Extracting the Non-ObservableStates in Alignment & Calibration Process for Gimballed Inertial Navigation Systems

S. M. SalehiAmiri; A. A. Nikkhah; H. Nobahari

Volume 7, Issue 3 , October 2014, Pages 1-8

Abstract
  This paper presents a method for calculation the non observable states in alignment and calibration process in gimballed inertial navigation system, using estimation method in static linear system and heuristic optimization algorithms. The non observable constant states in alignment process are horizontal ...  Read More

Comprehensive Pattern in Designing Low-Thrust Space Propulsion Systems

H. Fazeli; H. Naseh; M. Mirshams; A.B. Novinzadeh

Volume 7, Issue 3 , October 2014, Pages 9-21

Abstract
  Designing space propulsion systems as one of the important subsystems of the spacecrafts and upper stage space launch systems needs to bypass different and complicated steps. In this article the comprehensive process of designing liquid fuel low-thrust space propulsion systems was illustrated. In the ...  Read More

Second Order Level Set Method in Numerical Simulation of the Grain Burn-Back

M.M. Gheisari; S. M. Mirsajedi

Volume 7, Issue 3 , October 2014, Pages 23-32

Abstract
  In this research, second order level set method for simulation of grain burn-back analysis is presented and compared with the first order level set according to discretisation technique, accuracy , and CPU time. In this manner and at the first step, we describe total necessities of level set method that ...  Read More

Passage of Space Objects over the Territory of States from the Perspective of the International Law

H. Kazemi

Volume 7, Issue 3 , October 2014, Pages 33-42

Abstract
  When space vehicles did not take off horizontally (like airplanes), they had to cross airspace of states other than the launcher state. This phenomenon exists still now for the states who intend to launch space objects, especially when launch pads are located near borders of adjacent states. What has ...  Read More

Intelligent Satellite Orbit Prediction Based on Time Series Analysis

D. Bustan; N. Pariz; S. K. HosseiniSani

Volume 7, Issue 3 , October 2014, Pages 43-49

Abstract
  In this paper, a new approach for orbital position prediction of satellites, is introduced. As traditional methods are based on keplerian equations of motion, orbital disturbances are uasualy neglected for simplicity. This paper, suggests artificial intelligent time series peridiction methods for orbital ...  Read More

Design, Manufacturing and Test of a Three Degrees-of-Freedom Attitude Control Simulator for an Agile Micro-Satellite Based on Single Gimbal Control Moment Gyros

A.R. Aghalari; A. Kalhor; S. M. M. Dehghan; S. H. Cheheltani

Volume 7, Issue 3 , October 2014, Pages 51-67

Abstract
  The Agile Satellite Attitude Control System Simulator (ASACSS) is a laboratory system designed for the purpose of developing and testing attitude control algorithms in a low-risk, low-cost environment. In this paper, the design and development of the ASACSS is described, including hardware and software. ...  Read More

Remote Sensing Role in Land Use StudiesCase Study: Tehran Metropolitan and its Boundary

R. Sayahnia; M. F. Makhdoum; S. Faryadi

Volume 7, Issue 3 , October 2014, Pages 69-73

Abstract
  Land is a limited and vulnerable resource with many permanent and renewable benefits if it is used appropriately.By considering the limited lands and the need for updated data and information for land planning, necessity and importance of land use studies is clear. In fact remote sensing data with geographic ...  Read More

Ascending Phase Fuzzy Logic Guidance of Satellite Launch Vehicles for Reducing the Adverse Wind Effects

M. Sohrab; R. Zardashti; S. H. Jalali-Naini

Volume 7, Issue 3 , October 2014, Pages 75-82

Abstract
  In this paper, a fuzzy logic guidance algorithm is presented for the ascending phase of satellite launch vehicles in the presence of wind effects. In this algorithm, the midcourse constraints including maximum allowable angle of attack at the maximum dynamic pressure and the product of the dynamic pressure ...  Read More