Titlebook: Cryocoolers 11; R. G. Ross Book 2002 Springer Science+Business Media New York 2002 electronics.material.refrigeration.space

condone

Miniature Pulse Tube Cryocooler for Space Applicationsnding from NASA/GSFC. The cold end is a U-tube configuration, and is driven by a dual opposed piston flexure bearing compressor. The compressor utilizes a moving magnet linear motor and incorporates a number of features that simplify assembly and enhance reliability. This cooler is designed for 0.3

FID

Military Space Cryogenic Cooling Requirements for the 21st Centuryily on reliability and the achievement of long life. However, looking ahead at 21 st century military space applications, there are improvements needed in several aspects of current cooling technology including higher capacity cooling loads, mass reduction, and improvement in efficiency, low tempera

衰弱的心

Status of Programs for the DoD Family of Linear Drive Cryogenic Coolers for Weapon Systems have low input power, a quick cool-down tune, low vibration output, low audible noise, and higher reliability. This paper (1) outlines the characteristics of each cooler, (2) presents the status and results of qualification tests, and (3) presents the status and test results of efforts to increase

PRISE

Air Force Research Laboratory Cryocooler Characterization and Endurance Updatepers, technology sponsors, and technology users. This feedback is essential for cryocooler design enhancements and future cryogenic technology development efforts. There are two cryocoolers undergoing characterization at AFRL. These include the Astrium (formerly Matra Marconi Space) 10 K Cryocooler,

使閉塞

N斯巴達(dá)人

Protoflight Spacecraft Cryocooler Performance Results with a brassboard command and control module that provides simultaneous temperature and Adaptive Feed-Forward vibration control. The PSC with brassboard electronics have been delivered to the Air Force Research Lab in Albuquerque, where additional testing has validated the results obtained at Rayth

認(rèn)識(shí)

Characterization of Raytheon’s 60 K 2W Protoflight Spacecraft Cryocoolerich uses a mass balancer to reduce vibration. It is designed to lift a heat load of 2W at 60K, with a nominal rejection temperature of 300K. The characterization of the PSC involved a series of experiments, including cool-down to lowest temperature, design point verification, parameter optimization,

聾子

The Development of a 10 K Closed Cycle Stirling Cooler for Space Usege..The proof of concept program included the detail design of the optimized displacer and compressor, and the manufacture and assembly leading to proof of concept laboratory testing. During testing, the cooler reached a base temperature of 9.4 K.

盡責(zé)

Development of a 12 K Stirling Cycle Precooler for a 6 K Hybrid Cooler System is a continuance of our previous work on linear Stirling coolers. We have developed one-, two-, and three-stage Stirling coolers for various NASA and Department of Defense programs. For the Explorer 6 K, we have focused on adapting our three-stage Stirling cooler for operation at lower temperatures

重畫只能放棄

Thermodynamic Optimization of Multi-Stage Cryocoolersme typically available to perform optimization procedures combined with the large number of variables and their complex interaction results in sub-optimal products. This paper presents a concept for optimization that more rapidly converges on an optimal design.