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21 pages, 1880 KiB

Open AccessArticle

Fully Autonomous Orbit Determination and Synchronization for Satellite Navigation and Communication Systems in Halo Orbits

by Gheorghe Sirbu and Mauro Leonardi

Remote Sens. 2023, 15(5), 1173; https://0-doi-org.brum.beds.ac.uk/10.3390/rs15051173 - 21 Feb 2023

Cited by 4 | Viewed by 1816

Abstract

This paper presents a solution for autonomous orbit determination and time synchronization of spacecraft in Halo orbits around Lagrange points using inter-satellite links. Lagrange points are stable positions in the gravitational field of two large bodies that allow for a sustained presence of [...] Read more.

This paper presents a solution for autonomous orbit determination and time synchronization of spacecraft in Halo orbits around Lagrange points using inter-satellite links. Lagrange points are stable positions in the gravitational field of two large bodies that allow for a sustained presence of a spacecraft in a specific region. However, a challenge in operating at these points is the lack of fixed landmarks for orbit determination. The proposed solution involves using inter-satellite links to perform range and range-rate measurements, allowing for accurate computation of the spacecraft’s orbit parameters without the need for any facilities on Earth. Simulations using a fleet of three satellites in Near Rectilinear Halo Orbits around the Earth–Moon Lagrange point, proposed for the Lunar Gateway stations, were conducted to demonstrate the feasibility of the approach. The results show that inter-satellite links can provide reliable and accurate solutions for orbit determination with a DRMS error lower than one meter (90th percentile) and synchronization errors of around one nanosecond. This solution paves the way for a fully autonomous fleet of spacecraft that can be used for observation, telecommunication, and navigation missions. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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17 pages, 11923 KiB

Open AccessArticle

Sequential Processing of Inter-Satellite Doppler Tracking for a Dual-Spacecraft Configuration

by Flavio Petricca and Antonio Genova

Remote Sens. 2022, 14(21), 5383; https://doi.org/10.3390/rs14215383 - 27 Oct 2022

Viewed by 1237

Abstract

The navigation of future interplanetary spacecraft will require an increasing degree of autonomy to enhance space system performance. A real-time trajectory determination is of paramount importance to reduce the risks of operations devoted to the exploration of celestial bodies in the solar system [...] Read more.

The navigation of future interplanetary spacecraft will require an increasing degree of autonomy to enhance space system performance. A real-time trajectory determination is of paramount importance to reduce the risks of operations devoted to the exploration of celestial bodies in the solar system and to reduce the dependence and the loading on the ground systems. We present a technique for a sequential estimation of spacecraft orbits through the processing of line-of-sight relative velocity measurements that are acquired by the novel inter-satellite tracking system. This estimation scheme is based on the extended Kalman filter and is tested and validated in a realistic Mars mission scenario. Our numerical simulations suggest that the proposed navigation system can provide accuracies of a few meters in position and a few millimeters per second in velocity. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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21 pages, 555 KiB

Open AccessArticle

The Influence of Dynamic Solar Oblateness on Tracking Data Analysis from Past and Future Mercury Missions

by Rens van der Zwaard and Dominic Dirkx

Remote Sens. 2022, 14(17), 4139; https://0-doi-org.brum.beds.ac.uk/10.3390/rs14174139 - 23 Aug 2022

Cited by 2 | Viewed by 1255

Abstract

When the BepiColombo spacecraft arrives at Mercury in late 2025, it will be able to measure the orbit of the planet with unprecedented accuracy, allowing for more accurate measurements of the perihelion advance of the planet, as predicted by the Theory of General [...] Read more.

When the BepiColombo spacecraft arrives at Mercury in late 2025, it will be able to measure the orbit of the planet with unprecedented accuracy, allowing for more accurate measurements of the perihelion advance of the planet, as predicted by the Theory of General Relativity (GR). A similar effect is produced by the gravitational oblateness of the Sun through the zonal coefficient

J_{2 ⊙}

. The gravitational field of the Sun has been hard to determine despite centuries of observations, causing great uncertainties in experiments on GR. Recent publications in heliophysics suggest that

J_{2 ⊙}

is not a constant, but a dynamic value that varies with solar magnetic activity. The aim of this paper is to analyse what the effect is of suggested higher-order effects of the solar gravitational field on experiments of the perihelion advance of Mercury as predicted by GR. The orbit of Mercury and observations of the MESSENGER and BepiColombo spacecraft are simulated, and parameters corresponding to gravitational theory, as well as the oblateness

J_{2 ⊙}

including a time-variable component are estimated using a least-squares approach. The result of the estimation is that the amplitude of a periodic component can be found with an uncertainty of

3.7 \times 10^{- 11}

, equal to 0.017% the value of

J_{2 ⊙}

. From analysis of published experiments that used MESSENGER tracking data, it can already be deduced that the amplitude of the periodic variation cannot be higher than 5% of the value of

J_{2 ⊙}

. It is also found that if a periodic component exists with an amplitude greater than 0.04% the value of

J_{2 ⊙}

and it is not considered, it can lead to errors in the experiments of GR using BepiColombo data to the point that results falsely confirm or contradict the Theory of General Relativity. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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26 pages, 2076 KiB

Open AccessArticle

Cold Atom Interferometry for Enhancing the Radio Science Gravity Experiment: A Phobos Case Study

by Michael Plumaris, Dominic Dirkx, Christian Siemes and Olivier Carraz

Remote Sens. 2022, 14(13), 3030; https://0-doi-org.brum.beds.ac.uk/10.3390/rs14133030 - 24 Jun 2022

Cited by 2 | Viewed by 1600

Abstract

Interplanetary missions have typically relied on Radio Science (RS) to recover gravity fields by detecting their signatures on the spacecraft trajectory. The weak gravitational fields of small bodies, coupled with the prominent influence of confounding accelerations, hinder the efficacy of this method. Meanwhile, [...] Read more.

Interplanetary missions have typically relied on Radio Science (RS) to recover gravity fields by detecting their signatures on the spacecraft trajectory. The weak gravitational fields of small bodies, coupled with the prominent influence of confounding accelerations, hinder the efficacy of this method. Meanwhile, quantum sensors based on Cold Atom Interferometry (CAI) have demonstrated absolute measurements with inherent stability and repeatability, reaching the utmost accuracy in microgravity. This work addresses the potential of CAI-based Gradiometry (CG) as a means to strengthen the RS gravity experiment for small-body missions. Phobos represents an ideal science case as astronomic observations and recent flybys have conferred enough information to define a robust orbiting strategy, whilst promoting studies linking its geodetic observables to its origin. A covariance analysis was adopted to evaluate the contribution of RS and CG in the gravity field solution, for a coupled Phobos-spacecraft state estimation incorporating one week of data. The favourable observational geometry and the small characteristic period of the gravity signal add to the competitiveness of Doppler observables. Provided that empirical accelerations can be modelled below the nm/s

^{2}

level, RS is able to infer the 6 × 6 spherical harmonic spectrum to an accuracy of 0.1–1% with respect to the homogeneous interior values. If this correlates to a density anomaly beneath the Stickney crater, RS would suffice to constrain Phobos’ origin. Yet, in event of a rubble pile or icy moon interior (or a combination thereof) CG remains imperative, enabling an accuracy below 0.1% for most of the 10 × 10 spectrum. Nevertheless, technological advancements will be needed to alleviate the current logistical challenges associated with CG operation. This work also reflects on the sensitivity of the candidate orbits with regard to dynamical model uncertainties, which are common in small-body environments. This brings confidence in the applicability of the identified geodetic estimation strategy for missions targeting other moons, particularly those of the giant planets, which are targets for robotic exploration in the coming decades. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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9 pages, 2356 KiB

Open AccessCommunication

Low-SNR Doppler Data Processing for the InSight Radio Science Experiment

by Dustin Buccino, James S. Border, William M. Folkner, Daniel Kahan and Sebastien Le Maistre

Remote Sens. 2022, 14(8), 1924; https://0-doi-org.brum.beds.ac.uk/10.3390/rs14081924 - 15 Apr 2022

Cited by 4 | Viewed by 1551

Abstract

Radio Doppler measurements between the InSight lander and NASA’s Deep Space Network have been acquired for measuring the rotation of Mars. Unlike previous landers used for this purpose that utilized steerable high-gain antennas, InSight uses two fixed medium-gain antennas, which results in a [...] Read more.

Radio Doppler measurements between the InSight lander and NASA’s Deep Space Network have been acquired for measuring the rotation of Mars. Unlike previous landers used for this purpose that utilized steerable high-gain antennas, InSight uses two fixed medium-gain antennas, which results in a lower radio signal-to-noise ratio (SNR). Lower SNR results in additional thermal noise for Doppler measurements using standard processes. Through a combination of phase averaging and traditional data compression, the increased thermal noise due to low SNR can be removed for most of the signal of interest, resulting in more accurate Doppler measurements. During the first 900 days of InSight operations, Doppler measurements were improved by ~25% on average using this method. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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16 pages, 2877 KiB

Open AccessArticle

Rosetta CONSERT Data as a Testbed for In Situ Navigation of Space Probes and Radiosciences in Orbit/Escort Phases for Small Bodies of the Solar System

by Mao Ye, Fei Li, Jianguo Yan, Alain Hérique, Wlodek Kofman, Yves Rogez, Thomas P. Andert, Xi Guo and Jean-Pierre Barriot

Remote Sens. 2021, 13(18), 3747; https://0-doi-org.brum.beds.ac.uk/10.3390/rs13183747 - 18 Sep 2021

Cited by 2 | Viewed by 1797

Abstract

Many future space missions to asteroids and comets will implement autonomous or near-autonomous navigation, in order to save costly observation time from Earth tracking stations, improve the security of spacecraft and perform real-time operations. Existing Earth-Spacecraft-Earth tracking modes rely on severely limited Earth [...] Read more.

Many future space missions to asteroids and comets will implement autonomous or near-autonomous navigation, in order to save costly observation time from Earth tracking stations, improve the security of spacecraft and perform real-time operations. Existing Earth-Spacecraft-Earth tracking modes rely on severely limited Earth tracking station resources, with back-and-forth delays of up to several hours. In this paper, we investigate the use of CONSERT ranging data acquired in direct visibility between the lander Philae and the Rosetta orbiter, in the frame of the ESA space mission to comet 67P/Churyumov-Gerasimenko, as a proxy of autonomous navigation and orbitography science capability. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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17 pages, 5223 KiB

Open AccessArticle

Retrieving Doppler Frequency via Local Correlation Method of Segmented Modeling

by Lue Chen, Jinsong Ping, Jianfeng Cao, Xiang Liu, Na Wang, Zhen Wang, Ping Zhu, Mei Wang, Haijun Man, Fei Fan, Weitao Lu, Jing Sun and Songtao Han

Remote Sens. 2021, 13(14), 2846; https://0-doi-org.brum.beds.ac.uk/10.3390/rs13142846 - 20 Jul 2021

Cited by 5 | Viewed by 1958

Abstract

The high accuracy radio Doppler frequency is critical for navigating a deep space probe and for planetary radio science experiments. In this paper, we propose a novel method based on the local correlation of segmented modeling to retrieve Doppler frequency by processing an [...] Read more.

The high accuracy radio Doppler frequency is critical for navigating a deep space probe and for planetary radio science experiments. In this paper, we propose a novel method based on the local correlation of segmented modeling to retrieve Doppler frequency by processing an open-loop radio link signal from one single ground station. Simulations are implemented, which prove the validity of this method. Mars Express (MEX) and Tianwen-1 observation experiments were carried out by Chinese Deep Space Stations (CDSS). X-band Doppler frequency observables were retrieved by the proposed method to participate in orbit determination. The results show that the accuracy of velocity residuals of orbit determination in open-loop mode is from 0.043 mm/s to 0.061 mm/s in 1 s integration; the average accuracy of Doppler frequency is about 3.3 mHz in 1 s integration and about 0.73 mHz in 60 s integration. The Doppler accuracy here is better than that of the digital baseband receiver at CDSS. The algorithm is efficient and flexible when the deep space probe is in a high dynamic mode and in low signal to noise ratio (SNR). This will benefit Chinese deep space exploration missions and planetary radio science experiments. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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13 pages, 2900 KiB

Open AccessTechnical Note

Trajectory Determination of Chang’E-5 during Landing and Ascending

by Peng Yang, Yong Huang, Peijia Li, Siyu Liu, Quan Shan and Weimin Zheng

Remote Sens. 2021, 13(23), 4837; https://0-doi-org.brum.beds.ac.uk/10.3390/rs13234837 - 28 Nov 2021

Cited by 5 | Viewed by 1641

Abstract

Chang’E-5 (CE-5) is China’s first lunar sample return mission. This paper focuses on the trajectory determination of the CE-5 lander and ascender during the landing and ascending phases, and the positioning of the CE-5 lander on the Moon. Based on the kinematic statistical [...] Read more.

Chang’E-5 (CE-5) is China’s first lunar sample return mission. This paper focuses on the trajectory determination of the CE-5 lander and ascender during the landing and ascending phases, and the positioning of the CE-5 lander on the Moon. Based on the kinematic statistical orbit determination method using B-spline and polynomial functions, the descent and ascent trajectories of the lander and ascender are determined by using ground-based radiometric ranging, Doppler and interferometry data. The results show that a B-spline function is suitable for a trajectory with complex maneuvers. For a smooth trajectory, B-spline and polynomial functions can reach almost the same solutions. The positioning of the CE-5 lander on the Moon is also investigated here. Using the kinematic statistical positioning method, the landing site of the lander is 43.0590°N, 51.9208°W with an elevation of −2480.26 m, which is less than 200 m different from the LRO (Lunar Reconnaissance Orbiter) image data. Full article

(This article belongs to the Special Issue Methods of Precise Orbit Determination and Autonomous Navigation for Interplanetary Space Probes)

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