Experimental modelling of heat modes of small space vehicles and their external heat flows. II. Heat vacuum test results of the MS-1-TK-TV -type micro-sputnik mock-up

2002 ◽  
Vol 8 (4) ◽  
pp. 3-10 ◽  
Author(s):  
B.M. Rassamakin ◽  
◽  
V.A. Rogachyov ◽  
V.I. Khominich ◽  
S.M. Khayrnasov ◽  
...  
Keyword(s):  
External Heat ◽  
Space Vehicles ◽  
Test Results ◽  
Small Space ◽  
Experimental Modelling ◽  
Heat Flows ◽  
Vacuum Test

Experimental modeling of heat modes of small space vehicles and their external heat flows. I. TVK-2.5 heat vacuum plant

2002 ◽  
Vol 8 (1) ◽  
pp. 37-41 ◽  
Author(s):  
B.M. Rassamakin ◽  
◽  
V.A. Rogachyov ◽  
V.I. Khominich ◽  
Yu.V. Petrov ◽  
...  
Keyword(s):  
External Heat ◽  
Experimental Modeling ◽  
Space Vehicles ◽  
Small Space ◽  
Heat Flows

scholarly journals Investigation of the technology of mutual navigation and orientation of small space vehicles flying in formation

2019 ◽  
Vol 18 (1) ◽  
pp. 88-93
Author(s):  
A. V. Nebylov ◽  
V. V. Perliouk ◽  
T. S. Leontieva
Keyword(s):  
Video Camera ◽  
Space Vehicles ◽  
Radio Communication ◽  
Small Space ◽  
Modeling Simulation ◽  
Ground Station ◽  
Bench Experiment ◽  
Radio Communication System ◽  
The Cost ◽  
Orbital Constellation

The paper presents the problem of ensuring support of the flight of a group of small spacecraft (microsatellites) taking into account the small mutual distances between them. The purpose of using the orbital constellation specified is to create a radio communication system to control remote objects like unmanned aerial vehicles and ground robots located in hard-to-reach areas of the Earth from the Central ground station. To reduce the cost of microsatellite design, it was decided to rigidly fix the receiving and transmitting antennas on their housings and use the spatial orientation of the entire apparatus for antenna guidance. This seriously complicated the tasks of navigation and orientation of microsatellites in a formation and required the development of a new method for determining the orientation of a single microsatellite. The essence of the method is to process the image obtained by means of a video camera mounted on a nearby microsatellite. We used methods of computer vision. The results of mathematical modeling simulation, as well as the results of full-scale bench experiment confirming the efficiency of the proposed method are presented.

scholarly journals Research on the Application of Carbon Foam Absorbing Materials in Wireless Testing of Spacecraft Thermal Vacuum Test

2020 ◽  
Vol 316 ◽  
pp. 04004
Author(s):  
Du Chun-lin ◽  
Yin Xiao-fang ◽  
Qin Jia-yong ◽  
Liu Xiao-ning ◽  
Sun Yu-wei ◽  
...  
Keyword(s):  
Low Temperature ◽  
Carbon Foam ◽  
Thermal Testing ◽  
Test Results ◽  
Thermal Vacuum ◽  
Satellite Constellations ◽  
Testing Environment ◽  
Wireless Testing ◽  
Absorbing Materials ◽  
Vacuum Test

With the rise of mobile communication satellites and low-orbit Internet satellite constellations, wireless testing is required in spacecraft thermal vacuum test, and a comprehensive thermal testing environment for vacuum low-temperature absorption is needed. This paper clarifies the key parameters that need to be paid attention to in the application of vacuum absorbing materials under vacuum and low temperature environment, gives reference indexes, and puts forward the technical process and test results for the development of absorbing shroud.

scholarly journals An Airborne Offner Imaging Hyperspectrometer with Radially-Fastened Primary Elements

Sensors ◽  
2020 ◽  
Vol 20 (12) ◽  
pp. 3411 ◽  
Author(s):  
Nikolay Kazanskiy ◽  
Nikolay Ivliev ◽  
Vladimir Podlipnov ◽  
Roman Skidanov
Keyword(s):  
Optical Characteristics ◽  
Space Vehicles ◽  
Optical Scheme ◽  
Temperature Dependent ◽  
Small Space ◽  
Optical Components ◽  
Temperature Range ◽  
Optical Experiment ◽  
Simulation Results ◽  
Cold Chamber

We propose a new layout for the Offner imaging hyperspectrometer that is utilized onboard small space vehicles. The layout is based on a method of adjusting the adaptive temperature-dependent optical scheme by moving just two coaxial optical components located inside the hyperspectrometer. We present the results of modeling for a temperature range of −40 to +45 °C and an optical experiment using a heat and cold chamber for the range of 12 to 40 °C, proving the basic functionality of the proposed layout. Based on simulation results, the new layout is supposed to allow the hyperspectrometer to operate in a temperature range of −40 to +45 °C without its optical characteristics deteriorating, thus making it suitable for work onboard space or stratospheric vehicles.

Hybrid FEM-SECAM model for simulation of material restructuring under external heat flows

2008 ◽  
Author(s):  
V.E. Panin ◽  
D.D. Moiseenko ◽  
S. Yussif ◽  
S.V. Panin ◽  
P.V. Maksimov
Keyword(s):  
External Heat ◽  
Heat Flows

Design of Autonomous Foldable Docking Mechanism for Small Space Vehicles

2009 ◽  
Author(s):  
Gloria J. Wiens ◽  
Anake Umsrithong ◽  
Shawn Miller ◽  
Aneesh Koka ◽  
Travis Vitello
Keyword(s):  
Translational Control ◽  
Cost Effective ◽  
Satellite System ◽  
Space Vehicles ◽  
Small Space ◽  
Small Satellites ◽  
Cost Effective Approach ◽  
Adams Software ◽  
Docking Mechanism ◽  
Autonomous Docking

Over the past decade, small satellites have gained the interest of the space industry as a new and cost effective approach for servicing space assets. To address the special constraints inherent to the component miniaturization required for these satellites, researchers in the Space, Automation and Manufacturing Mechanisms Laboratory (SAMM) are exploring foldable mechanisms and their effectiveness for providing autonomous rendezvous and docking capabilities for small space vehicles. This paper focuses particularly on the design of autonomous docking mechanisms for space vehicles within the small satellite class known as picosatellite (size and mass requirements: 1 kilogram mass within a 10×10×10 centimeter cube). The docking mechanisms deployment scenario is a dual satellite system comprised of two small satellites (a chaser and a target). The chaser has attitude and translational control capability, while the target is a passive satellite having only attitude stabilization capability. This paper will first present a review of the existing docking mechanism technology utilized in space. This is followed by details of a foldable mechanism approach for providing small satellites autonomous docking capabilities. This includes geometric and dynamic analysis conducted in ADAMS software simulations.

Sign in / Sign up

Export Citation Format

Share Document