrared Detectors and preparation method thereof | |
| McGregor et al. | Micro-structured high-efficiency semiconductor neutron detectors | |
| Guechi et al. | The effect of water vapor on the performance of solar cells | |
| Zhang et al. | SuperDARN CUTLASS Finland radar observations of high-latitude magnetic reconnections under northward interplanetary magnetic field (IMF) conditions | |
| Bussoletti et al. | The GIADA experiment for Rosetta mission to comet 46P/Wirtanen: design and performances | |
| Atkins et al. | Status of the Milagro Gamma Ray Observatory | |
| Leese et al. | DEBIE: a low resource dust environment monitor | |
| CN116581190B (en) | Superlattice array infrared detector chip and preparation method | |
| Il’chuk et al. | Modeling and fabrication of three-dimensional silicon substrates with tailored shape and microtopography parameters for CdTe films | |
| Durin et al. | In-situ detection of meteoroids and orbital debris | |
| Kirkpatrick et al. | The Effects of Geometry on a-Si: H Solar Cell Performance | |
| Rolley et al. | Experimental comparison of a III: V triple-junction concentrator photovoltaic-thermoelectric (CPV-TE) hybrid module with commercial CPV and flat plate silicon modules | |
| McCullough | Status of the Milagro Gamma Ray Observatory | |
| Molina | Crack analysis in silicon solar cells |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |