Multi-Objective Optimization of Rocket-Based Combined-Cycle Engine Performance Using a Hybrid Evolutionary Algorithm

Pastrone, Dario Giuseppe; Sentinella, Matteo Rosa

doi:10.2514/1.41327

Cited by 26 publications

(9 citation statements)

References 14 publications

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“…The thrust augmenting potential of ejectors has been studied as far back as 1949, and the entrainment and compression ratios define a given ejector's performance [13]. Pastrone and Sentinella [48] have utilized a hybrid evolutionary algorithm to optimize the rocket-based combined-cycle engine performance, and a control-volume approach has been used to evaluate the ejector's performance.…”

Section: Ejector/ramjet Mode Transitionmentioning

confidence: 99%

Survey on the mode transition technique in combined cycle propulsion systems

Huang

Yan

Tan

2014

Aerospace Science and Technology

175

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Section: Ejector/ramjet Mode Transitionmentioning

confidence: 99%

Survey on the mode transition technique in combined cycle propulsion systems

Huang

Yan

Tan

2014

Aerospace Science and Technology

175

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“…The actual mission feasibility and characteristics are verified by means of a versatile evolutionary algorithm developed at Politecnico di Torino, 12,13,14 which is used to obtain an optimal solution, i.e., minimum ∆V , for each transfer leg.…”

Section: Leg Optimizationmentioning

confidence: 99%

Active Debris Removal Missions with Multiple Targets

Casalino

Pastrone²

2014

AIAA/AAS Astrodynamics Specialist Conference

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A method for the selection of the target sequence for the removal of exhausted upper stages, which are a considerable part of orbit debris in low Earth orbit, is proposed. The method is based on the evaluation of favorable opportunities to transfer the spacecraft between possible targets that have the same inclination. The effect of Earth's oblateness perturbation is particularly relevant in terms of regression of the nodes, and can be exploited to reduce the transfer costs. A fast procedure is used to estimate rendezvous time and cost. An evolutionary algorithm is then used to determine the actual legs of the most promising opportunities of multiple-target missions. The method is tested and used to design missions for the removal of five of the Russian Kosmos 3M rocket bodies still in orbit in the 82-degree inclination vicinity.

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“…This kind of vehicle takes off horizontally, sends payloads to a low Earth orbit, and returns back for a runway landing. An air‐breathing–based combined‐cycle engine is installed on the vehicle to adapt to altitude, which usually varies from zero to tens of kilometers. In addition, a lift‐body configuration is applied to facilitate endoatmospheric flight, which affords the lateral maneuver and helps to revise the trajectory to compensate for the deviation in launch time.…”

Section: Introductionmentioning

confidence: 99%

Ascent trajectory optimization for air‐breathing vehicles in consideration of launch window

Hong-yu

Wang

Cui

2019

Optim Control Appl Methods

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Summary This paper studies the optimal ascent trajectory for a one‐stage‐to‐orbit, air‐breathing vehicle. This kind of vehicle allows endoatmospheric lateral maneuver and thus can extend the launch window. To obtain the optimal orbit‐insertion trajectory in consideration of launch time, a novel optimization model is proposed by designing longitudinal and lateral profiles separately. The longitudinal flight aims to meet the orbital shape that contains the eccentricity and the angular momentum, which are transformed to boundary constrains in altitude, path angle, and velocity. For lateral motion, the orbit inclination and right ascension of ascending node are designed to vary simultaneously as the range. By designing an altitude profile, the terminal altitude and path angle are naturally met and removed from the constraints and accurate orbit insertion is realized by searching the total range and the initial azimuth. Then, the original problem is converted to a parameter optimization problem and solved by a hybrid optimization algorithm, in which the solution is first searched by a particle swarm optimization method and then refined by a modified golden section method. Simulation tests the proposed method with various scenarios. Compared to traditional launch vehicles, a launch window over 1.5 hours is derived without consuming the propellant in the upper stage.

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Multi-Objective Optimization of Rocket-Based Combined-Cycle Engine Performance Using a Hybrid Evolutionary Algorithm

Cited by 26 publications

References 14 publications

Survey on the mode transition technique in combined cycle propulsion systems

Survey on the mode transition technique in combined cycle propulsion systems

Active Debris Removal Missions with Multiple Targets

Ascent trajectory optimization for air‐breathing vehicles in consideration of launch window

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