Position Paper Space Debris Mitigation
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Design Characteristics of Iran's Ballistic and Cruise Missiles
Design Characteristics of Iran’s Ballistic and Cruise Missiles Last update: January 2013 Missile Nato or Type/ Length Diameter Payload Range (km) Accuracy ‐ Propellant Guidance Other Name System (m) (m) (kg)/warhead CEP (m) /Stages Artillery* Hasib/Fajr‐11* Rocket artillery (O) 0.83 0.107 6; HE 8.5 ‐ Solid Spin stabilized Falaq‐12* Rocket artillery (O) 1.29 0.244 50; HE 10 Solid Spin stabilized Falaq‐23* Rocket artillery (O) 1.82 0.333 120; HE 11 Solid Spin stabilized Arash‐14* Rocket artillery (O) 2.8 0.122 18.3; HE 21.5 Solid Spin stabilized Arash‐25* Rocket artillery (O) 3.2 0.122 18.3; HE 30 Solid Spin stabilized Arash‐36* Rocket artillery (O) 2 0.122 18.3; HE 18 Solid Spin stabilized Shahin‐17* Rocket artillery (O) 2.9 0.33 190; HE 13 Solid Spin stabilized Shahin‐28* Rocket artillery (O) 3.9 0.33 190; HE 20 Solid Spin stabilized Oghab9* Rocket artillery (O) 4.82 0.233 70; HE 40 Solid Spin stabilized Fajr‐310* Rocket artillery (O) 5.2 0.24 45; HE 45 Solid Spin stabilized Fajr‐511* Rocket artillery (O) 6.6 0.33 90; HE 75 Solid Spin stabilized Falaq‐112* Rocket artillery (O) 1.38 0.24 50; HE 10 Solid Spin stabilized Falaq‐213* Rocket artillery (O) 1.8 0.333 60; HE 11 Solid Spin stabilized Nazeat‐614* Rocket artillery (O) 6.3 0.355 150; HE 100 Solid Spin stabilized Nazeat15* Rocket artillery (O) 5.9 0.355 150; HE 120 Solid Spin stabilized Zelzal‐116* Iran‐130 Rocket artillery (O) 8.3 0.61 500‐600; HE 100‐125 Solid Spin stabilized Zelzal‐1A17* Mushak‐120 Rocket artillery (O) 8.3 0.61 500‐600; HE 160 Solid Spin stabilized Nazeat‐1018* Mushak‐160 Rocket artillery (O) 8.3 0.45 250; HE 150 Solid Spin stabilized Related content is available on the website for the Nuclear Threat Initiative, www.nti.org. -
Compendium of Space Debris Mitigation Standards Adopted by States and International Organizations”
COMPENDIUM SPACE DEBRIS MITIGATION STANDARDS ADOPTED BY STATES AND INTERNATIONAL ORGANIZATIONS 17 JUNE 2021 SPACE DEBRIS MITIGATION STANDARDS TABLE OF CONTENTS Introduction ............................................................................................................................................................... 4 Part 1. National Mechanisms Algeria ........................................................................................................................................................................ 5 Argentina .................................................................................................................................................................... 7 Australia (Updated on 17 January 2020) .................................................................................................................... 8 Austria (Updated on 21 March 2016) ...................................................................................................................... 10 Azerbaijan (Added on 6 February 2019) .................................................................................................................. 13 Belgium .................................................................................................................................................................... 14 Canada...................................................................................................................................................................... 16 Chile......................................................................................................................................................................... -
Orbiting Debris: a Space Environmental Problem (Part 4 Of
Orbiting Debris: A Since Environmential Problem ● 3 Table 2--of Hazardous Interference by environment. Yet, orbital debris is part of a Orbital Debris larger problem of pollution in space that in- cludes radio-frequency interference and inter- 1. Loss or damage to space assets through collision; ference to scientific observations in all parts of 2. Accidental re-entry of space hardware; the spectrum. For example, emissions at ra- 3. Contamination by nuclear material of manned or unmanned spacecraft, both in space and on Earth; dio frequencies often interfere with radio as- 4. Interference with astronomical observations, both from the tronomy observations. For several years, ground and in space; gamma-ray astronomy data have been cor- 5. Interference with scientific and military experiments in space; rupted by Soviet intelligence satellites that 14 6. Potential military use. are powered by unshielded nuclear reactors. The indirect emissions from these satellites SOURCE: Space Debris, European Space Agency, and Office of Technology As- sessment. spread along the Earth’s magnetic field and are virtually impossible for other satellites to Earth. The largest have attracted worldwide escape. The Japanese Ginga satellite, attention. 10 Although the risk to individuals is launched in 1987 to study gamma-ray extremely small, the probability of striking bursters, has been triggered so often by the populated areas still finite.11 For example: 1) Soviet reactors that over 40 percent of its available observing time has been spent trans- the U.S.S.R. Kosmos 954, which contained a 15 nuclear power source,12 reentered the atmos- mitting unintelligible “data.” All of these phere over northwest Canada in 1978, scatter- problem areas will require attention and posi- ing debris over an area the size of Austria; 2) a tive steps to guarantee access to space by all Japanese ship was hit in 1969 by pieces of countries in the future. -
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE. -
The Washington Institute for Near East Policy August
THE WASHINGTON INSTITUTE FOR NEAR EAST POLICY n AUGUST 2020 n PN84 PHOTO CREDIT: REUTERS © 2020 THE WASHINGTON INSTITUTE FOR NEAR EAST POLICY. ALL RIGHTS RESERVED. FARZIN NADIMI n April 22, 2020, Iran’s Islamic Revolutionary Guard Corps Aerospace Force (IRGC-ASF) Olaunched its first-ever satellite, the Nour-1, into orbit. The launch, conducted from a desert platform near Shahrud, about 210 miles northeast of Tehran, employed Iran’s new Qased (“messenger”) space- launch vehicle (SLV). In broad terms, the launch showed the risks of lifting arms restrictions on Iran, a pursuit in which the Islamic Republic enjoys support from potential arms-trade partners Russia and China. Practically, lifting the embargo could facilitate Iran’s unhindered access to dual-use materials and other components used to produce small satellites with military or even terrorist applications. Beyond this, the IRGC’s emerging military space program proves its ambition to field larger solid-propellant missiles. Britain, France, and Germany—the EU-3 signatories of the Joint Comprehensive Plan of Action, as the 2015 Iran nuclear deal is known—support upholding the arms embargo until 2023. The United States, which has withdrawn from the deal, started a process on August 20, 2020, that could lead to a snapback of all UN sanctions enacted since 2006.1 The IRGC’s Qased space-launch vehicle, shown at the Shahrud site The Qased-1, for its part, succeeded over its three in April. stages in placing the very small Nour-1 satellite in a near circular low earth orbit (LEO) of about 425 km. The first stage involved an off-the-shelf Shahab-3/ Ghadr liquid-fuel missile, although without the warhead section, produced by the Iranian Ministry of Defense.2 According to ASF commander Gen. -
Reusable Stage Concepts Design Tool
DOI: 10.13009/EUCASS2019-421 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND AEROSPACE SCIENCES (EUCASS) DOI: ADD DOINUMBER HERE Reusable stage concepts design tool Lars Pepermans?, Barry Zandbergeny ?Delft University of Technology Kluyverweg 1, 2629 HS Delft [email protected] yDelft University of Technology Kluyverweg 1, 2629 HS Delft Abstract Reusable launch vehicles hold the promise of substantially reducing the cost of access to space. Many different approaches towards realising a reusable rocket exist or are being proposed. This work focuses on the use of an optimisation method for conceptual design of non-winged reusable upper stages, thereby allowing it to take into account landing on land, sea or mid-air retrieval as well as landing the full stage or the engine only. As the optimisation criterion, the ratio of the specific launch cost of the reusable to the expendable version is used. The tool also provides for a Monte Carlo analysis, which allows for investigating the ruggedness of the design solution(s) found. The article will describe the methods implemented in the Conceptual Reusability Design Tool (CRDT) together with the modifications made to ParSim v3, a simulation tool by Delft Aerospace Rocket Engi- neering. Furthermore, it will present the steps taken to verify and validate CRDT. Finally, several example cases are presented based on the Atlas V-Centaur launch vehicle. The cases demonstrate the tools capa- bility of finding optimum and the sensitivity of the found optimum. However, it also shows the optimum when the user disables some Entry Descent and Landing (EDL) options. 1. Introduction To make space more accessible, one can reduce the cost of an orbital launch. -
Black Rain: the Burial of the Galilean Satellites in Irregular Satellite Debris
Black Rain: The Burial of the Galilean Satellites in Irregular Satellite Debris William F: Bottke Southwest Research Institute and NASA Lunar Science Institute 1050 Walnut St, Suite 300 Boulder, CO 80302 USA [email protected] David Vokrouhlick´y Institute of Astronomy, Charles University, Prague V Holeˇsoviˇck´ach 2 180 00 Prague 8, Czech Republic David Nesvorn´y Southwest Research Institute and NASA Lunar Science Institute 1050 Walnut St, Suite 300 Boulder, CO 80302 USA Jeff Moore NASA Ames Research Center Space Science Div., MS 245-3 Moffett Field, CA 94035 USA Prepared for Icarus June 20, 2012 { 2 { ABSTRACT Irregular satellites are dormant comet-like bodies that reside on distant pro- grade and retrograde orbits around the giant planets. They were possibly cap- tured during a violent reshuffling of the giant planets ∼ 4 Gy ago (Ga) as de- scribed by the so-called Nice model. As giant planet migration scattered tens of Earth masses of comet-like bodies throughout the Solar System, some found themselves near giant planets experiencing mutual encounters. In these cases, gravitational perturbations between the giant planets were often sufficient to capture the comet-like bodies onto irregular satellite-like orbits via three-body reactions. Modeling work suggests these events led to the capture of ∼ 0:001 lu- nar masses of comet-like objects on isotropic orbits around the giant planets. Roughly half of the population was readily lost by interactions with the Kozai resonance. The remaining half found themselves on orbits consistent with the known irregular satellites. From there, the bodies experienced substantial col- lisional evolution, enough to grind themselves down to their current low-mass states. -
10/2/95 Rev EXECUTIVE SUMMARY This Report, Entitled "Hazard
10/2/95 rev EXECUTIVE SUMMARY This report, entitled "Hazard Analysis of Commercial Space Transportation," is devoted to the review and discussion of generic hazards associated with the ground, launch, orbital and re-entry phases of space operations. Since the DOT Office of Commercial Space Transportation (OCST) has been charged with protecting the public health and safety by the Commercial Space Act of 1984 (P.L. 98-575), it must promulgate and enforce appropriate safety criteria and regulatory requirements for licensing the emerging commercial space launch industry. This report was sponsored by OCST to identify and assess prospective safety hazards associated with commercial launch activities, the involved equipment, facilities, personnel, public property, people and environment. The report presents, organizes and evaluates the technical information available in the public domain, pertaining to the nature, severity and control of prospective hazards and public risk exposure levels arising from commercial space launch activities. The US Government space- operational experience and risk control practices established at its National Ranges serve as the basis for this review and analysis. The report consists of three self-contained, but complementary, volumes focusing on Space Transportation: I. Operations; II. Hazards; and III. Risk Analysis. This Executive Summary is attached to all 3 volumes, with the text describing that volume highlighted. Volume I: Space Transportation Operations provides the technical background and terminology, as well as the issues and regulatory context, for understanding commercial space launch activities and the associated hazards. Chapter 1, The Context for a Hazard Analysis of Commercial Space Activities, discusses the purpose, scope and organization of the report in light of current national space policy and the DOT/OCST regulatory mission. -
Journal of Space Law
JOURNAL OF SPACE LAW VOLUME 24, NUMBER 2 1996 JOURNAL OF SPACE LAW A journal devoted to the legal problems arising out of human activities in outer space VOLUME 24 1996 NUMBERS 1 & 2 EDITORIAL BOARD AND ADVISORS BERGER, HAROLD GALLOWAY, ElLENE Philadelphia, Pennsylvania Washington, D.C. BOCKSTIEGEL, KARL·HEINZ HE, QIZHI Cologne, Germany Beijing, China BOUREr.. Y, MICHEL G. JASENTULIYANA, NANDASIRI Paris, France Vienna. Austria COCCA, ALDO ARMANDO KOPAL, VLADIMIR Buenes Aires, Argentina Prague, Czech Republic DEMBLING, PAUL G. McDOUGAL, MYRES S. Washington, D. C. New Haven. Connecticut DIEDERIKS·VERSCHOOR, IE. PH. VERESHCHETIN, V.S. Baarn, Holland Moscow. Russ~an Federation FASAN, ERNST ZANOTTI, ISIDORO N eunkirchen, Austria Washington, D.C. FINCH, EDWARD R., JR. New York, N.Y. STEPHEN GOROVE, Chairman Oxford, Mississippi All correspondance should be directed to the JOURNAL OF SPACE LAW, P.O. Box 308, University, MS 38677, USA. Tel./Fax: 601·234·2391. The 1997 subscription rates for individuals are $84.80 (domestic) and $89.80 (foreign) for two issues, including postage and handling The 1997 rates for organizations are $99.80 (domestic) and $104.80 (foreign) for two issues. Single issues may be ordered for $56 per issue. Copyright © JOURNAL OF SPACE LAW 1996. Suggested abbreviation: J. SPACE L. JOURNAL OF SPACE LAW A journal devoted to the legal problems arising out of human activities in outer space VOLUME 24 1996 NUMBER 2 CONTENTS In Memoriam ~ Tribute to Professor Dr. Daan Goedhuis. (N. J asentuliyana) I Articles Financing and Insurance Aspects of Spacecraft (I.H. Ph. Diederiks-Verschoor) 97 Are 'Stratospheric Platforms in Airspace or Outer Space? (M. -
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. -
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. -
Suborbital Reusable Launch Vehicles and Applicable Markets
SUBORBITAL REUSABLE LAUNCH VEHICLES AND APPLICABLE MARKETS Prepared by J. C. MARTIN and G. W. LAW Space Launch Support Division Space Launch Operations October 2002 Space Systems Group THE AEROSPACE CORPORATION El Segundo, CA 90245-4691 Prepared for U. S. DEPARTMENT OF COMMERCE OFFICE OF SPACE COMMERCIALIZATION Herbert C. Hoover Building 14th and Constitution Ave., NW Washington, DC 20230 (202) 482-6125, 482-5913 Contract No. SB1359-01-Z-0020 PUBLIC RELEASE IS AUTHORIZED Preface This report has been prepared by The Aerospace Corporation for the Department of Commerce, Office of Space Commercialization, under contract #SB1359-01-Z-0020. The objective of this report is to characterize suborbital reusable launch vehicle (RLV) concepts currently in development, and define the military, civil, and commercial missions and markets that could capitalize on their capabilities. The structure of the report includes a brief background on orbital vs. suborbital trajectories, as well as an overview of expendable and reusable launch vehicles. Current and emerging market opportunities for suborbital RLVs are identified and discussed. Finally, the report presents the technical aspects and program characteristics of selected U.S. and international suborbital RLVs in development. The appendix at the end of this report provides further detail on each of the suborbital vehicles, as well as the management biographies for each of the companies. The integration of suborbital RLVs with existing airports and/or spaceports, though an important factor that needs to be evaluated, was not the focus of this effort. However, it should be noted that the RLV concepts discussed in this report are being designed to minimize unique facility requirements.