Orbit maneuver for GEO on-orbit service satellite using Hohmann transfer

The optimization of the orbital Hohmann transfer

Acta Astronautica ◽

10.1016/j.actaastro.2009.03.010 ◽

2009 ◽

Vol 65 (7-8) ◽

pp. 1094-1097 ◽

Cited By ~ 4

Author(s):

Badaoui El Mabsout ◽

Osman M. Kamel ◽

Adel S. Soliman

Keyword(s):

Hohmann Transfer

Get full-text (via PubEx)

Effect of the Altitudes and Eccentricity of the Initial Orbit on Satellite Transition Efficiency

Iraqi Journal of Science ◽

10.24996/ijs.2021.62.2.33 ◽

2021 ◽

pp. 699-707

Author(s):

Omar A. Fadhil ◽

AbdulRahman H. Saleh

Keyword(s):

Low Earth Orbit ◽

Geosynchronous Orbit ◽

Orbit Plane ◽

Advanced Technique ◽

Parking Orbit ◽

Transfer Method ◽

Time Required ◽

Hohmann Transfer ◽

Satellite Transition ◽

Initial Orbit

This research dealt with choosing the best satellite parking orbit and then the transition of the satellite from the low Earth orbit to the geosynchronous orbit (GEO). The aim of this research is to achieve this transition with the highest possible efficiency (lowest possible energy, time, and fuel consumption with highest accuracy) in the case of two different inclination orbits. This requires choosing a suitable primary parking orbit. All of the methods discussed in previous studies are based on two orbits at the same plane, mostly applying the circular orbit as an initial orbit. This transition required the use of the advanced technique of the Hohmann transfer method for the elliptical orbits, as we did in an earlier research, namely the transition from the perigee of the initial orbit to the final orbit and then conducting the rotation of the orbit plane to match the plane for the desired final orbit. The effect of the perigee altitude of the initial orbit on the transition efficiency calculated for the values between 300 to 3000 km. It was found that increasing the altitude reduces the energy and fuel needed for transportation, but the time required for transportation increases, into account that the increased height of the initial or parking orbit also implies the requirement of higher energy to reach it. The effects of eccentricity (e) values of the initial orbit between 0.01 to 0.2 on the transition efficiency were calculated. It was found that the increase in (e) reduces the energy and fuel, but does not affect the time, required for transportation.

Get full-text (via PubEx)

Instantaneous Impact Point Guidance with Coast Arcs for Solid Rockets

International Journal of Aerospace Engineering ◽

10.1155/2021/5571877 ◽

2021 ◽

Vol 2021 ◽

pp. 1-12

Author(s):

Shengwei Jia ◽

Fugui Li ◽

Mingbo Tong

Keyword(s):

Velocity Vector ◽

Analytic Solution ◽

Structural Strength ◽

Ignition Time ◽

Impact Point ◽

Solid Rocket Motors ◽

Rocket Motors ◽

Solid Rockets ◽

Solid Rocket ◽

Hohmann Transfer

This paper proposed an analytical iterative guidance method with the desired instantaneous impact point constraint for solid rockets in “burn-coast-burn” trajectory mode. Solid rocket motors expect to remove the thrust termination mechanism to increase the structural strength and launch reliability, which induce new difficulties and challenges to the guidance problems. In terms of the “Hohmann transfer” principle, a pointing algorithm is deduced in depth to establish the theoretical relations among the ignition time, the required velocity vector, and the orbital element constraints and provides the analytical expression of the ignition time. Then, an analytic solution of the required velocity vector is derived based on orthogonal and nonorthogonal velocity vectors, and a complete guidance logic is used to solve the target orbit elements satisfying the desired instantaneous impact point. Finally, the application of the developed theoretical algorithm in this paper is conducted using a two-stage solid rocket. The proposed guidance method is verified by Monte Carlo simulations, and the testing results demonstrate the adaptability, strong robustness, and excellent performance for different desired impact point missions.

Get full-text (via PubEx)

SpaceX rocket data satisfies elementary Hohmann transfer formula

Physics Education ◽

10.1088/1361-6552/ab5f4c ◽

2020 ◽

Vol 55 (2) ◽

pp. 025011

Author(s):

Michael J Ruiz ◽

James Perkins

Keyword(s):

Hohmann Transfer

Get full-text (via PubEx)

Solution for Nonlinear Three-Dimensional Intercept Problem with Minimum Energy

Mathematical Problems in Engineering ◽

10.1155/2013/435725 ◽

2013 ◽

Vol 2013 ◽

pp. 1-8 ◽

Cited By ~ 2

Author(s):

Henzeh Leeghim ◽

Donghoon Kim ◽

James Turner

Keyword(s):

Optimization Problem ◽

Minimum Energy ◽

Three Dimensional ◽

Problem Formulation ◽

Initial Position ◽

Iteration Algorithm ◽

Trajectory Design ◽

Interplanetary Trajectory ◽

Classical Orbit ◽

Hohmann Transfer

Classical orbit intercept applications are commonly formulated and solved as Lambert-type problems, where the time-of-flight (TOF) is prescribed. For general three-dimensional intercept problems, selecting a meaningful TOF is often a difficult and an iterative process. This work overcomes this limitation of classical Lambert’s problem by reformulating the intercept problem in terms of a minimum-energy application, which then generates both the desired initial interceptor velocity and the TOF for the minimum-energy transfer. The optimization problem is formulated by using the classical Lagrangianfandgcoefficients, which map initial position and velocity vectors to future times, and a universal time variablex. A Newton-Raphson iteration algorithm is introduced for iteratively solving the problem. A generalized problem formulation is introduced for minimizing the TOF as part of the optimization problem. Several examples are presented, and the results are compared with the Hohmann transfer solution approaches. The resulting minimum-energy intercept solution algorithm is expected to be broadly useful as a starting iterative for applications spanning: targeting, rendezvous, interplanetary trajectory design, and so on.

Get full-text (via PubEx)