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1. 发明专利

JPH0710091A SIGHTING APPARATUS OF AIRCRAFT 失效
公开(公告)号：JPH0710091A
公开(公告)日：1995-01-13
申请号：JP12784194
申请日：1994-06-09
申请人： EUROCOPTER FRANCE
发明人： JIYATSUKU BURIYUNAN
IPC分类号： B64D45/08 , B64D47/00 , F41G3/22
摘要： PURPOSE: To simply fit a sighting system to a support by combining individual observing and individual axial directional fire devices integrated on the side parts and at the front of an aircraft, to connect both the devices to an on- aircraft computer. CONSTITUTION: A first observation device 9 has two photoelectronic sensors 12a and 12b directly and integrally fitted to the fuselage 2 of a helicopter 1 on both the sides of axis cores X-X in a longitudinal direction, and the respective sensors 12a and 12b are integrally fitted to side parts 2a and 2b corresponding to the helicopter 1, to cover the range of a relative azimuth of about 180 deg. and an elevation angle of 20 deg.-40 deg., so as to be indicated by observation quantity 13a and 13b respectively, thereby obtaining an observation shielding angle of over 360 deg.. A second axial directional fire device 10 is integrally fitted at a nose 8 or on a cockpit 3 of a helicopter, and these devices 9 and 10 are connected to an on-board computer 11.

2. 发明专利

JPH06156390A BODY STRUCTURE FOR HELICOPTER 失效
公开(公告)号：JPH06156390A
公开(公告)日：1994-06-03
申请号：JP18146593
申请日：1993-07-22
申请人： EUROCOPTER FRANCE
发明人： KUROODO BIETONADEE
IPC分类号： B64C1/12 , B64C1/00 , B64C1/06 , B64C27/00 , B64C27/04
摘要： PURPOSE: To improve rigidity by forming the central structure of a helicopter fuselage from mainly a skeleton to which covering elements defining the external shape of the fuselage are fixed, and forming it substantially into a hexahedron shape by a plurality of skeleton panels. CONSTITUTION: A helicopter fuselage includes a central structure 10 to which at least a front structure 12 and a rear structure 14 are jointed. The central structure 10 supports at least one engine 50 and is constituted of mainly a skeleton 16 to which covering elements defining the external shape of the fuselage are fixed. The skeleton 16 is formed substantially into a hexahedron shape by a plurality of skeleton panels 28 to 38 assembled together, or the skeleton 16 is, for example, formed substantially into a regular hexahedron shape by both fore and aft crossing panels 28, 30, both right and left side panels 32, 34, and both upper and lower horizontal panels 36, 38.

3. 发明专利

JPH0616190A AIRCRAFT ROTOR BLADE WITH APEX OF SWEEPBACK ANGLE 失效
公开(公告)号：JPH0616190A
公开(公告)日：1994-01-25
申请号：JP8343693
申请日：1993-04-09
申请人： EUROCOPTER FRANCE
发明人： FURANSOWA BUARENTAN TOURUMEI , DANIERU ANNU FUARUSHIERO
IPC分类号： B64C11/16 , B64C11/18 , B64C27/04 , B64C27/46 , B64C27/467
摘要： PURPOSE: To prevent a shock wave, a stall, a blade/vortex mutual action by incorporating first to fourth areas along a longitudinal direction in the blade, changing wing chordal lengths according to a specific function in the areas, setting a change of a deviation of an aerodynamic center so that front and rear edges of the blade do not display any damage. CONSTITUTION: The blade has a first area between 75% and 87% of the entire length measured from a rotating axial center of a boss from an inner edge of the blade in a longitudinal direction, a second area between 87% and 93%, a third area between 93% and 97%, and a fourth area extended to a free outer edge of the blade. A wing chordal length L is substantially linearly long in the first area, changed according to a cubic function in the second area, and changes constant in the third area and according to a parabolic function in the fourth area. As a result, the blade exhibits a swept-back angle due to a deviation of an aerodynamic center to an axial center, and the front edge 5 and the rear edge 6 of the blade may not display any damage. The edge 5 of the blade is a protrusion or linear and the edge 6 becomes a recess or linear.

4. 发明专利

JPH08285634A METHOD AND DEVICE FOR CORRECTING ERROR OF MEASURED VALUE OF MAGNETOMETER 失效
公开(公告)号：JPH08285634A
公开(公告)日：1996-11-01
申请号：JP32898695
申请日：1995-12-18
申请人： EUROCOPTER FRANCE
发明人： ERITSUKU SHIYARURU ASUU , JIYANNPOORU PETEIYON
IPC分类号： G01C25/00 , G01C17/38
摘要： PROBLEM TO BE SOLVED: To correct error in the measurement due to magnetic perturbation and positional mismatch of magnetometer easily, quickly and accurately by introducing a measurement of field, a time derivative thereof and a perturbation field into a logic model for error correction and determining coefficients. SOLUTION: When a transporting machine 3 is being steered, a value of field on the reference coordinates R1 measured through a magnetometer 2 and a field Hm' variable as a function of angular position dependent on the advancing direction and attitude are introduced into a theoretic model for correcting the error of magnetometer 2, Hc=[A].Hm+[T].Hm'+Hp, thus determining a corrected field Hc. In the formula, A represents a matrix due to soft iron perturbation and positional mismatch having no restriction on the angular value, T represents a matrix taking account of the delay between the attitude and advancing direction or the limit of passing band of magnetometer 2, and Hp represents a perturbation field. Since the field Hc can be regarded as a geomagnetic reference coordinates R2 projected onto coordinates R1 , error can be corrected by fixing coefficients for minimizing the error between the effective field value H and a field Hc on the coordinates R2 .

5. 发明专利

JPH07272800A ELECTRICAL CONNECTION ELEMENT AND CONNECTION 失效
公开(公告)号：JPH07272800A
公开(公告)日：1995-10-20
申请号：JP25679094
申请日：1994-10-21
申请人： EUROCOPTER FRANCE
发明人： JIYATSUKII RINIYURE
IPC分类号： H01R24/02 , H01R9/03 , H01R9/05 , H02G15/117 , H01R17/04
摘要： PURPOSE: To obtain an electrical connection element which has the electrical continuity of shields when a shield cable bundle is connected electrically. CONSTITUTION: An electrical connection element 13 is composed of a tube 17, and the nonshilding cable 2 and the shielded cable 3 of an electric cable bundle 1 pass through a hollow inside space 18 of the tube 17. And the tongue part 21 of the metal shield 6 of the electric cable bundle 1 contacts to the outer surface of the tube by surrounding the tube 17.

6. 发明专利

JPH0620033A READOUT DEVICE OF DISCRIMINATION MARK OF CONDUCTOR 失效
公开(公告)号：JPH0620033A
公开(公告)日：1994-01-28
申请号：JP1332893
申请日：1993-01-29
申请人： EUROCOPTER FRANCE
发明人： REON JIERUMAN SERUDA
IPC分类号： G06K7/10 , G06K9/20 , G06T1/00 , G06F15/64
摘要： PURPOSE: To provide a device for reading the identification mark of a conductor formed of at least one group of indicators written one by one on the outside surface of the vertical part of the insulating coating of the conductor. CONSTITUTION: This device is provided with an illuminating assembly 30 and a camera 25 which are arranged so as to be rotable around a vertical part 4A of an insulating coating 4 in order to form the pictures of the vertical line on the outside surface of the vertical part 4A of the insulating coating 4. Then, the complete peripheral pictures on the outside surface of the vertical part 4A of the insulating coating 4 can be formed for each vertical line. Thus, it is possible to easily recognize indicators by a known computerized character identifying device, and decide the identification of a conductor. Also, even when the rows of the indicators are not positioned at a center against an initial reading line, or not alternatively positioned exactly in parallel to the bus of the insulating coating, the pictures obtained by the camera can include all the indicators, the problem of the twist of the vertical part of the insulating coating with possibility can be solved, and the reading of the indication can be facilitated.

7. 发明专利

JPH0616192A METHOD FOR COUNTERACTING TORQUE PRODUCED BY HELICOPTER AND SINGLE MAIN ROTOR 失效
公开(公告)号：JPH0616192A
公开(公告)日：1994-01-25
申请号：JP8630093
申请日：1993-04-13
申请人： EUROCOPTER FRANCE
发明人： ROLLET PHILIPPE ALAIN , EGLIN PAUL GERHARD
IPC分类号： B64C27/04 , B64C13/16 , B64C27/82 , G05D1/08
摘要： PURPOSE: To effectively balance in an irregular fluctuation by providing an automatic rotation controller for automatically controlling a rotary angle of a steering wing as a function of a simultaneous pitch angle of a single rotor and a forward speed of a helicopter. CONSTITUTION: A simultaneous pitch angle DTORP given by a position sensor 15 corresponding to a control lever 16 and a forward speed V given by a sensor 17 are given to a computer 18, and a rotary value δ to be operated at a rudder 14 is given. The value δ is operated at an actuator 19 for controlling rotation of the rubber 14 around an axial center X-X to regulate a pitch of blade 12 of an anti-torque rotary blade 10 and to set a thrust YRA to zero. The computer 18 has a table for bringing measured set of the angle DTORPi and the speed Vi corresponding to a suitable value δi, and the value δi corresponding in the table is checked and operated at the actuator 19.

8. 发明专利

JPH08133191A COUNTER TORQUE DEVICE FOR HELICOPTER HAVING DUCT TYPE ROTOR AND PHASE MODULATION OF RECTIFICATION STATOR AND ROTOR BLADE 失效
公开(公告)号：JPH08133191A
公开(公告)日：1996-05-28
申请号：JP10430295
申请日：1995-04-27
申请人： EUROCOPTER FRANCE
发明人： MARUZE ANRIIJIEEMUSU RISHIYAAR , RUTEIO BUANSAN JIYAN RIYUTSUKU , ARUNOO JIRU RUI , ARUNOO REMI ERIYAN
IPC分类号： B64C27/82
摘要： PURPOSE: To reduce acoustic nuisance to a minimum while improving the aerodynamic performance of a ducted counter-torque device. CONSTITUTION: This flow-straightening stator 8 with aerodynamically profiled stationary vanes 9 is mounted downstream of a rotor 7 with blades 10 in a transverse duct 6 passing through the fairing at the tail of a helicopter. The blades 10 of the rotor 7 are distributed angularly about the axis of the rotor with uneven azimuth modulation such that any angle between two arbitrary blades 10 of the rotor 7 is different from any angle between two arbitrary vanes 9 of the flow-straightening stator.

9. 发明专利

JPH08198191A VARIABLE PITCH TYPE MULTIPLE BLADE ROTOR IN DUCT TYPE NEGATIVE TORQUE DEVICE OF HELICOPTER 失效
公开(公告)号：JPH08198191A
公开(公告)日：1996-08-06
申请号：JP10980095
申请日：1995-05-08
申请人： EUROCOPTER FRANCE
发明人： MONVAILLIER JEROME MICHEL , POLVEDA JACQUES JEAN
IPC分类号： B64C27/45 , B64C27/82
摘要： PURPOSE: To reduce the load required for control for varying or maintaining the pitch of a blade. CONSTITUTION: In this rotor 1, the pitch lever 23 of each blade 2 is connected to the tub 25 of a pitch control spider 26 via a ball joint of a wrist pin 24 and received with clearance in an oblong opening in a ring. The axially offset bearing surfaces 6, 7 of the cuff 5 of the blade 2 are provided at a radial clearance from the bearings 8, 9 of a hub 12 and can swivel about the pitch axis of the blade 12. These radial clearances enable the ball joint to make contact with the edge of the opening on the side of the ends of its minor axis, but prevent their contact on the side of the ends of the major axis of the opening.

10. 发明专利

JPH08133193A COUNTER TORQUE DEVICE HAVING TAIL ROTOR WITH DUCT AND RECTIFIER WITH DUCT IN ROTARY-WING AIRCRAFT SUCH AS HELICOPTER 失效
公开(公告)号：JPH08133193A
公开(公告)日：1996-05-28
申请号：JP10979995
申请日：1995-05-08
申请人： EUROCOPTER FRANCE
发明人： DEKIN ANDOREEMITSUSHIERU RUI , DARUDOTSUSO RUI JIYOZEFU , BARUKE ANRI FUERUNAN
IPC分类号： B64C27/82
摘要： PURPOSE: To facilitate installation and removal of a flow-straightening device by providing a casing of a rotary drive mechanism having a plurality of arms, support means provided at the radial outer ends of the arms, fastening means for centering and securing the annular hollow body of the flow-straightening device, and the like. CONSTITUTION: In an aircraft such as a helicopter, a flow-straightening device 8 for straightening flow is provided downstream of airflow produced by a rotor 7 in a duct 6 provided through fairing 5 at the rear of the helicopter. The flow-straightening device 8 has an annular body 14 having a built-in rotary drive mechanism and provided with fixed vanes 9 on its outer periphery. The rotary drive mechanism 18 is housed in a casing 17 having reinforcing arms 19 interconnected by circumferentially extending rims 25, and the rims 25 are provided in at least a portion of the casing 17 along its circumferential direction. The reinforcing arms 19 reinforced by triangular ribs 20 are supported at their outer ends by fastening means 26 such as bolts 31 and nuts 34.

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