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Goleta, CA, United States

LaunchPoint Technologies, Inc. | Date: 2014-12-01

An electromagnetic valve apparatus with nonlinear springs for variable valve timing in an internal combustion engine. The apparatus includes a valve, floating spring assembly, translational cam, and motor. The cam and spring serve to minimize lash and valve stem bending forces. During opening and closing of the valve, spring potential energy is converted into valve kinetic energy and then back into potential energy at the end of the motion. The potential energy is then available for the next opening/closing event. The motor initiates motion, replaces friction and vibration losses, and terminates motion. However, the motor supplies minimal energy as the valve opens and closes, and vice-versa, naturally due to combined effects of system inertia and the nonlinear spring. In addition to valve control, the apparatus may be applied to fuel injectors, or any reciprocating linear or rotary mechanism where electronic control is used.

LaunchPoint Technologies, Inc. | Date: 2010-08-02

A strength training apparatus adapted for conducting translatory motion against a counteracting resistance. The apparatus includes strength training devices wherein a carriage and corresponding guide means are provided for translating mass under the effect of gravity along a rectilinear or curvilinear path. Certain embodiments are configured for utilizing a selectable weight stack, loaded free weights or the users body weight as a primary resistance that is independent of velocity. The apparatus enhances the results of strength training and exercise equipment for providing velocity-dependent resistance in addition to static resistance provided by the apparatus at constant velocity. The apparatus includes velocity-dependent resistance provided by eddy current resistance caused by the interaction of an electrically conductive structure encountering relative motion with a magnetic field. The electrically conductive structure is secured to a frame and magnetic field is provided by one or more permanent magnets secured to the carriage.

LaunchPoint Technologies, Inc. | Date: 2011-02-28

A lightweight and efficient electrical machine element including a method of manufacture providing a stator winding for an electric machine which has a large portion of its volume containing electrically conductive strands and a small portion of its volume containing of an encapsulant material. The stator winding includes winding of a first phase (

Agency: Department of Defense | Branch: Navy | Program: SBIR | Phase: Phase II | Award Amount: 499.94K | Year: 2015

LaunchPoint Technologies proposes to build and test a laboratory demonstration of a helicopter electric tail rotor drive for a Bell 206 helicopter. The drive system will consist of a generator attached to the gearbox output for the rail rotor drive shaft and a dual halbach array permanent magnet motor to directly drive the tail rotor propeller. Purpose built power electronics will convert the AC power from the generator to a DC bus and then convert back to variable frequency AC for the tail rotor motor.

Agency: NSF | Branch: Standard Grant | Program: | Phase: | Award Amount: 149.60K | Year: 2013

This Small Business Innovation Research Phase I project will prove the feasibility of a high reliability motor drive optimized for lightweight propulsion systems for electric aircraft. The NASA green flight challenge proved the viability of electric flight with a 400 passenger mile per gallon pure electric flight last year, but products specific to this market are not yet available. Presently available motor drives limit the reliability of electric propulsion system to unacceptably low levels. These drives are designed for ground vehicles and have reliability significantly less than general aviation planes. These drives also require heavy load inductors to interface with the highest power density electric motors. The novel drive architecture proposed will provide high reliability and operate directly with low inductance motors in the 10 kW to >250 kW range. Rigorous reliability analysis techniques from the commercial aviation industry will be applied to system models to optimize the architecture for reliability and power density. The design will be validated in hardware by fabricating and testing a single phase of the drive. This drive coupled with an advanced motor will form an electric aircraft propulsion system with the highest power density available and a reliability level consistent with aviation usage.

The broader impact/commercial potential of this project is to address a developing market for propulsion systems that will enable non-polluting and reliable electric aviation in the small aircraft and Unmanned Aerial Vehicle (UAV) sectors. UAV use is expanding rapidly. Many domestic applications of UAVs such as law enforcement or surveying could be served by electric UAVs. Congress has mandated that the FAA integrate UAVs into the airspace, but present UAVs do not have reliability levels consistent with use in the civilian airspace. General aviation is looking to electric flight as a way to reduce operating costs and greenhouse emissions in an age of ever increasing fuel prices and concern for the environment. The FAA is updating regulations to create a class of Electric Light Sport Aircraft (eLSA), but no commercially available motor drives meet general aviation reliability levels. This project will combine rigorous commercial aviation high reliability electronics design techniques with power electronics designs from heavy industry motor drives to create an electric aviation motor drive that is lightweight, fault tolerant, and highly reliable. The proposed drive will have reliability levels consistent with operation of electric aircraft in the civilian airspace while still retaining exceptional power density.

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