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1 edition of **Optimal Orbit Insertion Strategies Using Combined High and Low Thrust Propulsion Systems** found in the catalog.

Optimal Orbit Insertion Strategies Using Combined High and Low Thrust Propulsion Systems

- 14 Want to read
- 38 Currently reading

Published
**1997** by Storming Media .

Written in English

- TEC031000

The Physical Object | |
---|---|

Format | Spiral-bound |

ID Numbers | |

Open Library | OL11850974M |

ISBN 10 | 1423566971 |

ISBN 10 | 9781423566977 |

The liquid rocket propulsion systems available in the United States stem from three generations of development. should be tailored to optimum application in a launch vehicle with a payload capacity of approximat pounds to low-Earth orbit (LEO). The proposed thrust level of the STME is , pounds. From Earth to Orbit. NASA Technical Reports Server (NTRS) Propulsion System and Orbit Maneuver Integration in CubeSats: Trajectory Control Strategies Using Micro Ion Propulsion . As detailed in this answer low thrust optimization is subject of ongoing research. There are a few closed-loop control laws which allow to achieve a locally optimal (but close to globally optimal) transfer solutions between two orbits. Petropoulos, Naasz and Ruggiero have .

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AFIT/GSO/ENY/97D OPTIMAL ORBIT INSERTION STRATEGIES USING COMBINED HIGH AND LOW THRUST PROPULSION SYSTEMS THESIS Presented to the Faculty of the Graduate School of Engineering of the Air Force Institute of Technology Air University In Partial Fulfillment of the Requirement for the Degree of Master of Science in Space Operations Darren W.

Johnson Cited by: 1. Additionally, for the low-thrust plane change the combined high- and low-thrust transfer offers the most benefit when the spacecraft wet mass is low; on a kg wet mass the reduction in total propellant mass is kg (26%), decreasing to a total propellant mass saving of kg (3%) on a kg wet by: 1.

Results from a variety of example space mission profiles yielded optimal orbit insertion strategies requiring both chemical and electric propulsion to provide a fraction of the LEO to GEO orbit.

Optimal Geostationary Orbit Transfers Using Onboard Chemical-Electric Propulsion. Combined high and low-thrust geostationary orbit insertion with radiation constraint.

Advanced propulsion for geostationary orbit insertion and north-south station by: Combined high and low-thrust geostationary orbit insertion with radiation constraint Acta Astronautica, Vol. Solving fuel-optimal low-thrust orbital transfers with bang-bang control using a novel continuation techniqueCited by: Optimal transfers from low Earth orbit to a pole-sitter position are investigated.

Low-thrust transfers outperform ballistic transfers regarding mass required in LEO. For a kg pole-sitter spacecraft kg is required in LEO for a Soyuz launch. Performance is improved by replacing upper stage transfer by low-thrust spiral. Low-thrust spiral requires only kg in LEO at cost of increased time of by: This equation has at least 2 solutions yielding opposite thrust directions, and it may even have 4 solutions.

For a launcher upper stage with a high thrust engine, the first solution corresponding to Eq. is obviously the optimal one. This is no longer true for low-thrust transfers which can present thrusting arcs opposite to the by: 3.

We use cookies to make interactions with our website easy and meaningful, to better understand the use of our services, and to tailor advertising. For further information, including about cookie. The low-thrust optimal control problem for the orbit transfer is now described.

Equations of Motion The dynamics of the spacecraft, modeled as a point mass, are described using modiﬁed equinoctial elements together with a fourth-order oblate gravity model and a continuous thrust propulsion system. Low-Thrust Orbit Transfer Optimization using a Combined Method R.

Esmaelzadeh Space Research Institute Tehran, Iran ABSTRACT A genetic algorithm is used together with calculus of variations to optimize an interplanetary trajectory for the Bryson-Ho Earth-to-Mars orbit.

Multi-Step Optimization Strategy for Fuel-Optimal In particular, low-thrust propulsion is an ideal option for missions to small objects (comets and aster- backs of direct methods are the high dimensionality of the problem and the convergence to suboptimal solutions, when the parametrization of the control does not fully cover the File Size: KB.

The results of numerical optimization of multi-orbit trajectories of the transfer of a low-thrust spacecraft to a high elliptic orbit are presented.

An analysis of characteristics of the optimal transfers including their structure is performed. The methods of description of the structures of optimal multi-orbit trajectories are suggested with the goal of their by: 1. propulsion systems for a single mission originating at the Earth.

If the payload already exists in LEO, NEP lifting costs are one-tenth those of conven-tional systems. In either case, the lifting expense saved by using low-thrust propulsion for this mis-sion is about the cost of seven Saturn V-class launchings.

Non-Keplerian Orbits Using Low Thrust, High ISP Propulsion Systems 1. IACC Non-Keplerian Orbits Using Low Thrust, High ISP Propulsion Systems Robert McKay1 @ Malcolm Macdonald1 [email protected] Francois Bosquillon de Frescheville2 [email protected] Massimiliano Vasile3.

Fig. 3, Fig. 4 show the time histories of orbit elements and thrust-steering angles for the day transfer. As a comparison, the time histories of orbit elements computed in Reference are also plotted in Fig.

the figure, it is clear that the proposed strategy drives the orbit elements to their target values in a more efficient : Lei Zhang, Bo Xu, Muzi Li, Fei Zhang.

Indeed, even though these low-thrusts do not allow to bring the satellite on a directly re-entering orbit, it may be envisaged to position the spacecraft on an orbit whose altitude is low enough to be able to predict its re-entry within some hours, therefore limiting the debris fallout zone to a small number of orbit ground-tracks, chosen in Cited by: 1.

Low thrust propulsion and gravity assist (GA) are among the most promising techniques for deep space explorations.

In this paper the two techniques are combined and treated comprehensively, both on modeling and numerical techniques. Fuel optimal orbit rendezvous via multiple GA is first formulated as optimal guidance with multiple interior constraints and then the optimal necessary conditions Cited by: between low-Earth orbit and low-lunar orbit.

The study of optimal trajectories for low-thrust spacecraft is an integral part of these research efforts. Much of the earlier work in low-thrust trajectories concerned orbital transfers in an inverse-square gravity field.

Edelbaum [] investigated optimal orbit-raising, rendezvous, and station keeping manueavers using low-thrust propulsion. Cited by: 5. Optimal Low-Thrust Deorbiting of Passively Stabilized LEO Satellites for a continuous low-thrust orbit control.

and shown how to apply them to various dynamical book is divided. Session 6: Analytical Approximations for Low Thrust Maneuvers As mentioned in the previous lecture, solving non-Keplerian problems in general requires the use of perturbation methods and many are only solvable through numerical integration.

However, there are a few examples of low-thrust space propulsion maneuvers for which we. The technology of high ISP propulsion systems with long lifetime and low thrust is improving, and opens up numerous possibilities for future missions.

The use of continuous thrust can be applied in all directions including prependicular to the flight direction to force the spacecraft out of a natural orbit (or A orbit) into a displaced orbit (a non-Keplerian or B orbit): such orbits could have Cited by: Dedicated guided and capture sets are introduced to exploit the combined use of low-thrust propulsion with stable manifolds trajectories, aiming at defining feasible first guess solutions.

Then, an optimal control problem is formulated to refine and improve by: 1. Introduction. The optimization of low-thrust trajectories is a well known subject, and is performed by using numerical procedures.

The two main approaches for optimizing a trajectory, the direct method (the problem is solved by means of gradient-based procedures) and indirect method (the problem is solved by means of shooting procedures) have been dealt with in many by: 9.

The problem of the transfer of a spacecraft with maximum payload from a fixed circular orbit to a given noncoplanar circular orbit in a spherical gravity field is solved.

The spacecraft is equipped with constant-power electric propulsion and energy storage. The cases of variable-thrust and constant-thrust propulsion are considered. The increase in the payload mass due to the energy Author: Ya. Tkachenko. Optimal Interplanetary Rendezvous Combining Electric Sail and High Thrust Propulsion System Alessandro A.

Quarta, Giovanni Mengali [9,10,11,12], allows a spacecraft to deliver a payload to some high-energy orbit an interplanetary mission strategy is likely to use additional and high-thrust propulsion systems for the escape and capture. analysis, theadvantage should be applicable to all launch orbit insertion is performed by the on-board electric vehicles.

Two payload power levels, 10 kW and 15 kW, propulsion system use the remaining Centaur stage fuel were assumed to be available for the electric propulsion and theavailableon-boardchemical fuelin an optimal one orbit Size: 1MB.

Dudley Court Press / Paperback / Pages isbn / isbn Book / Textbook Details Add to Comparison Cart enlarge Optimal Orbit Insertion Strategies Using Combined High and Low Thrust Propulsion Systems.

maneuvers: the first one using a linear and the second one using a quadratic form for the direction of the thrust. To obtain those low thrust sub-optimal maneuvers, the Euler-Lagrange equations are also used here, as done before in the optimal approachThey give. a set of differential equations that can be used to solve numerically the problem.

used to quickly determine the performance of electric propulsion orbit transfer vehicles CEPOTV) for any circular orbit to circular orbit transfer mission. By using the predicted optimal Isp method, parametric variation of Isp is not necessary thus eliminating one variable from a parametric Size: KB.

Combined high and low-thrust geostationary orbit insertion with radiation constraint. Acta Astronautica, Vol. Simple Open-Loop and Closed-Loop Guidance Strategies for Low-Thrust Spacecraft.

Direct Approach for Computing Near-Optimal Low-Thrust Earth-Orbit by: Low-Thrust Orbit Transfer Problem; Maximum Range of a Hang Glider; Minimum Time Supersonic Aircraft Climb; Moon Lander Problem; Orbit-Raising Problem; Reusable Launch Vehicle Entry; Robot Arm Problem; Space Station Reorientation Problem; Tumor Anti-Angiogenesis Problem; Two-Strain Tuberculosis Optimal Control Problem; Publications; User's Guide.

Low-thrust transfers between given orbits within the two-body problem are considered; the thrust is assumed power limited.

A simple method for obtaining the transfer trajectories based on the linearization of the motion near reference orbits is suggested. Required calculation accuracy can be reached by means of use of a proper number of the reference : A.

Sukhanov, A. Prado. Combined high and low-thrust geostationary orbit insertion with radiation constraint Acta Astronautica, Vol. Attitude Stability and Altitude Control of a Cited by: In this paper, displaced geostationary orbits using hybrid low-thrust propulsion, a complementary combination of Solar Electric Propulsion (SEP) and solar sailing, are investigated to increase the capacity of the geostationary ring that is starting to get congested.

The SEP propellant consumption is minimized in order to maximize the mission lifetime by deriving semi-analytical formulae for. FUEL-OPTIMAL, LOW-THRUST TRANSFERS BETWEEN LIBRATION POINT ORBITS A Thesis Submitted to the Faculty of Purdue University by Je rey R.

Stuart In Partial Ful llment of the Requirements for the Degree of Master of Science in Aeronautics and Astronautics May Purdue University West Lafayette, Indiana. Electric Propulsion For Low Earth Orbit Communication Satellites Steven R. Oleson NYMA, Inc. NASA Lewis Research Center Group Brookpark, Ohio, Electric propulsion was evaluated for orbit insertion, satellite positioning and de-orbit applications on big (hundredsFile Size: KB.

AN AUTOMATED SEARCH PROCEDURE TO GENERATE OPTIMAL LOW-THRUST RENDEZVOUS TOURS OF THE SUN-JUPITER TROJAN ASTEROIDS Jeffrey R. Stuart(1) and Kathleen C. Howell(2) (1)Graduate Student, Purdue University, School of Aeronautics and Astronautics, W.

Stadium Ave., West Lafayette, IN, [email protected] and a lower bound Tmin was put on the thrust magnitude: max 2 z 2 y 2 Tmin ≤u = ux +u +u ≤T (4) The upper bound is the maximum level of thrust provided by the selected low-thrust engine, the lower was taken times T max to avoid singularities in the Hessian matrix when minimum mass problems are.

OPTIMAL TRAJECTORIES TOWARDS NEAR-EARTH-OBJECTS USING SOLAR ELECTRIC PROPULSION (SEP) AND GRAVITY ASSISTED MANEUVER. Denilson Paulo Souza dos Santos1, Lorenzo Casalino2, Guido Colasurdo3. Antônio Fernando Bertachini de Almeida Prado4. 1,4 Division of Space Mechanics and Control – INPE.

C.P.São José dos Campos - SP, Brasil. Innovations in low-thrust chemical propulsion system technologies are being sought for deep-space, scientific, robotic mission applications. Delta Vs for the missions of interest range from m/sec to m/sec.

Technologies of interest are bipropellant engines with Isp greater than seconds, both pressure-fed and pump-fed, with chamber. Macdonald, Malcolm and Owens, Steven Robert Combined high and low-thrust geostationary orbit insertion with radiation constraint. Acta Astronautica, pp.

ISSN Fantino, E. and Flores, R.M. and Di Carlo, M. and Di Salvo, A. and Cabot, E. Geosynchronous inclined orbits for high-latitude communications.Electric Propulsion for Low Earth Orbit Constellations Steven R. Oleson Dynacs Engineering Company, Brook Park, Ohio John M.

Sankovic Lewis Research Center, Cleveland, Ohio Prepared for the JANNAF Propulsion Meeting sponsored by the Chemical Propulsion Information Agency Cleveland, Ohio, JulyNational Aeronautics and Space.Optimization results show a strong trend toward vehicles having low engine mass rather than high propulsive preformance, with optimum values of expansion ratio in the range of 40 to 45 and optimum lift-off thrust-to-weight ratios in the range of to INTRODUCTION Single-stage-to-orbit (SSTO) systems are being studied as potential File Size: 1MB.