Boris Yendler

A METHODOLOGY FOR ENVELOPING RELIABLE START-UP OF LHPS

The loop heat pipe (LHP) is known to have a lower limit on input power. Below this limit the system may not start properly creating the potential for critical payload components to overheat. The LHP becomes especially susceptible to these low power start-up failures following diode operation, intentional shut-down of the device, or very cold conditions. These limits are affected by the presence of adverse tilt, mass on the evaporator, and noncondensible gas in the working fluid. Based on analytical modeling correlated to startup test data, this paper will describe the key parameters driving this low power limit and provide an overview of the methodology for predicting a “safe start” design envelope for a given system and loop design. The amount of incipient superheat was found to be key to the enveloping procedure. Superheat levels have been observed to vary significantly based on evaporator design and even from unit to unit of identical designs. Statistical studies of superheat levels and active measures for limiting superheat should be addressed by both the hardware vendors and the system integrators.

Controlled ecological life support systems (CELSS) flight experimentation

The NASA CELSS program has the goal of developing life support systems for humans in space based on the use of higher plants. The program has supported research at universities with a primary focus of increasing the productivity of candidate crop plants. To understand the effects of the space environment on plant productivity, the CELSS Test Facility (CTF) has been been conceived as an instrument that will permit the evaluation of plant productivity on Space Station Freedom. The CTF will maintain specific environmental conditions and collect data on gas exchange rates and biomass accumulation over the growth period of several crop plants grown sequentially from seed to harvest. The science requirements of the CTF will be described, as will current design concepts and specific technology requirements for operation in micro-gravity.

Plant growth during the greenhouse II experiment on the Mir orbital station

We carried out three experiments with Super Dwarf wheat in the Bulgarian/Russian growth chamber Svet (0.1 m2 growing area) on the Space Station Mir. This paper mostly describes the first of these NASA-supported trials, began on Aug. 13, 1995. Plants were sampled five times and harvested on Nov. 9 after 90 days. Equipment failures led to low irradiance (3, then 4 of 6 lamp sets failed), instances of high temperatures (ca. 37 degrees C), and sometimes excessive substrate moisture. Although plants grew for the 90 d, no wheat heads were produced. Considering the low light levels, plants were surprisingly green, but of course biomass production was low. Plants were highly disoriented (low light, mirror walls?). Fixed and dried samples and the root module were returned on the U.S. Shuttle Atlantis on Nov. 20, 1995. Samples of the substrate, a nutrient-charged zeolite called Balkanine, were taken from the root module, carefully examined for roots, weighed, dried, and reweighed. The Svet control unit and the light bank were shipped to Moscow. An experiment validation test (EVT) of plant growth and experimental procedures, carried out in Moscow, was highly successful. Equipment built in Utah to measure CO2, H2O vapor, irradiance, air and leaf (IR) temperature, O2, pressure, and substrate moisture worked well in the EVT and in space. After this manuscript was first prepared, plants were grown in Mir with a new light bank and controller for 123 d in late 1996 and 39 days in 1996/1997. Plants grew exceptionally well with higher biomass production than in any previous space experiment, but the ca. 280 wheat heads that were produced in 1996 contained no seeds. Ethylene in the cabin atmosphere was responsible.

Noncondensible Gas, Mass, and Adverse Tilt Effects on the Start-up of Loop Heat Pipes

In recent years, loop heat pipe (LHP) technology has transitioned from a developmental technology to one that is flight ready. The LHP is considered to be more robust than capillary pumped loops (CPL) because the LHP does not require any preconditioning of the system prior to application of the heat load, nor does its performance become unstable in the presence of two-phase fluid in the core of the evaporator. However, both devices have a lower limit on input power: below a certain power, the system may not start properly. The LHP becomes especially susceptible to these low power start-ups following diode operation, intentional shut-down, or very cold conditions. These limits are affected by the presence of adverse tilt, mass on the evaporator, and noncondensible gas in the working fluid. Based on analytical modeling correlated to start-up test data, this paper will describe how the minimum power required to start the loop is increased due to the presence of mass, noncondensible gas, and adverse tilt. The end-product is a methodology for predicting a “safe start” design envelope for a given system and loop design.

Fuel Estimation for Stardust-NExT Mission

The success of the Stardust-NExT (New Exploration of Tempel 1) mission, which is a follow-on to the Stardust primary mission, depends upon an accurate knowledge of its remaining fuel. Measurements indicate that delaying the arrival of Stardust at Tempel 1 by at least 8 hours will maximize the probability of reaching the objective. Several techniques are used to measure the amount of remaining propellant in spacecraft. Bookkeeping, PVT (Pressure, Volume, and Temperature) and thermal Propellant Gauging System (PGS) are the most popular methods. The PGS method uses the temperature response of the tank to heating in order to infer the propellant load of the tank. Implementation of the PGS method for the Stardust spacecraft is discussed in the current paper. Along with the propellant estimation, an uncertainty analysis was conducted. The current paper compares fuel estimates made for Stardust by several techniques, including bookkeeping, PVT, and thermal PGS. These methods are described in detail, and their results and uncertainties for Stardust are compared. Based on these fuel estimates, project scientists have made their recommendations for the time-of-arrival adjustment. This paper shows how the PGS method can be useful for existing and future NASA/JPL missions. The accuracy of the fuel estimation by the thermal PGS method increases as the fuel load decreases due to the increased sensitivity of the temperature rise as the tank load decreases. The method can be used for mono- or bi-propellant propulsion systems with one-tank or multiple-tank configurations. Execution of the PGS method does not require model calibration during spacecraft Thermo-Vacuum Test.

Capillary Movement of Liquid in Granular Beds

Knowledge of capillary migration of liquids in granular beds in microgravity is essential for the development of a substrate based nutrient delivery sytem for the growth of plants in space. This problem is also interesting from the theoretical as well as the practical point of view. The purpose of this study was to model capillary water propagation through a granular bed in microgravity. In our ground experiments, water propagation is driven primarily by capillary force. Data for spherical partical sizes in the range from 0.46 to 2 mm have been obtained. It was shown that the velocity of water propagation is very sensitive to particle size. Theoretical consideration is also provided. Actual space flight experiments are planned for the future to confirm our results.

Options for Transpiration Water Removal in a Crop Growth System Under Zero Gravity Conditions

The operation of a microgravity crop-growth system is a critical feature of NASAs Closed Ecological Life Support System (CELSS) development program. Transpiration-evolved water must be removed from the air that is recirculated in such a system, perhaps supplying potable water in the process. The present consideration of candidate systems for CELSS water removal gives attention to energy considerations and to a mechanical, inertial-operation water-separation system that was chosen due to the depth of current understanding of its operation.

Preliminary evaluation of soil moisture probe for use with Arcillite.

There is a need for reliable methods of measuring the level and distribution of water in the solid substrates that are used for growing plants in space. In a microgravity environment, water distribution is governed generally by capillary forces. Arcillite is the solid substrate used in the ASTROCULTURE (TM) system which was developed for growing plants in space. The goal of this study is to evaluate the applicability of heat pulse moisture sensors for measuring moisture levels in Arcillite. The ASTROCULTURE system uses suction as a means of controlling the moisture level in Arcillite, but the spatial distribution of the moisture is left unknown. Studies of the moisture content in a cell experiment were conducted to calibrate a heat pulse moisture sensor and then the sensor was used in a suction experiment to verify moisture content and distribution. Results of the studies demonstrate that head pulse moisture sensors can be used to monitor moisture content and distribution within the root module of the ASTROCULTURE system.

Preliminary test results from the CELSS Test Facility Engineering Development Unit

As part of the NASA Controlled Ecological Life Support System (CELSS) Program, a CELSS Test Facility (CTF) is being planned for installation on the Space Station. The CTF will be used to provide data on the productivity and efficiency of a variety of CELSS higher plant crops grown in the microgravity environment of the Space Station. Tight environmental control will be maintained while data on gas exchange rates and biomass accumulation rates are collected. In order to obtain an early realistic determination of the subsystem and system requirements necessary to provide the environmental conditions specified for CTF crop productivity experiments, an Engineering Development Unit (EDU) has been designed, constructed and is in the process of subsystem and system testing at NASA Ames Research Center. The EDU is a ground test-bed which will be used to characterize the integrated performance of major subsystem technologies, to evaluate hardware candidates and control strategies required for the CTF, and to further define the ability to meet CTF requirements within present Space Station constraints. This paper reviews the functional requirements for the EDU, and focuses on the performance evaluation and test results of the various subsystems. Preliminary integrated performance results and control system operation are addressed, and plans for future science and technology testing are discussed.

An approach to the functional optimization of the CELSS Test Facility

An optimization of the CELSS Test Facility (CTF) subsystems and the entire CTF is necessary in order to meet strict limitations imposed on mass, volume, and power. Depending on the subsystem, other requirements must also be met. This paper shows the way to examine compatibility of requirements, to define an area of existing solutions (an operational envelope), and to find an optimal solution. The workability of the method is shown using problems of heat load on the Plant Growth Chamber, of optimization of the Vapor-Air Membrane Separation Device, and of finding a CTF configuration with minimum air pressure drop.