Apollo 11 lunar surface operations plan Final report
Apollo 11 mission planning for lunar surface exploration including equipment requirements, crew/equipment interfaces, and timelines for extravehicular activities
Wood, W. H., Jr.↗
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Crew interface definition study, phase 1
The timeline analysis of the Shuttle orbiter missions which was conducted in the Phase I Crew Interface Definition Study and the requirements for the man-in-the-loop simulation study are presented. Mission definitions and objectives are presented as they relate to various Shuttle Orbiter missions. The requirements for crew participation and the information required by the crew are discussed, and finally the rationale behind the display concept and calling procedures is given. The simulation objectives, the simulation mechanization, including a detailed presentation of the display and control concept, the simulator test plan and the results are discussed.
Callihan, J. C.↗
Shuttle on-orbit rendezvous targeting: Circular orbits
The strategy and logic used in a space shuttle on-orbit rendezvous targeting program are described. The program generates ascent targeting conditions for boost to insertion into an intermediate parking orbit, and generates on-orbit targeting and timeline bases for each maneuver to effect rendezvous with a space station. Time of launch is determined so as to eliminate any plane change, and all work was performed for a near-circular space station orbit.
Bentley, E. L.↗
Space Shuttle flight crew/computer interface simulation studies.
An approach to achieving an optimized set of crew/computer interface requirements on the Space Shuttle program is described. It consists of defining the mission phases and crew timelines, developing a functional description of the crew/computer interface displays and controls software, conducting real-time simulations using pilot evaluation of the interface displays and controls, and developing a set of crew/computer functional requirements specifications. The simulator is a two-man crew station which includes three CRTs with keyboards for simulating the crew/computer interface. The programs simulate the mission phases and the flight hardware, including the flight computer and CRT displays.
Callihan, J. C.↗
Astronomy sortie missions definition study. Volume 2, book 2: Appendix
An updated and coordinated baseline experiment definition document is presented for each of the candidate astronomy sortie mission telescopes and arrays. The experiment objectives, requirements, interfaces, timelines, and programmatic considerations are included.
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Shuttle sortie simulation using a Lear jet aircraft: Mission no. 1 (assess program)
The shuttle sortie simulation mission of the Airborne Science/Shuttle Experiments System Simulation Program which was conducted using the CV-990 aircraft is reported. The seven flight, five day mission obtained data on experiment preparation, type of experiment components, operation and maintenance, data acquisition, crew functions, timelines and interfaces, use of support equipment and spare parts, power consumption, work cycles, influence of constraints, and schedule impacts. This report describes the experiment, the facilities, the operation, and the results analyzed from the standpoint of their possible use in aiding the planning for experiments in the Shuttle Sortie Laboratory.
Mulholland, D. R.↗
Shuttle-Attached Manipulator System requirements.
Shuttle mission requirements and cost objectives have led to the selection of a Shuttle-Attached Manipulator System (SAMS) as a general purpose mechanism for docking, payload handling, and the general launch and retrieval of free-flying satellites. SAMS design requirements are discussed, giving attention to end effectors, kinematics, timelines, dynamics, load ratings, TV cameras and lights. Requirements for low-cost payload satellites are considered, taking into account satellites with modular subsystems which are designed for replacement and for resupply in orbit by SAMS.
Bodey, C. E.↗
Description of the docking module ECS for the Apollo-Soyuz Test Project.
The role of the Docking Module ECS (Environmental Control System) to be used on the Apollo-Soyuz Test mission is to provide a means for crewmen to transfer safely between the Apollo and Soyuz vehicles in a shirtsleeve environment. This paper describes the Docking Module ECS and includes the philosophy and rationale used in evaluating and selecting the capabilities that are required to satisfy the Docking Module's airlock function: (1) adjusting the pressure and composition of the atmosphere to effect crew transfer and (2) providing a shirtsleeve environment during transfer operations. An analytical evaluation is given of the environmental parameters (including CO2 level, humidity, and temperature) during a normal transfer timeline.
Guy, W. W.↗
Sleep-monitoring, experiment M133
The Skylab sleep-monitoring experiment simulated the timelines and environment expected during a 56-day Skylab mission. Two crewmembers utilized the data acquisition and analysis hardware, and their sleep characteristics were studied in an online fashion during a number of all night recording sessions. Comparison of the results of online automatic analysis with those of postmission visual data analysis was favorable, confirming the feasibility of obtaining reliable objective information concerning sleep characteristics during the Skylab missions. One crewmember exhibited definite changes in certain sleep characteristics (e.g., increased sleep latency, increased time Awake during first third of night, and decreased total sleep time) during the mission.
Frost, J. D., Jr.↗
Unmanned surface traverses of Mars and Moon: Science objectives, payloads, operations
Science objectives and properties to be measured are outlined for long surface traverse missions on Mars and the Moon, with remotely-controlled roving vehicles. A series of candidate rover payloads is proposed for each planet, varying in weight, cost, purpose, and development needed. The smallest weighs 35 kg; the largest almost 300 kg. A high degree of internal control will be needed on the Mars rover, including the ability to carry out complex science sequences. Decision-making by humans in the Mars mission includes supervisory control of rover operations and selection of features and samples of geological and biological interest. For the lunar mission, less control on the rover and more on earth is appropriate. Science portions of the rover mission profile are outlined, with timelines and mileage breakdowns. Operational problem areas for Mars include control, communications, data storage, night operations, and the mission operations system. For the moon, science data storage on the rover would be unnecessary and control much simpler.
Jaffe, L. D.↗
Payload analysis for space shuttle applications (study 2.2). Volume 3: Payload system operations analysis (task 2.2.1)
The technical and cost analysis that was performed for the payload system operations analysis is presented. The technical analysis consists of the operations for the payload/shuttle and payload/tug, and the spacecraft analysis which includes sortie, automated, and large observatory type payloads. The cost analysis includes the costing tradeoffs of the various payload design concepts and traffic models. The overall objectives of this effort were to identify payload design and operational concepts for the shuttle which will result in low cost design, and to examine the low cost design concepts to identify applicable design guidelines. The operations analysis examined several past and current NASA and DoD satellite programs to establish a shuttle operations model. From this model the analysis examined the payload/shuttle flow and determined facility concepts necessary for effective payload/shuttle ground operations. The study of the payload/tug operations was an examination of the various flight timelines for missions requiring the tug.
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IUS/TUG orbital operations and mission support study. Volume 3: Space tug operations
A study was conducted to develop space tug operational concepts and baseline operations plan, and to provide cost estimates for space tug operations. Background data and study results are presented along with a transition phase analysis (the transition from interim upper state to tug operations). A summary is given of the tug operational and interface requirements with emphasis on the on-orbit checkout requirements, external interface operational requirements, safety requirements, and system operational interface requirements. Other topics discussed include reference missions baselined for the tug and details for the mission functional flows and timelines derived for the tug mission, tug subsystems, tug on-orbit operations prior to the tug first burn, spacecraft deployment and retrieval by the tug, operations centers, mission planning, potential problem areas, and cost data.
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Digital command system
The correct processing of the Digital Command System (DCS), which provides a limited real-time means of controlling specific flight program functions, was verified. The ability of the flight program to correctly read and process DCS commands was verified. Tests made by the flight program after reading the contents of the command decoder register to establish the validity of the received data were verified through the following: DCS mode command verification, DCS data command verification, DCS data validation, and DCS error message. The operation of the following DCS commands accepted and processed by the flight program was tested: time base update, navigation update, generalized switch selector, memory dump, terminate, execute generalized maneuver, return to nominal timeline, ECS water control valve logic inhibit, execute maneuver, execute alternate sequence, targeting load, ladder magnitude limit, S-IVB/IU de-orbit, compressed data dump, and remove inhibit on the extraction maneuver.
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Simulation of man-machine interaction on shuttle payload manipulator
The main objective of this simulation was to evaluate the feasibility of a simplified control system for a remote manipulator for space shuttle payloads. The motion commanded by the operator through the control system to the six degree of freedom manipulator approximates that of a backhoe. Compatibility of low arm damping, heavy payloads, small clearances in the shuttle cargo bay and stringent mission timelines were evaluated. The effects of various devices to enhance visual cues were evaluated. Phase I of the simulation was capture of a payload flying free in space relative to the shuttle. Phase II was simulation of cargo stowage into a mockup of the space shuttle cargo bay. A shuttle remote manipulator control station mockup including TV monitors and hand controllers is used in the simulation. Results evaluating various parameters of the control system and the task, including arm flexibility, are presented.
Hookway, R. O.↗
Review of extravehicular activity for Shuttle program
Extravehicular activity (EVA) is a baselined Shuttle Orbiter capability. It can provide cost-effective servicing operations for payloads, on-orbit repair, and techniques for meeting various on-orbit contingencies. The basic EVA system planned consists of Orbiter-integral provisions, carry-on life support provisions, and EVA support equipment provisions. The Orbiter-integral provisions include the internal airlock, the EVA Egress module, and the docking module, each of which provides an egress path. The carry-on life support provisions will be two Extravehicular Mobility Units (EMU), composed of an Astronaut Life Support Assembly (ALSA) and a Space Suit Assembly (SSA). The support equipment includes tethers, special tools, translation aids, and workstations. The Shuttle Orbiter EVA requirements and possible tasks, EVA crew rescue equipment and techniques, crew support, EVA training, and EVA timeline activities are described.
Covington, J. H.↗
PPP/nonreal-time trajectory program interface requirements and capabilities
The selection process for interfacing a nonreal time trajectory program with the procedures and performance program is outlined; the interface provides summary data timelines for any desired trajectory profile. Consideration was given to two separate digital programs for satisfying capabilities. One was the CDC 6400 digital program BANDITO, and the second was the UNIVAC 1110 SVDS program.
Mcgavern, J. L.↗
User's manual for the Shuttle Electric Power System analysis computer program (SEPS), volume 2 of program documentation
The Shuttle Electric Power System Analysis SEPS computer program which performs detailed load analysis including predicting energy demands and consumables requirements of the shuttle electric power system along with parameteric and special case studies on the shuttle electric power system is described. The functional flow diagram of the SEPS program is presented along with data base requirements and formats, procedure and activity definitions, and mission timeline input formats. Distribution circuit input and fixed data requirements are included. Run procedures and deck setups are described.
Bains, R. W.↗
Atmospheric science facility pallet-only mode space transportation system payload (feasibility study), Volume 1
The economic and technical feasibility is assessed of employing a pallet-only mode for conducting Atmospheric Magnetospheric Plasmas-in-Space experiments. A baseline design incorporating the experiment and instrument descriptions is developed. The prime instruments are packaged into four pallets in a physical and functional manner compatible with the Space Transportation System capabilities and/or constraints and an orbiter seven-day mission timeline. Operational compatibility is verified between the orbiter/payload and supporting facilities. The development status and the schedule requirements applicable to the Atmospheric Science Facility mission are identified. Conclusions and recommendations are presented and discussed.
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