Real-Time EDL Navigation Performance Using Spacecraft to Spacecraft Radiometric Data

Burkhart, P. Daniel; Ely, Todd A.; Duncan, Courtney; Lightsey, Glenn; Campbell, B. Todd; Mogensen, Andy

doi:10.2514/6.2006-6566

Cited by 7 publications

(2 citation statements)

References 9 publications

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“…A first draft of such a system is being investigated for the MSL mission [28,29]. Two possible measurements are available: range and relative velocity.…”

Section: Innovative Observability Solutionmentioning

confidence: 99%

Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

Lévesque

Lafontaine

2007

Journal of Guidance, Control, and Dynamics

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Accurate navigation systems are required in the scope of Mars precision landing missions. This paper reviews some assumptions of the literature concerning the availability of the vehicle states for guidance during its atmospheric entry on Mars. It is demonstrated that currently used measurements are not sufficient to get complete observability of the entry dynamics. Therefore, four innovative measurement scenarios based on radio ranging are proposed to resolve the observability issue. The analyses and simulations show that the addition of the range measurements from known references helps to estimate accurately the position states along with some critical model parameters, contrary to inertial measurement unit navigation alone. Finally, the addition of the range measurement from a secondary free-falling dummy vehicle with known aerodynamics also ensures the observability of aerodynamic parameters of the lander vehicle. Nomenclature A, B, C, D = state-space matrices a B = acceleration components in the body frame, m=s 2 B = ballistic parameter, m 2 =kg C D = aerodynamic drag coefficient C L = aerodynamic lift coefficient D = aerodynamic drag force, N d = aerodynamic drag deceleration, m=s 2 g = gravitational acceleration, m=s 2 h = altitude, m h s = atmospheric scale height, m h 0 = reference altitude, m L = aerodynamic lift force, N L=D = lift-to-drag ratio m = vehicle mass, kg Q o = observability matrix q = dynamic pressure, kg=m s 2 R e = equatorial radius, m r = radial distance, m S = aerodynamic surface, m s = downrange, m t = time. s u = input vector v = inertial velocity, m=s 0= trim angle of attack, rad = flight-path angle, rad = latitude, rad = longitude, rad M = Mars gravitational constant, m 3 =s 2 = atmospheric density, kg=m 3 0 = atmospheric reference density, kg=m 3 = bank angle, rad = azimuth (clockwise from north), rad ! B = angular rate components in body frame

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“…A first draft of such a system is being investigated for the MSL mission [28,29]. Two possible measurements are available: range and relative velocity.…”

Section: Innovative Observability Solutionmentioning

confidence: 99%

Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

Lévesque

Lafontaine

2007

Journal of Guidance, Control, and Dynamics

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“…This partition uses the open-source RTEMS real-time operating system [20], providing multi-threading, amongst other services, to the application. The real-time performance, space heritage (for example, in the Herschel-Planck [21], Mars Science Laboratory [22] and Eu:CROPIS [23] missions) and availability of source code for evaluation, debugging and modification were important factors in the selection of RTEMS. NAVDLR receives image data from the cameras via IPC requests to the IOSCAM partition, which controls the hardware interface to the camera.…”

Section: Obc Architecturementioning

confidence: 99%

The MMX Rover on Phobos: The Preliminary Design of the DLR Autonomous Navigation Experiment

Vayugundla

Bodenmüller

Schuster

et al. 2021

2021 IEEE Aerospace Conference (50100)

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This paper summarizes the challenges of deep space planetary robotic-exploration missions, using the example of the DLR Autonomous Navigation Experiment within the MMX Rover project, and presents a preliminary design of the proposed solution to safe navigation of the MMX Rover on Phobos. The MMX Rover, a joint contribution of the German Aerospace Center (DLR) and the Centre National d'Etudes Spatiales (CNES) is part of the Martian Moons eXploration (MMX) Mission by the Japan Aerospace Exploration Agency (JAXA), whose mission objective is to understand the origin of the two Martian moons. The mission involves scientific data collection and a sample return from Phobos, the bigger of the two Martian moons. The mission is scheduled to launch in the third quarter of 2024. The MMX Rover will fly as a payload and will be jettisoned onto Phobos from a low altitude of about 40 metres. The rover has multiple objectives: terrain assessment to mitigate the risk for the sample-return approach of the spacecraft, exploration of the surface of Phobos and act as a scientific and technology demonstration platform. In this context, the Robotics and Mechatronics Institute, DLR, is preparing to perform an Autonomous Navigation Experiment as a technology demonstration to showcase the advantages of robot autonomy for exploring distant celestial bodies. If successful, the MMX Rover will be the first man-made object to land on and explore Phobos.

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A beacon configuration optimization method based on Fisher information for Mars atmospheric entry

Zhao

Cui

2017

Acta Astronautica

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Real-Time EDL Navigation Performance Using Spacecraft to Spacecraft Radiometric Data

Cited by 7 publications

References 9 publications

Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

Innovative Navigation Schemes for State and Parameter Estimation During Mars Entry

The MMX Rover on Phobos: The Preliminary Design of the DLR Autonomous Navigation Experiment

A beacon configuration optimization method based on Fisher information for Mars atmospheric entry

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