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Operationally Responsive Space (ORS) is focused on putting satellites in orbit in significantly less time than it currently takes. ORS is based on responding to an operational need quickly, but it should not be thought of as a new way to place national systems in orbit. Operational needs likely result from a need to augment an existing system or to replace a portion of an existing system. Whether a satellite is required as an augmentation or a replacement, it would need to be placed in orbit on the order of weeks, not years, as it would take to deploy a satellite from scratch. ORS systems will be a gap filler aimed at maintaining an existing advantage in unforeseen circumstances. This research shows, based on the available literature, how the needs for ORS can be broken down systematically into a set of requirements to be used to design a space system. It provides a basic concept of how an ORS satellite architecture would be developed. Finally, this research also defines a preliminary system design that would enable satellites to be launched on short notice.
The Dept. of Defense¿s (DoD) operational dependence on space has placed new and increasing demands on current space systems to meet commanders¿ needs. DoD¿s Operationally Responsive Space (ORS) concept is designed to more rapidly satisfy commanders¿ needs for information and intelligence during ongoing operations. Given the potential for ORS to change how DoD acquires and fields space capabilities to support the warfighter, this report discusses to what extent DoD: (1) is developing ORS to support warfighter requirements; and (2) has a plan that integrates ORS into existing DoD and intelligence community processes and architecture. Includes recommendations. Charts and tables.
The capability to rapidly deploy tactical satellites to meet a Joint Force Commander's immediate battlespace requirements is a well-documented joint capability need. Key U.S. strategic documentation cites the need for the capability to maintain persistent surveillance or an "unblinking eye" over battlespace and to rapidly reconstitute critical space capabilities to preserve situational awareness. The warfighter requires a tactical space-based deployment capability which employs a request to launch and operational deployment window of 90 to 120 days. This master's thesis executed two (2) major areas of work: apply, and reinforce the Operationally Responsive Space (ORS) mission tasks using the Joint Capabilities Integration Development System (JCIDS) process; then based on capability gap data generated from the process, analyze and define the capability gap of an ORS Adaptive Integration, Test and Logistics (IT & L) process for payload to bus deployment to meet the identified time scales. This document recommends engineering solutions and processes for the ORS IT & L "to-be" state for this warfighter capability. The ORS adaptive IT & L CONOPS developed as part of this work focuses on the Tactical Satellite Rapid Deployment System (TSRDS), which is an adaptive integration, test and logistics capability that enables rapid and effective payload to bus integration to meet a 90- to 120-day warfighter window.
The Unites States' first space systems programs were initially developed to meet the requirements of strategic users. Since the 1991 Gulf War there has been a growing dependence on the capabilities and support delivered by these programs to meet the requirements of nonstrategic users. The current National Security Space (NSS) architecture makes it rather difficult for all but critical strategic users to fully capitalize on the available assets. Timelines that were once adequate to deliver strategic capabilities are now not sufficient to allow a broader range of users to realize the benefit from using the available space systems. In addition, nonstrategic users run into challenges when they attempt to change the tasking requirements that would enable them to receive associated products and services that are useful and timely. With the identified gaps in the current NSS environment, the Integrated Product Team (IPT), consisting of 10 active duty military students, sought solutions to make space more "Operationally Responsive" (ORS) to its customers by 2025. Due to limited time and assets, the IPT narrowed the focus of the project to the four Joint Publication (JP) 3-14 "Joint Doctrine for Space Operations" mission areas of Space Support, Space Control, Force Enhancement, and Force Application. During this project, the IPT defined ORS from its perspective, developed the requirements to meet the identified NSS gaps, selected the final alternatives to satisfy those requirements, and suggested an implementation plan. While in the architecture process, the IPT conducted an in-depth evaluation of the original alternatives based on Responsiveness, Risk, Capability, and Cost. After building a foundation for further analysis, a total of 16 alternatives were chosen for the final ORS architecture. The alternative that provided the most responsiveness was to create a Single Space Agency.
The distance learning team was tasked to produce an architecture that would best support future Operationally Responsive Space requirements in the 2025 timeframe. The 'bottom line up front' to this analysis showed that the current space architecture already provides some level of responsiveness. However, ORS will demand modifications of the current space architecture vice certain pre-conceived notions of quick launch or a separate ORS architecture altogether. The team developed a 'baseline' vision for deeper analysis focused on the Combatant Commander supported by analytical categories named 'Pillars' as follows: Improved Organizational Relationships, Asset Loss Mitigation, Availability, Flexibility, and Streamlined Acquisition Processes. These pillars allowed the solutions, material and non-material, to be organized for further analysis, relevancy, and value to the architecture. Constraints and alternative solutions were considered. Analysis was further supported by a performance versus cost process which provided a final test of solution feasibility. Relative cost was determined by comparison of existing program or like capabilities with future inflation. Differing combinations of solutions could provide ORS value by modification of the metrics. The final analysis showed an Operationally Responsive Space architecture that meets all metrics and that could support all COCOM requirements.
Current space assets provide communication, navigation, and ISR capabilities using satellites designed for long life and high reliability. Those life and reliability requirements are due in part to the high cost and limited availability of space launch. Current space systems require years to develop due to the complicated specialized design and manufacturing processes. The high cost of launching space assets, and competition with the commercial launch market, require launch scheduling years in advance. Moreover, once it has been scheduled on a launch vehicle, it may take several months to checkout and integrate into the launch vehicle and several additional months to become operational once it's in space. This existing capability is not operationally responsive.
A design methodology for a new breed of launch vehicle capable of lofting small satellites to orbit is discussed. The growing need for such a rocket is great: the United States has no capabilities in place to quickly launch and reconstitute satellite constellations. A loss of just one satellite, natural or induced, could significantly degrade or entirely eliminate critical space-based assets which would need to be quickly replaced. Furthermore a rocket capable of meeting the requirements for operationally responsive space missions would be an ideal launch platform for small commercial satellites. The proposed architecture to alleviate this lack of an affordable dedicated small-satellite launch vehicle relies upon a combination of expendable medium-range military surplus solid rocket motor assets. The dissertation discusses in detail the current operational capabilities of these military boosters and provides an outline for necessary refurbishments required to successfully place a small payload in orbit. A custom 3DOF trajectory script is used to evaluate the performance of these designs. Concurrently, a parametric cost-mass-performance response surface methodology is employed as an optimization tool to minimize life cycle costs of the proposed vehicles. This optimization scheme is centered on reducing life cycle costs per payload mass delivered rather than raw performance increases. Lastly, a novel upper-stage engine configuration using Hydroxlammonium Nitrate (HAN) is introduced and experimentally static test fired to illustrate the inherent simplicity and high performance of this high density, nontoxic propellant. The motor was operated in both pulse and small duration tests using a newly developed proprietary mixture that is hypergolic with HAN upon contact. This new propellant is demonstrated as a favorable replacement for current space vehicles relying on the heritage use of hydrazine. The end result is a preliminary design of a vehicle built from demilitarized booster assets that complements, rather than replaces, traditional space launch vehicles. This dissertation proves that such capabilities exist and more importantly that the resulting architecture can serve as a viable platform for immediate and affordable access to low Earth orbit.
Designing complex space systems that will deliver value in the presence of an uncertain future is difficult. As space system lifetimes are now measured in decades, the systems face increased risk from uncertain future contexts. Tradespace exploration increases the designer's system knowledge during conceptual design and with dynamic analysis can predict the system's behavior in many possible future contexts. Designing flexible systems will allow mitigation of risk from uncertain future contexts and the opportunity to deliver more value than anticipated by the designers. Flexibility is a dynamic property of a system that allows it to take advantage of emergent opportunity and to mitigate risk by enabling the system to respond to changing contexts in order to retain or increase usefulness to system stakeholders over time. Identifying flexible designs has traditionally been accomplished through subjective or heuristic methods, leading to a qualitative assessment of system flexibility. Objective and quantitative measures of flexibility are required for analysis of flexibility in tradespace exploration, as the number of designs is often too large for traditional qualitative approaches. Value Weighted Filtered Outdegree is introduced as a metric for identifying valuably flexible systems in tradespace studies in order to improve decision making during the conceptual design phase. Dynamic Multi-Attribute Tradespace Exploration (Dynamic MATE) is used as the basic tradespace exploration method for Value Weighted Filtered Outdegree. Dynamic MATE applies decision theory to computer simulation of thousands of system designs, across hundreds of unique future contexts. Epoch-Era Analysis is used to parameterize future contexts for dynamic analysis of the designs' performance. Although dominated in static analysis, flexible designs are valuable in the presence of changing contexts. The usefulness of Value Weighted Filtered Outdegree is established through application to the design of a satellite radar system. The metric was able to identify designs that are valuably flexible, and exclude designs that carry change capability that does not add value to the design across selected epochs. Showing another application of Value Weighted Filtered Outdegree, a comparison of flexibility for an Operationally Responsive Space architecture is conducted which highlights the advantages of a modular architecture in the presence of changing user requirements.