34,621 research outputs found
MULTI-AGENT SYSTEM OF PROTECTING INFORMATION FROM UNAUTHORIZED ACCESS
This article lists methods and tools for unlocking data from the local network. Modern methods and software tools for protecting data from unauthorized access from local area network have been analyzed. The advantages and disadvantages of the DLP (Data Loss / Leakage Prevention) system are demonstrated to protect data from unauthorized access. The criteria for increasing the effectiveness of the DLP system and the multi-intellect DLP system were suggested.ΠΠ΅ΡΠ΅ΡΠΈΡΠ»Π΅Π½Ρ ΠΌΠ΅ΡΠΎΠ΄Ρ ΠΈ ΠΈΠ½ΡΡΡΡΠΌΠ΅Π½ΡΡ Π΄Π»Ρ ΡΠ°Π·Π±Π»ΠΎΠΊΠΈΡΠΎΠ²ΠΊΠΈ Π΄Π°Π½Π½ΡΡ
ΠΈΠ· Π»ΠΎΠΊΠ°Π»ΡΠ½ΠΎΠΉ ΡΠ΅ΡΠΈ. ΠΡΠΎΠ°Π½Π°Π»ΠΈΠ·ΠΈΡΠΎΠ²Π°Π½Ρ ΡΠΎΠ²ΡΠ΅ΠΌΠ΅Π½Π½ΡΠ΅ ΠΌΠ΅ΡΠΎΠ΄Ρ ΠΈ ΠΏΡΠΎΠ³ΡΠ°ΠΌΠΌΠ½ΡΠ΅ ΡΡΠ΅Π΄ΡΡΠ²Π° Π·Π°ΡΠΈΡΡ Π΄Π°Π½Π½ΡΡ
ΠΎΡ Π½Π΅ΡΠ°Π½ΠΊΡΠΈΠΎΠ½ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ Π΄ΠΎΡΡΡΠΏΠ° ΠΈΠ· Π»ΠΎΠΊΠ°Π»ΡΠ½ΠΎΠΉ ΡΠ΅ΡΠΈ. ΠΠΎΠΊΠ°Π·Π°Π½Ρ ΠΏΡΠ΅ΠΈΠΌΡΡΠ΅ΡΡΠ²Π° ΠΈ Π½Π΅Π΄ΠΎΡΡΠ°ΡΠΊΠΈ ΡΠΈΡΡΠ΅ΠΌΡ DLP, ΠΏΡΠ΅Π΄Π½Π°Π·Π½Π°ΡΠ΅Π½Π½ΠΎΠΉ Π΄Π»Ρ ΠΏΡΠ΅Π΄ΠΎΡΠ²ΡΠ°ΡΠ΅Π½ΠΈΡ ΠΏΠΎΡΠ΅ΡΠΈ / ΡΡΠ΅ΡΠΊΠΈ Π΄Π°Π½Π½ΡΡ
ΠΎΡ Π½Π΅ΡΠ°Π½ΠΊΡΠΈΠΎΠ½ΠΈΡΠΎΠ²Π°Π½Π½ΠΎΠ³ΠΎ Π΄ΠΎΡΡΡΠΏΠ°. ΠΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½Ρ ΠΊΡΠΈΡΠ΅ΡΠΈΠΈ ΠΏΠΎΠ²ΡΡΠ΅Π½ΠΈΡ ΡΡΡΠ΅ΠΊΡΠΈΠ²Π½ΠΎΡΡΠΈ ΡΠΈΡΡΠ΅ΠΌΡ DLP ΠΈ ΡΠΈΡΡΠ΅ΠΌΡ DLP Ρ ΠΌΠ½ΠΎΠ³ΠΎΠ°Π³Π΅Π½ΡΠ½ΡΠΌ ΠΈΠ½ΡΠ΅Π»Π»Π΅ΠΊΡΠΎΠΌ
Lithium/sulfur dioxide cell and battery safety
The new high-energy lithium/sulfur dioxide primary electrochemical cell, having a number of advantages, has received considerable attention as a power source in the past few years. With greater experience and improved design by the manufacturers, this system can be used in a safe manner provided the guidelines for use and safety precautions described herein are followed. In addition to a description of cell design and appropriate definitions, there is a safety precautions checklist provided to guide the user. Specific safety procedures for marking, handling, transportation, and disposal are also given, as is a suggested series of tests, to assure manufacturer conformance to requirements
The NASA Aerospace Battery Safety Handbook
This handbook has been written for the purpose of acquainting those involved with batteries with the information necessary for the safe handling, storage, and disposal of these energy storage devices. Included in the document is a discussion of the cell and battery design considerations and the role of the components within a cell. The cell and battery hazards are related to user- and/or manufacturer-induced causes. The Johnson Space Center (JSC) Payload Safety Guidelines for battery use in Shuttle applications are also provided. The electrochemical systems are divided into zinc anode and lithium anode primaries, secondary cells, and fuel cells. Each system is briefly described, typical applications are given, advantages and disadvantages are tabulated, and most importantly, safety hazards associated with its use are given
Comparison of microbial contamination levels on barbac and cotton herringbone twill cloth
Microbial contamination levels on barbac and cotton twill for astronaut isolation garment
Flight representative positive isolation disconnect
Resolutions were developed for each problem encountered and a tradeoff analysis was performed to select a final configuration for a flight representative PID (Positive Isolation Disconnect) that is reduced in size and comparable in weight and pressure drop to the developmental PID. A 6.35 mm (1/4-inch) line size PID was fabricated and tested. The flight representative PID consists of two coupled disconnect halves, each capable of fluid isolation with essentially zero clearance between them for zero leakage upon disconnect half disengagement. An interlocking foolproofing technique prevents uncoupling of disconnect halves prior to fluid isolation. Future development efforts for the Space Shuttle subsystems that would benefit from the use of the positive isolation disconnect are also recommended. Customary units were utilized for principal measurements and calculations with conversion factors being inserted in equations to convert the results to the international system of units
Power conditioning techniques
The technological developments required to reduce the electrical power system component weights from the state-of-the-art 2.0 kg/kW to the range of 0.1 to 0.2 kg/kW are discussed. Power level requirements and their trends in aerospace applications are identified and presented. The projected weight and launch costs for a 1MW power converter built using state-of-the-art technology are established to illustrate the need for reliable, ultralightweight advanced power components. The key factors affecting converter weight are given and some of the tradeoffs between component ratings and circuit topology are identified. The weight and launch costs for a 1MW converter using 0.1 kg/kW technology are presented. Finally, the objectives and goals of the Multi-Megawatt Program at the NASA Lewis Research Center, which is funded by the SDIO through the Air Force, are given
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