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Spacecraft Manoeuvring In The Vicinity Of A Near Circular Orbit

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Spacecraft Manoeuvring In The Vicinity Of A Near Circular Orbit

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Author : Andrey Baranov
language : en
Publisher:
Release Date : 2022-08

Spacecraft Manoeuvring In The Vicinity Of A Near Circular Orbit written by Andrey Baranov and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2022-08 with categories.

This book sets forth the theory of optimal manoeuvring in the vicinity of a circular orbit, describing the possible types of optimal solutions for the transfer and rendezvous problems in cases of coplanar and non-coplanar orbits. In order to find the manoeuvre parameters of these solutions, the book presents extremely simple analytical and numerical-analytical methods, and shows how they can be applied for the solution of basic manoeuvre problems for real spacecraft. It also details effective methods, used both in Russia and across the globe, for the active space object manoeuvre assessment, which will help to propagate collision hazards more accurately.

Spacecraft Manoeuvring In The Vicinity Of A Near Circular Orbit

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Author : Andrey Baranov
language : en
Publisher:
Release Date : 2023-04-24

Guidance And Control Of A Spacecraft To Rendevous And Dock With A Non Cooperative Target

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Author : Anantha Sayanam Komanduri
language : en
Publisher: Cuvillier Verlag
Release Date : 2011-11-22

Guidance And Control Of A Spacecraft To Rendevous And Dock With A Non Cooperative Target written by Anantha Sayanam Komanduri and has been published by Cuvillier Verlag this book supported file pdf, txt, epub, kindle and other format this book has been release on 2011-11-22 with Technology & Engineering categories.

Non-cooperative spacecrafts are those current or future assets in orbit which have lost their control authority in one or more degrees of freedom and cannot convey any information concerning their position, attitude or rates to facilitate Rendezvous and Docking/Berthing (RVD/B) process. A growing ﬁeld of study in space research is to develop On-Orbit Servicing (OOS) technology capable of dealing with these space- crafts, called targets, which are designed without any intention to be serviced. To render services such as repair, refuel or removal of the target from orbit, the chaser spacecraft should exhibit sophisticated RVD/B technology for formation ﬂy and ﬁnal stage docking/berthing operations of the mission. Assuming that the terminal capture operations of the target are to be performed by a suitable manipulator system on-board chaser, this study relies upon proven technology and outlines guidance and control methodologies to achieve rendezvous during proximity phases. The entry gate of chaser after phasing can be deﬁned at a distance of about 5 km in ± V-bar direction from the target in its orbit. To account for errors in modeling, navigation or actuation, proximity range operations from the entry gate are decomposed into three diﬀerent subphases as far range, inspection or ﬂy around and closer approach. From the entry gate and along the path of the chaser two hold points are deﬁned: ﬁrst to initiate an inspection and the second, which is close to the safe zone deﬁned around the target, to initiate a capture. The chaser is assumed to perform a station keeping maneuver at the second hold point until initial conditions for the capture are met. Possible scenarios pertaining to the behavior of the target in a circular orbit are considered and guidance schemes for diﬀerent subphases are presented using a combination of Hill-Clohessy-Willtshire (HCW) solution, elliptical ﬂy around, glides- lope algorithm etc. Relative controllers both for position and attitude of the chaser are also presented. A Linear Quadratic (LQ) controller for relative position and a Proportional Integral Derivative (PID) controller for relative attitude with angular velocity constraints are chosen to track down the error to achieve rendezvous and attitude synchronization with the non-cooperative target. A comparative analysis between diﬀerent guidance trajectories for important parameters such as time, fuel usage, minimum absolute distance and the maximum radial distance from the target is presented. Veriﬁcation of the proposed guidance and control methods is done by applying them to two diﬀerent case studies: the ﬁrst study incorporating a stabilized target in Geostationary Earth Orbit (GEO) and the second, with a spinning target in Low Earth Orbit (LEO). The methods presented here are general and provide a simulator to the chaser to perform rendezvous analysis with non-cooperative targets. To achieve RVD/B, the study proposes a careful combination of guidance solutions for diﬀerent phases of proximity operations, and for diﬀerent scenario’s of the target encountered by the chaser.

Determination Of Orbit Of A Spacecraft With Respect To An Object In A Known Circular Orbit

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Author : Robert Scott Dunning
language : en
Publisher:
Release Date : 1966

Determination Of Orbit Of A Spacecraft With Respect To An Object In A Known Circular Orbit written by Robert Scott Dunning and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1966 with Aerodynamics categories.

Spacecraft Navigation And Guidance

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Author : Maxwell Noton
language : en
Publisher: Springer Science & Business Media
Release Date : 2012-12-06

Spacecraft Navigation And Guidance written by Maxwell Noton and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2012-12-06 with Technology & Engineering categories.

The analysis and computational techniques associated with the navigation and guidance of spacecraft are now in a mature state of development. However the documentation has remained dispersed throughout conference papers, journals, company and contract rep orts, making it difficult to get a true, comprehensive picture of the subject. This text brings together the body of literature with suitable attention to the necessary underlying mathematics and computational techniques. It covers in detail the necessary orbital mechanics, orbit determination with emphasis on the SRIF algorithm, gr avity assist manoeuvres and guidance, both ground-based and autonomous. Attention is paid to all phases of a space mission including launch and re-entry, and whether culminating in an earth satellite or a deep space mission to planets or primitive bodies. Software associated with the text is available free to the reader by means of the Internet server of the publisher. 'Spacecraft Navigation and Guidance' is an invaluable aid for all those working within astronautics, aeronautics, and control engineering in general.

Use Of Orbit To Orbit Shuttles For Hyperbolic Rendezvous With Returning Planetary Spacecraft

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Author : David R. Brooks
language : en
Publisher:
Release Date : 1971

Use Of Orbit To Orbit Shuttles For Hyperbolic Rendezvous With Returning Planetary Spacecraft written by David R. Brooks and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1971 with Nuclear propulsion categories.

An Earth-return mode for interplanetary spacecraft via hyperbolic rendezvous is described. In this mode an orbit-to-orbit shuttle leaves a circular Earth orbit, performs a rendezvous with a returning interplanetary spacecraft as it approaches Earth on a hyperbolic trajectory, docks and performs desired transfers, and deboosts back into a circular Earth orbit while the spacecraft continues on its hyperbolic path. Two basic flight modes are proposed, and the equations for analyzing the maneuvers are derived. The initial mass in Earth orbit required fora rendezvous system utilizing chemical or nuclear propulsion compares favorably with the initial masses in Earth orbit chargeable to transport of some conventional Earth-return systems to a target planet and back. In addition, the maneuver has considerable merit as a backup and rescue system. For typical missions, orbit-to-orbit shuttles having initial masses in Earth orbit of up to 500 000 kg are required.

Semi Analytical Solutions For Proximity Operations In The Circular Restricted Three Body Problem

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Author : Davide Conte
language : en
Publisher:
Release Date : 2019

Semi Analytical Solutions For Proximity Operations In The Circular Restricted Three Body Problem written by Davide Conte and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2019 with categories.

The research presented in this dissertation aims at characterizing the relative motion between spacecraft in periodic orbits in the circular restricted three-body problem. Proximity operations maneuvers, such as rendezvous and station-keeping, are approximated using a semi-analytical approach, i.e. by combining the analytical approximation of the nominal periodic orbit of the targeted spacecraft or targeted orbital location with simplified equations of motion that are derived by assuming that the chasing spacecraft and target (or targeted location) are always "close" to each other. The presented method is compared to the "exact" solutions obtained by numerically integrating the non-linear equations of motion of the circular restricted three-body problem. Orbit propagation examples, i.e. control-free trajectories, are shown along with proximity operation maneuvers for which delta-v's are computed. Suitable initial conditions for proximity operations are also computed based on known orbital transfers to specific orbits of interest, including halo orbits and distant retrograde orbits in the Earth-Moon and Mars-Phobos systems. Propellant-optimal results are found and compared to nearby local minima for a given set of time constraints in order to find a maneuver that allows for flexibility regarding departure and arrival time along with contingency plans. This approximation is validated against the use of the more computationally expensive full nonlinear equations of motion of the three-body problem and the "area of applicability" of this method is defined based on a metric that takes into account the initial conditions used when initiating proximity operations and the time-of-flight required to accomplish such maneuvers. Sample results for the Earth-Moon and Mars-Phobos systems are presented for cis-lunar and cis-Martian orbits of interest. The implementation of this method in pre-phase A mission design is also demonstrated in a sample end-to-end Earth-to-Mars mission. The method presented in this dissertation is shown to accurately describe the control-free relative motion between spacecraft in addition to being able to predict the necessary delta-v maneuvers for various proximity operations. Additionally, this method requires less computational time than full numerical methods while being able to assess its accuracy and the validity of the results obtained. Limitations of this method are imposed on the initial relative position between spacecraft as a function of the time required to accomplish proximity operation maneuvers.

Orbital Maneuvering Vehicle Propulsion Requirement For Nearly Coplanar Nearly Circular Orbit Rendezvous Mission

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Author : Conrad George Jackson
language : en
Publisher:
Release Date : 1984

Orbital Maneuvering Vehicle Propulsion Requirement For Nearly Coplanar Nearly Circular Orbit Rendezvous Mission written by Conrad George Jackson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with Orbital rendezvous (Space flight) categories.

Minimum Thrust For Correcting Keplerian Orbits With Application To Interplanetary Guidance

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Author : Frederick W. Boltz
language : en
Publisher:
Release Date : 1968

Minimum Thrust For Correcting Keplerian Orbits With Application To Interplanetary Guidance written by Frederick W. Boltz and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1968 with Orbits categories.

Multiple Gravity Assist Interplanetary Trajectories

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Author : A V Labunsky
language : en
Publisher: CRC Press
Release Date : 1998-11-26

Multiple Gravity Assist Interplanetary Trajectories written by A V Labunsky and has been published by CRC Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998-11-26 with Science categories.

Reflecting the results of twenty years; experience in the field of multipurpose flights, this monograph includes the complex routes of the trajectories of a number of bodies (e.g., space vehicles, comets) in the solar system. A general methodological approach to the research of flight schemes and the choice of optimal performances is developed. Additionally, a number of interconnected methods and algorithms used at sequential stages of such development are introduced, which allow the selection of a rational multipurpose route for a space vehicle, the design of multipurpose orbits, the determination of optimal space vehicle design, and ballistic performances for carrying out the routes chosen. Other topics include the practical results obtained from using these methods, navigation problems, near-to-planet orbits, and an overview of proven and new flight schemes.

Spacecraft Manoeuvring In The Vicinity Of A Near Circular Orbit

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