Refine Your Search

Topic

Author

Affiliation

Search Results

Book

Everything Works Wonderfully

2014-07-01
EVERYTHING WORKS WONDERFULLY is a 250-page A4 softback book written to provide a structured source of guidance and reference information on Servitization and the management of physical assets for people at all levels in industry: • Senior executives considering the expansion of their businesses into the provision of Asset Management services for the products they design and manufacture; • Middle management wishing to know what needs to be done to look after the assets they are responsible for and who to approach for help; • ‘Hands-on’ engineers looking for contacts and advice on detailed tools and techniques. • Academics may also find the book useful as a source of contacts and ideas for research.
Standard

Verification Methods for MIL-STD-1760 Stores

2017-08-09
WIP
AS42702
This document establishes techniques for verifying that a Mission Store Interface (MSI) complies with the interface requirements delineated in MIL-STD-1760 Revision E.
Standard

Broadband 1553

2018-05-22
WIP
AS8774
This standard defines a broadband time division command/response multiplex data bus that co-exists and permits concurrent operation with a MIL-STD-1553 Data Bus and MIL-STD-1760 Appendix C. This standard allows utilization of legacy MIL-STD-1553 wiring and bus coupling.
Standard

Aerospace TSN Profile

2019-10-24
WIP
AS6675
Develop a profile of the TSN set of standards that is applicable to Avionics use cases, including AS6509 CAIN
Technical Paper

U.S. Drafted Guidelines on Orbital Debris and How to Convince Space Industries to Use Them

2000-03-06
2000-01-1370
Orbital debris mitigation policy has become outdated, and corporations that have an interest in space commerce have historically underused it. This paper studies the policy aspect of orbital debris mitigation, focusing on debris originating from spent rocket stages and telecommunications satellites. The commercialization of space, in particular the Lower Earth Orbit (LEO) has increasingly drawn the interest of space flight and telecommunications industries. This paper shows how new standards, policies, and regulations could affect industrial practices related to orbital debris mitigation. The formation of new policies will have a significant impact on commercial space industries.
Technical Paper

On the Insertion of a Legacy Conversion System into a Collaborative Virtual Prototyping System

2000-05-16
2000-01-1732
The paper has two main goals. Firstly, it emphasizes the importance of including a legacy CAD data conversion system into a collaborative virtual prototyping (CVP) environment. 2D legacy data is of great intellectual value to the designer as reference data for designing new parts. Therefore, a legacy conversion system will help the user model parts more efficiently than by starting from scratch. This paper will then discuss a feature extraction system (FES) as a potential solution. This FES has the ability to automatically convert 2D legacy data into a variety of part formats and representations in a feature-based form, where the feature-based model representation provides more essential semantic data to designers and analysis. Secondly, this paper will describe how this feature extraction system can be inserted and interfaced into a CVP environment. There are several aspects to this task. Firstly, identifying a suitable architecture to use as the basic CVP infrastructure.
Technical Paper

Development and In-orbit Performance of a Thermal Control System for Nickel-Cadmium Batteries Based on Loop Heat Pipes

2000-07-10
2000-01-2456
In 1995 TAIS Ltd developed and manufactured a Thermal Control System (TCS) for Nickel-Cadmium Batteries (NCB) based on Loop Heat Pipes (LHP). This TCS was ordered for the Chinese meteorological satellite FY-1C by Shanghai Institute of Spacecraft Engineering. The paper presents results of comparative analysis for some design features of the TCS, thermal vacuum test results, description of TCS layout for the NCB on board the FY-1 C satellite, test results for TSC after its integration into the satellite and flight telemetry data.
Technical Paper

STENTOR CPL: Ground Test and Modelling Results

2000-07-10
2000-01-2454
Necessity of thermal control of dissipative units located on the earth panel and thermally linked to the North and South radiators of a telecommunication satellite has been identified since many years ago. The thermal control of TV SAT TDF platforms was defined using this concept, but necessitated a complex heat pipe networks with on-ground test constraints. The emergence of the capillary-pumped two-phase loop authorises to perform the same function using one item with virtually no on-ground test constraints. Since 1995, Alcatel Space Cannes (formerly Aerospatiale Cannes), sponsored by CNES, have developed a STENTOR (“Satellite de Télécommunication pour l'Expérimentation de Nouvelles Technologies en Orbite”) 1000 W CPL. The ground qualification has been completed in 1999 and the flight qualification is planned late 2000 (launch of STENTOR satellite).
Technical Paper

An Overview of the Thermal Verification and Testing of Integral and Artemis Satellites

2000-07-10
2000-01-2497
Integral (INTErnational Gamma Ray Astrophysics Laboratory) is an ESA observatory scientific satellite to be used for gamma ray astronomy, while Artemis (Advanced Relay and TEchnology MISsion) is an ESA program to be used for data relay and technology demonstration. Both programs have been recently submitted to a System Environmental test campaign including extensive Thermal Balance tests with Solar Simulation performed in the Large Solar Simulation (LSS) chamber at ESTEC Noordwijk in 1998. Alenia Spazio, who has the role of Prime Contractor for both programs at Torino and Rome premises respectively for Integral and Artemis, is responsible of the Thermal Control of the satellites and the relevant verification aspects.
Technical Paper

Effect of Additional Installations in a Thermal Vacuum Chamber on the Thermal Behavior of the Test Article

2000-07-10
2000-01-2527
The thermal shroud of a thermal vacuum chamber is in most cases not perfectly closed. There are holes for windows and feedthroughs and some stands inside the shroud which influence the thermal behavior of the test article. Size and thermo- optical properties of the covers of the holes determine the effect on the temperature change of the test article. This influence is investigated for different cases as they occur in a thermal test chamber. Covers made of aluminized or black KAPTON and painted metal sheets are investigated. Mechanical fixtures are needed for installation of the test articles. By constraints of the test setup these fixtures often can't be designed as adiabatic or actively temperature controlled. For the case of large test articles with relatively low thermal heat capacity as reflectors for telecommunication satellites, the influence of the fixture on the final temperature is discussed for different cases and an optimized solution is presented.
Technical Paper

Computer and Microcontroller Techniques for Instrumentation and Control Systems in Advanced Life Support

2000-07-10
2000-01-2263
The use of embedded microcontrollers in ALS (Advanced Life Support) systems can create intelligent sensors and control systems. This integration requires cooperation between biologists and engineers who need to understand how biological systems can be controlled by mechatronic systems. Mechatronics is the synergetic combination of precision mechanical engineering, electronic control and systems thinking in the design of products and processes. Microcontrollers offer the ability to combine these concepts into working systems suitable for ALS.
Technical Paper

Design and Development of Loop Heat Pipes

2000-07-10
2000-01-2315
Future telecommunication and constellation satellites share a common objective to improve their thermal control performances when compared to the current state of the art. They are increasingly demanding in heat transport and thermal dissipation. Thus the use of classical thermal devices such as heat pipes or typical radiators are not sufficient anymore for the overall spacecraft thermal control. Therefore, the expected thermal control needs in the near future have motivated and directed, since about 5 years, new developments as e.g. Loop Heat Pipes. This technology is now almost mature and the industrialisation phase is being started. Indeed, as they give valuable possibilities and advantages to the thermal design of the platform, the LHPs constitute the most promising system to ensure particularly: □ The North / South radiator thermal coupling.
Technical Paper

Thermal-Gravitational Modelling and Scaling of Heat Transport Systems for Applications in Different Gravity Environments: Super-Gravity Levels & Oscillating Heat Transfer Devices

2000-07-10
2000-01-2377
Several publications describe research carried out at NLR on the thermal-gravitational modelling and scaling of two-phase heat transport systems for spacecraft applications. They dealt with mechanically and capillary pumped two-phase loops. The activities pertained to pure geometric, pure fluid to fluid, or hybrid scaling between a prototype system and a model at the same gravity level, and between a prototype in micro-gravity and a model on earth. Recent publications also include the scaling aspects of a prototype loop for a Moon or Mars base application and a terrestrial model. The work discussed here was carried out in the last couple of years. It concerns scaling to super-gravity levels, and was done because a promising super-gravity application for (two-phase) heat transport systems can be the cooling of high power electronics in spinning satellites and in military aircraft.
Technical Paper

High-Acceleration Performance of the Flat Swinging Heat Pipe

2000-07-10
2000-01-2376
The Flat Swinging Heat Pipe (FSHP) is a new cooling concept aiming at cooling of high power electronics at different acceleration loads, ranging from zero to ten times the earth's gravitation. The FSHP combines high heat transfer rates with the capability to withstand and operate under “any” acceleration condition. This paper briefly outlines the basic working principle of the FSHP, and describes the experiments and tests at normal gravity both in a prototype high-g FSHP and in a glass experimental FSHP. The experiments focussed on fluid distribution, on measurement of liquid and vapour slug oscillations and on the assessment of the best working fluid and filling ratio. High-acceleration experiments were carried out on a rotating table, capable of generating 8.4 times the earth's gravitation at the FSHP center. The paper discusses aspects of fluid distribution, measurement of fluid oscillations, selection of the optimal working fluid and optimal filling ratio.
Technical Paper

Data Acquisition and Power Control System for Thermal Test on Spacecraft at 4m Thermal Vacuum Chamber

2001-07-09
2001-01-2245
A computer based data acquisition and power control system has been designed and installed for conducting thermal test at 4M thermal vacuum chamber of ISRO Satellite Centre(ISAC), Bangalore, INDIA. The system consists of four main units viz. Temperature Signal Processing Unit(TSPU), Power and Control Unit(PACU), Spacecraft telemetry and thermal vacuum chamber facility data interface unit and Data Processing Unit(DPU). The system has capability of monitoring 512 thermocouple channels, 700 spacecraft telemetry thermal related parameters, facility parameters including chamber Vacuum level, chamber contamination level using Quartz Crystal Monitor data and 128 numbers of heat-flux/temperature control channels. TSPU and PACU are VME based system. DPU is based on Pentium processor with hot redundancy using Redundant Array Of Inexpensive Disks(RAID) to takeover in case of failure of a server. All the subsystem and their peripherals are networked using TCP/IP on Ethernet.
Technical Paper

On-Orbit Thermal Performance of RADARSAT-1 Spacecraft

2001-07-09
2001-01-2216
The Canadian RADARSAT-1 has successfully served the world as an earth observation satellite since Nov 1995. In this paper, the thermal performance of RADARSAT-1 over the 5 ears on orbit (Nov 1995–Nov 2000) has been analyzed through the telemetry temperature data. Analysis has been performed for the overall spacecraft, the subsystems and some selected units. The thermal control system of the RADARSAT-1 has been examined for cases of both normal orbital conditions and abnormal thermal environments and operations. The TCS has satisfactorily served RADARSAT-1 for a variety of thermal operations. The phenomenon of thermal-optical surface degradation has been directly observed from the thermal data, and varying behaviour of surface degradation has been detected.
X