Robotic Air Vehicle: A Pilot's Perspective

This paper focuses on concepts and technologies required to develop a robotic air vehicle (RAV). A vehicle of this type has the capability to be a launch and forget weapon system. The authors are engineers and pilots so they view both the technical approach and piloting issues with equal importance. RAV must have the machine intelligence to make decisions within the mission and battlefield constraints. This requires a piloting expert system and route planner to perform passive terrain following, terrain avoidance, obstacle avoidance, and autonomous navigation based on low cost sensor inputs such as a multifunction FLIR, digital terrain map, and directional reference systems. RAV is a cost effective way to fight in a threat environment where aircrew loss rates would be unacceptable. RAV provides the Air Force a means to expand its combat capabilities.     

Determining electron density profiles for the middle ionosphere

Using daytime numerical ionospheric profiles from W. Becker's mid-latitude collection, the geometric parameters of 3 or 4 LAY-functions were determined by best fit while all amplitudes were redetermined step by step with a least squares criterion. It appeared that the transition height and scale of the main function are interrelated while all other geometric parameters are independent. Median values for a spring and a summer period are found, and relations with the peak altitude and half-density thickness of the input profile are established.     

Electron density reference profile in the lower ionosphere

The new IRI formula, as accepted at the 1983 Stara Zagora Workshop, prescribes the use of Epstein functions for reproducing logarithmic electron density profiles. In this paper we discuss solutions which might be applicable to the lower ionosphere. The experimental data base is briefly reviewed. It appears that the stratification near 80 km must be accepted as a regular feature of the daytime lower ionosphere. The C-layer problem is left open. In order to reproduce such profiles, one needs three LAY-functions. Examples show that the weighted sum of these does very well represent experimental profiles, the amplitudes being determined by a least square fit. For profile synthesis (as in IRI) a least square determination of the three amplitudes, admitting four linear conditions, is proposed.     

The MESSENGER Spacecraft

The MErcury Surface, Space ENvironment, GEochemistry, and Ranging (MESSENGER) spacecraft was designed and constructed to withstand the harsh environments associated with achieving and operating in Mercury orbit. The system can be divided into eight subsystems: structures and mechanisms (e.g., the composite core structure, aluminum launch vehicle adapter, and deployables), propulsion (e.g., the state-of-the-art titanium fuel tanks, thruster modules, and associated plumbing), thermal (e.g., the ceramic-cloth sunshade, heaters, and radiators), power (e.g., solar arrays, battery, and controlling electronics), avionics (e.g., the processors, solid-state recorder, and data handling electronics), software (e.g., processor-supported code that performs commanding, data handling, and spacecraft control), guidance and control (e.g., attitude sensors including star cameras and Sun sensors integrated with controllers including reaction wheels), radio frequency telecommunications (e.g., the spacecraft antenna suites and supporting electronics), and payload (e.g., the science instruments and supporting processors). This system architecture went through an extensive (nearly four-year) development and testing effort that provided the team with confidence that all mission goals will be achieved. Larry E. Mosher passed away during the preparation of this paper.     

Erforschung der ionosphäre mit radiowellen von satelliten und raketen. Phasen-verfahren

Space Science Reviews -     

Berichtigung von druckfehlern

Ohne Zusammenfassung     

Erforschung der ionosphäre mit radiowellen von satelliten und raketen

Ohne Zusammenfassung     

Germination and elongation of flax in microgravity.

This experiment was conducted as part of a risk mitigation payload aboard the Space Shuttle Atlantis on STS-101. The objectives were to test a newly developed water delivery system, and to determine the optimal combination of water volume and substrate for the imbibition and germination of flax (Linum usitatissimum) seeds in space. Two different combinations of germination paper were tested for their ability to absorb, distribute, and retain water in microgravity. A single layer of thick germination paper was compared with one layer of thin germination paper under a layer of thick paper. Paper strips were cut to fit snugly into seed cassettes, and seeds were glued to them with the micropyle ends pointing outward. Water was delivered in small increments that traveled through the paper via capillary action. Three water delivery volumes were tested, with the largest (480 microliters) outperforming the 400 microliters and 320 microliters volumes for percent germination (90.6%) and root growth (mean=4.1 mm) during the 34-hour spaceflight experiment. The ground control experiment yielded similar results, but with lower rates of germination (84.4%) and shorter root lengths (mean=2.8 mm). It is not clear if the roots emerged more quickly in microgravity and/or grew faster than the ground controls. The single layer of thick germination paper generally exhibited better overall growth than the two layered option. Significant seed position effects were observed in both the flight and ground control experiments. Overall, the design of the water delivery system, seed cassettes and the germination paper strip concept was validated as an effective method for promoting seed germination and root growth under microgravity conditions.     

The state of the art in D-region IRI modelling

While describing the formulation of IRI-79, in so far as it is applicable to the sub E-peak electron density profile, an attempt is made to compare its predictions with the available experimental evidence. The improvements needed for D-region electron density modelling are summarized. The current D-region IRI modelling effort is illustrated with a typical example.