Documents / Official release
This Defense Intelligence Reference Document (DIA-08-1011-001), dated 1 November 2010, was prepared by the Defense Intelligence Agency's Defense Warning Office under the Advanced Aerospace Weapon System Applications program. It covers nanosatellite technologies, laser Lightcraft propulsion, a weapon mission selection study and a multi-megawatt laser study. The author recommends that the Department of Defense, working with NASA, bring laser Lightcraft propulsion research back to the United States and restart the Air Force X-50LR test flight program.
From the source:Release of 2026-09-18 Incident: 11/1/10, Las Vegas, Nevada. Released with redactions. This document is a Defense Intelligence Reference Document (DIRD), a technical reference format used by the Defense Intelligence Agency (DIA) to capture baseline knowledge on a specific topic for later analytic use. DIRDs are best understood as reference and synthesis products rather than as original research. It is one of 38 DIRDs produced under the Advanced Aerospace Weapon System Applications Program (AAWSAP) between 2009 and 2011. Because AAWSAP’s scope permitted a broad range of supporting topics, not every DIRD in the series directly concerns aerospace systems or future threat assessment. The following summary reflects the DIRD’s scope and framing at the time of writing and should not be read as implying current validation of the concepts discussed. This DIRD examines laser-propelled “Lightcraft” as a possible low-cost method to launch very small satellites into low Earth orbit by using a remote high-energy laser to supply most of the propulsion energy rather than relying entirely on onboard energy sources. The report combines a survey of nanosatellite trends with a review of “Lightcraft” propulsion concepts, vehicle design, beam-control requirements, and mission studies, and argues that the most promising application is the launch of nano- or pico-satellites, especially Earth- and space-observing payloads of a few kilograms or less. It presents the concept as potentially much cheaper than conventional multistage rockets for very small payloads, while also noting significant practical constraints including strict beam-riding geometry, atmospheric losses, demanding pointing and adaptive-optics requirements, and heavy dependence on large ground-, sea-, or air-based laser infrastructure. Overall, the document presents laser “Lightcraft” as a technically plausible launch concept whose attractiveness depends on whether the supporting laser and beam-control system can be made reliable and economical at operational scale.
UNCLASSIFIED/,'rOR: orrlCIAL USE 014Lf ground, sea and air launches of Lightcraft to LEO with air launch occurring at either subsonic or hyperson ic speed. Lightcraft Ground/Sea to Space Investigation The current Air Force Lightcraft vehicle concept has been designed for not only placing nanosats into LEO at low cost (Figure 14 ), but also for performing much of the nanosat function as well. In this concept the precision optics system that focuses ground/sea based laser light into t he Lightcraft's cowl area for propulsion is also used as a space telescope for viewing military targets on Earth and in space. And structural panels on the Lightcraft forebody are also used as solar panels that are unfurled in orbit for generation of satellite power. Thus, the current Lightcraft's design allocates only 0.1 kg of its 1.0 kg dry mass for exclusively nanosat functions. There is a military need for 1.0 kg to 2.0 kg nanosats with optical sensors for visual inspection of unknown objects in space and on Earth. Since conventiona l expendable rockets could conceivably be an alternative to laser powered Lightcraft for the rapid placement of military nanosats in LEO, a cursory comparison of Lightcraft and conventiona l rockets was made by Froning and Davis [26] to get some idea of their comparative costs. Hybrid rocket sizing and costing was based upon tactical strategic missile sizing and costing information possessed by H. D. Froning . Th is information related costs (in 1982 dollars) to rocket and payload characteristics. Lightcraft sizing assumed a propellant mass fraction of 0.5 and 1.0 MW of laser power per pou nd of payload (dry mass) placed into orbit. Costs for laser power and refurbishment were based upon AFRL estimates (amortized over a fewer number of flights). Although these Lightcraft and laser costs are higher (based upon much fewer flights) than those of previous AFRL estimates, they are believed to be consistent with the conventional rocket costs, and therefore applicable for relative cost comparisons. More detail ed future Lightcraft/conventional rocket designs and cost comparisons are, of course, needed before a strong argument can be made for either design. Shown in Table 2 is the estimated performance and weights (masses) for 3-stage hybrid rocket launch vehicles and single-stage laser-powered launch vehicles that are capable of placing nanosats of 1.0 kg, 5.0 kg, and 10 kg into LEO. And Table 3 shows estimated costs for hybrid rockets and laser-powered Lightcraft assuming 100 flights over a 10-year period. These estimated costs indicate that Lightcraft could boost nanosats in the 2.0 kg to 5.0 kg range into LEO at about 1/l0t h to 1/5th the cost of expendable rockets. But Lightcraft cost superiority over conventional rockets is less overwhelming for satellites that are significantly heavier. Thus Lig htcraft appear extremely attractive for satellite delivery missions only if Lightcraft dry masses, including the satell ites being carried, are less than about 5.0 kg. UNCLASSIFIED,<,<FOA QFFISIAL HSI!! 8HLY 30
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Official release, from the pursue collection. The PDF is mirrored here; the original link is above. 77 pages are in the text index: search them above, or from the library's search.