The Iris Deep-Space Transponder for the SLS EM-1 Secondary Payloads

Kobayashi, M. Michael; Holmes, S.; Yarlagadda, Anusha; Aguirre, Fernando; Chase, Matthew; Angkasa, Krisjani; Burgett, Brandon; McNally, Lauren; Dobreva, Tatyana; Satorius, E.

doi:10.1109/maes.2019.2905923

Cited by 20 publications

(10 citation statements)

References 4 publications

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“…The X-band radio for PRO-CYON provides a tone generator for Range and Range Rate (R&RR) and Delta Differential One-Way Range (𝛥-DOR) orbit determination with a high-power (15 W) output [155]. On the other hand, the IRIS transponder, developed for MarCO mission by the Jet Propulsion Laboratory, provides sequential/pseudo-noise ranging, 𝛥-DOR, and Doppler for navigation purposes with a RF output power of 4 W. Soon, six Cube-Sats within Artemis-1 mission program; LunaH-Map, Lunar IceCube, Lunar Flashlight, CubeSat for Solar PArticles, BioSentinel, and Near-Earth Asteroid Scout, will be supported by the third generation V2.1 IRIS Transponder [156] (shown in Fig. 13).…”

Section: Enabling Technologiesmentioning

confidence: 99%

Autonomous navigation for deep space small satellites: Scientific and technological advances

2022

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In recent years, there is a growing interest in small satellites for deep space exploration. The current approach for planetary navigation is based on ground-based radiometric tracking. A new era of low-cost small satellites for space exploration will require autonomous deep space navigation. This will decrease the reliance on groundbased tracking and provide a substantial reduction in operational costs because of crowded communication networks. In addition, it will be an enabler for future missions currently impossible. This review investigates available deep space navigation methods from an autonomy perspective, considering trends in proposed deep space small satellite missions. Autonomous crosslink radiometric navigation, which is one of the best methods for small satellites due to its simplicity and the use of existing technologies, is studied, including available measurement methods, enabling technologies, and applicability to the currently proposed missions. The main objective of this study is to fill the gap in the scientific literature on the autonomous deep space navigation methods, deeply for crosslink radiometric navigation and to aim at showing the potential advantages that this technique could offer to the missions being analyzed. In this study, a total of 64 proposed deep space small satellite missions have been analyzed found from a variety of sources including journal papers, conference proceedings, and mission websites. In those missions, the most popular destinations are found to be cislunar space and small bodies with the purpose of surface mapping and characterization. Even though various autonomous navigation methods have been proposed for those missions, most of them have planned to use the traditional ground-based radiometric tracking for navigation purposes. This study also shows that more than half of the missions can benefit from the crosslink radiometric navigation through the inter-satellite link.

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Section: Enabling Technologiesmentioning

confidence: 99%

Autonomous navigation for deep space small satellites: Scientific and technological advances

2022

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“…The Iris radio [13], [14] was the main payload of the two MarCO CubeSat spacecraft [15] that accompanied the Mars Insight lander [16] and provided a relay link during Insight's entry, descent, and landing phases. The two MarCO spacecraft are the first CubeSats in deep space.…”

Section: Determination Of Other Signal Parametersmentioning

confidence: 99%

“…For example, the Iris radio DAC frequency is 50 MHz [13], [14] and the UST radio DAC frequency is 150 MHz [21]. Based on this, it is possible to generate a table with possible values of ðK; bÞ that meet the required bandwidth for the specific radio.…”

Section: Figurementioning

confidence: 99%

Improved Signals for Differential One-Way Range

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et al. 2020

IEEE Aerosp. Electron. Syst. Mag.

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“…The LF spacecraft propulsion system is a novel technology developed by VACCO Industries, Inc. and will use "green" monopropellant [39]. The transfer of the raw measurements and the remote control of the spacecraft will be achieved by a miniaturized radio called "Iris" [40], which has recently been used by Mars Cube One (MarCO) CubeSats launched to Mars in May 2018. After the ejection of the LF spacecraft from the dispenser, four solar panels deployed in the configuration shown in Figure 1(a) will supply the electrical power to charge the spacecraft batteries.…”

Section: Lunar Flashlight Cubesatmentioning

confidence: 99%

Design and Characterization of the Multi-Band SWIR Receiver for the Lunar Flashlight CubeSat Mission

et al. 2019

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Lunar Flashlight (LF) is an innovative National Aeronautics and Space Administration (NASA) CubeSat mission that is dedicated to quantifying and mapping the water ice that is harbored in the permanently shadowed craters of the lunar South Pole. The primary goal is to understand the lunar resource potential for future human exploration of the Moon. To this end, the LF spacecraft will carry an active multi-band reflectometer, based on an optical receiver aligned with four high-power diode lasers emitting in the 1 to 2-μm shortwave infrared band, to measure the reflectance of the lunar surface from orbit near water ice absorption peaks. We present the detailed optical, mechanical, and thermal design of the receiver, which is required to fabricate this instrument within very demanding CubeSat resource allocations. The receiver has been optimized for solar stray light rejection from outside its field of view, and utilizes a 70 × 70-mm, aluminum, off-axis paraboloidal mirror with a focal length of 70 mm, which collects the reflected light from the Moon surface onto a single-pixel InGaAs detector with a 2-mm diameter, hence providing a 20-mrad field of view. The characterization of the flight receiver is also presented, and the results are in agreement with the expected performance obtained from simulations. Planned to be launched by NASA on the first Space Launch System (SLS) test flight, this highly mass-constrained and volume-constrained instrument payload will demonstrate several firsts, including being one of the first instruments onboard a CubeSat performing science measurements beyond low Earth orbit, and the first planetary mission to use multi-band active reflectometry from orbit.

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The Iris Deep-Space Transponder for the SLS EM-1 Secondary Payloads

Cited by 20 publications

References 4 publications

Autonomous navigation for deep space small satellites: Scientific and technological advances

Autonomous navigation for deep space small satellites: Scientific and technological advances

Improved Signals for Differential One-Way Range

Design and Characterization of the Multi-Band SWIR Receiver for the Lunar Flashlight CubeSat Mission

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