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    <title>Transport Research International Documentation (TRID)</title>
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    <copyright>Copyright © 2026. National Academy of Sciences. All rights reserved.</copyright>
    <docs>http://blogs.law.harvard.edu/tech/rss</docs>
    <managingEditor>tris-trb@nas.edu (Bill McLeod)</managingEditor>
    <webMaster>tris-trb@nas.edu (Bill McLeod)</webMaster>
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      <title>Transport Research International Documentation (TRID)</title>
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    <item>
      <title>Aviation to Aerospace: Emerging Space Flight Operations and their Significance to Law, Policy, and the Science of Social Space</title>
      <link>https://trid.trb.org/View/1631574</link>
      <description><![CDATA[This article considers the impact of a recent U.S. presidential announcement of the creation of a “Space Force,” designed as a sixth branch of the military.  The author focuses on the impact of the Space Force initiative on civil commercial passenger space flight growth in the private sector and on the larger public area of international competition regarding space travel.  The author offers an historical perspective to structure one’s thinking on these issues, covering topics including aviation development during the two world wars and the subsequent “cold war;” technology, the diffusion of the jet, and the emergence of rockets; aerospace policy development, including the model of maritime law and space as a final frontier; human rights law; the development of civil aviation in the United States; energy, climate, security, and technology risk; the cultural history of space flight; political and commercial considerations; techno-optimism and economic development; China’s space race envisioned as a new cold war and Chinese space law; speedy progress toward a new theory of aviation economics and policy; and the promise of sub-orbital point-to-point passenger flight. A case study from Canada, focusing on Canadian Airways as an analogy to space operations, is presented. The author concludes with a brief discussion of the role of human curiosity, discovery, and freedom of movement in space-domain ownership and security.]]></description>
      <pubDate>Tue, 18 Jun 2019 11:32:35 GMT</pubDate>
      <guid>https://trid.trb.org/View/1631574</guid>
    </item>
    <item>
      <title>User Guides for Noise Modeling of Commercial Space Operations—RUMBLE and PCBoom</title>
      <link>https://trid.trb.org/View/1510943</link>
      <description><![CDATA[As commercial space launch vehicles begin testing and become operational, many noise issues as well as the effects from sonic booms will need to be evaluated. The Aviation Environmental Design Tool (AEDT) is designed to evaluate the effects of noise and emissions from aircraft, but does not have the ability to predict noise and sonic boom effects from commercial space operations. Two tools were developed in this project to predict noise and sonic boom to be used in the noise modeling evaluation process. RUMBLE 2.0 predicts rocket noise, and PCBoom4 was modified to predict sonic boom from commercial space operations. The models are based on a database that compiles information on the vehicles and engine/motors used. This report comprises the user’s guide for each tool, and ACRP Web-Only Document 33: Commercial Space Operations Noise and Sonic Boom Modeling and Analysis is the contractor’s final report on the methodology and development of these tools.  The software for PCBoom and RUMBLE can be found on the TRB website by searching for ACRP Research Report 183.]]></description>
      <pubDate>Wed, 02 May 2018 09:38:22 GMT</pubDate>
      <guid>https://trid.trb.org/View/1510943</guid>
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    <item>
      <title>Route of the rockets : how vintage passenger cars helped the space shuttle fly</title>
      <link>https://trid.trb.org/View/1501029</link>
      <description><![CDATA[]]></description>
      <pubDate>Mon, 05 Feb 2018 15:41:11 GMT</pubDate>
      <guid>https://trid.trb.org/View/1501029</guid>
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      <title>Modified Regression Rate Formula of PMMA Combustion by a Single Plane Impinging Jet</title>
      <link>https://trid.trb.org/View/1458537</link>
      <description><![CDATA[A modified regression rate formula for the uppermost stage of Cascaded Multistage Impinging-jet (CAMUI) type hybrid rocket motor is proposed in this study. Assuming a quasi-steady, one-dimensional, an energy balance against a control volume near the fuel surface is considered. Accordingly, the regression rate formula which can calculate the local regression rate by the quenching distance between the flame and the regression surface is derived. An experimental setup which simulates the combustion phenomenon involved in the uppermost stage of a CAMUI-type hybrid rocket motor was constructed and the burning tests with various flow velocities and impinging distances were performed. A PMMA slab of 20 mm height, 60 mm width, and 20 mm thickness was chosen as a sample specimen and pure oxygen and O₂/N₂ mixture (50/50 vol.%) were employed as the oxidizers. The time-averaged regression rate along the fuel surface was measured by a laser displacement sensor. The quenching distance during the combustion event was also identified from the observation. The comparison between the purely experimental and calculated values showed good agreement, although a large systematic error was expected due to the difficulty in accurately identifying the quenching distance.]]></description>
      <pubDate>Tue, 28 Mar 2017 17:09:32 GMT</pubDate>
      <guid>https://trid.trb.org/View/1458537</guid>
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    <item>
      <title>Frontiers of Engineering: Reports on Leading-Edge Engineering from the 2016 Symposium</title>
      <link>https://trid.trb.org/View/1453697</link>
      <description><![CDATA[This volume presents papers on the topics covered at the National Academy of Engineering’s 2016 US Frontiers of Engineering Symposium. Every year the symposium brings together 100 outstanding young leaders in engineering to share their cutting-edge research and innovations in selected areas. The 2016 symposium was held September 19–21 at the Arnold and Mabel Beckman Center in Irvine, California. The topics covered at the 2016 symposium were (1) pixels at scale: high-performance computer graphics and vision, (2) extreme engineering: extreme autonomy in space, air, land, and under water, (3) water desalination and purification, and (4) technologies for understanding and treating cancer.  The session Extreme Engineering: Extreme Autonomy in Space, Air, Land, and Under Water provided an overview of four domains where recent algorithmic and mechanical advances are enabling the design and deployment of robotic systems where autonomy is pushed to the extreme. The session started with a presentation on the challenges of precision landing for reusable rockets, the technology required, and what will be needed to extend precision landing to planets other than Earth. The next presentation focused on autonomous microflying robots with design innovations inspired by avian flight. This was followed by a talk on the robotic cheetah, the first four-legged robot to run and jump over obstacles autonomously, and the management of balance, energy, and impact without human interaction. The fourth and final presentation covered motion guidance for ocean sampling by underwater vehicles.]]></description>
      <pubDate>Mon, 27 Feb 2017 09:25:40 GMT</pubDate>
      <guid>https://trid.trb.org/View/1453697</guid>
    </item>
    <item>
      <title>Challenges in accommodating commercial space operations in the NAS : with the impending increase in commercial space flight comes new tasks for managing air traffic</title>
      <link>https://trid.trb.org/View/1333381</link>
      <description><![CDATA[]]></description>
      <pubDate>Wed, 03 Dec 2014 14:19:34 GMT</pubDate>
      <guid>https://trid.trb.org/View/1333381</guid>
    </item>
    <item>
      <title>Space demilitarization treaties in a new era of manned nuclear spaceflights</title>
      <link>https://trid.trb.org/View/1239696</link>
      <description><![CDATA[]]></description>
      <pubDate>Mon, 04 Feb 2013 10:40:47 GMT</pubDate>
      <guid>https://trid.trb.org/View/1239696</guid>
    </item>
    <item>
      <title>Numerical Investigation of Swirl Injector LOX/GH2 Ratio Influence Over Combustion Conditions Into a Liquid Rocket Engine</title>
      <link>https://trid.trb.org/View/1105490</link>
      <description><![CDATA[Swirl injectors are widely used in liquid rocket engines, gas turbine engines, diesel engines, industrial furnaces and so forth. Even though the design procedure of a swirl injector is more difficult than that of an impinging jet injector, swirl injectors have many advantages, such as atomization quality, wide operation range with stability and uniform mixing efficiency. The spraying mechanism of a swirl injector is such that a liquid sheet is injected with the tangential velocity due to tangential entries, so a liquid sheet is discharged with a specific spray angle which corresponds to the ratio of axial and tangential velocity and the air core is formed. The mixture ratio of Liquid O2 and Fuel (H2) for such types of injectors may be throttled from 2:1, which is the upper limit for functioning for current Liquid Rocket Engines (LRE) impinging jet axial injectors, up to 10:1. This paper intends to numerically investigate the impact of swirl injector LOX/GH2 ratio over combustion conditions into a LRE using state of the art numeric simulation technologies. The outcome of this work is to completely define the relation between LOX/GH2 ratio and the combustion conditions inside the rocket engine.]]></description>
      <pubDate>Wed, 20 Jul 2011 07:26:24 GMT</pubDate>
      <guid>https://trid.trb.org/View/1105490</guid>
    </item>
    <item>
      <title>Orbital service utility vehicle for a low earth orbit fuel depot</title>
      <link>https://trid.trb.org/View/858188</link>
      <description><![CDATA[]]></description>
      <pubDate>Mon, 05 May 2008 17:05:15 GMT</pubDate>
      <guid>https://trid.trb.org/View/858188</guid>
    </item>
    <item>
      <title>MN TOUCAN; RO-RO/LO-LO ROCKET CARRIER COMPLETED BY MERWEDE SHIPYARD</title>
      <link>https://trid.trb.org/View/455928</link>
      <description><![CDATA[The ro-ro/lo-lo vessel MN TOUCAN was built by IHC Holland NV, Kinderdijk, The Netherlands for Compagnie Morbihannaise & Nantaise de Navigation, Nantes, France.  The vessel was especially designed for the transport of Ariane rockets from Europe to Kourou, French Guiana.  General arrangement drawings are included in the article.  The principal particulars of MN TOUCAN are: propulsion                                         2 x MaK 6M32 length, overall                                         115.50m length, between perpendiculars                          105.60m breadth, moulded                                         20.00m depth, main deck                                          6.50m depth, upper deck                                        15.35m draught                                                   5.00m tonnage, gross register                                   9,140 tonnage, deadweight                                      4,250t speed                                               15.50 knots crew                                                         24]]></description>
      <pubDate>Mon, 04 Mar 1996 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/455928</guid>
    </item>
    <item>
      <title>HUMAN FACTORS ENGINEERING DESIGN CRITERIA FOR FUTURE SYSTEMS, REPORT 3: DESIGN CRITERIA EVOLVING FROM THE MULTIPLE LAUNCH ROCKET SYSTEM (MLRS) OPERATIONAL TEST 3</title>
      <link>https://trid.trb.org/View/387914</link>
      <description><![CDATA[This document compares human factors engineering-related problems identified in the U.S. Army Operational Test and Evaluation Agency MLRS (Multiple Launch Rocket System) Operational Test III with relevant criteria statements. These criteria were reviewed to determine if they provided adequate guidance for making informed design judgments. Areas where existing criteria are inadequate or nonexistent were identified and new complete criteria developed. The new criteria are presented in a format designed to facilitate their use in the design of future similar systems.]]></description>
      <pubDate>Thu, 21 Jul 1994 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/387914</guid>
    </item>
    <item>
      <title>LASER-HEATED HEAT-EXCHANGER THRUSTER</title>
      <link>https://trid.trb.org/View/342734</link>
      <description><![CDATA[No abstract provided.]]></description>
      <pubDate>Tue, 31 Mar 1992 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/342734</guid>
    </item>
    <item>
      <title>ENVIRONMENTAL DATA RECORDER (EDR) QUALIFICATION FINAL TEST REPORT</title>
      <link>https://trid.trb.org/View/340018</link>
      <description><![CDATA[No abstract provided.]]></description>
      <pubDate>Thu, 31 Oct 1991 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/340018</guid>
    </item>
    <item>
      <title>UNITED STATES AIRCRAFT, MISSILES AND SPACE CRAFT.6TH ED</title>
      <link>https://trid.trb.org/View/215324</link>
      <description><![CDATA[No abstract provided.]]></description>
      <pubDate>Thu, 31 Oct 1985 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/215324</guid>
    </item>
    <item>
      <title>LAUNCHING THE ROCKET INDUSTRY IN THE UNITED STATES : DOMESTIC REGULATION OF PRIVATE EXPENDABLE LAUNCH VEHICLES</title>
      <link>https://trid.trb.org/View/218901</link>
      <description><![CDATA[No abstract provided.]]></description>
      <pubDate>Thu, 31 Oct 1985 00:00:00 GMT</pubDate>
      <guid>https://trid.trb.org/View/218901</guid>
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