The Shuttle's Science Objectives
		IN-CABIN PAYLOADS (excerpted from NASA Human Spaceflight) MSX The Midcourse Space Experiment contains no flight hardware. The payload will require orbiter thruster firings to be used as a sensor calibration and evaluation target for the space-based ultraviolet, infrared, and visible sensors on the MSX satellite. The satellite will be in an approximately 560 nautical mile, 99 degree inclination orbit. MSX was launched April 24, 1996. For MSX, a crew member will fire either the Primary Reaction Control System (PRCS) or Orbital Maneuvering System (OMS) thrusters while in the Field Of View (FOV) of the MSX satellite sensors. Thruster firing data may be collected during any encounter with the orbiter. MSX is sponsored by the United States Air Force Missile Systems Center and NASA. SIMPLEX The Shuttle Ionespheric Modification with Pulsed Local Exhaust payload has no flight hardware; Orbiter OMS thruster firings will be used to create ionospheric disturbances for observation by the SIMPLEX radars. SIMPLEX has four different radar sites used for collecting data: 1) Arecibo, 2) Kwajalein, 3) Milestone Hill, and 4) Jicamarca. One of the radar sites (Arecibo) will also use a low-level laser to observe the effects on the ionosphere resulting from the thruster firing. The objective of the SIMPLEX activity is to determine the source of Very High Frequency (VHF) radar echoes caused by the orbiter and its OMS engine firings. The Principal Investigator (PI) will use the collected data to examine the effects of orbital kinetic energy on ionospheric irregularities and to understand the processes that take place with the venting of exhaust materials. SIMPLEX sensors may collect data during any encounter opportunity when the orbiter support activities meet the criteria defined. SWUIS The Southwest Ultraviolet Imaging System is based around a rugged, 18 cm (7 inch) diameter Maksutov-design Ultraviolet (UV) telescope and a UV-sensitive, image-intensified Charge-Coupled Device (CCD) camera that frames at video frame rates. By combining the video data in a computer on the ground, scientists can obtain sensitive photometric measurements of astronomical targets. The video-framing also freezes out the attitude jitter of the Shuttle, thereby eliminating the need for the expensive pointing control platforms many Shuttle astronomy payloads have used in the past. The SWUIS is stored in the orbiter middeck lockers during launch and entry and is assembled for on-orbit operations. The SWUIS will be mounted in either the orbiter side hatch window, Aft Flight Deck (AFD) overhead windows, or the pilot-side forward window via Space Shuttle Provided (SSP) standard mounts/brackets and a customer provided mount adapter. Onboard STS-93, SWUIS will be exploring both the Earth and the planets. Observations are planned to study upper atmospheric airglow, and to image the Moon in the UV for the first time in order to study space weathering. Other observations will include the search for a long-suspected population of small bodies orbiting close to the Sun, called the Vulcanoids. SWUIS will also obtain the first-ever measurements of the reflectivity of Mercury in the UV and finally search for new species in the magnetospheres of Jupiter and Saturn. SWUIS will be making its second flight aboard STS-93. GOSAMR The Gelation of Sols: Applied Microgravity Research is a middeck experiment allowing chemical gelation to form precursors for advanced ceramic materials by the mixing of nanometer-sized colloidal sols doped with micron and larger particulate matter and a gelling agent. The overall objective of GOSAMR is to investigate the influence of microgravity on the processing of gelled sols. In particular, the purposes are to demonstrate that composite ceramic precursors composed of large particulates and small colloidal sols can be produced in space with more structural uniformity. It will also show that this improved uniformity will result in finer matrix grain sizes and superior physical properties. Postflight analytical characterization techniques will be employed to ascertain differences in physical structure and properties between microgravity and Earth-processed samples. The payload will be housed in one standard NASA-supplied middeck stowage locker. The payload will incorporate chemical containment to provide for hazard control. Typical chemical components will be either colloidal silica sols doped with organic and inorganic colloidal particulates. Fifty to one hundred 5 cc samples will be generated by varying the particle sizes and loadings, the length of gelation times, and sol sizes. STL-B The objectives of the Space Tissue Loss - B experiment are to validate models for muscle, bone, and endothelial cell biochemical and functional loss induced by microgravity stress; to evaluate cytoskeleton, metabolism, membrane integrity and protease activity in target cells, and to test tissue loss pharmaceuticals for efficacy. The focus of STL-B is direct video observation of cells in culture through the use of a video microscope imaging system with the objective of demonstrating near real-time interactive operations to detect and induce cellular responses. Experiment activities can be performed without any crew intervention other than initiation of the experiment at the beginning of on-orbit payload operations and termination of the experiment prior to deorbit preparation. LFSAH The Light Weight Flexible Solar Array Hinge consists of several hinges fabricated from shape memory alloys. Shape memory deployment hinges offer controlled shockless deployment of solar arrays and other spacecraft appendages. LFSAH demonstrates this deployment capability for a number of hinge configurations. The experiment is contained in a single enclosure that requires 28 volt DC external power. Actuation of the hinges is accomplished by serial activation of front panel switches. LFSAH operations are monitored and displayed on front panel Light Emitting Diodes (LEDs). Data is logged using a self-contained system as well as video taped using the standard 8mm camcorder. CCM The objectives of the Cell Culture Module are to validate models for muscle, bone, and endothelial cell biochemical and functional loss induced by microgravity stress; to evaluate cytoskeleton, metabolism, membrane integrity and protease activity in target cells; and to test tissue loss pharmaceuticals for efficacy. The experiment unit fits into a single standard middeck locker which has a modified locker door with its panels removed. The experiment consists of two major subassemblies, the power/electronics module and the analysis module. The CCM-C configuration also incorporates fluid path cooling. This is provided by a 4° C active cooling chamber and associated cabling and driver circuitry for active media cooling. Experiment activities can be performed without any crew intervention other than initiation of the experiment at the beginning of on-orbit payload operations and termination of the experiment prior to deorbit preparation. SAREX II The Shuttle Amateur Radio Experiment is designed to demonstrate the feasibility of amateur short-wave radio contacts between the shuttle and ground-based amateur radio operators, often called "hams". SAREX also serves as an educational opportunity for schools around the world to learn about space first hand by speaking directly to astronauts aboard the shuttle via ham radio. Ham radio operators will communicate with the shuttle using VHF-FM voice transmission, a mode that makes contact widely available without the purchase of expensive equipment. SAREX-II will be using Configuration C-Q which is the same as configuration C with the exception that the Digital Signal Processor (DSP) Unit installed between the headset and the SAREX Interface Module. The function of the DSP Unit is to provide digital signal processing of the downlink and uplink audio transmissions to enhance the voice clarity and quality. SAREX II C-Q will include all of the components of Configuration C. Configuration C consists of the hand held FM transceiver, interface module, payload and general support computer (PGCS), spare battery set, window antenna, packet module, SAREX headset assembly, personal recorder, and the required cable assemblies. The packet module contains a power supply and packet terminal node controller (TNC). The power supply provides power for the TNC and the hand held transceiver. The TNC interconnects with a radio transceiver so that data to and from the computer is transmitted to and received from other amateur radio stations. Configuration C is capable of operating in either the voice or data mode in communications with amateur stations within loss of sight (LOS) of the orbiter. This configuration can be operated in the attended mode for voice communication and either the attended or automatic mode for data communications. EarthKAM The EarthKAM payload will conduct Earth observations using the Electronic Still Camera (ESC) installed in the overhead starboard window of the Aft Flight Deck (AFD). The EarthKAM payload will use an ESC provided as Government-furnished Equipment (GFE), a Payload and General Support Computer (PGSC) (IBM Thinkpad 755C) connected to the onboard Ethernet Local Area Network (LAN), and Personal Computer Memory Card International Association (PCMCIA)/Small Computer System Interface (SCSI) cards with integral cable. The ESC will be bracket-mounted to the overhead window facing nadir to image various student-selected sites on the Earth. Other than equipment setup, initial camera pointing, and possible camera lens changes, no crew intervention is required for nominal operations. The EarthKAM desires the use of a dedicated ESC and can share the PGSC resource with other Space Shuttle Program (SSP) users. EarthKAM requires that the PGSC be connected to the onboard Ethernet LAN to accomplish the EarthKAM primary flight objectives unless the OCA PGSC is used to support the EarthKAM operations. During each night-time orbital period, EarthKAM image data and log files will be remotely downlinked via Ku-band Channel 2 or 3 and the Camera Control Files (CCF) will be uplinked by command from the ESC-OCA/EarthKAM console located in the Mission Control Center (MCC). PGIM The Plant Growth Investigations in Microgravitypayload is a series of experiments which will be flown in the Plant Growth Facility (PGF). The PGF will support whole plant growth for up to 30 days by providing acceptable environmental conditions for normal plant growth. The scientific experiments will be selected from investigators who respond to the annual Office of Life and Microgravity Science and Applications' (OLMSA) NASA Research Announcement (NRA). The PGF is composed of the following subsystems: Control and Data Management (CDMS), Fluorescent Light Module (FLM), Atmospheric Control Module (ACM), Plant Growth Chambers (PGC), Support Structure Assembly (SSA), and the Generic External Shell (GES). The complete PGF will replace one middeck locker and operates on 28 V direct current (dc) power. CGBA The Commercial Generic Bioprocessing Apparatus payload hardware allows for sample processing and stowage functions. The Generic Bioprocessing Apparatus - Isothermal Containment Module (GBA-ICM) is temperature controlled to maintain a preset temperature environment, controls the activation and termination of the experiment samples, and provides an interface for crew interaction, control and data transfer. The GBA-ICM is a self-contained incubation and refrigeration module unit used to stow and process several types of experiments in microgravity. The GBA-ICM housing is a lightweight aluminum/insulation clad structure. The front portion of the housing contains the electronics, thermal and crew interface subsystems. The rear portion of the unit is the isolated, temperature-controlled portion that houses the experiment sample containers; i.e, standard GSP's, T-GAPS, Auto-GAP's, Illuminated Culture Vessels (ICV's), or cameras. Each GBA-ICM can be fitted with an internal light source. The fluid cooling/heating loops embedded between the aluminum casing and the foam insulation are used to maintain accurate preset temperatures. The CGBA payload will be flown in Configuration A which contains two GBA-ICM units. MEMS The Micro-Electrical Mechanical System payload examines the performance, under launch, microgravity, and reentry conditions of a suite of MEMS devices. These devices include accelerometers, gyros, and environmental and chemical sensors. The MEMS payload is self-contains and requires activation and deactivation only. All experiment monitoring and data recording is done through integrated components. Power, however, is required from just prior to ascent through deorbit. The MEMS payload will utilize one middeck locker and a modified door (front panels removed). An accelerometer and mounting plate will be attached to the inside back of the middeck locker prior to insertion into the orbiter. A power cable will be connected to the payload's locker during installation into the orbiter. BRIC The Biological Research in Canisters payload was designed to investigate the effects of space flight on small arthropod animals and plant specimens. The BRIC payload has three hardware configurations defined by a specific flight's scientific requirements. STS-93 will be using the Block II configuration which consists of two BRIC 60 canisters, one pair of cryogenic gloves, and one gaseous nitrogen freezer (GN2) in a single middeck locker. The flight crew will be available at regular intervals to monitor and control payload/experiment operations. The Block II configuration will also require a crew member to don a pair of insulating gloves, remove a canister from the locker and replace it in the GN2 freezer. Return to Science Objectives

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