17 November 2017 How going mad can have its advantages
Author Affiliations +
Proceedings Volume 10563, International Conference on Space Optics — ICSO 2014; 105633W (2017) https://doi.org/10.1117/12.2304088
Event: International Conference on Space Optics — ICSO 2014, 2014, Tenerife, Canary Islands, Spain
Abstract
Going mad is not commonly looked upon as a positive event. Going MAD however (where MAD stands for Multiple Analogue Digital) can have its advantages. The MAD concept is a new concept of sun-sensing which will allow producing highly radiation tolerant, low power quasi digital sunsensors on a chip which will be able to operate from a single power supply and even at higher temperatures.
Leijtens: How going mad can have its advantages

I.

INTRODUCTION

Going mad is not commonly looked upon as a positive event. Going MAD however (where MAD stands for Multiple Analogue Digital) can have its advantages. The MAD concept is a new concept of sun-sensing which will allow producing highly radiation tolerant, low power quasi digital sunsensors on a chip which will be able to operate from a single power supply and even at higher temperatures.

The concept brings small but fully autonomous digital sunsensors within reach and could lead to a shift in the way sunsensors are applied on items like satellites, interplanetary rovers or even trackers used for concentrated photo voltaic applications (which is a terrestrial application)

This paper will discuss the initial MAD concept as well as an implementation which can be used to produce a sunsensor on chip.

II.

The MAD concept

The “invention” of the MAD concept was driven by discussions on albedo sensitivity of analogue sunsensors and the related desire to develop digital sunsensors which don’t exhibit this issue due to the fact that digital sunsensors discriminate between Earth’s albedo and the sun by looking at the amplitude as well as the angular extend of the source. As the Albedo [1] sensitivity is largely driven by the field of view of an analogue sunsensor the measured attitude can deviate considerably from the actual attitude of the spacecraft. Depending on orbit height of the S/C and on the angular configuration of S/C, Sun and Earth, albedo signal can be a significant part of the measurement signal generated in analogue sensors. This may even result in attitude measurement errors up to10 to 15 degrees generated in low Earth orbits. Due to the large FOV of coarse sunsensors, these sensors are affected by albedo effects the strongest. Fine sunsensor (which use an additional aperture at a specified distance above the actual detector are much less affected, but these sensors are more complicated and consequently significantly more expensive than coarse sunsensors. The aperture in analogue Fine Sun Sensors restricts light from external objects (like solar panels, antennae or body parts of the spacecraft) as well as light reflected from the earth from entering the sensor to a large extend. The actual reduction of these signals largely depends on the field of view of the sensors. Depending on the way the sunsensors are constructed, the angular range to which a sunsensor is sensitive for albedo inputs in general significantly extends beyond the actual measurement range (Field of View) of the sensors. As an example of this we can have a look at the BiSon 64 sunsensor which is a typical fine sunsensor based on a four quadrant photodiode. As indicated in Figure 1 the measurement field of view of this sensor is 64.5 degrees (in diagonal). This measurement range however is defined by the angle for which the sun spot created by the aperture is shifted to one side of the quadrant detector. Up until this angle signal is generated in all four channels of the sunsensor. For angles extending beyond this range, the sunspot will be on one detector halve only, causing a decreasing intensity over increasing angle. Light from disturbing sources (including Earth albedo) may reach the detector for any input angle up to 80.9 degrees of arc (in diagonal) and cannot be discriminated from direct sun input

Figure 1

BiSon 64 field of view restrictions

00139_PSISDG10563_105633W_page_2_1.jpg

As shown in Figure 2 in main symmetry planes of the sensor the angles are different but still very significant. For small field of view sunsensors like the BiSon 6 shown in Figure 3 the albedo sensitivity field of view will be nearly 3 times as large as the measurement range. Nevertheless this range will always decrease if the measurement range decreases which is why the measurement range should be restricted as much as possible. For this reason the BiSon 64 susensors have a measurement range of ±64 degrees in diagonal instead of the more common ±64 degrees on axis. This seems only a small difference, but significantly improves the albedo sensitivity due to the geometric properties of the earth/satellite combination (as will be explained later)

Figure 2

BiSon 64 sensitivity angles in symmetry planes.

00139_PSISDG10563_105633W_page_3_1.jpg

Figure 3

BiSon 6 field of view definition

00139_PSISDG10563_105633W_page_3_2.jpg

Although the input outside the measurement field of view can be restricted by means of additional baffles, it means a clear distinction has to be made between the measurement range and the albedo sensitive range when considering albedo issues.

The MAD concept takes the albedo sensitivity as well as the measurement range of the sunsensors into account. The principle is based on the presumption that the majority of satellites will be earth pointing. In case the satellite is earth pointing, it will be dependent on the altitude of the orbit at which aspect angle the sun will appear when getting out of eclipse.

This fact is demonstrated in Figure 4 where a (fairly low) attitude of 500km is taken for the satellite. From this figure it can be seen that the sun will only impinge upon the satellite with an angle which is 22 degrees (or more for higher S/C altitudes) inclined with respect to the normal of the satellite side panel.

Figure 4

End of eclipse angles for MAD configuration

00139_PSISDG10563_105633W_page_4_1.jpg

This automatically means that any albedo signal can only enter the sensor at angles larger than 22 degrees with respect to the normal of the side panel as otherwise the signal is not reflecting from either clouds or the earth’s surface.

When the sunsensors are tilted by 45 degrees with respect to the satellites panels, and the measurement angle of the sunsensors is 64 degrees (on axis) it can be seen that the albedo signal will never give any signal within the measurement range of the sunsensor (as 45+22= 67) This means that with a common analogue sunsensor tilted over an angle of 45 degrees (for instance) and a baffle it should be possible to create a situation where earths albedo will have no influence on the attitude measurement. As multiple analogue sunsensors will be required to measure the attitude over the orbit (until the sun goes into eclipse at the other end of the trajectory) without albedo sensitivity (which is the main reason why people want digital sunsensors) the concept is dubbed multiple analogue digital sunsensor.

As mentioned the field of view for albedo signal will have to be restricted by means of a baffle, but this baffle will drastically increase the size and mass of the sensors. (see Figure 5). The shown FSS has a field of view of 138*138 degrees (on axis) in which no albedo signal shall be generated to ensure the rated accuracy. This means that a MAD configuration can be provided on basis of these sensors for spacecraft altitudes higher than 600km.

Figure 5

Moog Bradford (TNO) FSS and BiSon 64 sunsensors

00139_PSISDG10563_105633W_page_4_2.jpg

If we calculate the limit angle at which albedo can still reach the sensor for different altitudes Figure 6 it can be seen that the angle only very slowly goes down with the altitude of the spacecraft.

Figure 6

albedo limit angle for different altitudes @45 degree sunsensor rotation:

00139_PSISDG10563_105633W_page_5_1.jpg

The difference between 500km and 1500km altitude is only some 14 degrees. For a BiSon 64 sunsensor with 56 degrees measurement angle on axis (64 degrees in diagonal) the on axis exclusion angle is 77.3 degrees (see Figure 2) for a similar sensor with 64 degrees in main symmetry plane this would be 80.8 degrees. Although this doesn’t seem much of a difference, it has a significant effect on the albedo sensitivity. Where the first sensor will be completely insensitive to earth albedo for altitudes higher than 1160km’s, the latter will only reach this for altitudes higher than 1500km.

Although exact calculations would involve taking the curvature of the earth and the exact field of view for various input angles of the sensors into account it can be reasoned that the albedo generated signal will change approximately to the square of the observation angle as the strip of the earth will not only get higher but also wider. If we then compare the expected performance of a sunsensor with 64 degrees in diagonal (which is needed to provide full spherical coverage with 6 sensors) of a sensor with 64 degrees in main symmetry planes, we can see a clear difference (see Figure 7 where the spacecraft angle is the limit albedo angle seen by the spacecraft given as 68 degrees in Figure 4)

Figure 7

relative albedo sensitivity in MAD configuration of sensor with 64 degrees in diagonal or 64 degree in main symmetry plane

00139_PSISDG10563_105633W_page_5_2.jpg

Figure 8

MADoC operating principle

00139_PSISDG10563_105633W_page_7_1.jpg

Vanaf hier is je lettertype veranderd.

Based on the above it can be concluded that a BiSon 64 sunsensor is ideally suited to provide near 0 albedo sensitivity when mounted in the MAD configuration. The main disadvantages associated with this solution are the fact that the BiSon 64 sunsensors output analogue signals which require the addition of some extra processing electronics and would need to be tilted for this specific configuration.

III.

Digital sunsensors on chip

In order to mitigate albedo effects, it is possible to image the sun on a 2D camera through a pinhole and use algorithms to discriminate between the intensity of the direct sun signal and the albedo signal. These so called digital sunsensors have been under investigation for many years by companies like Selex ES [2] and TNO [3],[4]. Although the principle is very simple and the algorithms by now are well developed there are a number of issues associated with these developments that need to be addressed before a high reliability and cost effective solution can be offered to the market.

For space applications, the reliability of the solution is a main driving factor. With the advent of (semi) commercial space applications and constellations, there is an increasing demand for more cost effective solutions though. Integrating all functionality on a single chip generally means that significant non-recurring charges will be incurred but recurring production is more cost effective. As several sunsensors are generally used on a single spacecraft, the associated production volume is sufficient to justify investing in a sunsensor on chip solution or production automation in general [5].

For this scheme to work, the sensors will have to be universally applicable and should not need modifications between applications. This calls for a number of properties:

Universal electrical interface

Wide operating temperature range

Ease of mounting

Next to this the sensor should need minimum adjustments or calibrations in order to be able to cost effectively produce the systems.

For a digital sunsensor the above requirements pose a number of challenges.

Although there are a number of standard electrical interfaces available (RS422, I2C, Canbus, Spacewire, MILSTD-1553 etc.) there is no interface which would fit all applications due to the lack of standardization of digital sunsensor interfaces. RS422 for instance seems to be the best option, but will not allow implementing plug and play functionality which is currently under development. I2C and Canbus don’t fulfill the EMC requirements generally posed to flight hardware (no single point distributed ground configuration possible) and other interfaces are too heavy on either physical size or power requirements (or both)

The wide operating temperature range is needed for sunsensors as they are generally mounted on the exterior of the spacecraft and therefore exposed to significant temperature cycles and more extreme temperatures than electronics mounted inside the spacecraft. In order to avoid saturation of the pixels, a digital sunsensor will have to use an intensity reducing filter. This can be either a neutral density filter or a wavelength limiting filter or both. Doing so however means that the dark current generated within the pixel will become an issue as this current will increase with increasing sensor temperature and will eventually lead to saturation in the pixels for higher temperatures (thus rendering the sensor useless). This mechanism is the dominant factor which limits the operating temperature range of a digital sunsensor. It is evident that the temperature increase due to its own power dissipation of a common digital sunsensor should be limited to the largest extend possible to increase the working operating range.

The power dissipation is also related to the ease of mounting in the sense that the sensors are projected to be quite small, which consequently leads to high power densities (W/m3) for any power dissipated which will be difficult to divert by means of radiation due to the low surface area available. This again means that power dissipated will have to be transported by means of conduction to the mounting feet of the sensors which will pose increasing constraints to the thermal properties of the spacecraft mounting positions with increasing power dissipation.

IV.

MAD on Chip (MADoC)

The MAD principle described above seems to lead to a very high reliability and cost effective solution but would best be implemented while using an additional electronics box which has inputs for multiple analogue sunsensors and a single digital output (and an isolated DC/DC converter) to avoid a lot of analogue input channels on the on board computer. When implemented this way the most critical drawback would be the fact that the sensors have to be mounted in such a way that they are tilted 45 degrees with respect to the spacecraft thus needing an additional mechanical interface. As an alternative one could develop a MAD configuration on chip by dividing the field of view in multiple smaller fields of view by reducing the size of the aperture and selecting for instance an 8*8 matrix detector. This will effectively split the field of view up in a number of smaller fields of view, thus allowing discrimination between sun illuminated FOV sections and albedo illuminated FOV sections much like a standard digital sunsensor (where the field of view is split up in many more pixels). The advantage of this approach would be the fact that each FOV section can have its own analogue to digital converter associated with it, and there would be no need for an intensity reducing filter. The latter is a strong advantage as these filters are costly and difficult to tune to the full well capacity of the pixels of a standard digital sunsensor. As a result a MADoC sunsensor will be much easier to produce, will have a better reproducibility, will be able to operate over a larger temperature range (as pixel dark current is less of a concern if not of no concern at all) and therefore significantly cheaper.

Although the actual algorithm and configuration would need to be investigated, the size of the aperture would probably best be slightly larger than a single pixel to allow for an optimal determination of the sun position. The worst albedo sensitivity would be achieved just after coming out of eclipse or just prior to going into eclipse as shown in Figure 9. For this situation it even seems possible to reduce the albedo effects by presuming the albedo is constant over the earth’s surface and compensating for the fact that some pixels are fully illuminated by albedo (7,8,9) some pixels are partially illuminated (4,5,6) and some pixels are looking towards deep space (1,2,3)

Figure 9

MADoC maximum albedo situation

00139_PSISDG10563_105633W_page_7_2.jpg

Since a sunsensor only needs an update rate of some 100Hz as a maximum (for fast rotating satellites) and there is a very high level of photocurrent available, the ADC’s can be high accuracy low power types and not much power is needed for the signal processing. Due to this, it is expected that the power consumption for the entire chip will be determined for 90 % by the data interface and the power supply regulation circuits. It is in any event to be expected that the power for the entire implementation can stay well below 5 mW which will bring autonomous powering options within reach. To this extend it is suggested that only a series regulator is included on chip so as to allow supplying the sensor from a single triple junction solar cell directly or from a regulated or non-regulated power supply through a resistor or small passive filter.

When comparing published data available on other sunsensor on chip implementations like th Selex SE SSoaC and the TNO APS+ some expected performance improvements can be indicated. It should be born in mind though that the albedo sensitivity around the eclipse period will be less for this implementation (although nearly full albedo insensitivity can be guaranteed for a major part of the orbit.

propertiesSELEX SE SSoaCTNO APS+MADoC
Size (mm2)8.6*8.75*55*5
Number of pixels512*512368*3688*8
ADC resolution (bit)101214
Operating voltage (V)53.3/1.81.8
Power consumption (mW)186/911)23.6<5
Operating temperature-40..+70-40..+80-40..+125
Data interfaceSpacewire/RS422Modified RS4222)UART

[1] power consumption of the chip largely depends on the data interface selected.

[2] The interface used is an RS422 like interface but since the sensor is internally operating at 3.3V and 1.8V the required 5V for RS422 cannot be delivered.

V.

MAD or MADoC that is the question

As indicated above there are advantages to using a MAD configuration and it seems that an on chip implementation is possible which will allow for some unique properties never found before in a sunsensor on-chip. Bearing in mind that sunsensor can be made very small but mounting accuracies will limit the obtainable size reduction for the packaging (the BiSon 64 has a mounting repeatability of 0.05 degrees with two high accuracy holes which need to be >4cm apart to be able to guarantee this) the main issue will not be size reduction but total system cost and flexibility of application.

MAD (using BiSon 64)MADoC
Highest reliability sunsensors on exterior of satellite0.18 µm CMOS has shown good radiation tolerance but design measures will have to be (and can be) taken to ensure radiation tolerance
Mounting under 45 degrees required which is a disadvantage for ease of mountingCan be mounted directly on spacecraft panel
Needs an additional electronics box but this leaves the possibility to add isolated DC/DC converter and RS422 or spacewire interfaceNeeds a connection to the spacecraft for every sensor but this could possibly be made wireless
Can be available within short termRequires significant investments and development time
  

Based on the above, no straight forward conclusion can be drawn but the fact that both solutions have advantages and disadvantages. The main advantage of a MAD configuration based on BiSon 64 sensors is the fact that it can be applied very rapidly. As the sensors are already available and readout electronics can be either included in the on-board computer or a dedicated electronics box can be developed and qualified quite quickly this solution can be applied to just about any satellite for which the attitude and orbit control subsystem is currently being developed.

VI.

Conclusions

The MAD concept is explained along with some reasoning as to why it can have advantages to go MAD for future spacecraft.

References

[2] 

P. Fidanzaty et all, Miniature sunsensor on a chip optimization, ESA GNC conference, 2011 Karlovy Vary.Google Scholar

[3] 

C.W. de Boom et all, Flight experience of TNO sunsensors, ESA GNC conference 2011 Karlovy Vary,Google Scholar

[4] 

C. W. de Boom et all, Mini-DSS: Miniaturized High-Precision Sun-Angle Measurement”, ESA GNC Karlovy Vary,Google Scholar

[5] 

J. Leijtens, From space to Earth and back (sunsensors on a detour), ESA GNC conference 2014 Porto.Google Scholar

© (2017) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
J. A. P. Leijtens, J. A. P. Leijtens, } "How going mad can have its advantages", Proc. SPIE 10563, International Conference on Space Optics — ICSO 2014, 105633W (17 November 2017); doi: 10.1117/12.2304088; https://doi.org/10.1117/12.2304088
PROCEEDINGS
9 PAGES


SHARE
RELATED CONTENT

OPTEL μ LEO to ground laser communications terminal flight...
Proceedings of SPIE (September 25 2017)
As reliable as the sun
Proceedings of SPIE (November 17 2017)
Development status of FSAT--a standard spacecraft bus
Proceedings of SPIE (July 05 1994)
Task Planning Issues For An In-Orbit Service Manipulator
Proceedings of SPIE (October 27 1988)
Miniature star tracker for small remote sensing satellites
Proceedings of SPIE (January 09 1995)
HDOS HD-1003 star tracker
Proceedings of SPIE (June 12 1995)

Back to Top