Press Release 18 June Siemens sells electric aircraft-propulsion business to Rolls-Royce Agreement signed: Rolls-Royce to acquire eAircraft Sale to accelerate development of sustainable air transport Rolls-Royce intends to become the leading supplier of electric and hybrid-electric propulsion systems for aircraft Siemens will continue to support the transition to electric aviation with its digital solutions portfolio Closing expected in late Prototypes of their electric propulsion systems especially developed for aviation are presented together with airframe manufacturers, who have partnered with siemens to power their innovative aircraft.
Statement concerning the accident on May 31st, According to the resolution of the Hungarian authorities released end of September, Siemens is not liable for the accident and our systems have worked without any failures during the flight. Our thoughts are with the families and friends of those involved in the incident. The complete propulsion system including a new generator, inverters and control systems has been developed by Siemens eAircraft and is expected to provide meaningful insights into the application of hybrid-electric systems for aircraft during future operation.
Highest power density inverter for electric aircraft. Siemens has developed a tiny inverter of highest power density for electric and hybrid-electric aircraft. It took its first flight on a Magnus eFusion electric test plane. The Siemens inverter "SD" uses silicon-carbide semiconductors and has a micro channel cooling plate. Siemens develops propulsion system for the CityAirbus airtaxi Heart of the electric propulsion systems is the newly developed SPD electric motor.
It has been specially designed for this specific application. Tiny inverter of highest power density The new inverter for electric and hybrid-electric aircraft uses silicon-carbide semiconductors. Highest power density inverter for electric aircraft Siemens has developed a tiny inverter of highest power density for electric and hybrid-electric aircraft.
Siemens develops propulsion system for the CityAirbus airtaxi. Since Airbus and Siemens have been working together on the development of hybrid-electric drive systems for the aviation sector. One of the pioneering aircraft that the partners are designing together is the four-seat CityAirbus. On the path to its maiden flight, which is scheduled for late this year, the aircraft has now reached an important milestone: The drive system that Siemens developed for the CityAirbus has been put into operation in a test on the ground.
Heart of the electric propulsion systems is the newly developed SPD electric motor. In addition to 8 coupled motors Siemens supplies the inverters and the energy management system for the CityAirbus demonstrator. This drive system was delivered in an extremely short period of time.
Its development took just over nine months from the initial concept to the finished prototype. World-record electric motor for the first time at the international Paris Air Show.
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For the first time Siemens presented its' world-record electric motor for aircraft at the international Paris Air Show. The motor in the aerobatic plane Extra LE was demonstrated at the daily air show where the electric powered Extra took a glider up to the air. In addition to the Kilowatts world-record electric motor, Siemens also presented two further propulsion systems of different power classes. World-record electric motor for aircraft sets new records. Siemens has developed a new type of electric motor that, with a weight of just 50 kilograms, delivers a continuous output of about kilowatts — five times more than comparable drive systems.
On Thursday, March 23, , the Extra LE aerobatic plane, powered by the propulsion system from Siemens, set two new speed records. On Friday, March 24, , the Extra LE gave another premiere performance by becoming the world's first electric aircraft to tow a glider into the sky. The nearly silent aerotow piloted by Walter Extra took a type LS8-neo glider up to a height of meters in only 76 seconds.
Siemens is contributing this technology to the cooperative project that Siemens and Airbus agreed to in April for driving the development of electrically powered flight. Electric drives are scalable, and Siemens and Airbus will be using the record-setting motor as a basis for developing regional airliners powered by hybrid-electric propulsion systems. Siemens is determined to establish hybrid-electric propulsion systems for aircraft as a future area of business.
Press Release 07 December Electric motor from Siemens sets new world climb record Extra LE electric plane sets world record New climb performance record: altitude of 3, meters in just 4 min 22 sec World air sports federation FAI confirms world record.
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Vortex generators have been used with a variety of flow control surfaces to mix low momentum fluid flow associated with a boundary air layer of the flow control surface with a high momentum fluid flow outside of the boundary air layer. The use of such vortex generators in a variety of aircraft have produced improvements in maneuver effectiveness.
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However, permanently installed wing vortex generators produce drag penalties and may accrete foreign matter such as ice shapes that significantly degrade the proper performance of the aircraft. Retractable vortex generators have been developed to compensate for these problems. Bauer U.
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However, the retractable vortex generators described in these documents require modification of the structure on which it is disposed to allow for internal space into which the vortex generator may be retracted when not in use. This requirement for adequate space to accommodate the vortex generators may influence the design of the wing or other structure in a negative manner.
This also requires that a wing, or other such structure having a flow control surface to which a vortex generator is desired to be added cannot be easily retrofitted for such vortex generators. Campbell U. The vortex generator of Campbell is formed of a shape memory alloy that is in the deflected position when no electric signal is applied to an associated heater and is in the undeflected position when an electric signal is applied to the associated heater.
However in both the deflected and undeflected states the vortex generator protrudes outside of the flow control surface and, while the undeflected state may produce less drag in comparison with the deflected state, the protrusion will still produce some undesirable residual drag and does not alleviate the problem of ice accretion on the exposed vortex generators.
The present invention provides a flow control device including a flow control surface over which fluid is designed to flow in a predetermined direction. An actuator is associated with each of the vortex generators, each actuator is adapted to position the associated vortex generator between the extended and retracted states.
In one embodiment, the acute angle that the vortex generators make with the predetermined direction is between 5 to 45 degrees when in the extended state. In one example, the actuator may be a heater that actuates a shape memory material made from a nickel-titanium alloy. However other types of electromechanical actuators may also be used. In one example, the vortex generator may be in the form of a fin that is parallel to the flow control surface when in the retracted state and set at an angle between 0 and degrees when in the extended state.
The flow control device as described provides reduction of drag and ice accumulation on flow control surfaces without requiring space in the flow control device to be reserved for the retracted vortex generators. Thus the retractable vortex generators of the current invention may be applied to a large variety of flow control surfaces without the necessity of extensive retrofitting of the flow control surfaces.
An array of vortex generators 30 are illustrated in an extended position. Vortex generators 30 are substantially flat structures that are generally perpendicular with respect to the plane of the control surface when extended. Each of the vortex generators 30 are constructed so as to be pivotable about a pivot axis The pivot axis 40 forms an acute angle a with the flow direction or primary wind direction F so as to facilitate the generation of a swirling fluid flow.
As shown the vortex generators have pivoted about pivot axis 40 so as to lie in generally parallel, overlying relation with the upper flow control surface In one embodiment, the retracted vortex generators lie in abutting contact with the upper flow control surface In this state the vortex generators are out of the way of the flow thus substantially eliminating drag effects from the vortex generators. Thus the vortex generators are extended when needed and retracted at all other flight conditions without requiring any space in the flow control device for storing the vortex generator when not in use.
In the illustrated embodiments, surface 20 has a substantially continuous, unmodified shape. It can be appreciated, therefore, that the vortex generators as illustrated in the figures herein can be retrofitted onto many different types of previously manufactured surfaces In another embodiment not shown , the upper surface area on which the vortex generator is disposed when deployed is slightly recessed.
Such a recess may have a depth that is of the same dimension as the thickness of the vortex generator, so that the vortex generator's exposed surface when retracted is substantially flush with adjacent surface portions of surface The vortex generator is actuated by a motor or actuator 50 so as to be repositioned between the retracted and extended state. In this example the actuator includes a heater 70 controlled by electrical input 80 from an external controller. The vortex generator 30 is formed with a shape memory alloy such as nickel-titanium alloys and is initially deformed to be in the extended position as shown in FIG.
In the extended position of FIG. Upon application of heat by the heater 70 above the particular transition temperature of the shape memory material, the vortex generator returns to the non-deformed state as shown in FIG. In another embodiment, the shape memory alloy vortex generator is initially in a retracted non-deployed position as illustrated in FIG. When heat is applied to the shape memory alloy vortex generator it moves from its retracted position of FIG.
A variety of types of actuators may be used to perform the pivoting function as described as evident to a person of ordinary skill in the art. For example thermal bimorph actuators, piezoelectric bimorph actuators as well as any other actuators capable of creating a pivoting action may be employed as the actuators of the present invention. In one embodiment, the flow control device of the present invention is employed as part of a wing of a tiltrotor aircraft.
Although a particular configuration of the vortex generators has been shown, the present invention is not limited to this configuration and a variety of other arrangements may be used in creating co-rotating as well as counter-rotating effects. Although the shape of the individual vortex generators has been shown as triangular, the present invention is not limited to this shape and other shapes of the vortex generator such as rectangular shapes or other shapes may be used.
While a particular embodiment of the present invention has been shown and described, it will be apparent to those skilled in the art that a variety of modifications may be made without departing from the teachings of the present invention. A flow control device comprising: a flow control surface over which fluid is designed to flow in a predetermined direction;.
A flow control device according to claim 1 , wherein the acute angle is from 5 to 45 degrees. A flow control device according to claim 1 , wherein the vortex generators are formed of a shape memory material, and wherein the actuator includes a heater that actuates the shape memory material. A flow control device according to claim 1 , wherein each of the respective vortex generators is in the form of a fin that lies parallel to the flow control surface when in the retracted state and is set at an angle greater than 0 degrees and less than degrees with respect to the flow control surface when in the extended state.
A flow control device according to claim 1 , wherein the flow control surface is part of a tiltrotor vehicle. An aircraft comprising: a tiltrotor wing;. An aircraft according to claim 6 , wherein the acute angle is from 5 to 45 degrees.
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An aircraft according to claim 6 , wherein the actuator includes a heater and wherein the vortex generators comprise a shape memory material that can be moved based on actuation of the heater. An aircraft according to claim 6 , wherein each of the respective vortex generators is in the form of a fin that lies parallel to the flow control surface when in the retracted state and is set at an angle greater than 0 degrees and less than degrees with respect to the flow control surface when in the extended state.