Accurate Real-Time Prediction Guidance Using Numerical Integration for Reentry Spacecraft

Matsumoto, Shuichi; Kondoh, Yoshinori; Suzuki, Yusuke; Yamamoto, Hifumi; Kobayashi, Sei; Motoyama, Noboru

doi:10.2514/6.2013-4646

Cited by 4 publications

(5 citation statements)

References 2 publications

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“…( 13) is an implicit guidance law using a reference trajectory and based on that implemented on the OREX mission. 10 The guidance was updated every 5 seconds throughout the trajectory. The accuracy deteriorates if the initial conditions between the reference trajectory and actual flight trajectory becomes too large.…”

Section: Results With Variable L/d Morphing Eventsmentioning

confidence: 99%

Application of an Optimal Control Allocation Scheme with Structural Load and Aero Heating Feedback for a Morphing Inflatable Aerodynamic Decelerator

Bassett

Pei

Slagle

et al. 2018

2018 AIAA Atmospheric Flight Mechanics Conference

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Precision landing of large payloads on Mars presents a challenge to the Entry, Descent, and Landing (EDL) community. Previous studies indicated that by incorporating the capability for a Hypersonic Inflatable Aerodynamic Decelerator (HIAD) to morph during reentry would result in a more accurate landing footprint by allowing modulation of the liftto-drag (L/D) vector directly instead of through bank angle control. However, morphing the HIAD shape for trajectory control may expose the HIAD to potential structural loads or aero heating concerns. In this study, the application of an optimal control allocation (OCA) technique was investigated that would to enable the morphing HIAD to maximize trajectory control capabilities while simultaneously keeping the structural loads and aero heating below some thresholds. This concept was demonstrated in a 3 degree-of-freedom (DOF) EDL simulation and provides basis for future research.

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Section: Results With Variable L/d Morphing Eventsmentioning

confidence: 99%

Application of an Optimal Control Allocation Scheme with Structural Load and Aero Heating Feedback for a Morphing Inflatable Aerodynamic Decelerator

Bassett

Pei

Slagle

et al. 2018

2018 AIAA Atmospheric Flight Mechanics Conference

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“…The calculated drag acceleration, D cal , is calculated using the air density model of the US standard atmosphere 76 13 as shown in Eq. (9). Since the observation matrix of air drag for altitude is less sensitive to air density error, we use simple exponential air density model to calculate the observation matrix as shown in Eq.…”

Section: Observation Equations For Imu-dm Integrated Navigationmentioning

confidence: 99%

“…However, reentry guidance error analyses in Ref. 9 showed that we need to make more effort to meet the targeted reentry guidance accuracy of 1 km, particularly give considerable misalignment errors of inertial reference for inertial navigation during GPS signal blackouts and unpredictable upper-level wind variation. …”

Section: Introductionmentioning

confidence: 98%

“…8 To resolve this disadvantage, we proposed real-time prediction guidance using numerical integration for reentry spacecraft in Ref. 9. There, we showed the feasibility of applying the real-time prediction guidance using numerical integration for reentry flight using the latest high performance 64-bit space-qualified MPU such as HR5000(80MHz) 10 and evaluated the reentry guidance accuracy of the real-time prediction guidance using numerical integration with IMU-GPS-ST integrated navigation, accurate range prediction using measured upperlevel wind information, and simple terminal reentry guidance to ensure reentry guidance accuracy to within 0.77 km (1σ), i.e.…”

Section: Introductionmentioning

confidence: 99%

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IMU-DM Integrated Navigation and Terminal Reentry Guidance for Accurate Guided Reentry Flight

Matsumoto

Kondoh

Haruki

et al. 2015

AIAA Guidance, Navigation, and Control Conference

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High-accuracy reentry guidance has become increasingly important for reentry capsule spacecraft. For example, in an advanced concept study of the Japanese manned reentry capsule, an attempt has been made to land the capsule on the Japanese mainland. For this purpose, the targeted reentry guidance accuracy is to within 1 km at the point of parachute deployment. To meet this high requirement, we have been developing accurate real-time prediction guidance using numerical integration for reentry spacecraft. This guidance method is an explicit guidance law using real-time numerical integration to predict the accurate range during reentry flight, which already includes IMU-GPS integrated navigation, on-orbit alignment by star tracker and measured wind information utilization for range prediction. However, reentry guidance error analyses we did using those guidance methods showed that we need to made more effort to meet the targeted reentry guidance accuracy of 1 km, particularly given the considerable residual alignment error of inertial navigation and unpredictable upper-level wind variation. Accordingly we added the IMU-DM (Drag Measurement) integrated navigation and improved terminal reentry guidance to the accurate real-time prediction guidance using numerical integration for reentry spacecraft.This paper outlines the real-time prediction guidance using numerical integration (REP-NI Guidance), describes the methods and performances of IMU-DM integrated navigation and improved terminal reentry guidance and shows guidance accuracy using those methods by guidance error analyses and Monte Carlo simulations.

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“…Using orbit determination results, a Monte Carlo simulation for aeroassisted guidance flight at EDL was performed using real-time prediction guidance 4) and Mars-GRAM (Mars Global Reference Atmospheric Model). Parameters of the entry capsule was assumed as shown in Table 4.…”

Section: Orbit Determination and Aerodynamic Guidancementioning

confidence: 99%

Orbit Plan and Mission Design for Mars EDL and Surface Exploration Technologies Demonstrator

Ogawa

Haruki

Kondoh

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Mars EDL (entry, descent and landing) and surface exploration demonstration working group in Japan Aerospace Exploration Agency (JAXA) has assessed and discussed feasibility of a Martian rover mission to be launched in early 2020s. The primary objectives of this mission are to demonstrate technologies required for EDL and surface exploration of a massive planet with an atmosphere, to investigate Martian geochronology and to search for signs of lives, past or present, and to determine when the ocean was lost in the Martian history. The launch date is targeted in early 2020's in our study. In this paper, we investigate launch opportunities during 2020's and propose several launch windows considering some system requirements. Feasible interplanetary transfer trajectories from Earth to Mars are proposed. Assuming direct entry and following aerodynamic guidance in Martian atmosphere, we connected interplanetary and aerodynamic trajectories so as to land on an aimed point. Precision analysis of orbit determination at the entry and landing is also shown.

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Accurate Real-Time Prediction Guidance Using Numerical Integration for Reentry Spacecraft

Cited by 4 publications

References 2 publications

Application of an Optimal Control Allocation Scheme with Structural Load and Aero Heating Feedback for a Morphing Inflatable Aerodynamic Decelerator

Application of an Optimal Control Allocation Scheme with Structural Load and Aero Heating Feedback for a Morphing Inflatable Aerodynamic Decelerator

IMU-DM Integrated Navigation and Terminal Reentry Guidance for Accurate Guided Reentry Flight

Orbit Plan and Mission Design for Mars EDL and Surface Exploration Technologies Demonstrator

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