# Astronomical Tasks for Tests of X-Ray Optics in VZLUSAT-1 Nanosatellite

Authors: Martin Blazek; Petr Pata; Adolf Inneman; Petr Skala
Journal: Advances in Astronomy
 (2017)

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## Abstract

VZLUSAT-1 nanosatellite (scheduled launch in spring 2017 from India) is a CubeSat mission which, besides other instrumentation, contains X-ray desk to perform efficiency tests of the X-ray optics. In this article the analysis of potential observational candidates for VZLUSAT-1 X-ray board is presented together with the suggestion of observational modes, laboratory measurements, and estimations of exposure settings.


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## Body

## 1. Introduction

VZLUSAT-1 is a nanosatellite developed in VZLU (http://www.vzlu.cz/) Institute in Prague (Czech Republic) and its launch is scheduled for April 2017 from India. Its architecture corresponds to CubeSat missions with the size of two standard units [1]. The goals of this nanosatellite include meteorological and radiation measurements, composite material experiments, and tests of X-ray optics in the space environment. X-ray board consists of “Lobster eye” optics [2], which is to be tested in space, two ultraviolet sensors (pointing the same direction as the X-ray optics), one infrared sensor and TimePix detector [3] working in two modes to measure either count of X-ray photons or their spectral energetic distribution. Lobster eye optics has not been tested yet in space research. To perform the efficiency tests in space environment, one can use the X-ray observations of the Sun, lunar reflections, terrestrial reflections, cosmic background, and brightest astronomical X-ray sources.


## 2. VZLUSAT-1

VZLUSAT-1 is a two-unit nanosatellite (ca. 10 × 10 × 20 cm) with X-ray optics having focal lengthf of 250 mm. TimePix detector onboard VZLUSAT-1 has 256 × 256 pixels each having physical size of 55 μm. Total size (with side d) of the chip is 14.08 × 14.08 mm. For this configuration, the field of view (FOV) is 3.2° for the square side and 4.5° for diagonal direction. For estimated low-orbit speed (roughly 90 minutes per orbit) of the satellite with the theoretical assumption of zero rotation the FOV would move by 4° per minute. Particularly during first few weeks before the stabilization of the satellite the FOV would depend, namely, on the satellite rotation. The layout of the satellite from [1] can be seen in Figure 1.Figure 1
Optical layout of X-ray package inside VZLUSAT-1 satellite (image taken from [1]).The sensitivity of the detector is determined by the 300μm thick silicon layer. Spectral variation of such a layer in X-ray can be simulated from the data given by National Institute of Standards and Technology (https://www.nist.gov/pml/data/xraycoef/) based on X-ray mass attenuation coefficients [4] as can be seen in Figure 2. Highest sensitivity of complete instrument (TimePix detector + X-ray optics) is inside the spectral range of 3–8 keV, while rapidly declining for higher energies.Figure 2
Relative transmission of X-ray detector onboard VZLUSAT-1 based on silicon mass attenuation coefficients.Exact orbital elements are unknown until the successful launch, but the inclination of the orbit should be as close to polar orbit as possible. Because of the low-orbit position the elements would vary during a time due to the atmospheric dissipation. Electromagnetic stabilization is supposed to point the satellite along its orbiting trajectory. Webpageshttp://vzlusat1.cz/en/ provide images and information about technological setup and satellite itself. Corresponding scientific description can be found in [5]. The principals of astrophysical X-ray monitoring from this CubeSat mission are then explained in [6].


## 3. Solar Observations

Our Sun is the brightest natural regular source of X-ray photons for our satellite. The size of the Sun (0.53°) will roughly cover one-sixth of FOV and depending on the observational angle it would pass through the FOV in 56–75 seconds. If ideally having a polar orbit and no internal rotation then the satellite would catch the Sun twice a year with six months break. Due to the larger FOV than the size of the Sun (with its ecliptical speed of 1.01° per day), there might be maximal theoretical chance to catch the complete Sun in those two periods 16 times a day during 3-4 days each time roughly for 1 minute. Practically the orbital elements and rotation will be more complicated so the chance will be much lower and will need exact computations of the rotation and orbital predictions.Due to the changes in the solar activity the X-ray flux varies. GOES-15 satellite (https://www.ngdc.noaa.gov/stp/satellite/goes/) with one of the instruments having observational spectral range from 0.5 Å to 4 Å (3–25 keV) has very similar X-ray spectral sensitivity and therefore is the best option for calibration of the sensors and estimation of their initial settings. The solar X-ray light curve from GOES-15 satellite in 3–25 keV energy range for the period from January 2014 to May 2015 can be seen in Figure 3. The flux F varies from 10-9 up to 1.8·10-4 W m−2 with the mean F¯S and median F~S values(1)F¯S=9.8·10-8Wm-2,F~S=4.3·10-9Wm-2.Figure 3
Solar X-ray observations by GOES-15 satellite in 0.5 Å–4 Å spectral range (3–25 keV) in (a) and near UV observations by SORCE satellite in spectral range 231–309 nm in (b) during the period from January 2014 to May 2015.
(a) (b)Outside several solar flare activity the X-ray intensity of the Sun in spectra range of 3–25 keV remains in general in the degree range between nW/m2 and μW/m2.


### 3.1. Solar UV Hunting

For possible hunting of the solar position with fast-rotating and fast-moving low-orbit satellite one wide-field and one narrow-field ultraviolet (UV) sensor are incorporated into X-ray board. Those two sensors SG01LB18 have spectral responsivity between 231 nm and 309 nm with its peak in 280 nm (UVB/UVC). Effective chip area of this sensor is 1 mm2. The data (http://lasp.colorado.edu/sorce/) taken by the SORCE (Solar Radiation and Climate Experiment) [7] shows quite stable flux (in terms of degree compared to X-ray data) with the mean value FUV at(2)FUV=17.917±0.063Wm-2for the same period as investigated for X-ray. UV data from SORCE satellite [7] can be seen in Figure 3. Assuming perpendicular observation by UV sensor and its effective collection area the solar power caught by the sensor would be ca. 18 μW.


## 3.1. Solar UV Hunting

For possible hunting of the solar position with fast-rotating and fast-moving low-orbit satellite one wide-field and one narrow-field ultraviolet (UV) sensor are incorporated into X-ray board. Those two sensors SG01LB18 have spectral responsivity between 231 nm and 309 nm with its peak in 280 nm (UVB/UVC). Effective chip area of this sensor is 1 mm2. The data (http://lasp.colorado.edu/sorce/) taken by the SORCE (Solar Radiation and Climate Experiment) [7] shows quite stable flux (in terms of degree compared to X-ray data) with the mean value FUV at(2)FUV=17.917±0.063Wm-2for the same period as investigated for X-ray. UV data from SORCE satellite [7] can be seen in Figure 3. Assuming perpendicular observation by UV sensor and its effective collection area the solar power caught by the sensor would be ca. 18 μW.


## 4. Lunar Observations

The Moon is not producing X-rays, although it is reflecting some ratio generated in the Sun. The ROSAT mission (Röntgen Satellite [8]) measured the Moon in the X-ray spectrum during the first quarter and measured the total power of the lunar X-rays published in 1991 which were PM = 1.2·1012 erg s−1 [9]. Assuming the distance of the Moon as DM=3.8·108 m (low-orbit is negligible) then the X-ray flux FM at the satellite during the Full Moon phase (multiplication factor 2) can be estimated as(3)FM=2·PM4πDM2≐1.3·10-13Wm-2,which is just 4 orders lower than the median solar X-ray flux computed in previous section; hence lunar observations should be configured with ten thousand time longer expositions than solar observations to provide similar signal-to-noise ratio. Although this estimation might have error of another degree as the spectral range of ROSAT mission was 0.1–2 keV.UV detectors on board are useful for fast detection of solar presence in the field of view, although false reflection from the Moon can be caught as well. The Global Ozone Monitoring Experiment GOME [10] was launched in 1995 and was observing several terrestrial and extraterrestrial phenomena including lunar albedo in the spectral range covering near UV and visible light. For VZLUSAT-1 UV sensors it is crucial to set lower limit of positive detection to avoid confusion between the Sun and the Moon. The averaged geometrical Moon albedo measured by GOME between 1995 and 1996 in the spectral range 231–309 nm goes from 3 to 5 percent [11]. Assuming highest albedo of this spectral range and Full Moon reflection then the flux of the Moon in UV would be maximally(4)FUV=896±3mWm-2,which in the case of effective collection area of VZLUSAT-1 UV sensors correspond to the power of 0.9 μW.One disadvantage of lunar observation compared to solar observation is its nonpoint spatial reflection of X-rays. Even though the instrumental optics provide one-dimensional focus of source (into line), the Moon would cover approximately one-sixth of FOV during Full Moon, which has to be taken in account during actual observation and analysis.


## 5. Astronomical Observations

Many astronomical X-ray sources are Soft X-ray Transients (SXT) which are bursts of X-ray binary systems with accreting neutron stars or black hole. Like other high energy astronomical phenomena as Gamma-ray bursts, those SXT are just occasional (often single) flares which usually last hours or days. It is highly improbable that VZLUSAT-1 could catch those sources accidentally, although some brightest galactic regular X-ray sources have to be checked if they can be potentially observational candidates. Similar X-ray spectral range to VZLUSAT-1 X-ray detector has space instrument XMM-Newton [12] (X-ray Multi-Mirror Mission) of European Space Agency, 0.2–12 keV. Table 1 shows several potential astronomical candidates for quality tests of the Lobster eye optics [2] on board VZLUSAT-1. The mean flux F¯X, median F~X, maximal flux Fmax, and minimal flux Fmin in Table 1 are converted from ergcm-2s-1. The data in this table come from 3XMMS-DR5 catalogue (http://heasarc.gsfc.nasa.gov/W3Browse/xmm-newton/xmmssc.html) of XMM-Newton project, which is extended from standard 2XMMS catalogue [13].Table 1
List of potential astronomical X-ray sources to be used as observational candidates for tests of X-ray optics. Data are computed from 3XMMS-DR5 catalogue of XMM-Newton mission. The measured fluxesF @ 0.2–12 keV in this table represent the mean F-X, the median F~X, the minimal Fmin, and the maximal value Fmax.
Name Type F - X [W m−2] F ~ X [W m−2] F m i n [W m−2] F m a x [W m−2] Mrk 421 Blazar 4.3 ⋅ 1 0 - 13 3.5 ⋅ 1 0 - 13 1.2 ⋅ 1 0 - 18 1.2 ⋅ 1 0 - 12 3C 273 Blazar 1.7 ⋅ 1 0 - 13 1.6 ⋅ 1 0 - 13 2.7 ⋅ 1 0 - 14 2.8 ⋅ 1 0 - 13 1ES 1959+650 Blazar 1.4 ⋅ 1 0 - 13 1.4 ⋅ 1 0 - 13 1.4 ⋅ 1 0 - 13 1.5 ⋅ 1 0 - 13 Capella Star 9.9 ⋅ 1 0 - 14 1.1 ⋅ 1 0 - 13 7.1 ⋅ 1 0 - 15 1.9 ⋅ 1 0 - 13 V1223 Sgr Star 9.4 ⋅ 1 0 - 14 9.4 ⋅ 1 0 - 14 — — Mrk 501 Blazar 6.3 ⋅ 1 0 - 14 6.5 ⋅ 1 0 - 14 4.5 ⋅ 1 0 - 14 7.9 ⋅ 1 0 - 14 η Car Star 5.6 ⋅ 1 0 - 14 5.5 ⋅ 1 0 - 14 3.4 ⋅ 1 0 - 15 1.7 ⋅ 1 0 - 13 AB Dor Star 5.2 ⋅ 1 0 - 14 4.9 ⋅ 1 0 - 14 3.8 ⋅ 1 0 - 14 7.7 ⋅ 1 0 - 14 V2400 Oph Star 4.7 ⋅ 1 0 - 14 4.7 ⋅ 1 0 - 14 4.4 ⋅ 1 0 - 14 5.0 ⋅ 1 0 - 14 FO Aqr Star 3.9 ⋅ 1 0 - 14 3.9 ⋅ 1 0 - 14 — — 3C 454.3 Blazar 2.9 ⋅ 1 0 - 14 2.9 ⋅ 1 0 - 14 1.2 ⋅ 1 0 - 14 4.5 ⋅ 1 0 - 14 EV Lac Star 1.8 ⋅ 1 0 - 14 1.8 ⋅ 1 0 - 14 — — V711 Tau Star 4.2 ⋅ 1 0 - 14 1.6 ⋅ 1 0 - 14 1.1 ⋅ 1 0 - 17 1.4 ⋅ 1 0 - 13 GK Per Nova 6.1 ⋅ 1 0 - 14 1.5 ⋅ 1 0 - 14 1.1 ⋅ 1 0 - 14 1.6 ⋅ 1 0 - 13 3C 279 Blazar 1.5 ⋅ 1 0 - 14 1.5 ⋅ 1 0 - 14 1.5 ⋅ 1 0 - 14 1.6 ⋅ 1 0 - 14 BL Lac Blazar 1.4 ⋅ 1 0 - 14 1.4 ⋅ 1 0 - 14 9.4 ⋅ 1 0 - 15 1.8 ⋅ 1 0 - 14 S5 0716+714 Blazar 1.7 ⋅ 1 0 - 14 1.2 ⋅ 1 0 - 14 7.2 ⋅ 1 0 - 15 3.7 ⋅ 1 0 - 14 V2487 Oph Nova 6.5 ⋅ 1 0 - 15 6.5 ⋅ 1 0 - 15 5.9 ⋅ 1 0 - 15 7.1 ⋅ 1 0 - 15 3C 66A Blazar 1.5 ⋅ 1 0 - 15 1.5 ⋅ 1 0 - 15 1.2 ⋅ 1 0 - 16 3.0 ⋅ 1 0 - 15 SgrA∗ Milky Way center 1.4 ⋅ 1 0 - 14 1.4 ⋅ 1 0 - 15 3.9 ⋅ 1 0 - 17 6.9 ⋅ 1 0 - 14 V834 Cen Star 7.7 ⋅ 1 0 - 15 9.0 ⋅ 1 0 - 16 3.4 ⋅ 1 0 - 17 2.2 ⋅ 1 0 - 14 M31 Galaxy 2.0 ⋅ 1 0 - 15 3.5 ⋅ 1 0 - 16 7.9 ⋅ 1 0 - 18 1.6 ⋅ 1 0 - 14Outside those astronomical objects listed in Table1, there is another X-ray source, which cannot be observed directly by XMM-Newton due to its high luminosity: Sco X-1 (or V818 Sco) [14]. This low mass X-ray binary is actually the brightest X-ray source in the sky other than the Sun or the diffuse X-ray background radiation and estimation from XMM-Newton instrument in the range 2–10 keV are according to [15](5)FSco=3.4·10-8ergcm-2s-1=3.4·10-11Wm-2.Older measurements from RXTE satellite (Rossi X-ray Timing Explorer) from  1999 in [16] estimate the flux in a bit wider spectral range 2–20 keV as(6)FSco=2.4·10-7ergcm-2s-1=2.4·10-10Wm-2,which is just 1-2 orders lower than the median solar flux as counted in previous sections.


## 6. Calibration Procedure and Filtering

To get the estimation of detectable fluxes of potential observational candidates, the laboratory measurements are necessary. Lobster eye optics [2] together with TimePix detector [3] was tested in X-ray tunnel with source in Titanium X-ray emission of 4.5 keV. Optical module was composed of 182 glass wedges of the average thickness 150 μm and 90 reflective double-sided gold-plated foils. X-ray testing was realized in the vacuum chamber at the University of Colorado at Boulder, USA. The X-ray tube with a Ti anode (energy 4.5 keV) was used as the source of X-rays. The source-to-detector distance was 18 m. Setup of the instrument inside the tunnel is in Figure 5.Figure4 shows the sum of the counts on the detector with 4.5 keV energy for 3 different modes: darkframe including just radiation background, mode just with TimePix detector without optics, and mode with complete set including the optics. The crosses in the image represent raw measured data, while the solid line for each mode (excluding basic darkframe) represent mathematical result after filtration.Figure 4
Laboratory count-rates @ 4.5 keV Titanium X-ray emission for clear data (no optics), Lobster eye data, and closed shutter (darkframe with cosmic background). Crosses represent raw data and solid lines results after mathematical 8-neighbour one photon event filtration.Figure 5
Experimental setup for calibration procedure inside vacuum chamber of X-ray optics (University of Colorado at Boulder): image taken from [1].Total size of the used chip is 14.08 × 14.08 mm, from which the area of the detector isA=1.9712·10-4 m2. Incident flux on the detector FLAB can be expressed as(7)FLAB=nE0TA,where E0 is the energy of photons, n their number, T exposure time, and A already mentioned aperture. The count-rates R=n/T for these measurements can be converted to fluxes according to (7). Measured count-rates and converted fluxes for the exposures between 1 and 20 seconds (Figure 4) are both in Table 2. From this table it can be seen that the scattering on the optics reduces the total flux on the detector with the ratio S=(15±2.7)% (the ratio between the case of count-rate without and with the optics).Table 2
Count-ratesR and fluxes F of Lobster eye optics compared to clear data without optics at 4.5 keV Titanium X-ray emission. Raw measured data between 1 and 20 seconds and mathematically filtered data correspond to Figure 4.
R r a w R filtered F r a w F filtered [counts⋅s-1] [10-12 W⋅m−2] No optics 182± 11 166± 19 662± 40 604± 69 Lobster eye 27.3± 4.8 26.1± 4.2 99± 18 95± 15The space background simulation is difficult, but the nanosatellite PROBA-V [17] carried onboard similar detector (Medipix). From results we can estimate that most of the background noise would be done by heavier particles (protons, neutrons, and α-particles). These particles produce traces in our imaging system much larger than one-pixel area. The idea of the image processing filtration for space conditions is based on keeping just one-pixel photon events with filtering out cosmic background including heavier particles (such as α-particles or protons). For sparse events such an 8-neighbour pixel filtration works sufficiently while for denser areas made by longer exposures it filters out even hidden one-pixel X-ray photon events. Due to low radio downlink rate the filtering is processed immediately on the satellite.


## 7. Expected Count-Rates

To estimate the count-ratesR of selected astronomical observational candidate fluxes F from Figure 1, one would need photon energy EM, TimePix spectral sensitivity κ(EM) of the instrument at this energy, effective area of the detector A, and the transmission coefficient of the instrument including the optics: S=0.15±0.027 @ 4.5 keV (see previous section).When assuming simplified flat spectral emissions of the candidates then the corresponding photon energiesEM for the specific spectral range can be easily estimated as the mean value of this spectral range. Overview of analysed catalogues is in Table 3. Included are appropriate spectral ranges, mean energies EM, and TimePix spectral sensitivities κ(EM). The estimated count-rates R would be therefore(8)R=S·κEM·FAEM.Table 3
Mean spectral energiesEM for selected space instruments and catalogues used in this article together with corresponding spectral sensitivity κ(EM) of TimePix detector.
Project catalogue Targets Range [keV] E M [keV] κ ( E M ) [—] GOES-15 Sun 3–25 14 0.587 ROSAT Moon 0.1–2 1.05 0.999 XMM-Newton Deep sky objects 0.2–12 6.1 0.999 RXTE Sco X-1 2–20 11 0.833Table4 summarizes the count-rates R given by (8). Estimated fluxes for this table were calculated in previous sections, and the corresponding mean energies EM and TimePix spectral sensitivities κ(EM) are taken from Table 3. In results of Table 4, R¯ is the mean count-rate per second, R~ the median value, and Rmax the maximal value. Only the observational candidates with estimated chance of catching one photon per one minute are selected in Table 4. The reason is in expected field view, which would move from one side to the other in approximately 50 seconds (depending on actual orbit geometry of satellite). Other candidates from Table 1 can be computed according to (8).Table 4
Estimations of count-rates per secondR of selected observational candidates for X-ray optics with TimePix sensor onboard VZLUSAT-1 mission. Only the observational candidates with estimated chance of catching one photon per one minute are shown; the other candidates from Table 1 can be computed from (8).
R - R ~ R m a x [counts⋅s−1] Sun 76 33 1400000 Full Moon 0.023 — — Sco X-1 (RXTE) 3.37 — — Sco X-1 (XMM) 1.03 — — Mrk 421 0.013 0.01 0.036


## 8. Observation Modes

Due to the conditions and limits discussed in previous sections we suggest following observing modes for X-ray desk on VZLUSAT-1 mission:(i)
Simple imaging: For given parameters (exposure, filtration, binning, and spectroscopic/counting TimePix mode) the instrument would provide single individual data. For each observation one single command is necessary.(ii)
Adrenalin mode: The most important test candidate for optics is the Sun. Therefore several infrared and ultraviolet detectors with wider field of the view are installed to alert the main TimePix detector if some sources with higher values cross the path of the view.(iii)
Monitoring mode: In the meantime when the other instruments and missions onboard VZLUSAT-1 are turned off the X-ray desk may regularly repeat the observations with just one critical parameter (e.g., total sum) influencing whether the data are interesting to be saved or not for later download to the Earth. The onboard memory capacity exceeds the uplink and downlink volume estimated for the mean life of the satellite. This monitoring mode can be proceeding even without direct radio connection with ground command station (which is expected twice a day) for a longer period of time. For such a long-term monitoring only one command in memory is necessary (compared to simple imaging mode).


## 9. Conclusion

This article shows the options to test the Lobster eye optics in the space onboard VZLUSAT-1 nanosatellite mission. Astronomical observational candidates are investigated, and estimation of technical settings is presented with necessary laboratory X-ray measurements and analysis.



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