Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems

http://www-eng.lbl.gov/~shuman/NEXT/MATERIALS&COMPONENTS/Pressure_vessels/spinform_PV.pdf

A study on failure characteristic of spherical pressure vessel

Space-based persistent surveillance provides decision makers with information necessary to effectively respond to both natural and man-made crises. This thesis investigates a reconfigurable constellation strategy that utilizes on-demand, maneuverable satellites to provide focused regional coverage with short revisit times at greatly decreased cost when compared to traditional static satellite constellations. The thesis develops and demonstrates a general framework to guide the design and optimization of reconfigurable satellite constellations specifically tailored to stakeholder objectives while considering requirement uncertainty. The framework is novel in that it avoids many of the assumptions and simplifications of past research by: 1. explicitly considering uncertainty in future operating conditions; 2. concurrently optimizing constellation pattern design, satellite design, and operations design; and, 3. investigating layered and asymmetric patterns. The framework consists of three elements: a detailed simulation model to compute constellation performance and cost for a variety of architectures and patterns, Monte Carlo simulation to determine how well each design performs under uncertain future conditions, and a parallel multi-objective evolutionary algorithm developed from the -NSGA-II genetic algorithm to find designs that maximize performance while simultaneously minimizing cost. Additionally, a new performance metric is developed to measure directly how well a design meets desired temporal and spatial sampling requirements and a decision model and optimal assignment process is developed to determine how to employ the option of reconfigurability to respond to specific regional events. The framework was used to perform 85 optimization runs selected to compare the costeffectiveness of several constellation architectures over varied operating conditions and coverage requirements. All optimization runs were performed in less than three months, demonstrating that parallel computing coupled with sophisticated optimization routines enable rapid spiral development of satellite constellations. Results show that reconfigurable constellations cost 20 to 70% less than similarly performing static constellations for the scenarios studied. The cost savings grows with increasingly demanding coverage requirements. Results from optimizing a fully asymmetric constellation pattern led to two the development of new ‘quasi’-asymmetric patterns that were found to significantly outperform symmetric patterns

Optimization and valuation of recongurable satellite constellations under uncertainty

An unprecedented combination of high propellant fraction and small size is required for affordable-scale Mars return, regardless of the number of stages, or whether Mars orbit rendezvous or in-situ propellant options are used. Conventional space propulsion technology is too heavy, even without structure or other stage subsystems. The application of launch vehicle design principles to the development of new hardware on a tiny scale is therefore suggested. Miniature pump-fed rocket engines fed by low pressure tanks can help to meet this challenge. New concepts for engine cycles using piston pumps are described, and development issues are outlined.

/pdf/mars-ascent-propulsion-options-for-small-sample-return-pr9xjp9eml.pdf

Mars ascent propulsion options for small sample return vehicles

A titanium-lined composite overwrapped pressure vessel (COPV) for Xenon storage was designed for the ETS VIII spacecraft. This tank has a nominal propellant volume of 50 liters (3050 cubic inches) and a nominal weight of 7 kg (15.4 pounds). The maximum expected operating pressure is 150 bar (2175 psi), 50 cycles. Proof pressure requirement is 187.5 bar (2719 psi), 5 cycles, and the minimum burst pressure is 225 bar (3264 psi). The tank is designed to hold 89 kg (196 pounds) of Xenon. The ETS VIII Xenon tank design is based on a flight-qualified Xenon tank to take advantage of its design and flight heritage. To minimize risk, the ETS VIII Xenon tank is designed to use only existing manufacturing technology. Manufacturing cost is minimized by using existing tooling. Nonlinear material and geometric modeling techniques were used to analyze this tank. Stress analysis showed positive margins of safety for pressure cycle fatigue, vibration fatigue and minimum burst pressure over the design requirements. Development and Qualification testing verified the design margins and showed the design analyses to be conservative.

Design and manufacture of the ETS VIII Xenon tank

Design, development, qualification, and manufacture of the HS 601 propellant tank

The design and manufacture of a pressure vessel for aerospace application is a major undertaking requiring significant amount of resources. The large pool of talents needed to carry out these tasks include stress analysts, design engineers, manufacturing engineers, planners, tool engineers, NC programmers, test engineers, and highly skilled workers such as machinists, welders, heat treat technicians, inspectors, and test technicians, plus program managers to put all the different pieces of the puzzle together. These people have to perform design analyses, create drawings for parts and assemblies, write process procedures, generate NC programs, produce tool drawings, build manufacturing tooling, plan manufacturing sequences, generate shop travelers, write test procedures, and produce test reports. Suffice it to say the non-recurring cost to design and manufacture a pressure vessel can be high. One of the ways Pressure Systems, Inc. (PSI) and its customers use to keep this cost down is to develop derivative tanks based on existing, qualified tank designs. This approach utilizes, as much as possible, analyses previously performed, documents previously generated, and tooling previously manufactured. The approach has been in practice at PSI for over three decades. It accounts for nearly 80% of the over 350 qualified tank designs developed by PSI. Over the years this approach has saved the government and our commercial customers tens of millions of dollars. Additional benefits derived from this approach include accelerated program schedule, qualification status, and flight heritage. This paper provides some examples of PSI’s long and extensive history in the development of derivative tanks.

Low cost derivative tanks for spacecraft and launch vehicles

NASA’s Dragonfly mission will sample surface materials from multiple sites on Saturn’s largest moon, Titan, in exploration of its potential for prebiotic chemistry. We are developing and delivering a compact pulsed UV laser transmitter, developed in-house at NASA’s Goddard Space Flight Center, capable of directing programmable 266 nm pulse energies to a small sample of surface material for laser desorption mass spectrometry (LDMS) performed by the on-board Dragonfly Mass Spectrometer (DraMS). The mail goal for this effort was to develop a flight-capable, two-part design, employing a remotely located fiber coupled pumping source, and a UV transmitter unit that can operate in short bursts with minimal change in laser pulse characteristics such as beam quality, pointing, energy, and pulse width. The DraMS UV source will require a 7+ year transit to the Saturn system; where upon deployment on Titan’s surface, must demonstrate a combination of survivability, reliability, operational capability, and performance yet developed in a flight-qualified solid-state laser transmitter. Once Dragonfly is safely operational, the Titan Hydrocarbon Analysis Nanosecond Optical Source (THANOS) UV laser will perform for 3+ years in Titan’s extreme surface and atmospheric conditions in several locations.

Development of a programmable UV laser source for the Dragonfly Mass Spectrometer (DraMS)

NASA’s Dragonfly mission is a rotorcraft lander which will explore several geologic locations on Saturn’s moon, Titan and investigate evidence of surface-level prebiotic chemistry as well as search for chemical signatures of water-based and/or hydrocarbon-based life. To perform molecular composition investigations in-situ, the payload includes the Dragonfly Mass Spectrometer (DraMS), being developed at NASA’s Goddard Space Flight Center (GSFC). DraMS will utilize laser desorption mass spectrometry (LDMS) to interrogate surface samples and measure the organic composition. Enabling this science capability is the Throttled Hydrocarbon Analysis by Nanosecond Optical Source (THANOS) laser being developed at NASA-GSFC. The THANOS laser is comprised of a solid state, passively Q-Switched Nd:YAG oscillator which is frequency converted to 266 nm and utilizes a RTP high voltage electro-optic for pulse energy control. The laser outputs <2.0 ns pulses with a maximum energy of approximately 200 uJ which can be emitted in 1 - 50 shot bursts at 100 Hz while performing LDMS science operations. The laser has the capability to throttle its UV pulse energy output from full attenuation to maximum energy to provide varying levels of fluence on samples in the DraMS instrument. We report on the THANOS’ laser technology development and space qualification effort including vibration, thermal vacuum cycling, radiation as well as optical damage testing due to Titan’s atmospheric composition, performed at NASA-GSFC from 2019 through 2022.

Technology development of a solid state 266 nm laser for NASA’s Dragonfly mission

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Papers

Design, development, qualification, and manufacture of the HS 601 propellant tank

Low cost derivative tanks for spacecraft and launch vehicles

Development of a programmable UV laser source for the Dragonfly Mass Spectrometer (DraMS)

Technology development of a solid state 266 nm laser for NASA’s Dragonfly mission