EP2720943A1 - System for integrating a diesel engine in a drone - Google Patents

System for integrating a diesel engine in a drone

Info

Publication number
EP2720943A1
EP2720943A1 EP12731301.3A EP12731301A EP2720943A1 EP 2720943 A1 EP2720943 A1 EP 2720943A1 EP 12731301 A EP12731301 A EP 12731301A EP 2720943 A1 EP2720943 A1 EP 2720943A1
Authority
EP
European Patent Office
Prior art keywords
engine
drone
cylindrical element
fixed manner
sprockets
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12731301.3A
Other languages
German (de)
French (fr)
Inventor
Christophe Soutif
Emmanuel Joubert
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus DS SAS
Airbus Group SAS
Original Assignee
Cassidian SAS
European Aeronautic Defence and Space Company EADS France
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Cassidian SAS, European Aeronautic Defence and Space Company EADS France filed Critical Cassidian SAS
Publication of EP2720943A1 publication Critical patent/EP2720943A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/14—Direct drive between power plant and rotor hub
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/04—Aircraft characterised by the type or position of power plant of piston type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines

Definitions

  • the present invention relates to a system for integrating a diesel engine in an aircraft without a human pilot, such as a drone. More particularly, an object of the invention is to mitigate, or even absorb, the vibrations or vibratory waves that are propagated through the airframe by the diesel engine when it is operating.
  • UAV Unmanned Aerial Vehicle
  • the task of a drone is to carry a payload designed to carry out missions relating to surveillance, or intelligence, or combat.
  • the size and weight of such aircraft varies according to the operational capabilities required of them. In fact, the weight of a drone may be a value anywhere in a range from a few kilograms to several tons.
  • aerial drones differ from each other in terms of both their propulsion and power supply systems.
  • fixed-wing drones which have the same general appearance as an aeroplane, and which have various flying ranges and are capable of flying at various altitudes.
  • the primary task of this kind of drones is to track the movement of a target.
  • target is understood to mean a person, a group of individuals, or also an object or a number of objects, that is moving or stationary within a field of vision of sensors installed in this drone.
  • the length and volume of these drones are respectively proportional to the degree of autonomy with which they carry out their mission, in other words, the lenght depends on the quantity of fuel they can carry to supply their propulsion system, and on their payload, which may for example includes surveillance instrumentation, weaponry, missiles, or similar.
  • rotary-wing drones which have the same general appearance as helicopters, such as the ORKA developed by Cassidian.
  • ORKA developed by Cassidian.
  • the advantage of this drone is that it is able to maintain a geostationary position above a target. It also has a degree of flight autonomy that enables it to fly for 5 to 6 hours, and it is powered by a petrol engine.
  • stealth is understood to mean that the characteristics of the drone are designed to create a smaller signature, undetectable or unidentifiable by a radar system or by an individual.
  • the objective of the present invention is to resolve all of these disadvantages of the prior art.
  • the invention suggests a system for integrating a diesel engine in a helicopter-type drone.
  • Using of a diesel engine instead of a petrol engine makes it possible to reduce fuel consumption without having to increase the size, volume and weight of the drone.
  • the invention suggests a diesel engine that resolves these problems and at the same time enables the drone to fly autonomously for longer than 8 hours.
  • the diesel engine according to the invention comprises a device for absorbing vibrations.
  • the object of the invention is therefore an engine intended for use in a drone and comprising at least one cylinder that is capable of confining the combustion, inside which a piston performs a reciprocating linear motion, said reciprocating linear motion being converted into rotary motion by means of a crankshaft, characterized in that the engine is a diesel engine.
  • a device for absorbing the torque vibrations of the engine said device being mounted in fixed manner on one end of the crankshaft for the purpose of attenuating the vibrations;
  • the vibration absorbing device comprises:
  • crankshaft adapter on which a first cylindrical element is mounted in the manner of a pivot.said element being furnished with claws and teeth that are chamfered so as to enable three sprockets to be assembled,
  • a support shaft one end of which is furnished with an assembly of spacer rings, ball bearings and a locking ring, said locking ring being configured so as to engage in fixed manner inside the adapter, the support shaft being mounted in fixed manner inside a flywheel such that the plate is pressed against the wheel;
  • the three sprockets are made from elastomer materials
  • the second cylindrical element comprises a ring having an external diameter larger than that of the first cylindrical element and an internal diameter identical with that of the first cylindrical element, the dimensions of the diameters of said rings being configured such that they fit in the adapter;
  • the plate has an internal orifice through which the first cylindrical element passes through as well as the sprockets;
  • a further object of the invention is a rotary-wing drone having a frame in which are located at least the following:
  • control unit associated with said set of sensors, characterized in that it comprises an engine according to any one of the preceding characteristics.
  • the engine is suspended on the ends of three elastomer mounts, cleverly arranged around the engine so that the center of rigidity is located close to the center of gravity of the suspended part of the engine;
  • a tail boom comprising a proximal end mounted in fixed manner on the frame, and a distal end supporting a tail rotor via a gearbox, said gearbox being coupled with the transmission chain of the engine via a transmission shaft of the tail rotor;
  • the tail boom includes a tailplane at its distal end
  • FIG. 1 a schematic representation of a stealth type helicopter drone according to an embodiment of the invention
  • FIG. 2 a schematic representation of the diesel engine integration system according to an embodiment of the invention
  • FIG. 4 a detailed schematic representation of the elements that make up the absorption device according to an embodiment of the invention.
  • FIG 1 is a diagrammatic representation of a rotary wing drone 1 according to one embodiment of the invention.
  • This drone 1 comprises, but is not limited to, a frame 2 that supports landing skids 3a, 3b in fixed manner.
  • Frame 2 is designed such that it is able to support an engine 4, a set of sensors 13 (illustrated in figure 1) designed for carrying out surveillance, and/or intelligence collection and/or guiding the movement of drone 1 , and a control unit 14 (illustrated in figure 2) associated with this set of sensors.
  • a control unit 14 of such kind is known to one skilled in the art and does not constitute an object of our invention. It therefore serves no purpose to describe this control unit 14 in greater detail here. At all events, such a control unit 14 is capable of enabling the drone 1 to operate completely autonomously with regard to its movement and positioning relative to a target based on data that has been transmitted to it beforehand.
  • target is used to mean a person, a group of individuals, or also an object or group of objects that is moving or located within a field of vision of sensors 13 of the drone 1.
  • drone 1 is equipped with a communications unit (not shown) that is connected to control unit 14 so that it is able to relay the guidance instructions transmitted by the operator to the control unit via a supervision interface (not shown).
  • a tail boom 5 comprises a proximal end 5a that is mounted in fixed manner on frame 2, and a distal end 5b that supports a tail rotor 6 via a gearbox (not shown).
  • This gearbox is coupled to the transmission chain of engine 4 via a transmission shaft 7 of the tail rotor.
  • distal end 5b of the boom is equipped with a tailplane (not shown).
  • Engine 4 is a diesel engine instead of the petrol engine that is used in the prior art. The sole purpose of using such a diesel engine is to increase the flying autonomy of drone 1 , raising it from 5 hours to more than 8 hours.
  • Engine 4 is a classic diesel engine, generally used for motor vehicles, in order to reduce manufacturing costs. Thus, engine 4 converts the energy generated by combustion of the fuel into mechanical energy. To do this, engine 4 includes a number of generic elements that are known to one skilled in the art and therefore do not appear in the figures.
  • engine 4 is equipped with one or more cylinders designed to contain combustion cycles. Inside each cylinder, a piston slides in a reciprocating linear movement. This linear movement is converted into rotary movement by means of a connecting rod that connects the piston to a crankshaft.
  • crankshaft is used to describe a series of cranks on a shaft.
  • a flywheel (not shown), which in motor vehicles is normally linked to a clutch and/or a starter motor ring gear.
  • pulley wheel 8 At the other end of the crankshaft there is a pulley wheel 8, which pulley wheel 8 is coupled with pulley wheel 10 by means of a belt 9 to transmit the rotary movement of the crankshaft to a transmission system 11.
  • This transmission system 11 comprises a journal 12, on which rotor vanes 13a, 13b are mounted in fixed manner.
  • Pulley wheel 8 is also coupled with tail rotor transmission shaft 7 via a further belt (not shown).
  • engine 4 Since engine 4 generates an enormous quantity of heat, engine 4 is equipped with a cooling circuit that is routed as closely as possible to the zones where the heat is generated in order to maintain an optimum temperature in engine 4 and the interior of drone 1. A heat transfer fluid is forced through the cooling circuit by means of a pump 15 until it reaches a radiator 16 mounted in fixed manner on the frame, one of the surfaces of which radiator 16 gives onto the exterior of drone 1. Thus when flying, the air outside the drone 1 passes through radiator 16, and undesirable energy from engine 4 is transferred to the ambient air.
  • drone 1 comprises a fuselage 17 designed using stealth principles, as shown in figure 1.
  • stealth will be understood to mean that the characteristics of drone 1 are designed to create a reduced signature, one that is undetectable or unidentifiable by a radar system or an individual.
  • Fuselage 17 is also furnished with vents 18 designed to improve the ventilation of engine 4.
  • Radiator 16 is located at the front of the fuselage to maximise its air intake.
  • an orifice 19 is provided in the fuselage so that radiator 16 is able to have a surface 16a that is in contact with the exterior of drone 1.
  • the invention is configured firstly such that engine 4 is suspended at the ends of three elastomer mounts (not shown), cleverly arranged around engine 4 so that the centre of rigidity is located close to the centre of gravity of the suspended part of engine 4.
  • the invention is configured such that the flywheel of engine 4 is coupled to a vibration absorbing device 20.
  • This device 20 comprises an adapter 22 for the engine shaft, on which is mounted an antivibration shaft coupling system.
  • This antivibration shaft coupling system comprises a first cylindrical element 23 with an orifice passing completely through it so that it is able to be fitted on adapter 22 in the manner of a pivot.
  • This cylindrical element 23 is furnished with claws and teeth which are chamfered to allow a set of three elastomer sprockets 24, 25, 26 to be assembled.
  • a ring 27 is then placed over sprocket 26 before it is covered by a further cylindrical element 28.
  • This cylindrical element 28 comprises a ring having an external diameter that is larger than that of cylindrical element 27 but an internal diameter exactly the same as that of element 27, so that it is able to fit into adapter 22.
  • Cylindrical element 28 comprises claws and teeth that are designed to engage with elastomer sprockets 24, 25, 26 and with element 27.
  • a ring 29 is interposed in fixed manner between a plate 30 and cylindrical element 28. The plate is furnished with an internal orifice to allow element 27 to pass through together with sprockets 24, 25, 26.
  • a support shaft 31 is equipped at one end thereof with an assembly of spacer rings 32, 33, 34, ball bearings 35, 36 and a locking ring 37 so that it is able to fit in fixed manner inside engine shaft adapter 22.
  • the support shaft is mounted in fixed manner inside an elastomer flywheel 21 such that plate 30 is pressed against flywheel 21.
  • Adapter 22 is mounted in fixed manner on the end of the crankshaft so as to absorber the vibrations caused by the torque of the engine, and thus attenuate these vibrations.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Remote Sensing (AREA)
  • Vibration Prevention Devices (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)

Abstract

The present invention relates to a rotary-wing drone (1) comprising a frame in which are located: - a set of sensors (13) designed for performing tasks of surveillance and/or intelligence gathering and/or assisting with the guidance of the drone (1), and - a control unit (14) associated with this set of sensors (13), characterized in that it comprises a diesel engine (4).

Description

SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE
Field of the invention
The present invention relates to a system for integrating a diesel engine in an aircraft without a human pilot, such as a drone. More particularly, an object of the invention is to mitigate, or even absorb, the vibrations or vibratory waves that are propagated through the airframe by the diesel engine when it is operating.
Prior art and technical problems encountered
The prior art in the field of aeronautics includes aircraft without a human pilot on board, Unmanned Aerial Vehicle (UAV), generally called drones. The task of a drone is to carry a payload designed to carry out missions relating to surveillance, or intelligence, or combat. The size and weight of such aircraft varies according to the operational capabilities required of them. In fact, the weight of a drone may be a value anywhere in a range from a few kilograms to several tons.
These aerial drones differ from each other in terms of both their propulsion and power supply systems. At present, there is a category of drones, called fixed-wing drones, which have the same general appearance as an aeroplane, and which have various flying ranges and are capable of flying at various altitudes. The primary task of this kind of drones is to track the movement of a target. In this context, the term target is understood to mean a person, a group of individuals, or also an object or a number of objects, that is moving or stationary within a field of vision of sensors installed in this drone.
The length and volume of these drones are respectively proportional to the degree of autonomy with which they carry out their mission, in other words, the lenght depends on the quantity of fuel they can carry to supply their propulsion system, and on their payload, which may for example includes surveillance instrumentation, weaponry, missiles, or similar.
There is also another category of drones, known as rotary-wing drones, which have the same general appearance as helicopters, such as the ORKA developed by Cassidian. The advantage of this drone is that it is able to maintain a geostationary position above a target. It also has a degree of flight autonomy that enables it to fly for 5 to 6 hours, and it is powered by a petrol engine.
Accordingly, there is a need to increase the autonomy of such drones so that they are able to remain in the theatre of operations for longer. At the same time, it is difficult to increase this autonomy without increasing the size of the aircraft so that it can carry more petrol, which in turn renders it more visible and potentially more vulnerable to a possible attack in the respective theatre of operations.
In order to reduce the visibility and therewith the vulnerability of this type of drone, it features a fuselage configured to lend it certain stealth characteristics, as shown in figure 1. The term stealth is understood to mean that the characteristics of the drone are designed to create a smaller signature, undetectable or unidentifiable by a radar system or by an individual.
Explanation of the invention
The objective of the present invention is to resolve all of these disadvantages of the prior art. To this end, the invention suggests a system for integrating a diesel engine in a helicopter-type drone.
Using of a diesel engine instead of a petrol engine makes it possible to reduce fuel consumption without having to increase the size, volume and weight of the drone.
However, replacing the petrol engine with a diesel engine in drones to increase their autonomy presents a number of design engineering difficulties, particularly arising from the vibrations generated by the diesel engine, but also due to the difficulty of finding an existing diesel engine that is certifiable and of sufficiently low weight.
The invention suggests a diesel engine that resolves these problems and at the same time enables the drone to fly autonomously for longer than 8 hours. To this end, the diesel engine according to the invention comprises a device for absorbing vibrations.
Diesel engines originating from the automotive industry may be used, thereby enabling production costs to be kept low. By using such engines, it is also possible to take advantage of certified reliability and a negligible maintenance requirement. The object of the invention is therefore an engine intended for use in a drone and comprising at least one cylinder that is capable of confining the combustion, inside which a piston performs a reciprocating linear motion, said reciprocating linear motion being converted into rotary motion by means of a crankshaft, characterized in that the engine is a diesel engine.
The invention also includes any of the following characteristics:
- a device for absorbing the torque vibrations of the engine, said device being mounted in fixed manner on one end of the crankshaft for the purpose of attenuating the vibrations;
- the vibration absorbing device comprises:
- a crankshaft adapter on which a first cylindrical element is mounted in the manner of a pivot.said element being furnished with claws and teeth that are chamfered so as to enable three sprockets to be assembled,
- a first cylindrical element mounted over the sprocket before a second cylindrical element is placed over it, said second cylindrical element being furnished with claws and teeth designed to enable them to engage with the sprockets as well as with the first cylindrical element,
- a ring interposed in fixed manner between a plate and the second cylindrical element,
- a support shaft, one end of which is furnished with an assembly of spacer rings, ball bearings and a locking ring, said locking ring being configured so as to engage in fixed manner inside the adapter, the support shaft being mounted in fixed manner inside a flywheel such that the plate is pressed against the wheel;
- the three sprockets are made from elastomer materials;
- the second cylindrical element comprises a ring having an external diameter larger than that of the first cylindrical element and an internal diameter identical with that of the first cylindrical element, the dimensions of the diameters of said rings being configured such that they fit in the adapter;
- the plate has an internal orifice through which the first cylindrical element passes through as well as the sprockets;
- the flywheel is made from elastomer material. A further object of the invention is a rotary-wing drone having a frame in which are located at least the following:
- a set of sensors designed for performing surveillance and/or reconnaissance and/or guiding the movement of the drone, and
- a control unit associated with said set of sensors, characterized in that it comprises an engine according to any one of the preceding characteristics.
The invention further comprises the following characteristics:
- the engine is suspended on the ends of three elastomer mounts, cleverly arranged around the engine so that the center of rigidity is located close to the center of gravity of the suspended part of the engine;
- a tail boom comprising a proximal end mounted in fixed manner on the frame, and a distal end supporting a tail rotor via a gearbox, said gearbox being coupled with the transmission chain of the engine via a transmission shaft of the tail rotor;
- the tail boom includes a tailplane at its distal end;
- landing skids are attached in fixed manner to the frame.
Brief description of the figures
The invention will be understood more clearly upon reading the following description and reviewing the accompanying figures. The figures are provided purely for illustrative purposes and are not intended to be limiting of the invention in any way. The figures show:
- Figure 1 : a schematic representation of a stealth type helicopter drone according to an embodiment of the invention;
- Figure 2: a schematic representation of the diesel engine integration system according to an embodiment of the invention;
- Figure 3: a representation of the vibration absorption devices in the system of figure 2;
- Figure 4: a detailed schematic representation of the elements that make up the absorption device according to an embodiment of the invention.
Description of the invention
It should be noted from the outset that the figures are not drawn to scale.
The following embodiments are examples. Although the description refers to one or more embodiments, this does not necessarily mean that each reference relates to the same embodiment, or that the characteristics apply only to one embodiment. Single characteristics of different embodiments may also be combined to create other embodiments.
Figure 1 is a diagrammatic representation of a rotary wing drone 1 according to one embodiment of the invention. This drone 1 comprises, but is not limited to, a frame 2 that supports landing skids 3a, 3b in fixed manner. Frame 2 is designed such that it is able to support an engine 4, a set of sensors 13 (illustrated in figure 1) designed for carrying out surveillance, and/or intelligence collection and/or guiding the movement of drone 1 , and a control unit 14 (illustrated in figure 2) associated with this set of sensors.
A control unit 14 of such kind is known to one skilled in the art and does not constitute an object of our invention. It therefore serves no purpose to describe this control unit 14 in greater detail here. At all events, such a control unit 14 is capable of enabling the drone 1 to operate completely autonomously with regard to its movement and positioning relative to a target based on data that has been transmitted to it beforehand.
In the rest of this description, the term target is used to mean a person, a group of individuals, or also an object or group of objects that is moving or located within a field of vision of sensors 13 of the drone 1.
In a variant of the invention, an operator is authorised to guide the drone 1 by radio control using a dedicated keyboard and/or joystick (not shown). To this end, drone 1 is equipped with a communications unit (not shown) that is connected to control unit 14 so that it is able to relay the guidance instructions transmitted by the operator to the control unit via a supervision interface (not shown).
A tail boom 5 comprises a proximal end 5a that is mounted in fixed manner on frame 2, and a distal end 5b that supports a tail rotor 6 via a gearbox (not shown). This gearbox is coupled to the transmission chain of engine 4 via a transmission shaft 7 of the tail rotor. In a variant of the invention, distal end 5b of the boom is equipped with a tailplane (not shown).
Engine 4 is a diesel engine instead of the petrol engine that is used in the prior art. The sole purpose of using such a diesel engine is to increase the flying autonomy of drone 1 , raising it from 5 hours to more than 8 hours. Engine 4 is a classic diesel engine, generally used for motor vehicles, in order to reduce manufacturing costs. Thus, engine 4 converts the energy generated by combustion of the fuel into mechanical energy. To do this, engine 4 includes a number of generic elements that are known to one skilled in the art and therefore do not appear in the figures. For this purpose, engine 4 is equipped with one or more cylinders designed to contain combustion cycles. Inside each cylinder, a piston slides in a reciprocating linear movement. This linear movement is converted into rotary movement by means of a connecting rod that connects the piston to a crankshaft. The term crankshaft is used to describe a series of cranks on a shaft. At one end of this crankshaft there is a flywheel (not shown), which in motor vehicles is normally linked to a clutch and/or a starter motor ring gear. At the other end of the crankshaft there is a pulley wheel 8, which pulley wheel 8 is coupled with pulley wheel 10 by means of a belt 9 to transmit the rotary movement of the crankshaft to a transmission system 11. This transmission system 11 comprises a journal 12, on which rotor vanes 13a, 13b are mounted in fixed manner. Pulley wheel 8 is also coupled with tail rotor transmission shaft 7 via a further belt (not shown).
Since engine 4 generates an enormous quantity of heat, engine 4 is equipped with a cooling circuit that is routed as closely as possible to the zones where the heat is generated in order to maintain an optimum temperature in engine 4 and the interior of drone 1. A heat transfer fluid is forced through the cooling circuit by means of a pump 15 until it reaches a radiator 16 mounted in fixed manner on the frame, one of the surfaces of which radiator 16 gives onto the exterior of drone 1. Thus when flying, the air outside the drone 1 passes through radiator 16, and undesirable energy from engine 4 is transferred to the ambient air.
In order to reduce the visibility and thus also the vulnerability of drone 1 in a military or civilian theatre of operations, drone 1 comprises a fuselage 17 designed using stealth principles, as shown in figure 1. For the rest of this description, the term stealth will be understood to mean that the characteristics of drone 1 are designed to create a reduced signature, one that is undetectable or unidentifiable by a radar system or an individual. Fuselage 17 is also furnished with vents 18 designed to improve the ventilation of engine 4. Radiator 16 is located at the front of the fuselage to maximise its air intake. For this purpose, an orifice 19 is provided in the fuselage so that radiator 16 is able to have a surface 16a that is in contact with the exterior of drone 1.
However, when engine 4 is operating, it generates vibrations. In fact, these vibrations are essentially caused by the fact that the crankshaft is driven in rotary manner by a series of thrusts emanating from the successive movements of the pistons in the cylinders.
To solve this problem of vibration, the invention is configured firstly such that engine 4 is suspended at the ends of three elastomer mounts (not shown), cleverly arranged around engine 4 so that the centre of rigidity is located close to the centre of gravity of the suspended part of engine 4.
Secondly, the invention is configured such that the flywheel of engine 4 is coupled to a vibration absorbing device 20. This device 20 comprises an adapter 22 for the engine shaft, on which is mounted an antivibration shaft coupling system. This antivibration shaft coupling system comprises a first cylindrical element 23 with an orifice passing completely through it so that it is able to be fitted on adapter 22 in the manner of a pivot. This cylindrical element 23 is furnished with claws and teeth which are chamfered to allow a set of three elastomer sprockets 24, 25, 26 to be assembled. A ring 27 is then placed over sprocket 26 before it is covered by a further cylindrical element 28. This cylindrical element 28 comprises a ring having an external diameter that is larger than that of cylindrical element 27 but an internal diameter exactly the same as that of element 27, so that it is able to fit into adapter 22. Cylindrical element 28 comprises claws and teeth that are designed to engage with elastomer sprockets 24, 25, 26 and with element 27. A ring 29 is interposed in fixed manner between a plate 30 and cylindrical element 28. The plate is furnished with an internal orifice to allow element 27 to pass through together with sprockets 24, 25, 26. A support shaft 31 is equipped at one end thereof with an assembly of spacer rings 32, 33, 34, ball bearings 35, 36 and a locking ring 37 so that it is able to fit in fixed manner inside engine shaft adapter 22. The support shaft is mounted in fixed manner inside an elastomer flywheel 21 such that plate 30 is pressed against flywheel 21. Adapter 22 is mounted in fixed manner on the end of the crankshaft so as to absorber the vibrations caused by the torque of the engine, and thus attenuate these vibrations.

Claims

1 - A diesel engine (4) intended for use in a drone (1 ), comprising at least:
- a cylinder, capable of confining combustion, inside which a piston performs a reciprocating linear motion, said reciprocating linear motion being converted into rotary movement by means of a crankshaft,
- a device (20) for absorbing vibrations caused by the engine torque,
- said diesel engine being suspended at the end of three elastomer mounts arranged around the engine in such manner that the centre of rigidity is located close to the centre of gravity of the suspended engine.
2 - The engine (4) according to claim 1 , characterized in that the device (20) is mounted in fixed manner on one end of the crankshaft in order to attenuate the vibrations.
3 - The engine (4) according to any one of the preceding claims, characterized in that the device (20) for absorbing vibrations comprises:
- a crankshaft adapter (22) on which a first cylindrical element (23) is mounted in the manner of a pivot, said element (23) being furnished with claws and teeth that are chamfered so as to enable three sprockets (24, 25, 26) to be assembled,
- a cylindrical element (27) mounted over the sprocket (26) before being covered in turn by another cylindrical element (28), said cylindrical element (28) being furnished with claws and teeth designed to enable them to engage with the sprockets (24, 25, 26) as well as with the cylindrical element (27),
- a ring (29) interposed in fixed manner between a plate (30) and the cylindrical element (28),
- a support shaft (31), one end of which is furnished with an assembly of spacer rings (32, 33, 34), ball bearings (35, 36) and a locking ring (37), said locking ring being configured so as to engage in fixed manner inside the adapter (22), said support shaft (31 ) being mounted in fixed manner inside a flywheel (21) such that the plate (30) is pressed against the flywheel (21).
4 - The engine (4) according to claim 3, characterized in that the three sprockets (24, 25, 26) are made from elastomer material. 5 - The engine (4) according to claim 3 or 4, characterized in that the cylindrical element (28) comprises a ring having an external diameter larger than that of the cylindrical element (27) and an internal diameter identical with that of the cylindrical element (27), the dimensions of the diameters of these rings being configured such that they fit in the crankshaft adapter (22).
6 - The engine (4) according to any of claims 3 to 5, characterized in that the plate (30) has an internal orifice through which the element (27) passes through as well as the sprockets (24, 25, 26).
7 - The engine (4) according to any of claims 3 to 6, characterized in that the flywheel (21) is made from an elastomer material.
8 - A rotary-wing drone (1) including a frame in which are located:
- a set of sensors (13) designed for performing surveillance and/or reconnaissance and/or guiding the movement of the drone (1), and
- a control unit (14) associated with said set of sensors (13), characterized in that it comprises a diesel engine (4) according to any one of the preceding claims.
9 - The drone (1) according to claim 8, characterized in that the engine (4) is suspended on the ends of three elastomer mounts arranged around the engine (4) so that the center of rigidity is located close to the center of gravity of the suspended engine (4).
10 - The drone (1) according to claim 8, characterized in that it comprises a tail boom (5) comprising a proximal end (5a) mounted in fixed manner on the frame (2), and a distal end (5b) supporting a tail rotor (6) via a gearbox, said gearbox being coupled with the transmission chain of the engine (4) via a transmission shaft (7) of the tail rotor (6).
11 - The drone (1) according to claim 12, characterized in that said tail boom (5) includes a tailplane at its distal end (5b).
12 - The drone (1) according to claim 8, characterized in that landing skids (3a, 3b) are attached to the frame (2) in fixed manner.
EP12731301.3A 2011-06-20 2012-06-18 System for integrating a diesel engine in a drone Withdrawn EP2720943A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1101898A FR2976553A1 (en) 2011-06-20 2011-06-20 SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE
FR1102501A FR2976554B1 (en) 2011-06-20 2011-08-10 SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE
PCT/EP2012/002562 WO2012175187A1 (en) 2011-06-20 2012-06-18 System for integrating a diesel engine in a drone

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EP2720943A1 true EP2720943A1 (en) 2014-04-23

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WO2012175187A1 (en) 2012-12-27
FR2976553A1 (en) 2012-12-21
FR2976554A1 (en) 2012-12-21
FR2976554B1 (en) 2014-01-10

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