{"product_id":"guidance-and-control-of-a-spacecraft-to-rendevous-and-dock-with-a-non-cooperative-target-von-anantha-sayanam-komanduri","title":"Guidance and Control of a Spacecraft to Rendevous and Dock with a Non-cooperative Target","description":"\u003cp\u003eNon-cooperative spacecrafts are those current or future assets in orbit which have\u003c\/p\u003e\u003cp\u003elost their control authority in one or more degrees of freedom and cannot convey any\u003c\/p\u003e\u003cp\u003einformation concerning their position, attitude or rates to facilitate Rendezvous and\u003c\/p\u003e\u003cp\u003eDocking\/Berthing (RVD\/B) process. A growing ¿eld of study in space research is to\u003c\/p\u003e\u003cp\u003edevelop On-Orbit Servicing (OOS) technology capable of dealing with these space-\u003c\/p\u003e\u003cp\u003ecrafts, called targets, which are designed without any intention to be serviced.  To\u003c\/p\u003e\u003cp\u003erender services such as repair, refuel or removal of the target from orbit, the chaser\u003c\/p\u003e\u003cp\u003espacecraft should exhibit sophisticated RVD\/B technology for formation ¿y and ¿nal\u003c\/p\u003e\u003cp\u003estage docking\/berthing operations of the mission.\u003c\/p\u003e\u003cp\u003eAssuming that the terminal capture operations of the target are to be performed\u003c\/p\u003e\u003cp\u003eby a suitable manipulator system on-board chaser,  this study relies upon proven\u003c\/p\u003e\u003cp\u003etechnology and outlines guidance and control methodologies to achieve rendezvous\u003c\/p\u003e\u003cp\u003eduring proximity phases. The entry gate of chaser after phasing can be de¿ned at a\u003c\/p\u003e\u003cp\u003edistance of about 5 km in ± V-bar direction from the target in its orbit. To account\u003c\/p\u003e\u003cp\u003efor errors in modeling, navigation or actuation, proximity range operations from the\u003c\/p\u003e\u003cp\u003eentry gate are decomposed into three di¿erent subphases as far range, inspection or\u003c\/p\u003e\u003cp\u003e¿y around and closer approach.\u003c\/p\u003e\u003cp\u003eFrom the entry gate and along the path of the chaser two hold points are de¿ned:\u003c\/p\u003e\u003cp\u003e¿rst to initiate an inspection and the second, which is close to the safe zone de¿ned\u003c\/p\u003e\u003cp\u003earound the target, to initiate a capture. The chaser is assumed to perform a station\u003c\/p\u003e\u003cp\u003ekeeping maneuver at the second hold point until initial conditions for the capture are\u003c\/p\u003e\u003cp\u003emet.  Possible scenarios pertaining to the behavior of the target in a circular orbit\u003c\/p\u003e\u003cp\u003eare considered and guidance schemes for di¿erent subphases are presented using a\u003c\/p\u003e\u003cp\u003ecombination of Hill-Clohessy-Willtshire (HCW) solution, elliptical ¿y around, glides-\u003c\/p\u003e\u003cp\u003elope algorithm etc. Relative controllers both for position and attitude of the chaser\u003c\/p\u003e\u003cp\u003eare also presented.  A Linear Quadratic (LQ) controller for relative position and a\u003c\/p\u003e\u003cp\u003eProportional Integral Derivative (PID) controller for relative attitude with angular\u003c\/p\u003e\u003cp\u003evelocity constraints are chosen to track down the error to achieve rendezvous and\u003c\/p\u003e\u003cp\u003eattitude synchronization with the non-cooperative target.  A comparative analysis\u003c\/p\u003e\u003cp\u003ebetween di¿erent guidance trajectories for important parameters such as time, fuel\u003c\/p\u003e\u003cp\u003eusage, minimum absolute distance and the maximum radial distance from the target\u003c\/p\u003e\u003cp\u003eis presented.  Veri¿cation of the proposed guidance and control methods is done by\u003c\/p\u003e\u003cp\u003eapplying them to two di¿erent case studies: the ¿rst study incorporating a stabilized\u003c\/p\u003e\u003cp\u003etarget in Geostationary Earth Orbit (GEO) and the second, with a spinning target\u003c\/p\u003e\u003cp\u003ein Low Earth Orbit (LEO).\u003c\/p\u003e\u003cp\u003eThe methods presented here are general and provide a simulator to the chaser to\u003c\/p\u003e\u003cp\u003eperform rendezvous analysis with non-cooperative targets.  To achieve RVD\/B, the\u003c\/p\u003e\u003cp\u003estudy proposes a careful combination of guidance solutions for di¿erent phases of\u003c\/p\u003e\u003cp\u003eproximity operations, and for di¿erent scenariös of the target encountered by the\u003c\/p\u003e\u003cp\u003echaser.\u003c\/p\u003e\u003cdiv class=\"aw-variant-hidden-subtitle-div\" id=\"aw-variant-subtitle-9783869559452\"\u003e\u003ch3\u003e\u003c\/h3\u003e\u003c\/div\u003e","brand":"Libri","offers":[{"title":"Softcover - 9783869559452","offer_id":39454413291613,"sku":"9783869559452","price":36.7,"currency_code":"EUR","in_stock":true}],"thumbnail_url":"\/\/cdn.shopify.com\/s\/files\/1\/0940\/0622\/files\/96d6fb00-9d69-495f-a743-9a9319fb90fb.jpg?v=1776144966","url":"https:\/\/shop.autorenwelt.de\/products\/guidance-and-control-of-a-spacecraft-to-rendevous-and-dock-with-a-non-cooperative-target-von-anantha-sayanam-komanduri","provider":"Autorenwelt Shop","version":"1.0","type":"link"}