General Perturbations Theories Derived from the 1965 Lane Drag Theory

Lane, Max H.; Hoots, Felix R.

doi:10.21236/ada081264

Cited by 29 publications

(12 citation statements)

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“…The SGP4 orbit propagator uses an analytic low-order solution to Newton's second law, giving a realistic model for gravitational potential and a dissipative atmospheric environment (Picone et al, 2005). This model is used for near-Earth satellites and was developed in 1970 by Ken Cranford (Lane and Hoots, 1979), and is a simplification of the more complex theory of Lane and Cranford, which uses a power density function for the atmosphere and a gravitational model from Brouwer's solution (Brouwer, 1959). Outlined below is a summary of the results deriving the position of a satellite from columns 09-63 of line 2 of each TLE, which use the following orbital elements (n o ), to calculate the position and velocity vectors from the observer to a given satellite in the radial direction as r andṙ, respectively, using the method used in Space Track (Kelso et al, 1988):…”

Section: Physics and Mathematics Of Calculationsmentioning

confidence: 99%

Directed energy interception of satellites

She

Hettel

Lubin

2019

Advances in Space Research

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High power Earth and orbital-based directed energy (DE) systems pose a potential hazard to Earth orbiting spacecraft. The use of very high power, large aperture DE systems to propel spacecraft is being pursued as the only known, feasible method to achieve relativistic flight in our NASA Starlight and Breakthrough Starshot programs.In addition, other beamed power mission scenarios, such as orbital debris removal and our NASA program using DE for powering high performance ion engine missions,

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Section: Physics and Mathematics Of Calculationsmentioning

confidence: 99%

Directed energy interception of satellites

She

Hettel

Lubin

2019

Advances in Space Research

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“…Some algorithms for orbit propagation are available. The user can choose between the two-body algorithm (Vallado, 2013), which considers a perfect Keplerian orbit, SGP4 (Lane and Hoots, 1979), or a J2 perturbation algorithm (Vallado, 2013; Wertz, 1978), which is the default.…”

Section: Simulator Designmentioning

confidence: 99%

Modeling and design of a multidisciplinary simulator of the concept of operations for space mission pre-phase A studies

Chagas

Sousa

Louro

et al. 2018

Concurrent Engineering

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Nowadays, it is practically impossible to develop a complex project without the assistance of a comprehensive set of modeling and simulation tools. In space engineering, they are used throughout the product design cycle, from component up to the system level. In conceptual, pre-phase A studies of a space mission, these tools are essential to explore more broadly the design space, in the search for suitable candidate system solutions for the mission. They are also of prime importance in helping to reduce the design time in integrated concurrent design environments. Here, a multidisciplinary tool for concept of operation simulation, developed to be used in that kind of environments, is presented. FOrPlan has the main purpose of performing functional simulations of the satellite and associated ground segments, providing a dynamic verification of the mission designed operational concept. Through the use of suitable graphical interfaces, key parameters of the mission functional scenarios can be presented to the design team and other mission stakeholders, allowing them also a better understanding of the mission operational concept. The simulator presents high flexibility such that it can be quickly customized to different mission scenarios. It has been used successfully at the Space Missions Integrated Design Center (CPRIME) of the Brazilian National Institute for Space Research. In this article, the structure of FOrPlan is presented, and its main features highlighted through results of concept of operation simulations performed for a scientific space mission study that was carried out recently at CPRIME.

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“…In fact the gravitational model includes the effects of the first five zonal harmonics of the earth [3]. The atmospheric model assumes a static, non-rotating, spherically symmetrical atmosphere whose density ρ can be described by the power function [4], [5] o o q s r s…”

Section: Sgp4 Propagation Modelmentioning

confidence: 99%

A numerical comparative study of propagation models, the Cosmos2251 and Iridium33 satellites collision case study

Navabi

Hamrah

2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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In this paper, the trajectory of space objects is modeled and predicted and their orbital data is extract using the information measured by optical and radar instruments. Space objects include operational and non-operational satellites and space debris. Nowadays, one of the most important space issues is the prediction of the collisions between the space objects. Some data can be gathered using measurement tools for a specific time, however for determination of the instantaneous position of space objects, the prediction methods are needed. Then if it is necessary, the collision avoidance maneuvers will be performed using the propagation model's results. In this paper, three propagation models are considered and a comparative study of Cosmos2251 and Iridium33 satellites close approach is presented and the results are discussed.

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General Perturbations Theories Derived from the 1965 Lane Drag Theory

Cited by 29 publications

References 0 publications

Directed energy interception of satellites

Directed energy interception of satellites

Modeling and design of a multidisciplinary simulator of the concept of operations for space mission pre-phase A studies

A numerical comparative study of propagation models, the Cosmos2251 and Iridium33 satellites collision case study

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