Multipole field electromagnetic launcher (MFEL) is a new type of induction launcher that can produce radial magnetic field. This paper proposed different driving coil connection patterns of MFEL and analyzed their performance through experimental and simulation methods. To verify the conceptual feasibility, a small-size single stage capacitor-driven MFEL was built and tested for the first time. Powered by a 100 μF capacitor bank charged to 3000 V, the launcher is able to accelerate a 50.4 g projectile to a velocity of 13.3 m/s. Characteristics of MFEL including inductance gradient, driving current, eddy current distribution, and magnetic field distribution were analyzed as well.

Connection Pattern Research and Experimental Realization of Single Stage Multipole Field Electromagnetic Launcher

In this paper, we propose an improved launch mode called multistage twisty multipole electromagnetic launcher. The twisty multipole magnetic field configuration is resolved, and the group power supply module is considered. The induced eddy current of the projectile is considered, and the analysis of electromagnetic force and torque has been performed. A full 3-D transient motion simulation with multiple degrees of freedom is carried on the three-stage twisty octapole field electromagnetic launcher. The simulation results indicate that the magnetic torque of rotational motion is impressively large and the transverse displacement of the projectile is much little. The torsion option of multistage pole coils makes little influence on axial acceleration force and exit velocity comparing with the appositional configuration. The theoretical analysis and numerical simulations indicate that the projectile is accelerated with spinning motion about its axis which could keep the projectile fly stability. We suggest this launch mode could be applied in the evacuated tube transportation vehicle.

Analysis and Evaluation of Three-Stage Twisty Octapole Field Electromagnetic Launcher

The market for microsatellite and nanosatellite launch has grown appreciably over the last few years with commercial, military, and research applications involved to an increasing extent. A significant growth area has been the development of autonomous swarms in which multiple small satellites interact cooperatively as systems to provide interrelationships and redundancy. Because the options for launching small satellites are restricted, the promise afforded by these new developments is also limited. Large conventional rocket boosters are available only from a few nations and launch opportunities are, therefore, limited not only by cost but also by launcher availability and launch window opportunities. Several commercial organizations (SpaceX, Orbital Sciences, Blue Origin, Virgin Galactic, Bigalow Aerospace, SpaceDev, and so) are attempting to address this need but continue to use conventional rocket approaches, albeit sometimes in innovative ways. In this paper, the opportunities for electromagnetic launch to provide an alternative that could have lower cost and increased availability from a dedicated facility are discussed.

Electromagnetic Space Launch Considerations

This paper discusses the establishment of a Supportability Technology Development Roadmap as a guide for developing capabilities intended to allow NASA s Constellation program to enable a supportable, sustainable and affordable exploration of the Moon and Mars. Presented is a discussion of supportability, in terms of space facility maintenance, repair and related logistics and a comparison of how lunar outpost supportability differs from the International Space Station. Supportability lessons learned from NASA and Department of Defense experience and their impact on a future lunar outpost is discussed. A supportability concept for future missions to the Moon and Mars that involves a transition from a highly logistics dependent to a logistically independent operation is discussed. Lunar outpost supportability capability needs are summarized and a supportability technology development strategy is established. The resulting Lunar Surface Systems Supportability Strategy defines general criteria that will be used to select technologies that will enable future flight crews to act effectively to respond to problems and exploit opportunities in an environment of extreme resource scarcity and isolation. This strategy also introduces the concept of exploiting flight hardware as a supportability resource. The technology roadmap involves development of three mutually supporting technology categories, Diagnostics Test and Verification, Maintenance and Repair, and Scavenging and Recycling. The technology roadmap establishes two distinct technology types, "Embedded" and "Process" technologies, with different implementation and thus different criteria and development approaches. The supportability technology roadmap addresses the technology readiness level, and estimated development schedule for technology groups that includes down-selection decision gates that correlate with the lunar program milestones. The resulting supportability technology roadmap is intended to develop a set of technologies with widest possible capability and utility with a minimum impact on crew time and training and remain within the time and cost constraints of the Constellation program.

/pdf/a-lunar-surface-system-supportability-technology-development-4lw8jj8cri.pdf

A Lunar Surface System Supportability Technology Development Roadmap

Electromagnetic launch assist has the potential to provide a highly reliable reusable first stage to a space access system infrastructure at a lower overall cost. This paper explores the benefits of a smaller system that adds the advantages of a high specific impulse air-breathing stage and supersonic launch speeds. The method of virtual specific impulse is introduced as a tool to emphasize the gains afforded by launch assist. Analysis shows launch assist can provide a 278-s virtual specific impulse for a first-stage solid rocket. Additional trajectory analysis demonstrates that a system composed of a launch-assisted first-stage ramjet plus a bipropellant second stage can provide a 48-percent gross lift-off weight reduction versus an all-rocket system. The combination of high-speed linear induction motors and ramjets is identified, as the enabling technologies and benchtop prototypes are investigated. The high-speed response of a standard 60 Hz linear induction motor was tested with a pulse width modulated variable frequency drive to 150 Hz using a 10-lb load, achieving 150 mph. A 300-Hz stator-compensated linear induction motor was constructed and static-tested to 1900 lbf average. A matching ramjet design was developed for use on the 300-Hz linear induction motor.

/pdf/first-stage-of-a-highly-reliable-reusable-launch-system-id56sw2fnu.pdf

First Stage of a Highly Reliable Reusable Launch System

Future human exploration of the moon will require the development of capabilities for in situ resource utilization. Transport of lunar-derived commodities such as fuel and oxygen to orbiting resource depots has been proposed to enable refueling landers or other vehicles. A lunar electromagnetic launch (LEML) system could be an effective means of transporting materials as an alternative to nonrenewable chemical-based propulsion systems. An example LEML concept is presented based on previous studies, existing electromagnetic launch technologies, and the National Aeronautics and Space Administration's human exploration architecture. A preliminary assessment of the cost versus benefit of such a system is also offered; the conclusion, however, is not as favorable for LEML as originally suggested.

/pdf/a-lunar-electromagnetic-launch-system-for-in-situ-resource-19gagr5thi.pdf

A Lunar Electromagnetic Launch System for In Situ Resource Utilization

Future human exploration of the moon will require the development of capabilities for in-situ resource utilization (ISRU). Transport of lunar-derived commodities such as fuel and oxygen to orbiting resource depots has been proposed to enable refueling landers or other vehicles. A lunar electromagnetic launch (LEML) system could be an effective means of transporting materials, as an alternative to non-renewable chemical-based propulsion systems. An example LEML concept is presented based on previous studies, existing EML technologies, and NASA's human exploration architecture. A preliminary assessment of the cost-versus-benefit of such a system is also offered; the conclusion, however, is not as favorable for LEML as originally suggested.

/pdf/a-lunar-electromagnetic-launch-system-for-in-situ-resource-1ky3qun4cw.pdf

A Lunar Electromagnetic Launch System for In-Situ Resource Utilization

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A Lunar Electromagnetic Launch System for In Situ Resource Utilization

A Lunar Electromagnetic Launch System for In-Situ Resource Utilization