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/ /fOR. 8FFI61Ak U&i 0'911.¥ The communications subsystem is further complicated by constellations requiring spin stabilized nanosats. A spinning nanosat cannot easily point an antenna toward Earth. Therefore, a low gain omni antenna is assumed and communications must take place near perigee, when the range is 3 to 5 Earth radii. A large ground antenna and high data rate compression must be used to achieve reasonable data rates with minimum power. This places an additional burden on the ground stations for both sensitive receivers/bit synchronizers and advanced decoders. These same considerations limit data rate for satellite-to-satellite communication. Although the inclusion of an onboard command receiver is high ly desired, it puts an additional strain on an already challenged nanosat mass and power budget. For this reason, the concept of a totally autonomous, receiverless nanosat design appears most attractive. However, "receiver-on-a-chip" technology has advanced to the point where including a receiver onboard looks feasible. The biggest disadvantage of a receiver now becomes the ground personnel and software needed to support the ability to command the nanosat. Command actions taken onboard will of course be limited to basic functions such as "transmit data" because of the lack of redundancy and mechanical functions. Although scenarios have been defined to allow nanosats to autonomously determine when to transmit their stored data, utilizing a receiver to control the telemetry downlink from the ground still has value. The capability of uploading flight software changes, as well as sending a master reset if necessary, would also exist with such an onboard command receiver. MECHANICAL AND STRUCTURES The nanosat mechanical system will be kept as simple as possible. The ideal nanosat mechanical design should consist of a one-piece structure on which all other components are mounted. Multifunctional structures can provide thermal control, shielding and serve as substrates for printed circuit boards. For example, diamond facesheet honeycomb panels can serve as a structure, thermal conductor and radiator, and printed circuit board substrates. The diamond facesheet provides ten times greater thermal conductivity than aluminum and can dissipate heat from high power density electronics modules with a low mass comparable to carbon fiber composites. Another example is the structural battery system. It consists of a honeycomb panel whose core is filled with the cells of a nickel-hydrogen battery (or other flight qualified cell technology). Concurrent engineering and fabrication techniques will be used to create a single computer model for the design, analysis (structural, thermal, and dynamic), and fabrication of the nanosat and its components. Dynamic modeling capabilities to simulate nanosat deployments will provide faster designs and a reduction in the amount of deployment testing required. This approach will significantly lower development costs by reducing duplication of effort, chances of errors, the number of drawings and paperwork required. Mass production techniques not traditionally used for spaceflight hardware will be used, such as casting and injection molding. Options being considered for the nanosat structure material are: cast aluminum; cast aluminum-beryllium alloy; injection molded UNCLASSIFIED,<,<FOA QFFIEiIAL HSI!! OHLY 8
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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.