Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing

2016 ◽  
Vol 120 (1226) ◽  
pp. 573-599 ◽  
Author(s):  
B. Chudoba ◽  
G. Coleman ◽  
L. Gonzalez ◽  
E. Haney ◽  
A. Oza ◽  
...  
Keyword(s):  
Low Earth Orbit ◽  
Geostationary Orbit ◽  
Earth Orbit ◽  
Orbital Transfer ◽  
Geo Satellite ◽  
Satellite Servicing ◽  
Geo Satellites ◽  
Kennedy Space ◽  
Cost Factors ◽  
Concept Of Operations

ABSTRACTIn an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architecture-concept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 – CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to/from geostationary orbit (Concept of Operations 2 – CONOP 2). The study concludes that a capsule and de-orbit propulsion module system sized for the geostationary satellite servicing mission is feasible for a direct insertion/re-entry concept of operation CONOP 1. Vehicles sized for CONOP 2 show overall total mass savings when utilising the aero-assisted orbital transfer vehicle de-orbit propulsion module options compared to the pure propulsive baseline cases. Overall, the consideration of technical, operational and cost factors determine if either the aero-assisted orbital transfer vehicle concepts or the re-usable/expendable ascent/de-orbit propulsion modules is the preferred option.

scholarly journals Efficiency in Carrying Cargo to Earth Orbits: Spaceports Repositioning

2016 ◽  
Vol 4 (20) ◽  
pp. 6
Author(s):  
Jakub Hospodka ◽  
Zdeněk Houfek
Keyword(s):  
Earth Rotation ◽  
Low Earth Orbit ◽  
Earth Orbit ◽  
Atmospheric Drag ◽  
Significant Cost ◽  
Space Flights ◽  
Kennedy Space Center ◽  
Kennedy Space ◽  
Earth Orbits ◽  
Launch Platform

Space flights are in these days not any more question of technology, but more question of costs. One way how to decrease cost of launch is change of home spaceport. Change of home spaceport for different rockets is a way to achieve more efficient launches to space. The reason is different acceleration achieved from Earth rotation. We added several mathematical calculations of missions to Low Earth Orbit and Geostationary Earth Orbit to show bonuses from Earth rotation and effect of atmospheric drag on specific rockets used these days. We discussed only already used space vessels. Namely Arianne 5, Delta 4 heavy, Proton-M, Zenit and Falcon9. For reaching GEO we discuss possibility of using Hohmman transfer, because none of aforementioned vessels is available for direct GEO entry. As possible place for launch we discussed spaceports Baikonur, Kennedy Space center, Guyana Space center and Sea Launch platform. We present results in form of additional acceleration for each spaceport, and we also project this additional acceleration in means payload increase. In conclusion we find important differences between vessel effectivity based on spaceport used for launch. Change of launch location may bring significant cost decrease for operators.

A Comparative Study of Satellite Orbits as Low Earth Orbit (LEO) and Geostationary Earth Orbit (GEO)

2015 ◽  
Vol 6 (2) ◽  
Author(s):  
Sandeep Vishwakarma ◽  
Aradhana S. Chauhan ◽  
Shoeba Aasma
Keyword(s):  
Satellite Orbit ◽  
Low Earth Orbit ◽  
Geostationary Orbit ◽  
Earth Orbit ◽  
Satellite Orbits ◽  
Satellite Systems ◽  
Broadcast Television ◽  
Television Use ◽  
Gps System ◽  
Orbiting Systems

It is known facts that satellites are used to receive the signal at geostationary orbit by remaining stationary above a particular point on the Earth. The orbit that is chosen for a satellite depends upon its application. Those used for direct broadcast television use geostationary orbit. Many communication satellites similarly use geostationary orbit. Other satellite systems used for satellite phones use Low Earth orbiting systems. Similarly, satellite systems used for navigation like Nav-star or Global Positioning (GPS) system occupy a relatively Low Earth Orbit. There are also many other types of satellites : Weather satellites Research satellites and many others. Each will have its own type of orbit depending upon its application. The actual satellite orbit that is chosen will depend on factors including its function, and the area of serving. At some instances, the satellite orbit may be as low as 100 miles (160 km) for a Low Earth Orbit (LEO), whereas others may be over 22 000 miles (36000 km) high as in the case of a Geostationary Orbit (GEO). The satellite may even has an elliptical rather than a circular orbit.

scholarly journals Design PV system for a small GEO satellite and studying the effect of using different types of propulsion

2019 ◽  
Vol 8 (1) ◽  
pp. 54
Author(s):  
A. Lotfy ◽  
W. Anis ◽  
Joseph V. M. Halim
Keyword(s):  
Research Work ◽  
Lithium Ion ◽  
Earth Orbit ◽  
Pv System ◽  
Analytical Comparison ◽  
Geo Satellite ◽  
Different Types ◽  
Key Factor ◽  
Geo Satellites ◽  
Photo Voltaic

<p>This paper presents an optimum design of the solar Photo-Voltaic (PV) power system for small Geostationary Earth Orbit (GEO) satellites using triple junction solar cells and advanced Lithium Ion batteries. The paper applies the proposed system on various propulsion technologies; full chemical, full electrical and hybrid propulsions. This research work studies the capability to fulfil efficiently all the satellite power requirements during both the launching and the on-station phases while reducing the high cost challenge. Since the propulsion type is a key factor for the satellite cost, an economic analysis is demonstrated and investigated in two different strategies. The first scenario fixes the satellite weight and offers the revenue due to the increase in the satellite payload. However, the second scenario evaluates the saving profits due to the reduction in the satellite weight using the same number of satellite transponders. The analytical comparison among the different propulsion techniques shows the superior advantages of using the full electrical satellites.   </p>

scholarly journals Precise Relative Orbit Determination for Chinese TH-2 Satellite Formation Using Onboard GPS and BDS2 Observations

2021 ◽  
Vol 13 (21) ◽  
pp. 4487
Author(s):  
Bin Yi ◽  
Defeng Gu ◽  
Kai Shao ◽  
Bing Ju ◽  
Houzhe Zhang ◽  
...  
Keyword(s):  
Orbit Determination ◽  
Low Earth Orbit ◽  
Asia Pacific ◽  
Earth Orbit ◽  
Reference Orbit ◽  
Satellite Formation ◽  
Relative Orbit ◽  
Comparison Results ◽  
Geo Satellites ◽  
The Impact

TH-2 is China’s first short-range satellite formation system used to realize interferometric synthetic aperture radar (InSAR) technology. In order to achieve the mission goal of InSAR processing, the relative orbit must be determined with high accuracy. In this study, the precise relative orbit determination (PROD) for TH-2 based on global positioning system (GPS), second-generation BeiDou navagation satellite system (BDS2), and GPS + BDS2 observations was performed. First, the performance of onboard GPS and BDS2 measurements were assessed by analyzing the available data, code multipath errors and noise levels of carrier phase observations. The differences between the National University of Defense Technology (NDT) and the Xi’an Research Institute of Surveying and Mapping (CHS) baseline solutions exhibited an RMS of 1.48 mm outside maneuver periods. The GPS-based orbit was used as a reference orbit to evaluate the BDS2-based orbit and the GPS + BDS2-based orbit. It is the first time BDS2 has been applied to the PROD of low Earth orbit (LEO) satellite formation. The results showed that the root mean square (RMS) of difference between the PROD results using GPS and BDS2 measurements in 3D components was 2.89 mm in the Asia-Pacific region. We assigned different weights to geostationary Earth orbit (GEO) satellites to illustrate the impact of GEO satellites on PROD, and the accuracy of PROD was improved to 7.08 mm with the GEO weighting strategy. Finally, relative orbits were derived from the combined GPS and BDS2 data. When BDS2 was added on the basis of GPS, the average number of visible navigation satellites from TH-2A and TH-2B improved from 7.5 to 9.5. The RMS of the difference between the GPS + BDS2-based orbit and the GPS-based orbit was about 1.2 mm in 3D. The overlap comparison results showed that the combined orbit consistencies were below 1 mm in the radial (R), along-track (T), and cross-track (N) directions. Furthermore, when BDS2 co-worked with GPS, the average of the ambiguity dilution of precision (ADOP) reduced from 0.160 cycle to 0.153 cycle, which was about a 4.4% reduction. The experimental results indicate that millimeter-level PROD results for TH-2 satellite formation can be obtained by using onboard GPS and BDS2 observations, and multi-GNSS can further improve the accuracy and reliability of PROD.

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