A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight first quarterly report, jul. - sep. 1964
Highly conductive nonaqueous electrolytes for high energy battery
CONDUCTIVITY↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight third quarterly report, jan. - mar. 1965
Electrochemical study of prospective electrode- electrolyte systems for high-energy primary battery with minimum of 200 watt hours per pound of total battery weight
ELECTRODE↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight fourth quarterly report, apr. - jun., 1965
High energy density primary battery development - anode-electrolyte, cupric fluoride cathode, and chemical stability tests
COPPER FLUORIDE↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Seventh quarterly report, Jan. 1 - Mar. 31, 1966
Cathodic materials for high energy density storage battery
ENERGY STORAGE DEVICE↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Quarterly report, 1 Oct. - 31 Dec. 1966
High energy density primary battery - film formation on cupric fluoride cathodes discharged in organic electrolytes
COPPER FLUORIDE↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Quarterly report, Jul. 1 - Sep. 30 1966
Evaluation of various anode-electrolyte and cathode-electrolyte combinations for high energy density battery
BATTERY↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Fifth quarterly report, 1 Jul. - 30 Sep. 1965
High energy density primary battery development - electrochemical half-cell screening of anode- electrolyte combinations, cell discharge, and potential studies
ELECTROCHEMICAL CELL↗
A program to develop a high-energy density primary battery with a minimum of 200 watt hours per pound of total battery weight Sixth quarterly report, Oct. 1 - Dec. 31, 1965
Lithium anodes, inorganic and organic cathodes, vacuum-distilled solvents, and methods for sintering cupric fluoride on lightweight metal substrates - development of high energy battery
BATTERY↗
Minimum Heating Re-Entry Trajectories for Advanced Hypersonic Launch Vehicles
Optimal re-entry trajectories are generated for reusable launch vehicles which minimize: (1) the heat absorbed at the vehicle surface, (2) the lower surface temperature, and (3) the heat absorbed by the internal structure. The approach uses the energy state approximation technique and a finite control volume heat transfer code coupled to a flight path integration code. These trajectories are compared to the optimal re-entry trajectory minimizing the integrated convective heat rate to determine which trajectory produces the minimum internal structural temperatures for a given thermal protection system. Three different thermal protection systems are considered: tile, blanket, and metallic.
Robert Windhorst↗
Formal Functional Test Designs with a Test Representation Language
The application of the category-partition method to the test design phase of hardware, software, or system test development is discussed. The method provides a formal framework for reducing the total number of possible test cases to a minimum logical subset for effective testing. An automatic tool and a formal language were developed to implement the method and produce the specification of test cases.
J M Hops↗
JPL Experience with the Mars Pathfinder, Mission Simulation Battery
A summary of the Mars Pathfinder Battery is given. The battery survived 47 days at 25 deg. C; it survived a 7 month stand at 10 to -5 deg. C; it met and exceeded 40 ampere-hour capacity for EDL; it met the 30 cycle minimum for Mars surface operation; and the project power profile for MArs surface operation does not yield energy balance.
Perrone, Dave↗
On-Demand Production of Hypergols: Steps Towards Scalability
During FY 2025, the team at KSC focused on taking the 2024 proof-of-concept demonstration of hypergol production using novel methods and began scaling up production and increasing purity. The team was able to more than triple the production of hydrazine using a novel method with a drastic increase in the purity. The current method, albeit still limited to production rates on the order of mg/hr, provides a cost savings of approximately 14x when compared to market value pricing through the Defense Logistics Agency (DLA) website. The benefit of this technology is the ability to produce some hypergolic fuels using constituents in Earth’s atmosphere, eliminating most chemical commodity logistics. This technology also allows for the return of domestic production of hypergolic propellant.
Kenneth Engeling↗
HST Replacement Battery Initial Performance
The Hubble Space Telescope (HST) original Nickel-Hydrogen (NiH2) batteries were replaced during the Servicing Mission 4 (SM4) after 19 years and one month on orbit.The purpose of this presentation is to highlight the findings from the assessment of the initial sm4 replacement battery performance. The batteries are described, the 0 C capacity is reviewed, descriptions, charts and tables reviewing the State Of Charge (SOC) Performance, the Battery Voltage Performance, the battery impedance, the minimum voltage performance, the thermal performance, the battery current, and the battery system recharge ratio,
Krol, Stan↗
Computation of Optimal Interplanetary Low-Thrust Trajectories With Bounded Thrust Magnitude By Means of the Generalized Newton-Raphson Method
The generalized Newton-Raphson method, an iterative procedure for solving nonlinear operator equations, has been extended in application to variational problems with bounded control variables. A minimum fuel interplanetary low thrust orbital transfer problem is worked out in detail to demonstrate the practical aspects of the algorithm as well as its computational effectiveness. The control variables are the thrust magnitude, limited from zero to some prescribed maximum value, and the thrust steering angle.
Computation↗
The 50 AMP-hour nickel cadmium battery manual
The battery is designed with a minimum battery to cell weight ratio consistent with adequate containment for operating conditions and dynamic environments and minimized weight. The battery is fully qualified and the environments to which it was successfully subjected were selected by NASA Goddard to cover a wide range of probable uses. The battery is suitable for either near-Earth geosynchronous missions, is compatible with passive or active thermal control systems and may be electrically controlled by a variety of changing routines. The initial application of the 50 A.H. Battery is a near-Earth mission aboard the LANDSAT D Satellite.
Webb, D. A.↗
Li-ion EMU Battery Testing
A 45Ah Lithium ion (Li-Ion) battery comprised of 5 Yardney prismatic cells was evaluated to replace the silver-zinc cells in the Extra-vehicular Mobility Unit (EMU). Tests determined that the five cell battery can meet the mission objective of 500 duty cycles and maintain a minimum voltage of 16.0 V without an individual cell voltage dropping below 3.0V. Forty real time cycles were conducted to develop BOL trend data. Decision to switch to accelerated cycling for the remaining 460 cycles was made since Real Time cycling requires 1 day/cycle. Conclusions indicate that battery replacement would indeed be prudent.
Rehm, Raymond↗
Biosynthesized Thermoplastic/Regolith Composites for Closed-Loop In-Space Manufacturing
In-Space Manufacturing (ISM) is vital to supporting a sustained human presence on the Moon or Mars. With payload launch prices ranging from $4,000 to more than $1 million per kg, reducing payload mass is of critical interest. Using in-situ resources for ISM is particularly attractive as it allows for a system of Earth-independent manufacturing for the Lunar surface, reducing the initial payload mass that is required for current ISM systems that rely on terrestrially synthesized materials. This talk presents new composite materials made from Lunar and Martian regolith and Poly(3-hydroxybutyrate) (PHB), a thermoplastic that offers the ability to be biosynthesized in space using various in-situ resources like organic waste or atmospheric CO2 as feedstock. The addition of regolith provides a route to creating materials with a diverse set of properties which will be discussed. The development of these materials represents the first step in creating a system of closed-loop ISM, which is critical to establishing a lasting human presence in space.
In situ resource utilization↗
Polymer/Regolith Composites for In-Space Manufacturing on the Moon and Mars
In-Space Manufacturing (ISM) is vital to supporting a sustained human presence on the Moon or Mars. With payload launch prices ranging from $4,000 to more than $1 million per kg, reducing payload mass is of critical interest. Using in-situ resources for ISM is particularly attractive as it allows for a system of Earth-independent manufacturing for the Lunar surface, reducing the initial payload mass that is required for current ISM systems that rely on terrestrially synthesized materials. This talk presents new composite materials made from Lunar and Martian regolith and Poly(3-hydroxybutyrate) (PHB), a thermoplastic that offers the ability to be biosynthesized in space using various in-situ resources like organic waste or atmospheric CO2 as feedstock. The addition of regolith provides a route to creating materials with a diverse set of properties which will be discussed. The development of these materials represents the first step in creating a system of closed-loop ISM, which is critical to establishing a lasting human presence in space.
In-situ resource utilization↗