Lower thermospheric density structure derived from late decay phases of satellite orbits

In order to obtain new insight into the detailed structure of the lower thermosphere the long-established method of drag analysis again proves to be a powerful tool. For near-circular satellite orbits, in addition to the semi-major axis, the eccentricity and the argument of perigee are strongly influenced by atmospheric drag. With the help of a new computational scheme, which is based on fundamental equations of satellite drag analysis, the amplitudes and phases of global density variations are derived.     

Future Directions in Automation and Robotics for Manufacturing

The current emphasis on designing flexible manufacturing systems, particularly in the electronics manufacturing industry, is bringing automation and robotics technologies to the factory at increasing rates. The rate of advance in these technologies raises serious concerns among engineers and managers about how to proceed in building modern manufacturing systems. A large portion of this uncertainty results from the difficulty of fitting technological advances into the existing models of manufacturing. What is needed is a new framework within which to perceive automation and robotics which will permit the adoption of more encompassing design strategies and principles to be followed in the practice of modernizing and maintaining advanced electronics manufacturing systems. This paper provides a framework that might be adopted to structure new strategies for incorporating automation and robotics in manufacturing. The approach is one that we at SRI have found useful in considering automation and robotics issues for the NASA Space Station and other complex systems which need to incorporate new technologies throughout long lifetimes. These same issues are becoming increasingly important in electronics manufacturing system design and development.     

The Lunar Orbiter Laser Altimeter Investigation on the Lunar Reconnaissance Orbiter Mission

The Lunar Orbiter Laser Altimeter (LOLA) is an instrument on the payload of NASA’s Lunar Reconnaissance Orbiter spacecraft (LRO) (Chin et al., in Space Sci. Rev. 129:391–419, 2007). The instrument is designed to measure the shape of the Moon by measuring precisely the range from the spacecraft to the lunar surface, and incorporating precision orbit determination of LRO, referencing surface ranges to the Moon’s center of mass. LOLA has 5 beams and operates at 28 Hz, with a nominal accuracy of 10 cm. Its primary objective is to produce a global geodetic grid for the Moon to which all other observations can be precisely referenced.     

Verifying command sequences for satellite systems

A formal basis for the design of a checker used in validating safe schedules and in selecting error recovery schedules for satellite control systems is presented. This design includes a high-level specification of checker behavior and properties (called flight rules) of safe schedules. Specifications are written in timed linear logic (TLL). Validation of schedules is performed in terms of real-time telemetry and deduction system proof rules. Telemetry (state information for satellite subsystems) serves as input to the checker. Detection of violation of a flight rule by the checker results in the selection of a contingency plan (error recovery schedule). The checker is illustrated by an example involving the TOPEX/Poseidon Oceanographic Satellite System     

Potential cost reductions for three STS/Spacelab mission modes

Based on the results of studies carried out by ESA several possibilities are discussed to achieve mission cost reductions for large Spacelab instrument facilities as compared to their flight on several 7-day duration Spacelab missions. As an example three scientific telescope facilities are selected (LIRTS, EXSPOS, GRIST) which are defined to a Phase A level.Three new mission modes are considered:

• —Shuttle attached Spacelab mission mode with extended flight duration (up to 30 days) for which the application of planned capability extensions and new elements of the STS/Spacelab (e.g. Short Spacelab Pallets, Power Extension Package) are investigated.

• —Shuttle deployed mission mode, for which the telescope, accommodated on a Spacelab pallet, is docked to the Power Module, a new element of the Space Transportation System under study by NASA.

• —Free-flying mission mode, for which Shuttle launched dedicated missions of the facilities are considered, assuming varying degrees of autonomy with respect to supporting services of the Shuttle.

Reduction of costs have been considered on the levels of single mission cost and total programme cost. Fundamentally the charges for the instrument can be reduced by constraining the mass/volume factors with respect to the Shuttle capability. However, the instrument as part of a payload is only viable if an acceptable resource sharing including observation time can be achieved. Any single instrument will require several mission opportunities or one mission which achieves a similar or longer total observation programme.Based on an identification of instrument modifications of the Phase A baseline designs to favour cost reductions and on a derivation of technical requirements, constraints and finally budgetary cost comparisons an attempt is made to assess the advantages and disadvantages of the different mission modes.The favoured option for GRIST is a 2–3 weeks sortie mission followed after refurbishment by a longer Power Module docked mission. For LIRTS and EXSPOS the free-flying pallet modes are very attractive in terms of the longer durations achieved and in terms of cost per unit operating time.     

Communicating processes in designing asynchronous circuits

Asynchronous circuits are circuits that operate without a common global clock. They are potentially suitable for low-power devices. This paper describes an approach to verify speed-independent asynchronous circuits by using a protocol validation tool