Device to set aircraft windmill up to working position

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft emergent power plant release. Aircraft windmill set-up device is arranged in fuselage compartment. The latter has skin and structural elements, hatch with cover articulated with structural elements, crosswise and lengthwise walls. Windmill has casing with bar first end secured thereto. This device comprises windmill retracted position lock, windmill release power drive and hatch cover opening mechanism. Bar second end is secured at compartment crosswise wall, at its bottom. Power drive thrust part is articulated with compartment top part crosswise wall while drive actuator is articulated with windmill bar second end. Hatch cover swivel with compartment structural elements is equipped with brackets with supports rigidly secured to hatch cover while arms are articulated with compartment structural elements. Cover opening mechanism is furnished with link composed of aligned body and rod connected to turn relative to each other about common axis. Besides, it has two journals with first ends articulated with link ends, second end being articulated with said bar nearby its first end. Second end is articulated with hatch cover.

EFFECT: simplified design, higher reliability, decreased weight and higher safety.

7 cl, 8 dwg

 

The technical solution relates to aircraft equipment, in particular equipment aircraft and can be used in the construction of devices of the release of emergency power systems for passenger aircraft.

Known release device emergency power plant, as described in the application for the invention of the Russian Federation No. 95111053 (IPC B64D 41/00, publ. 10.06.1997,).

The known device includes a housing with an earring charms, lock the retracted position, the actuator (in the terminology of the patent - spring cylinder) and duosonic. This one rocking of dusenyka installed on the frame, and the other is connected to the frame.

The known device is capable of producing movement of the emergency power plant with a maximum speed in the beginning of the movement after opening the lock retracted position and a maximum braking immediately before fixation in a released position.

The disadvantage of this solution is the ability to move only emergency power plant. When placing emergency power installation in the compartment of the aircraft requires additional mechanical devices for opening the valves of the hatch cover, which is associated with increasing mass of the entire device.

The closest analogue may be adopted technical solution for Putin is in the Russian Federation for invention №2396186 "Device for the emergency release power plant of the aircraft" (IPC B64D 47/00, publ. 10.08.2010,, application No. 2009106661 25.02.2009,).

Specified in the patent, the device is placed in the hold of the aircraft, equipped with power elements (in the terminology of the patent-frame) and hatch covers (doors). It is housed in the rear fuselage near the plane of symmetry of the aircraft.

Device for the emergency release of energy installation of a wind turbine includes a housing mechanism, translational actuator for opening the lock retracted position, dvukhzonnykh mechanism forming the kinematic lock fixing of a wind turbine in a released position, the thrust mechanism (traction drive of the leaf), the actuator of the release of a wind turbine.

The turbine is equipped with a housing, which is rigidly fixed to one end of the rod. The second end of the rod of a wind turbine attached to the upper transverse force element of the fuselage, and the supporting part of the actuator of the release of a wind turbine is pivoted in the lower part of the housing of the mechanism and its actuating portion pivotally connected with dvuhtomnika mechanism.

In this case the mechanism is fastened using brackets on the power elements in the hold of the aircraft.

On the body of the mechanism hinged related to each other, the mechanism for opening the lid of the hatch and release mechanism of a wind turbine.

The opening mechanism slid the key manhole equipped with a swivel connected by three rods, the upper and lower triplicity rocking chairs, earring, focus limit deviation lower techplace rocking, rocking chair front. Two of the rods mechanism opening the hatch covers one ends pivotally connected with the hatch, and the other ends through the said rockers, a third rod, earring - mentioned translational drive.

The release mechanism of a wind turbine equipped with a hinge connected the two shoulders rocking, draft, proximity switches with item effects.

Pull the release mechanism of a wind turbine at one end pivotally connected to the turbine and at the other end through one of the shoulders and element exposure rocking - mentioned power-driven release of a wind turbine, and the second arm of a rocking chair is a member of dvuhtomnika mechanism.

The known device for the emergency release power plant allows to use it for seaplanes or amphibians that require release of this setup up.

The disadvantage of this solution is that the hatch compartment contains two sash, and opening the valves and release the emergency power plant produced from the various actuators and mechanisms. In addition, the housing of the mechanism is equipped with a large number of structural elements. The presence of two cusps hatch actuators and a large number of elem is now device complicates the design of the device, increases its mass and the probability of asynchronous release emergency power installation and opening of the valves hatch, reduces the reliability of the device. Furthermore, this solution requires emergency power plant near the plane of symmetry of the aircraft and does not allow its installation in the side from the specified plane.

The technical problem to be solved by the proposed technical solution is the design of the transfer device in the operating position of the wind turbine of the aircraft, which combines the functions of a nomination of a wind turbine and opening the lid of the hatch cover and provides simultaneous execution of these functions in combination with the capability of placing a wind turbine in the compartment, the lid of which is offset from the plane of symmetry of the aircraft.

This solution delivers the exception of the installation of a separate structure to perform the function of opening the lid of the hatch cover, the labor reduction during Assembly of the structural elements during production and maintenance of aircraft.

The technical result of the claimed invention is the ability to move the thrust open the hatch in several planes, providing an exception asynchrony in the moving rod of a wind turbine and cover Liu the compartment and in different planes, in combination with the simplification of the structure, increased reliability, reduced weight and allow translation of a wind turbine into position through the hatch, offset from the plane of symmetry of the aircraft.

The technical result from the use of the invention is achieved as follows.

A device translation in the operating position of the wind turbine plane, which is placed in the compartment of the fuselage, provided with a casing and a power element, manhole with cover. Cover of the hatch cover hinged to power elements of the compartment.

In the known device, the turbine is equipped with a housing, which is rigidly fixed to the first end of the rod. In addition, the known device translation in the operating position of the wind turbine plane contains the retracted position of the wind turbine, the actuator release of a wind turbine and a mechanism for opening the lid of the hatch.

In the inventive solution, it is new that the transfer device in the operating position of the wind turbine of the aircraft placed in the compartment, which is provided with transverse and longitudinal walls. The second end of the rod pivotally mounted on the transverse wall of the compartment in its lower part. The base actuator pivotally mounted on the transverse wall of the compartment in its upper part, and its Executive part pivotally connected to the second end of the rod of a wind turbine.

In addition, the inventive device is new, that swivel hatch with power elements cover is provided sickle-shaped brackets. The Foundation of the Crescent-shaped brackets are rigidly connected to the hatch, and their console pivotally connected with the power elements of the compartment.

In accordance with the inventive solution, the mechanism for opening the lid of the claimed device is equipped with a thrust, which is made of placed coaxially to each other corps thrust and rod. The body of the rod and the rod are connected to each other with a possibility of rotation relative to each other around a common axis. In addition, in the inventive device, the mechanism for opening the lid provided with two pins, the first ends of which are pivotally connected to the ends of the specified thrust. The second end of one of the trunnions pivotally connected to the rod near its second end and the second end of the other of the axles hinged to the hatch.

The use of these features allows you to solve the technical problem and to obtain the technical result.

In addition, the housing of the turbine can be provided with a locking rod element placed on the side surface of the housing. In this lock the retracted position of the wind turbine can be firmly fixed on the longitudinal wall of the compartment and provided with a bracket that secures the locking rod case element of a wind turbine in the zafa cerovina position. The bracket should be carried out can be rotated to release the core element. Mount lock the retracted side of the longitudinal wall of the compartment allows you to keep the turbine compartment, excluding the effect of the air flow, to combine the location of the castle with the axis of the locking rod element and lock the turbine in the compartment in an unusable state. Supply lock the retracted position indicated by the bracket gives the opportunity to fix the wind turbine in the retracted position and in the event of an emergency by turning the bracket to release the locking rod element for output of a wind turbine from the compartment into position.

Most preferably the casing thrust mechanism opening hatch cover to provide a blind hole, in which the rigid sleeve and insert into the sleeve, the said rod, allowing the rod to perform axial rotation in the sleeve, providing a mechanism for opening the lid of the hatch synchronously with the rotation of the rod of a wind turbine.

In addition, the hinged connection of the second end of the axle mechanism for opening the lid of the post may be provided with a bearing sleeve which covers the second end of the axle and secured in the hole of the bracket installed on the side of the rod facing the hatch. Below is ipnic specified swivel allows the trunnion to perform axial rotation in the bearing sleeve and to provide a mechanism for opening the hatch covers in place of the connection pins to the bar.

In addition, the hinged connection of the second end of the axle mechanism for opening the lid with the hatch cover may be provided with a bearing sleeve which covers the second end of the axle and secured in the hole of the bracket installed on the hatch near one of the Crescent-shaped brackets. Supply specified bearing swivel allows the trunnion to perform axial rotation in the bearing sleeve and to provide a mechanism for opening the hatch covers in place of the connection pins with the hatch.

In addition, the hinged connection of the first end of each trunnion mechanism for opening the lid with a pull may be made in the form of connection "ear plug", and "ear" are provided with end thrust, and the item "fork" of the first end of the axle. The presence of compounds of the ear-plug" allows traction to rotate in a plane different from the plane of rotation of the above mentioned hinge joints and to provide a mechanism for opening the lid of the hatch in the joints of the ends of the rod with pins.

The proposed solution is illustrated in the following figures:

Fig.1 - the design of the transfer device in the operating position of the wind turbine plane in the retracted position when viewed from the front (plating compartment not shown);

Fig.2 - the design of the transfer device in the operating position of the wind turbine of the aircraft in the fired position when viewed from the front (plating compartment not shown);

Fig.3 - the design of the transfer device in the operating position of the wind turbine plane in the retracted position when the form on the right side (plating compartment not shown);

Fig.4 - the design of the transfer device in the operating position of the wind turbine of the aircraft in a released position when the form on the right side (plating compartment not shown);

Fig.5 - the design of the transfer device in the operating position of the wind turbine of the aircraft in the released position in the square when viewed from the front (plating compartment not shown);

Fig.6 - the design of the mechanism for opening the lid of the hatch with the bracket attached to the rod of a wind turbine and a bracket mounted on the hatch;

Fig.7 - pull design of the mechanism for opening the lid of the hatch in the ISO;

Fig.8 is a cross - section of the thrust mechanism for opening the lid of the hatch;

The transfer device in the operating position of the wind turbine 1 aircraft approved for inclusion in the operation of a wind turbine and feeding electric current consumers, particularly necessary for the continuation of flight in an emergency in case of failure of generators and engines.

The inventive device is made to ensure the simultaneous opening of the cover, which houses the turbine in the retracted position, and a translation of a wind turbine from the retracted to the working position in the RAID the next air stream.

The transfer device in the operating position of the wind turbine 1 of the aircraft placed in the compartment of the fuselage, which is provided with plating and structural members 2, Luke 3 cover 4.

The inventive transfer device in the operating position of the wind turbine plane preferably in the fore part of the fuselage of the aircraft in the compartment, which is provided with transverse 10 and 11 longitudinal walls.

The longitudinal wall 11 of the compartment may be offset from the plane of symmetry of the aircraft, it is most preferable to place it parallel to the plane of symmetry of the aircraft.

The wind turbine 1 includes a housing 5, which is placed on the shaft of the generator (see Fig.3, 5). On the housing 5 of a wind turbine is rigidly fixed to the first end of the rod 6.

The design of the transfer device in the operating position of the wind turbine, in addition, contains the 7 retracted position of the wind turbine, the power actuator 8 release of a wind turbine and the mechanism 9 open hatch.

The housing 5 of a wind turbine equipped with a locking rod element 17 (see Fig.1, 5), which is rigidly fixed on the side surface of the housing 5. The locking rod element 17 provides the hold of a wind turbine 1 in the retracted position by means of lock 7. Lock 7 should be fixed at the bracket 22, which is rigidly fixed on the longitudinal wall 11.

The transverse wall Otsuka is equipped with three fixed on the brackets 23, 24, 25. The brackets 23 and 24 are located in the lower part of the transverse wall. Suitable two of these bracket 23, 24 are placed next to each other and to connect them protruding portion rigidly attached to them axis 27. The third bracket 25 of the transverse wall is provided with a double eye, should be placed over the above two brackets 23, 24 in the upper part of the transverse wall 10.

The second end of the rod 6 of a wind turbine is hinged to the transverse wall 10 of the compartment in its lower part. It is installed on the axis connecting the two lower brackets 23, 24 of the transverse wall 10 can be rotated around the specified axis. And 6 bar near the second end is provided with a double eyelet 26 (see Fig.3, 5).

The actuator 8 of the release of the wind turbine includes a hydraulic cylinder with a spring mechanism, which is the reference part, and a piston rod constituting the Executive part. Thus the end face of the cylinder support part and the end of the piston rod of the Executive part of the actuator 8 release of a wind turbine is provided with elements "ear".

The base actuator 8 release of a wind turbine is pivotally connected to the bracket 25 of the transverse wall 10 of the compartment in its upper part, and its Executive part - with double eyelet 26 of the second end of the rod 6 of a wind turbine.

The fastening support part of the actuator 8 you USCA wind turbine on the transverse wall 10 of the cover is made through the connection element of the "ear" of the end of the cylinder and double lugs of the bracket 25 of the transverse wall 10, and mount the Executive part with the second end of the rod 6 through the connection element of the "ear" of the piston rod with double eyelet 26 of the second end of the rod 6.

Cover 4 3 hatch hinged on power elements 2 bays. Swivel cap 4 hatch with power elements 2 compartment provided with a Crescent-shaped brackets 12, which are rigidly connected to the cover 4 of the hatch, and their console protruding from the bases of the brackets pivotally connected with the power elements 2 compartment (see Fig.2, 5). Each Crescent-shaped bracket 12 is placed on the inner side of the cover 4 of the hatch, and the console is made to "ear". Each power element 2 compartment provided with a rigidly mounted thereon a bracket, made with double eye, which is connected with the element of the "ear" of the respective Crescent-shaped bracket 12. These brackets with double eyelets and Crescent-shaped brackets 12 between the cover and hatch form hinges which are located on the same axis.

Mechanism 9 (see Fig.3, 4, 5) opening hatch fitted with a thrust of 13 and two pins 16 (see Fig.2, 6). Rod 13 is made of placed coaxially to each other enclosure 14 and rod 15. Case 14 and the rod 15 are connected to each other with a possibility of rotation relative to each other around a common axis (see Fig.7, 8). Rod 13 is further provided with W is the left main coronary artery 19. The housing 14 of the thrust provided with a blind hole, in which is rigidly fixed to the sleeve 19. The rod 15 near its mid-fitted collar. The rod 15 is inserted into the sleeve 19 to the level of the flange and is fixed in the sleeve nut with a clearance to allow axial rotation of the rod 15 in the sleeve 19 of the rod 13.

The first ends of the mentioned pins 16 pivotally connected to the ends of the specified rod 13 (see Fig.6): the first end of one of them connected to the housing 14 of thrust, and the first end of the other with the rod 15. The hinged connection of the first end of each pin 16 with thrust 13 is made in the form connections "ear plug". Moreover, the item "ear" is equipped with both ends of the rod 13, which are located on the side of the rod 15, and the housing 14. Element "fork" is equipped with the first end of each pin 16. The item is a "fork" of the first end of one of the pins 16 is connected to the element of the "ear" of the rod 15 thrust. The item is a "fork" of the first end of the other axle 16 is connected to the element of the "ear" of the housing 14 thrust.

The second end of one of the trunnions 16 pivotally connected to the rod 6 near its second end and the second end of the other axle 16 hinged to the cover 4 of the hatch.

The hinged connection of the second end of the first of these pins 16 with the rod 6 of a wind turbine equipped with a bearing. Bearing this connection is made with the sleeve, which covers the second end of asanas axle 16. The said bearing is placed in the cylindrical hole of the bracket 21, which is mounted on the first end of the rod 6 of the wind turbine from the side adjacent to the opening 3.

The hinged connection of the second end of the second mentioned pins 16 with the cover 4 of the hatch is also provided with a bearing. Bearing this connection is made with the sleeve, which covers the second end of the specified pin 16 (see Fig.6). The said bearing is placed in the cylindrical hole of the bracket 20, which is mounted on the inner surface of the cover 4 of the hatch near one of the Crescent-shaped brackets 12 swivel cap with power elements of the compartment.

In flight during normal operation of the power supply system of the aircraft, the wind turbine is located and locked in the retracted position inside the hatch compartment of the fuselage, the closed hatch cover (see Fig.1, 3).

A hydraulic cylinder with a spring loaded mechanism supporting part of the actuator of the release of a wind turbine is ready to work. Under the influence of the spring mechanism supporting part of the actuator of the release of a wind turbine creates a pressure on the piston rod of the Executive part.

With the failure of two engines, the failure of the main power supply of the aircraft in flight includes the transfer device in the operating position of the wind turbine.

Works C the IOC retracted position of the wind turbine to the opening. In this clip, retaining locking the anchor body of a wind turbine in the locked position, rotates and releases the locking rod case element of a wind turbine. In this wind turbine is removed from the lock in the lock retracted position.

Along with this, under the pressure of the spring mechanism of the cylinder support part of the piston of the Executive part of the actuator of the release of a wind turbine is moved to the extreme position, acting on the second end of the rod through the hinge connected to them double eye rod. Under the specified impact rod with a wind turbine in the hold of the aircraft begins to rotate from the retracted position.

In the process of turning the rod specified force then acts on the mechanism of opening the hatch covers. Pivotally connected first and second axle bearings of the brackets of the first end of the rod and the cap and pull the specified mechanism, moving in different planes, transmit the force on the hatch. Manhole cover under this influence starts to open synchronously to rotate the rod of a wind turbine, opening and releasing the opening of the hatch to exit the compartment of a wind turbine. Moreover, the manhole cover is moved in a plane other than the plane of rotation of the rod.

As a result, the wind turbine from a retracted position within the compartment of the fuselage interpret the given operating position, in the air flow outside of the fuselage, and simultaneously, the manhole cover is open.

Simultaneous movement on the issue of a wind turbine into position and opening the hatch covers is due to the possibility of moving the traction using the swivel mechanism opening the hatch covers in several planes.

After the release of a wind turbine and output it to operating speed under the influence of the velocity head of the air its generator is connected to the required bus power supply system of the aircraft.

In the released state in the whole range of flight regimes generator of a wind turbine provides the power required required consumers.

Thus, the proposed technical solution of the transfer device in the operating position of the wind turbine of the aircraft creates an opportunity to move the thrust open the hatch in several planes.

This capability provides an exception asynchrony movement and simultaneous rotation of the rod of a wind turbine and the hatch cover in different planes, simplified design, improved reliability, reduced weight and volume of the transfer device in the operating position of the wind turbine of the aircraft, as well as increasing the safety of the flight.

In the end provides the exception of the installation of the individual is the first structure to perform the function of opening the lid of the hatch cover, the labor reduction during Assembly of the structural elements during production and maintenance of aircraft.

It is most preferable to use the present invention in the design of aircraft transport category for the placement of a wind turbine in the forward compartment, alcove adjacent to the front landing gear. In this niche of the front landing gear is placed in the symmetry plane of the aircraft. As the longitudinal walls of the compartment of a wind turbine is used is offset by some distance from the plane of symmetry of the plane wall niches front landing gear, with the hatch cover with a wind turbine is offset from the plane of symmetry of the aircraft sideways at a greater distance.

1. The transfer device in the operating position of the wind turbine of the aircraft placed in the compartment of the fuselage, provided with a casing and a power element, hatch with cover, hinged to power elements of the compartment, while the wind turbine is equipped with a housing, which is rigidly fixed to the first end of the rod, in addition, the device contains the retracted position of the wind turbine, the actuator release of a wind turbine and a mechanism for opening the lid of the hatch, characterized in that the fuselage is equipped with transverse and longitudinal walls, the second end of the rod pivotally mounted on the transverse wall of the compartment at the bottom of the hour and, the base actuator pivotally mounted on the transverse wall of the compartment in its upper part, and its Executive part pivotally connected to the second end of the rod of a wind turbine, in addition, the hinged connection of the cover with the power elements of the cover is provided sickle-shaped brackets which are rigidly connected to the hatch, and the console pivotally connected with the power elements of the compartment, mechanism for opening the lid is equipped with a thrust, made of placed coaxially to each other of the housing and a rod connected with the possibility of rotation relative to each other around a common axis, and two pins, the first ends of which are pivotally connected to the ends of the specified thrust the second end of one of them pivotally connected to the rod near its first end and the second end of the other of them hinged to the hatch.

2. The transfer device in the operating position of the wind turbine of the aircraft under item 1, characterized in that the housing of a wind turbine equipped with a locking rod element placed on the side of the case.

3. The transfer device in the operating position of the wind turbine of the aircraft under item 2, characterized in that the lock retracted position of the wind turbine is rigidly fixed on the longitudinal wall of the compartment and provided with a bracket that secures the locking rod case element of wind is vegetale locked in a fixed position, when this bracket is made to rotate to release the core element.

4. The transfer device in the operating position of the wind turbine of the aircraft under item 1, characterized in that the housing thrust mechanism opening hatch fitted with blind hole, in which is rigidly fixed to a sleeve into which is inserted the said rod.

5. The transfer device in the operating position of the wind turbine of the aircraft under item 1, characterized in that the hinged connection of the second end of the axle above-mentioned mechanism with a hatch provided with a bearing sleeve which covers the second end of the axle and secured in the hole of the bracket installed on the hatch near one of the Crescent-shaped brackets.

6. The transfer device in the operating position of the wind turbine of the aircraft under item 1, characterized in that the hinged connection of the second end of the axle above-mentioned mechanism with a rod provided with a bearing sleeve which covers the second end of the axle and secured in the hole of the bracket installed on the side of the rod facing the hatch.

7. The transfer device in the operating position of the wind turbine of the aircraft under item 5 or 6, characterized in that the hinged connection of the first end of each pin above-mentioned mechanism with a pull-type connection "ear plug", and "ear" are provided with end thrust, and elements of the Ohm fork first end of each axle.



 

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7 cl, 1 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed platform comprises bundle of aircraft coupled by flexible rope transmitting forces and incorporating electric power transmission and control signal channels. One of said aircraft carries windmill. Method of locating high-altitude platform consists in locating aircraft in stable wind flows displacing at different speed relative to earth and/or different directions. Besides, it includes retaining said bundle at preset point or its displacement relative to earth in preset direction by aerodynamic controls and power plants. Difference in energy of wind flows is used at invariable flight altitude to said end as well as power generated by windmill at one aircraft and transmitted to other aircraft. Payload is arranged at aircraft or connection rope.

EFFECT: longer high-altitude flight.

4 cl, 5 dwg

Drone // 2492119

FIELD: transport.

SUBSTANCE: invention relates to systems exploiting drones for observation of earth surface and transmission of signals indicating location of ground structures. Invention aims at increasing output voltage required for drone onboard radar transmitter module power supply by isolating the drone onboard hardware power supply from drone onboard radar transmitter module power supply to decrease electric interferences in common power supply system. Note here that this design allows decreasing onboard radar operating range. Proposed device comprises generator with permanent magnets, controlled sync rectifier, electric power accumulator, voltage stabiliser and system control electronic unit. Permanent magnet coils number N in extra miniature sync generator is set by the ratio N≥0.005 lrB, where l is rotor length, Ir is inner radius (m), B is rotor magnetic induction.

EFFECT: simplified transmitter, higher system reliability and radar power potential.

1 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft power supply systems. Proposed system P is designed to increase aircraft power supply system output and consists of the following components: power supply 10 with channel K extending between two openings (4, 5, 85, 95) at fuselage R of aircraft F, turbine 12 with generator 14 arranged in channel K, covering device 6 to stop front opening 4, open-close device 61 and unlocking device 61 connecting with covering device 6. Said unlocking device locks covering device when current of first intensity signal is fed thereto and unlocks it when current of second intensity signal is fed thereto. Note here that signal second intensity exceeds the first one by preset magnitude. Besides it includes drive device 41, 42 functionally coupled with open-close device 61 to generate go-no-go signal, go-switch 27 functionally coupled with power generation control device 25 and with unlocking device 62. The latter controls unlocking device 62 by second signal intensity to lock covering device 8 in response to power request signal from power generation control device 25.

EFFECT: higher reliability of power supply.

14 cl, 3 dwg

FIELD: transport.

SUBSTANCE: fuel cell system module 10 for aircraft 32 is composed of tail boom to be secured to airframe section 30 by fastener intended for split joint of fuel cell system module elements to aircraft airframe structural component.

EFFECT: structural element of said module makes integral part of aircraft outer skin 34 in jointed state.

8 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to power engineering and may be used in power controller 1 design to control aircraft hydride power source. Power controller 1 allows measuring power demand of consuming hardware 2. Said device 1 allows determining first operating characteristic of first power source 3 and second operating characteristic of second power source 4. First power source 1 and second power source 4 serves to generate first and second required portions of necessary demand.

EFFECT: efficient supply of power to consuming hardware.

14 cl, 6 dwg

FIELD: transport.

SUBSTANCE: set of invention relates to aircraft electric power supply circuit. Proposed circuit comprises power distribution circuit 16 and electric hardware supply circuit 5b, and electric power generator 27 incorporates with aircraft engine to supply anti-icing circuit 5a. Electric hardware comprises nacelle consuming components 5b connected DC voltage distribution with bus 35 connected with voltage converter circuit 34 supplied by distribution circuit 17. Anti-icing circuit 5a comprises, at least, one resistor 61 to dissipate electricity sent back to DC voltage distribution circuit 35 by, at least, some of nacelle consuming components. Aircraft comprises above described power supply circuit.

EFFECT: simplified design, reduced power consumption and power losses.

9 cl, 3 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft auxiliary power plant. Proposed power plant comprise conversion reactor, battery of fuel cells, fuel storage and feed units communicated with conversion reactor, afterburner, turbine with its shaft supporting compressor and electric generator. Conversion reactor generating synthesis gas is integrated with battery of said fuel cells. Synthesis gas generation channel communicates with fuel or oxygen feed channels and intermediate gas manifold of synthesis gas passage into fuel cells, while anode and cathode gas discharge channels are communicated with afterburner.

EFFECT: higher power output and reduced fuel consumption.

3 cl, 1 dwg

FIELD: transport.

SUBSTANCE: invention relates to system and method of electric power distribution inside aircraft. Proposed system comprises primary 10 and secondary 11 systems for distribution of electric power from several sources (12-16) to aircraft using components (18, 19) via configured electrical and/or electronic components of protection/switchgear. Every Primary system 10 receives power from power sources (12-16) to transmit it into using components (18) that feature high consumption of electric power. Secondary system 11 receives power from primary system 10 to transmit it into using components (19) that feature low consumption of electric power. Proposed method consists in that electric power from several sources is distributed using primary and secondary system (10, 11) and fed into aircraft using equipment via configured electrical and/or electronic components of protection/switchgear controlled by instructions using electronic components. Note here that said system (10, 11) comprises electronic means of instructions wherein loaded is configuration file (FC1, FC2) to assign setting status for every component of protection/ switchgear.

EFFECT: possibility to activate or deactivate power supply without using procedures on loading onboard software in installation of new equipment.

19 cl, 2 dwg

FIELD: power plants for auxiliary-purpose flying vehicles.

SUBSTANCE: proposed system includes panel of lifting surface of flying vehicle with device for localization of overflow of airflow; this device includes flow-through nacelle, power loop and air-jet engine with exit nozzle. Axis of nacelle lies in way of motion of lifting surface of flying vehicle; inlet part is made in form of side inlet window located on lower part of lifting surface panel. Power loop includes at least one wind wheel with at least one electric power generator which are arranged inside flow-through nacelle in parallel with inlet window. Engine is mounted in outlet part of flow-through nacelle.

EFFECT: extended field of application; enhanced safety of flight.

3 dwg

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