Launch Activity and Orbital Debris Mitigation Second Quarter 2002 Quarterly Launch Report
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Itu Recommendation Itu-R S.1003.2
SPACE DEBRIS MITIGATION STANDARDS ITU RECOMMENDATION ITU‐R S.1003.2 International mechanism: International Telecommunications Union (ITU) Recommendation ITU‐R S.1003.2 (12/2010) Environmental protection of the geostationary‐satellite orbit Description: ITU‐R S.1003.2 provides guidance about disposal orbits for satellites in the geostationary‐ satellite orbit (GSO). In this orbit, there is an increase in debris due to fragments resulting from increased numbers of satellites and their associated launches. Given the current limitations (primarily specific impulse) of space propulsion systems, it is impractical to retrieve objects from GSO altitudes or to return them to Earth at the end of their operational life. A protected region must therefore be established above, below and around the GSO which defines the nominal orbital regime within which operational satellites will reside and manoeuvre. To avoid an accumulation of non‐functional objects in this region, and the associated increase in population density and potential collision risk that this would lead to, satellites should be manoeuvred out of this region at the end of their operational life. In order to ensure that these objects do not present a collision hazard to satellites being injected into GSO, they should be manoeuvred to altitudes higher than the GSO region, rather than lower. The recommendations embodied in ITU‐R S.1003.2 are: – Recommendation 1: As little debris as possible should be released into the GSO region during the placement of a satellite in orbit. – Recommendation 2: Every reasonable effort should be made to shorten the lifetime of debris in elliptical transfer orbits with the apogees at or near GSO altitude. -
Recommendation Itu-R S.1003-2*
Recommendation ITU-R S.1003-2 (12/2010) Environmental protection of the geostationary-satellite orbit S Series Fixed-satellite service ii Rec. ITU-R S.1003-2 Foreword The role of the Radiocommunication Sector is to ensure the rational, equitable, efficient and economical use of the radio-frequency spectrum by all radiocommunication services, including satellite services, and carry out studies without limit of frequency range on the basis of which Recommendations are adopted. The regulatory and policy functions of the Radiocommunication Sector are performed by World and Regional Radiocommunication Conferences and Radiocommunication Assemblies supported by Study Groups. Policy on Intellectual Property Right (IPR) ITU-R policy on IPR is described in the Common Patent Policy for ITU-T/ITU-R/ISO/IEC referenced in Annex 1 of Resolution ITU-R 1. Forms to be used for the submission of patent statements and licensing declarations by patent holders are available from http://www.itu.int/ITU-R/go/patents/en where the Guidelines for Implementation of the Common Patent Policy for ITU-T/ITU-R/ISO/IEC and the ITU-R patent information database can also be found. Series of ITU-R Recommendations (Also available online at http://www.itu.int/publ/R-REC/en) Series Title BO Satellite delivery BR Recording for production, archival and play-out; film for television BS Broadcasting service (sound) BT Broadcasting service (television) F Fixed service M Mobile, radiodetermination, amateur and related satellite services P Radiowave propagation RA Radio astronomy RS Remote sensing systems S Fixed-satellite service SA Space applications and meteorology SF Frequency sharing and coordination between fixed-satellite and fixed service systems SM Spectrum management SNG Satellite news gathering TF Time signals and frequency standards emissions V Vocabulary and related subjects Note: This ITU-R Recommendation was approved in English under the procedure detailed in Resolution ITU-R 1. -
Soft Passivation of Spacecraft Pressure Vessels
First Int'l. Orbital Debris Conf. (2019) 6042.pdf Soft Passivation of Spacecraft Pressure Vessels William P. Schonberg Civil Engineering Department, Missouri University of Science & Technology, Rolla, MO 65409 [email protected] ABSTRACT Most spacecraft have at least one pressurized vessel on board. In addition to a hole, it is possible that a pressure vessel may experience catastrophic failure as a result of a hypervelocity impact, such as by a micrometeoroid or space debris particle. If a tank rupture were to occur on-orbit following a micrometeoroid or orbital debris particle impact, not only could it lead to loss of life, but it would also generate a tremendous amount of debris that could compromise future space assets working in similar orbits. As a result, NASA and other space agencies have put in place design requirements to prevent additional sizable debris from being created in the event of a catastrophic pressure vessel failure. These requirements typically state that stored energy devices are to be passivated at the end of a spacecraft’s mission or useful life. Since many spacecraft designs are not be able to comply with some aspects of those requirements, an alternative, so-called “soft passivation” option was added. This paper provides a summary of a project performed with the intent of providing guidelines and considerations that can be used by satellite programs to help satisfy passivation requirements using a “soft passivation” approach, that is, when not able to perform complete hard passivation. 1 INTRODUCTION Most spacecraft have at least one pressurized vessel on board. For robotic spacecraft, it is usually a liquid propellant tank. -
Rendezvous and Proximity Operations: Friend Or Foe?
Promoting Cooperative Solutions for Space Sustainability Rendezvous and Proximity Operations: Friend or Foe? Victoria Samson, Washington Office Director Secure World Foundation “Supporting Diplomacy: Clearing the Path for Dialogue” UNIDIR Geneva, Switzerland May 28-29, 2019 ©2019 Secure World Foundation. Used with Permission www.swfound.org UNIDIR May 29 ,2019 @SWFoundation Development of OOS and RPO Capabilities Promoting Cooperative Solutions for Space Sustainability • On-orbit servicing (OOS) and rendezvous and proximity operations (RPO) are key to enabling future of on-orbit activities • Benefits and challenges – Greatly increase the viability of and benefits from space activities – Raises a number of diplomatic, legal, safety, operational, and policy challenges that need to be tackled • OOS and RPO are not new, and are already international – 50+ years of experience in doing it with human spaceflight, but increasingly shifting to robotic/autonomous – Multiple countries/companies developing and testing RPO capabilities • How to develop norms and standards to enable cooperative OOS/RPO and mitigate challenges? UNIDIR May 29, 2019 2 www.swfound.org @SWFoundation RPO Activities and Counterspace Objectives Promoting Cooperative Solutions for Space Sustainability • Global Counterspace Capabilities: An Open Source Assessment, April 2019 – www.swfound.org/counterspace – Compiles and assesses publicly available information on the counterspace capabilities being developed by multiple countries across five categories: direct-ascent, co-orbital, -
The Disposal of Spacecraft and Launch Vehicle Stages in Low Earth Orbit
THE DISPOSAL OF SPACECRAFT AND LAUNCH VEHICLE STAGES IN LOW EARTH ORBIT Nicholas L. Johnson NASA Johnson Space Center, Houston, TX, USA, [email protected] ABSTRACT restricting the orbital lifetimes of spacecraft and launch vehicle stages residing in or passing through LEO after Spacecraft and launch vehicle stages abandoned in mission termination. The primary purpose of this action Earth orbit have historically been a primary source of is to enhance space safety by significantly constraining debris from accidental explosions. In the future, such the potential of future accidental collisions, which in satellites will become the principal cause of orbital turn could result in the creation of large numbers of new debris via inadvertent collisions. To curtail both the orbital debris. near-term and far-term risks posed by derelict spacecraft and launch vehicle stages to operational space systems, Not surprisingly, the majority of mass in Earth orbit numerous national and international orbital debris today (> 5000 metric tons) resides in non-operational mitigation guidelines specifically recommend actions spacecraft and launch vehicle stages. This mass also which could prevent or limit such future debris represents the largest segment of cross-sectional area, generation. Although considerable progress has been i.e., collision hazard, for future debris generation. In the made in implementing these recommendations, some 1980’s, early National Aeronautics and Space changes to existing vehicle designs can be difficult. Administration (NASA) projections of the potential Moreover, the nature of some missions also can present long-term growth of the Earth’s satellite population technological and budgetary challenges to be compliant identified the increasing amount of mass in Earth orbit with widely accepted orbital debris mitigation measures. -
Legal and Regulatory Considerations of Small Satellite Projects
Legal and Regulatory Considerations of Small Satellite Projects Christopher D. Johnson, Secure World Foundation 1. Overview of the Legal and Regulatory Framework 2. International Space Law 3. National Space Law 4. Contractual and Operational Concerns 5. End-of-Life and Space Debris Mitigation 6. International Frequency Allocation and Coordination 7. National Frequency Allocation and Coordination 8. Conclusion Engineering constraints and technological hurdles are not the only obstacles to the successful completion of a small satellite project. You must also understand the legal and regulatory responsibilities and requirements from the outset. Consider a situation where your small satellite is integrated as a secondary payload and is already on the launch pad. Your country’s foreign ministry suddenly contacts you and orders you to halt the launch, as the government is unwilling to accept any potential international governmental responsibility for your operations. It turns out that the government lacks national legislation regulating space activities, but has ratified a number of international treaties related to outer space. Additionally, its radio frequency administrator has not granted you a radio license or notified other nations of your intended use of certain frequencies, and radio interference is likely. Despite being ready to launch, your satellite project will likely be halted until you clarify and resolve these issues. 1 This chapter outlines the legal and regulatory issues impacting small satellite missions, and offers a process to handle them as they arise during the different phases of your project. Section 5.1 is an overview of the entire legal and regulatory landscape, introducing laws from a variety of sources—including international space law, national legislation, contracts between partners, insurance policies, and the international and national regimes for radio frequency coordination. -
Advantages of Small Satellite Carrier Concepts for LEO/GEO Inspection and Debris Removal Missions
Utah State University DigitalCommons@USU Space Dynamics Lab Publications Space Dynamics Lab 1-1-2014 Advantages of Small Satellite Carrier Concepts for LEO/GEO Inspection and Debris Removal Missions David K. Geller Utah State University Randy Christensen Adam Shelley Follow this and additional works at: https://digitalcommons.usu.edu/sdl_pubs Recommended Citation Geller, David K.; Christensen, Randy; and Shelley, Adam, "Advantages of Small Satellite Carrier Concepts for LEO/GEO Inspection and Debris Removal Missions" (2014). Space Dynamics Lab Publications. Paper 52. https://digitalcommons.usu.edu/sdl_pubs/52 This Article is brought to you for free and open access by the Space Dynamics Lab at DigitalCommons@USU. It has been accepted for inclusion in Space Dynamics Lab Publications by an authorized administrator of DigitalCommons@USU. For more information, please contact [email protected]. Geller, David K., Derick Crocket, Randy Christensen, and Adam Shelley. 2014. “Advantages of Small Satellite Carrier Concepts for LEO/GEO Inspection and Debris Removal Missions.” International Journal of Space Science and Engineering 2 (2): 115–34. http://www.sffmt2013.org/PPAbstract/4028p.pdf. Int. J. Space Science and Engineering, Vol. 2, No. 2, 2014 115 Advantages of small satellite carrier concepts for LEO/GEO inspection and debris removal missions David K. Geller* and Derick Crocket Utah State University, 4130 Old Main, Logan, Utah 84322, USA Fax: 435-797-2952 E-mail: [email protected] E-mail: [email protected] *Corresponding author Randy Christensen and Adam Shelley Space Dynamics Laboratory, 1695 N. Research Park Way, North Logan, Utah, 84341, USA Fax: 435-713-3013 E-mail: [email protected] E-mail: [email protected] Abstract: This work focuses on two important types of space missions: close-in satellite inspection of LEO/GEO high-value assets to detect and/or resolve anomalies, and LEO/GEO debris disposal missions to reduce space hazards. -
Working Document on Developing an ITU-R Small Satellite HB WP 4A
Radiocommunication Study Groups Source: Document 4A/TEMP/47 Annex 13 to Document 4A/246-E Subject: Small Satellite Handbook 9 March 2021 English only Annex 13 to Working Party 4A Chairman’s Report WORKING DOCUMENT ON DEVELOPING AN ITU-R SMALL SATELLITE HANDBOOK Based on contributions 4A/183 and 4A/239, Working Party (WP) 4A have prepared this draft revision to Annex 14 of the WP 4A Chairman’s Report (Document 4A/155) for the Small Satellite Handbook, following offline consultation as directed by the first Plenary session of WP4A. Annex 14 of document 155 contained only the skeleton of the handbook and all content to the various sections has been added from contributions 4A/183 and 4A/239 to this meeting. This text is shown as clean text in the attached document. Text shown with revision marks indicates changes during the informal consultations during the WP 4A meeting. The attached updated document is proposed to remain as a working document towards Small Satellite Handbook. More contributions to further progress the work on this handbook is encouraged for the future meetings of WP 4A. Editorially, in further work, use of recognized ITU terminology as defined in the ITU-R literature (e.g., Radio Regulations, ITU-R V-series Recommendations and/or Rec. ITU-R S.673) should be ensured to be used throughout this handbook. Considering that this handbook is still at an early stage of development, it may be premature to consider liaison statement to other working parties including reply liaison statement to WP 5A in response to their liaison statement 4A/42 and to WP 7B in response to their liaison statement 4A/69. -
End-Of-Life Disposal Concepts for Libration Point Orbit and Highly
Author's Accepted Manuscript End-of-life disposal concepts for libration point Orbit and highly elliptical orbit missions Camilla Colombo, Elisa Maria Alessi, Willem van der Weg, Stefania Soldini, Francesca Leti- zia, Massimo Vetrisano, Massimiliano Vasile, Alessandro Rossi, Markus Landgraf www.elsevier.com/locate/actaastro PII: S0094-5765(14)00434-2 DOI: http://dx.doi.org/10.1016/j.actaastro.2014.11.002 Reference: AA5254 To appear in: Acta Astronautica Cite this article as: Camilla Colombo, Elisa Maria Alessi, Willem van der Weg, Stefania Soldini, Francesca Letizia, Massimo Vetrisano, Massimiliano Vasile, Alessandro Rossi, Markus Landgraf, End-of-life disposal concepts for libration point Orbit and highly elliptical orbit missions, Acta Astronautica, http://dx.doi. org/10.1016/j.actaastro.2014.11.002 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting galley proof before it is published in its final citable form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. Original article presented at IAA-AAS-DyCoSS2. Updated version submitted to Acta Astronautica END-OF-LIFE DISPOSAL CONCEPTS FOR LIBRATION POINT ORBIT AND HIGHLY ELLIPTICAL ORBIT MISSIONS Camilla Colombo1, Elisa Maria Alessi2, Willem van der Weg3, Stefania Soldini4, Francesca Letizia5, Massimo Vetrisano6, Massimiliano Vasile7, Alessandro Rossi8, Markus Landgraf9 Libration Point Orbits (LPOs) and Highly Elliptical Orbits (HEOs) are often se- lected for astrophysics and solar terrestrial missions. -
IADC Space Debris Mitigation Guidelines (Rev. 1)
IADC-02-01 Revision 1 September 2007 INTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE IADC Action Item number 22.4 IADC Space Debris Mitigation Guidelines Issued by Steering Group and Working Group 4 Table of Contents 1 Scope ..............................................................................................................................................................5 2 Application......................................................................................................................................................5 3 Terms and definitions...................................................................................................................................5 3.1 Space Debris ..................................................................................................................................................5 3.2 Spacecraft, Launch Vehicles, and Orbital Stages ......................................................................................5 3.3 Orbits and Protected Regions ......................................................................................................................6 3.4 Mitigation Measures and Related Terms ....................................................................................................6 3.5 Operational Phases ...................................................................................................................................7 4 General Guidance ..........................................................................................................................................7 -
ESA Space Debris Mitigation Compliance Verification Guidelines
ESA UNCLASSIFIED – For Official Use estec European Space Research and Technology Centre Keplerlaan 1 2201 AZ Noordwijk The Netherlands T +31 (0)71 565 6565 F +31 (0)71 565 6040 www.esa.int ESA Space Debris Mitigation Compliance Verification Guidelines Prepared by ESA Space Debris Mitigation WG Reference ESSB-HB-U-002 Issue 1 Revision 0 Date of Issue 19 February 2015 Status Approved Document Type HB Distribution ESA ESA UNCLASSIFIED – For Official Use Title ESA Space Debris Mitigation Compliance Verification Guidelines Issue 1 Revision 0 Author ESA Space Debris Mitigation WG Date 19 February 2015 Approved by ESSB Date Reason for change Issue Revision Date First issue 1 19 February 2015 Issue 1 Revision 0 Reason for change Date Pages Paragraph(s) Page 2/95 ESSB-HB-U-002 Date 19 February 2015 Issue 1 Rev 0 ESA UNCLASSIFIED – For Official Use Table of contents 1 Scope .................................................................................................................... 6 2 References ............................................................................................................ 7 3 Terms, definitions and abbreviated terms ......................................................... 8 3.1 Terms from other standards ................................................................................. 8 3.2 Terms specific to the this document .................................................................... 9 3.3 Abbreviated terms ................................................................................................11 -
Understanding Long-Term Orbital Debris Population Dynamics
First Int'l. Orbital Debris Conf. (2019) 6097.pdf Understanding long-term orbital debris population dynamics Hugh G. Lewis University of Southampton, Astronautics Research Group, Faculty of Engineering and Physical Sciences, Boldrewood Innovation Campus 176/2041, Southampton SO16 7QF, UK, [email protected] ABSTRACT Linear growth of the orbital debris population is observed in the results of many evolutionary models when they are used to simulate the effects of the widespread adoption of the Inter-Agency Space Debris Coordination Committee (IADC) debris mitigation guidelines. Such linear growth seemingly confirms the belief that adopting these debris mitigation guidelines will have substantial and positive benefits on the orbital debris population. However, this outcome is not expected from analyses of simple systems models. Either the systems model is too simplistic, or the linear growth of the debris population is actually the beginnings of exponential growth, which is difficult to discern over the typical analysis period. To resolve this ambiguity, the Debris Analysis and Monitoring Architecture to the Geosynchronous Environment (DAMAGE) model was used to perform ultra-long projections of the future debris population ≥ 10 cm in Low Earth Orbit (LEO) under highly optimistic debris mitigation conditions. The DAMAGE results showed that the linear growth rate observed for the first 200 years of the projection period was transient and the growth was exponential, even with the ongoing and widespread adoption of debris mitigation measures. The population growth was driven by the accumulation of orbital debris at altitudes between 1200 km and 1500 km, even though simulated launch activity to that region was limited.