Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions

Hawkins, Matt; Guo, Yanning; Wie, Bong

doi:10.5139/ijass.2012.13.2.154

Cited by 34 publications

(26 citation statements)

References 21 publications

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“…[20][21][22][23][24][25][26][27][28][29]. In this section, we briefly describe a multi-impact terminal guidance algorithm that is required for the proposed MKIV system [29].…”

Section: Mkiv Terminal Guidancementioning

confidence: 99%

Planetary defense mission concepts for disrupting/pulverizing hazardous asteroids with short warning time

et al. 2017

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This paper presents an overview of space mission concepts for disrupting or pulverizing hazardous asteroids, especially with warning time shorter than approximately 10 years. An innovative mission concept, referred to as a nuclear hypervelocity asteroid intercept vehicle (HAIV) system, employs both a kinetic-energy impactor and nuclear explosive devices. A new mission concept of exploiting a multiple kinetic-energy impactor vehicle (MKIV) system that doesn't employ nuclear explosives is proposed in this paper, especially for asteroids smaller than approximately 150 m in diameter. The multiple shock wave interaction effect on disrupting or pulverizing a small asteroid is discussed using hydrodynamic simulation results.A multi-target terminal guidance problem and a planetary defense mission design employing a heavy-lift launch vehicle are also briefly discussed in support of the new non-nuclear MKIV mission concept. The nuclear HAIV and non-nuclear MKIV systems complement to each other to effectively mitigate the various asteroid impact threats with short warning time.

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“…[20][21][22][23][24][25][26][27][28][29]. In this section, we briefly describe a multi-impact terminal guidance algorithm that is required for the proposed MKIV system [29].…”

Section: Mkiv Terminal Guidancementioning

confidence: 99%

Planetary defense mission concepts for disrupting/pulverizing hazardous asteroids with short warning time

et al. 2017

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“…This mark is the targeted impact location of each sensor. These points are the Center of mined pulses scheduled at 6300, 3600, and 1000 seconds before impact, which are implemented using kinematic impulse (KI) guidance taken from Hawkins [22]. After this is completed, the system switches over to closed-loop PN guidance at the last 270 seconds before impact.…”

Section: Closed-loop Guidance Simulationsmentioning

confidence: 99%

IR Telescope and Sensor Characterization for Hypervelocity Asteroid Intercept Guidance

Lyzhoft

Wie

2014

AIAA/AAS Astrodynamics Specialist Conference

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This paper presents the performance characterization of an infrared sensor and selected optics for an asteroid intercept vehicle traveling at hypervelocity speeds. The feasibility of using an IR sensor for hypervelocity intercept of ballistic missiles has been demonstrated by Raytheon's Exoatmospheric Kill Vehicle (EKV). In our previous work, hypervelocity impact guidance using an infrared sensor was studied for an asteroid intercept mission. However, optical telescope design for the mission was not considered. In this paper, further investigation in how telescope design will effect the performance and precision impact location of the Hypervelocity Asteroid Intercept Vehicle is described. Nomenclature F Overall System Focal Length f 1 Primary Mirror Focal Length (m) M Telescope Magnification b * Telescope Back Focus (m) p Primary Mirror Intercept Point (m) p Secondary to Cassegrain Focus (m) B Mirror Separation (m) D o Primary Mirror Diameter (m) D p Image Plane Size (m) D s Secondary Mirror Diameter (m) R 1 Radius of Curvature Primary Mirror (m) R 2 Radius of Curvature Secondary Mirror (m) z 1 Primary Mirror Surface Location (m) z 2 Secondary Mirror Surface Location (m) b 2 Paraboloid Parameter k sb Surface Brightness Coefficient L Radiance of Asteroid (W/m 2 /sr.) h Planck's Constant (m 2 kg/s) c Speed of Light in Vacuum (m/s) λ Wavelength of Radiation (m) k B Boltzmann Constant (m 2 kg/s 2 /K) Emissivity of Object τ optics Optics Transmission Coefficient r ast Asteroid Mean Radius (m) τ int Exposure Time (s) N Number of Exposures E Irradiance (W/m 2 ) λ max Peak Emission Wavelength (m) ψ Maximum Energy per Photon (J) Φ Photon Flux (photons/m 2 /sec) r ast Smallest Mean Radius of Asteroid (m) T ast Temperature of the Asteroid (K) R ast Distance from Sensor to Asteroid (m) q Charge of an Electron (coulombs) b Wien's Displacement Constant (m K) G

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“…In this problem, the duration from a given instant of time t until the end of the manoeuvre is known as time‐to‐go, t go ( t )= t f − t , the norm of the relative velocity vector ‖ v ( t )‖=‖ v S ( t )− v T ( t )‖ is known as closing speed, and the direction from target to spacecraft is known as line‐of‐sight λ ( t ). For further details on the Space D&L problem, the reader is referred to the works of Simplício et al and Hawkins et al Also in these references, the application of closed‐loop guidance techniques for the computation of appropriate acceleration laws is addressed.…”

Section: Phobos Mission Benchmarkmentioning

confidence: 99%

Synthesis and analysis of robust control compensators for Space descent & landing

Simplicio

Marcos

Joffre

et al. 2018

Intl J Robust & Nonlinear

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Summary In this article, a complete modelling, synthesis, and analysis methodology of control compensators for descent and landing (D&L) on small planetary bodies is presented. These missions are scientifically very rewarding but technically extremely challenging due to the complex and poorly known environment around those bodies, which calls for the ability to manage competing robustness and performance requirements. While this issue is typically addressed via the redefinition of D&L guidance strategies, here, it is tackled through the augmentation with a simple yet robust control compensator. This compensator is designed using linear fractional transformation modelling to capture the interplay with uncertain gravity fields and the recently developed structured H∞ optimisation framework, which has been proved particularly suitable for industry‐oriented applications. The proposed approach is completely generic but uses the scenario of a landing on the Martian moon Phobos as an illustrative example. Different compensators are then verified and compared analytically via the structured singular value μ and through high‐fidelity Monte Carlo simulation.

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Spacecraft Guidance Algorithms for Asteroid Intercept and Rendezvous Missions

Cited by 34 publications

References 21 publications

Planetary defense mission concepts for disrupting/pulverizing hazardous asteroids with short warning time

Planetary defense mission concepts for disrupting/pulverizing hazardous asteroids with short warning time

IR Telescope and Sensor Characterization for Hypervelocity Asteroid Intercept Guidance

Synthesis and analysis of robust control compensators for Space descent & landing

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