This paper presents the topic of using solid rocket propulsion for de-orbiting spacecraft,in order to fulfil space debris mitigation requirements.The benefits and disadvantages of using such means are discussed.A dedi...This paper presents the topic of using solid rocket propulsion for de-orbiting spacecraft,in order to fulfil space debris mitigation requirements.The benefits and disadvantages of using such means are discussed.A dedicated system can be implemented in the satellite design phase and shall be a key subsystem of platforms inserted into orbit.Uncontrolled,semi-controlled and controlled de-orbit can be completed using solid rocket motors.Their impact on the space debris environment is discussed.Specific requirements for dedicated propellants and systems are provided.While the majority of presently developed rocket systems worldwide require high burn rates,several applications,including de-orbiting,benefit from solid propellants with decreased regression rates.This allows limiting spacecraft accelerations and loads during de-orbit manoeuvres.Moreover,the requirement of minimising solid particle generation is presented.Heritage technology from the Mercury and Gemini human spaceflight programmes,where de-orbit motors were used,is shown.Historical Soviet,American and Chinese film-return-capsule solid propellant retrorockets,enabling deorbit,are also presented.A detailed survey of current work worldwide on end-of-life disposal using solid propulsion is included.Challenges of developing dedicated systems are discussed.Finally,an outlook on solid rocket motor utilisation for space debris mitigation is provided.展开更多
In recent years,defunct satellites mitigation in the geostationary orbit(GEO) has become a hot issue in the space field.How to transfer defunct geostationary satellites to the graveyard orbit safely,economically and e...In recent years,defunct satellites mitigation in the geostationary orbit(GEO) has become a hot issue in the space field.How to transfer defunct geostationary satellites to the graveyard orbit safely,economically and efficiently presents new challenges to spacecraft dynamics and control.This paper conducts an in-depth investigation on tether-tugging de-orbit issues of defunct geostationary satellites.Firstly,a four-phase tether-tugging de-orbit scheme including acceleration,equilibrium,rotation and return is proposed.This scheme takes into consideration how to avoid the risks of tether ripping,tug-target collision,and tether twist,and how to achieve the mission objective of fuel saving.Secondly,the dynamics model of the tether combination system is established based on Lagrange equation,and the four phases of tether-tugging de-orbit scheme are simulated respectively.Simulation results indicate that the scheme is theoretically feasible and satisfies the design objectives of safety,economy and efficiency,providing a technical approach for engineering application.展开更多
基金financed by the Polish National Agency for Academic Exchange(No.PPI/APM/2018/1/00032/U/001)Work presented from projects of ESA includes work done during preliminary phases of ASPro(Pre-Qualification of Aluminium-Free Solid Propellant)and SPRODEM(Solid Propellant De-orbit Motor Engineering Model Development)projects funded within the General Support Technology Programme(GSTP)。
文摘This paper presents the topic of using solid rocket propulsion for de-orbiting spacecraft,in order to fulfil space debris mitigation requirements.The benefits and disadvantages of using such means are discussed.A dedicated system can be implemented in the satellite design phase and shall be a key subsystem of platforms inserted into orbit.Uncontrolled,semi-controlled and controlled de-orbit can be completed using solid rocket motors.Their impact on the space debris environment is discussed.Specific requirements for dedicated propellants and systems are provided.While the majority of presently developed rocket systems worldwide require high burn rates,several applications,including de-orbiting,benefit from solid propellants with decreased regression rates.This allows limiting spacecraft accelerations and loads during de-orbit manoeuvres.Moreover,the requirement of minimising solid particle generation is presented.Heritage technology from the Mercury and Gemini human spaceflight programmes,where de-orbit motors were used,is shown.Historical Soviet,American and Chinese film-return-capsule solid propellant retrorockets,enabling deorbit,are also presented.A detailed survey of current work worldwide on end-of-life disposal using solid propulsion is included.Challenges of developing dedicated systems are discussed.Finally,an outlook on solid rocket motor utilisation for space debris mitigation is provided.
基金supported by the National Hi-Tech Research and Development Program of China ("863" Project) (Grant No. 2011AA7044026)
文摘In recent years,defunct satellites mitigation in the geostationary orbit(GEO) has become a hot issue in the space field.How to transfer defunct geostationary satellites to the graveyard orbit safely,economically and efficiently presents new challenges to spacecraft dynamics and control.This paper conducts an in-depth investigation on tether-tugging de-orbit issues of defunct geostationary satellites.Firstly,a four-phase tether-tugging de-orbit scheme including acceleration,equilibrium,rotation and return is proposed.This scheme takes into consideration how to avoid the risks of tether ripping,tug-target collision,and tether twist,and how to achieve the mission objective of fuel saving.Secondly,the dynamics model of the tether combination system is established based on Lagrange equation,and the four phases of tether-tugging de-orbit scheme are simulated respectively.Simulation results indicate that the scheme is theoretically feasible and satisfies the design objectives of safety,economy and efficiency,providing a technical approach for engineering application.
