25 September 2017 Design of the optical communication system for the asteroid impact mission
Author Affiliations +
Proceedings Volume 10562, International Conference on Space Optics — ICSO 2016; 105622W (2017) https://doi.org/10.1117/12.2296213
Event: International Conference on Space Optics — ICSO 2016, 2016, Biarritz, France
Abstract
The Asteroid Impact Mission (AIM) is part of the joint Asteroid Impact and Deflection Assessment (AIDA) project of ESA, DLR, Observatoire de la Côte d´Azur, NASA, and Johns Hopkins University Applied Physics Laboratory (JHU/APL).
Heese, Sodnik, and Carnelli: DESIGN OF THE OPTICAL COMMUNICATION SYSTEM FOR THE ASTEROID IMPACT MISSION

Biarritz, France

18–21 October 2016

Edited by Bruno Cugny, Nikos Karafolas and Zoran Sodnik

00010_PSISDG10562_105622W_page_1_1.jpg

Design of the Optical Communication System for the Asteroid Impact Mission

C. Heese

Z. Sodnik

I. Carnelli

00010_PSISDG10562_105622W_page_1_2.jpg

1.

INTRODUCTION

The Asteroid Impact Mission (AIM) is part of the joint Asteroid Impact & Deflection Assessment (AIDA) project of ESA, DLR, Observatoire de la Côte d´Azur, NASA, and Johns Hopkins University Applied Physics Laboratory (JHU/APL). The intention of AIDA is to send two spacecraft to the binary asteroid 65803 Didymos (1996 GT):

  • An asteroid impactor - the NASA/APL Double Asteroid Redirection Test (DART) mission led by JHU/APL.

  • An asteroid rendezvous and observation spacecraft (AIM) led by ESA.

AIM is a small, low-cost technology mission of opportunity to explore and demonstrate technologies for future deep-space missions, while addressing planetary defense objectives and performing asteroid scientific investigations on the binary asteroid Didymos (1996 GT). The asteroid’s larger component Didymain has a diameter of 800 meters and Didymoon of 150 meters and their separation is about 1.1 km. The main mission objectives are to determine the binary asteroid’s orbital and rotation dynamics as well as the mass, geophysical properties and surface and subsurface structure, both before and after the DART impact. In addition, AIM is to demonstrate novel spacecraft technologies and operations to advance science and exploration missions, particularly optical communications and the use of an RF inter-satellite link with CubeSats in interplanetary space. If approved it will be ESA’s first mission to a binary asteroid.

The AIM mission has five primary research objectives to determine:

  • 1. The binary asteroid’s physical properties like size, mass, shape and density. This will be realized by creating a shape model based on inputs from the Visual Imaging System (VIS) and a laser altimeter (OPTEL-D).

  • 2. The binary asteroid’s orbital and rotation dynamics, using as a minimum a Visual Imaging System (VIS).

  • 3. The geophysical surface properties. The VIS instrument is used for detecting surface features and the Thermal InfraRed Imager (TIRI) for surface roughness. In addition the subsurface structure will be probed with the High-Frequency Radar (HFR) and the accelerometers on the MASCOT-2 lander.

  • 4. The deep internal structure of the moonlet with the low-frequency radar (LFR).

  • 5. The albedo calibration to improve ground-based observation of other object. This will be accomplished by measuring the albedo with the VIS, TIRI and HFR instruments and comparing to measurements from ground.

The four primary technology research objectives are:

  • 1. Telecommunication Engineering eXperiment (TEX) to qualify and end-to-end deep-space (starting at 0.5 AU) optical link.

  • 2. Moonlet Engineering eXperiment (MEX) to demonstrate aseroid landing and extened operation on it.

  • 3. CubeSat Opportunity Payload Intersatellite Networking Sensors (COPINS) to demonstrate deep-space inter-satellite links.

  • 4. Infra-Red Instrument Navigation Aid (IRINA) to demonstrate the use of an IR instrument potential to support rendezvous phases.

The optical communication system for the spacecraft will not only serve as a first technology demonstration of a deep space optical communication payload, but will also significantly contribute to the research objectives. This is possible as it can be reconfigured in-flight to a high-precision laser altimeter. A description of this mode of operation will be detailed elsewhere.

This paper gives an overview of the AIM mission and presents the design of the laser communication system to be installed on the AIM spacecraft and in ESA’s Optical Ground Station (OGS).

2.

AIM MISSION TIMELINE

Figure 1 shows the AIM mission timeline with launch in October 2020 and arrival at Didymos in June 2022. After an early characterization phase, several Cubesats and the Mascot lander will be released in August 2022. In August and September a detailed characterization of the binary asteroid system will be performed. In October 2022 the DART impact characterization will take place, which will be followed by post impact monitoring. The mission is scheduled to end in December 2022.

Figure 1.

AIM mission timeline.

00010_PSISDG10562_105622W_page_3_1.jpg

The optical communication link will become operational in July 2022 at distances below 75 Mio km and continue through closest approach of Didymos to Earth of about 12 Mio km in September 2022 until the end of the mission in December 2022.

3.

OPTICAL COMMUNICATION SYSTEM

As the available development time for the laser communication system is extremely short, equipment from ESA’s collaboration with NASA in the Lunar Laser Communication Demonstration (LLCD) experiment is intended to be reused. LLCD was performed in 2013/2014 in collaboration with MIT Lincoln Labs and JPL and these organizations, as well as others, are very welcome to participate in the AIM laser communication experiment by contributing their own optical ground stations and optical communications equipment.

As NASA provided the flight segment for LLCD only hardware for the optical ground station is available, namely the receiver, demodulation, decoding and data storage system. A summary of the optical communication system operational parameters are shown in Table 1.

Table 1

Optical Communication Link Parameters.

 OGSAIM
ParameterValueUnitValueUnit
Geographic longitude:16° 30’ 36.36”WestNA 
Geographic latitude:28° 17’ 58.29”NorthNA 
Altitude above sea level:2393m75 – 15Mio km
Receiver aperture diameter:1016mm135mm
Receive wavelength:1.55μm1.064μm
Receive filter bandwidth:5nm5nm
Receiver effective focal length:13300mm135mm
Detector/camera pixel diameter:200μm30μm
Transmit wavelength:1064nm1550nm
Transmitter aperture diameter:250mm135mm
Transmitter modulation:½ camera frame rate of the AIM camera 16PPM
Transmit data rate:none 195kbps

This paragraph is organized as follows: In Section 0 the design of the laser communication terminal (named OPTEL-D) on board of the AIM spacecraft is introduced and some specific point of interest are highlighted. Next, the optical ground station (OGS) systems are described in Section 3.2 and the link budgets are given in Section 3.3. Section 3.4 describes the receiver and transmitter alignment.

3.1

DESIGN OF THE OPTICAL COMMUNICATION TERMINAL ON AIM (OPTEL-D)

OPTEL is the name of a family of optical communication terminals designed over the last 15 years by RUAG Space. OPTEL-D, where D stands for deep space, is based on this design heritage and on components that are available to technology readiness level up to TRL6. OPTEL-D’s single mirror coarse pointing assembly (CPA) can move in azimuth and (to a limited extend) in elevation direction and is used to sequentially perform communication links with Earth and laser ranging of the asteroid’s surface. Figure 2 shows the CPA mounted onto an interface plate connected via three vibration-damping legs (yellow) to a satellite panel. A 135 mm aperture diameter telescope and all optical and electronical components are located on the opposite side of the interface plate covered by a housing and thus inside the spacecraft. The use of an interface plate for the optical head ensures a parallel integration flow of the spacecraft. The alignment of the optical head can be finalized at the OPTEL-D payload integrator without interference with the satellite platform integration.

Figure 2.

OPTEL-D laser communication terminal schematically mounted on a satellite panel (base plate adapter) with the coarse pointing assembly protruding out of the S/C and the optical bench inside the S/C

00010_PSISDG10562_105622W_page_4_1.jpg

Figure 3 shows the schematic design of OPTEL-D. The light from an Earth Beacon is received via the coarse pointing assembly (CPA) and an off-axis telescope assembly (TLA) with a free optical diameter of 135 mm.

Figure 3.

Schematic design of OPTEL-D

00010_PSISDG10562_105622W_page_5_1.jpg

The technology readiness level of the TLA is TRL 9 (used in all laser communication terminals of the European Data Relay System, EDRS). The Earth Beacon light may be superimposed with light from an Inertial Pseudo Star Reference Unit (IPSRU). This can be used to cancel out platform vibrations, improving the back-to-earth pointing capabilities of the terminal. The implementation of an IPSRU has not been decided yet. This is a trade-off between payload and platform complexity.

The Earth Beacon is also routed via two Dichroic Beam Splitters (DBS) onto Mercury Cadmium Tellurite (MCT) Beacon Camera and TX Monitor. It provides the pointing, acquisition and tracking functionality and enables calibration of the transmitter and receiver via a Point Ahead Assembly (PAA), a corner-cube retro-reflector (Retro) and the DBS.

The laser data transmitter is routed in the opposite direction via a Point Ahead Assembly (PAA).

A laser ranging functionality (spacecraft to Didymos) will be implemented into OPTEL-D. The currently preferred concept is the use of a circulator inserted into the single-mode output fiber of the power laser transmitter. With the second output of the circulator connected to an InGaAs detector OPTEL-D will be able to simultaneously transmit and receive over link distances below 100 km. A pseudo-random bit sequence will be transmitted towards the target and upon reflection cross-correlated for range determination. Scanning the target with the FPA (or PAA) will produce a three dimensional surface map to support the scientific research objectives.

3.2

ESA OPTICAL GROUND STATION (OGS)

The European Space Agency’s Optical Ground Station (OGS) is located at the Observatorio del Teide (OT) in the Canary Islands (Tenerife, Spain) shown in Figure 4. Its main purpose is to check out and commission laser communication terminals onboard orbiting spacecraft, i.e. EDRS. In addition the OGS is used for space debris, asteroid and near Earth object detection and for standard astronomical observations.

Figure 4.

The Observatorio del Teide in Tenerife, Spain (left) and OGS building, which open dome shutter (right).

00010_PSISDG10562_105622W_page_5_2.jpg

The Canary island archipelago also offers the opportunity to perform inter-island experiments. From the island of La Palma, at a distance of 142 km, laser and quantum communications experiments are being performed.

The OGS building houses a 1 m aperture diameter Zeiss telescope. Current development status of the AIM communication terminal confirms that all objectives for OPTEL-D can be met with the existing 1 m telescope. For the AIM mission the availability of larger ground based telescopes is being investigated and negotiations are ongoing with the Rohzen National Astronomical Observatory in Bulgaria. Rohzen could make a 2 m Zeiss telescope available and serve as a backup baseline.

The 1 m sized OGS will also validate the use of larger telescopes for future deep-space optical communication missions. From a link budget point of view the ground telescope diameter scales linearly with link distance and a successful link with the 1 meter diameter OGS telescope over 0.5 AU would therefore validate a 5 m diameter telescope over 2.5 AU (longest distance to Mars) and a 12 m telescope over 6 AU (longest distance to Jupiter).

Figure 5 (left) shows the equatorial mount of the OGS telescope. It is also called an English mount, because the hour axis (which is parallel to the Earth axis) is supported on both sides, by a (higher) North pillar and a South pillar.

Figure 5.

Equatorially mounted 1 m Zeiss telescope of the OGS (left) and Coudé optical path schematics (right)

00010_PSISDG10562_105622W_page_6_1.jpg

Figure 5 (right) shows the Coudé optical path routing via an evacuated feed-through, which prevents turbulent air exchange and therefore scintillation effects between the telescope floor and the Coudé floor. However, for the AIM mission the Coudé path will be altered by removing the first mirror at the lower right end of the hour axis, such that the Coudé focus will move to the telescope floor inclined by the latitude of the OGS, namely by 28.3 degrees. In this way all refractive elements in the Coudé path are avoided and powerful uplink beacon lasers can be launched from there.

The OGS laser uplink beacon will be intensity modulated at half the camera frame rate on AIM. By subtraction of subsequent image frames the beacon laser can be distinguished from the Earth background and other sources.

Laser downlink communication from the AIM spacecraft will be performed from the stationary Coudé focus.

The receiver design is based on the development for the Lunar Laser Communication Demonstration (LLCD), where a ½-rate serially concatenated pulse-position modulation (SCPPM) turbo like code was implemented. The modulation format is 16-PPM and the user data rate was 38.55 Mbps. For the AIM mission the modulation format will stay 16-PPM, but the user data rate is reduced to 195 kbps at the longest link distance of 75 Mio km.

3.3

LINK BUDGET CALCULATIONS

Table 2 shows the downlink budget from the AIM spacecraft to the OGS and Table 3 the uplink budget. Both tables indicate the budgets for the maximum and the minimum link distances of 75 Mio km and 15 Mio km respectively.

Table 2

Downlink Budget from AIM to OGS

ParameterValueUnit
Transmitter  
Tx average power (3 Watt):34.8dBm
Tx antenna gain (135 mm):108.7dB
Tx truncation, WFE and transmission loss (0.63):-2.2dB
Channel   
Free-space loss (75 - 15 Mio km):-355.7-341.7dB
Scintillation, mis-pointing, atmospheric absorption and scattering loss:-3.4dB
Receiver  
Rx antenna gain (1016 mm):126.3dB
Rx transmission and filter loss (0.5):-3.0dB
Link margin (0.5)-3.0dB
Power at receiver (1.8 pW – 4.5 pW):-97.5-83.5dBm
Blue sky brightness (4.2 pW):-83.8dBm
Channel capacity391391kbps

Table 3

Uplink Budget from OGS to AIM per detector pixel

 1064 nm
ParameterValueUnit
Transmitter  
Tx average power (4x 600W = 2400 W):63.8dBm
Tx antenna gain (250 mm):98.1dB
Co-alignment pointing loss (0.9)-0.5dB
Tx transmission loss (0.8):-1.0dB
Channel  
Free-space loss (75 - 15 Mio km):-359.0-345.0dB
Atmospheric absorption and scattering loss:-8.2dB
Receiver  
Rx antenna gain (135 mm):112.0dB
Rx transmission loss inclusive filter (0.7):-1.6dB
Power at receiver (0.2 pW – 5.9 pW):-96.3-82.3dBm
Earth background (1.9 pW):-87.14dBm

For the downlink a 3 Watt average power limited amplifier is assumed and the modulation format is 16-PPM. To keep the energy density low, the pulse duration is set to 512 ns. Adding 4 guard slots to the 16-PPM modulation the symbol duration is 10.24 µs and the pulse repetition rate 97.7 kHz. This results in a raw data rate of 391 kbps. With a code rate of 0.5 the effective user data rate becomes 195 kbps from 75 Mio km link distance. During its mission the AIM spacecraft will approach earth further resulting in a reduced free space loss. This gain in received photos per laser pulse will be used to increase the data-rate to the Mbps regime. With constant transmitted average power, one can increase the pulse repetition rate and the data rate.

The effective duty cycle of the 16-PPM modulation with guard slots is 0.05 resulting in a modest laser peak power of 100 Watts, which can be handled by space qualified fiber amplifiers.

The detector diameter at the receiving OGS is 200 µm, covering a field of 3.1 arcsec with a focal length of 13.3 m. The downlink budget is put in relation with the blue-sky brightness (at daytime), however all communication downlinks from Didymos in 2022 will be performed with the OGS in darkness and the blue-sky brightness can be ignored.

With the optical power of 1.8 pW arriving at the detector surface, we expect to achieve data-rates close to the channel capacity by making use of SCPPM coding. According to first simulations based on a Poisson noise dominated, PPM communication channel, we need to ensure a detector noise below ld < 106 with a detector quantum efficiency of QE > 0.5 (s. Figure 6).

Figure 6.

Channel capacity dependence on detector dark noise (left) and quantum efficiency.

00010_PSISDG10562_105622W_page_7_1.jpg

In Table 3 the uplink budget is calculated for four 600 W laser beacon sources transmitted from the OGS at wavelengths of 1064 nm. The transmit apertures are selected as 250 mm. This leads a beam divergence of the laser beacon (35.3 µrad at 1/e2), which needs to be aligned to the receive path and to calibration stars with an accuracy at least five times better.

A 2.4 kW beacon needs to be launched from multiple sub-apertures (e.g. four) of the OGS telescope in order to reduce the power density of the optical surfaces. This can be done by using four individual lasers or with a single laser split into four beams. The four laser solution has the advantage of operational redundancy and of a more homogenous far-field illumination pattern caused by the superposition of four laser beams. A single laser solution would generate stronger interference effects (fades and surges) in the far field caused by beam interference due to the coherence length of the laser.

The uplink budget for the beacon laser is presented in Table 3. At longest link distance, the earth background outshines the received optical power by almost 10 dB. Therefore, a slow modulation of the uplink laser is used to distinguish between background and signal photons.

3.4

OGS RECEIVER/TRANSMITTER DESIGN AND ALIGNMENT

The transmit laser is coupled into the telescope’s Coudé path via a dichroic beam splitter (a glass plate that reflects the wavelength spectrum above 1.2 µm and transmits the wavelength spectrum below 1.2 µm), whose reflection is optimized for 1.06 µm and transmission for 1.55 µm.

For alignment of the optical axes of transmitter and receiver, a high precision (<1 arcsec) corner-cube retro-reflector (CCRR) with a diameter of 120 mm is mounted at the 1 m aperture of the OGS telescope. A weak 1550 nm pilot laser beam, co-aligned to and emitted from the transmit laser, is then retro-reflected through the telescope and the beam splitter towards the four quadrant detector.

4.

CONCLUSIONS

The technical design challenges of the optical communication system for the Asteroid Impact Mission (AIM) have been presented. Despite a link distance of “only” 75 Mio km, which is short in comparison to planetary distances, it was found that acquisition of the laser beams from the space terminal and from the ground terminal are the most challenging issues. The use of a modulated continuous wave beacon laser turned out to be the most efficient implementation, allowing the space terminal to target the ground terminal with sufficient precision.

It is hoped that the Asteroid Impact Mission (AIM) will become the first demonstration of a deep-space optical communication link.

ACKNOWLEDGMENT

The authors would like to thank Igor Zayer, Robert Daddato and Klaus-Jürgen Schulz from ESOC for helpful discussions.

REFERENCES

[1] 

Asteroid Impact Mission, Payload Assessment (AIM 3P), CDF Integrated Design Model (IDM), © 2004 - 2014 by ESA.Google Scholar

[2] 

Z. Sodnik, B. Furch B, H. Lutz, “The ESA Optical Ground Station - Ten Years Since First Light”, ESA bulletin 132, November 2007, pp. 34 – 40.Google Scholar

[3] 

T. Jono, Y. Takayama, N. Kura, K. Ohinata, Y. Koyama, K. Shiratama, Z. Sodnik, B. Demelenne, A. Bird, and K. Arai, “OICETS on-orbit laser communication experiments,” Proc. SPIE, 2006, vol. 6105, pp. 13–23.Google Scholar

[4] 

R. Lange R., B. Smutny, “Homodyne BPSK-based optical inter-satellite communication links”, Proc. SPIE, 2007, Vol. 6457, p. 645703.Google Scholar

[5] 

K.-J. Schulz, J. Rush et al., “Optical Link Study Group Final Report,” IOAG-15b, June 2012.Google Scholar

[6] 

LLCD Lunar Lasercom Space Terminal (LLST) to Co-operating Ground Terminal (CGT) Interface Control Document, LLCD-CGT-ICD-001, Goddard Space Flight Center.Google Scholar

[7] 

F. Arnold, M. Mosberger, J. Widmer and F. Gambarara, “Ground receiver unit for optical communication between LADEE spacecraft and ESA ground station”, SPIE, 2014, vol. 8971Google Scholar

[8] 

M. Sans, Z. Sodnik, I. Zayer and R. Daddato, “Design of ESA’s Optical Ground Station for Participation in LLCD”, Proc. ICSOS 2012, AjaccioGoogle Scholar

[9] 

B.S. Robinson, D.M. Boroson, D.A. Burianek, D.V. Murphy, “The Lunar Laser Communications Demonstration,” Space Optical Systems and Applications (ICSOS), 2011 International Conference on, pp.54–57, 11-13 May 2011.Google Scholar

[10] 

Z. Sodnik, H. Smit, M. Sans, I. Zayer, M. Lanucara, I. Montilla, A. Alonso, “LLCD Operations using the Lunar Lasercom OGS Terminal”, SPIE, 2014, vol. 8971Google Scholar

© (2017) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
C. Heese, Z. Sodnik, I. Carnelli, "Design of the optical communication system for the asteroid impact mission", Proc. SPIE 10562, International Conference on Space Optics — ICSO 2016, 105622W (25 September 2017); doi: 10.1117/12.2296213; https://doi.org/10.1117/12.2296213
PROCEEDINGS
8 PAGES


SHARE
Back to Top