WO2012024838A1 - Transducer mounting structure for a vertical tail of an aircraft - Google Patents

Transducer mounting structure for a vertical tail of an aircraft Download PDF

Info

Publication number
WO2012024838A1
WO2012024838A1 PCT/CN2010/076384 CN2010076384W WO2012024838A1 WO 2012024838 A1 WO2012024838 A1 WO 2012024838A1 CN 2010076384 W CN2010076384 W CN 2010076384W WO 2012024838 A1 WO2012024838 A1 WO 2012024838A1
Authority
WO
WIPO (PCT)
Prior art keywords
mounting
transducer
stiffener
secured
mounting flange
Prior art date
Application number
PCT/CN2010/076384
Other languages
French (fr)
Inventor
Yuping Li
Original Assignee
Airbus Sas
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 Airbus Sas filed Critical Airbus Sas
Priority to PCT/CN2010/076384 priority Critical patent/WO2012024838A1/en
Publication of WO2012024838A1 publication Critical patent/WO2012024838A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • B64C5/06—Fins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/0005—Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear

Definitions

  • This invention relates to a mounting structure in an aircraft, especially to a transducer mounting structure used for mounting a transducer in a vertical tail of the aircraft.
  • a rudder for implementing the control of orientation of the aircraft in horizontal direction is disposed in a vertical tail of an aircraft.
  • a transducer is provided in the manner of being mounted on a fitting of the vertical tail so as to sense the horizontal angle of the rudder in real time and transmit it to a control system of the aircraft, thereby accurate control of rudder can be achieved.
  • a vertical tail is located in the rear portion of a conventional aircraft.
  • a rudder 2 shown in Fig.2 is mounted in the vertical tail 1.
  • Fig.3 shows a conventional mounting bracket for rudder transducer 3, which comprises a transducer rod mounting portion 31 and a mounting flange 32 formed horizontally.
  • the transducer rod mounting portion 31 is pivotally connected to a rod 41 of the transducer 4, and the mounting flange 32 is used to fix the mounting bracket 3 to an upper lug 51 of the fitting 5 in the vertical tail via screw fasteners, so that transducer 4 is capable of moving with respect to mounting bracket 3.
  • the object of this invention is to eliminate the above shortcomings of the conventional technique, and provide a novel transducer mounting structure which is convenient to mount without compromise in mounting strength.
  • a transducer mounting structure for a vertical tail of an aircraft which comprises a mounting bracket which includes a transducer rod mounting portion extending outwardly from a body of the mounting bracket, the transducer rod mounting portion being pivotally connected to a rod of a transducer, and a mounting flange extending outwardly from the body of the mounting bracket, the mounting flange being secured to a fitting of the vertical tail; wherein said mounting flange extends outwardly in an approximately vertical direction, and is secured to a side surface of a stiff ener of the fitting.
  • said mounting flange is formed in an substantially triangle shape by expanding laterally while extending in the vertical direction, and the portion of the stiffener which fits with the mounting flange is formed in the corresponding shape.
  • a plurality of mounting holes are formed in the mounting flange, and corresponding through holes are formed in the stiffener, the mounting flange being secured to the stiffener by a plurality of screw fasteners passing through said mounting holes and said through holes.
  • the central area of the mounting flange where the mounting holes are formed recesses by a certain distance with respect to the periphery thereof such that heads of the screw fasteners would not expose outside of the mounting flange when the screw fastener is mounted.
  • one end of the rod is pivotally connected to the transducer rod mounting portion via a first hinge, and the other end thereof is pivotally connected to said transducer via a second hinge.
  • the mounting flange is secured to the stiffener of the fitting by riveting.
  • the side surface of the stiffener where the mounting bracket is secured faces away an adjacent stiffener.
  • the side surface of the stiffener where the mounting bracket is secured faces an adjacent stiffener.
  • this invention has following advantageous effect: a spacious mounting space is achieved thanks to the vertically formed mounting flange of the mounting bracket which thus can be secured to the stiffener vertically, thereby no intervention between the tools and other components will occur during the operation of drilling hole and fastening screw fasteners, and productivity can be improved significantly.
  • Fig.l shows a rear portion of an aircraft with a vertical tail
  • Fig.2 show a rudder provided in the vertical tail
  • Fig.3 shows a conventional transducer mounting bracket
  • Fig.4 show transducer mounting configuration by use of the conventional transducer mounting bracket
  • Fig.5 a transducer mounting bracket according to an embodiment of the invention
  • Fig.6 show transducer mounting configuration by use of the transducer mounting bracket according to the embodiment of the invention.
  • Fig.7 is the transducer mounting configuration of Fig.6 viewed in another point of view.
  • Fig.5 shows a transducer mounting bracket 6 according to an embodiment of this invention.
  • Fig.6 shows transducer mounting configuration by use of the transducer mounting bracket 6 according to the embodiment of the invention.
  • the transducer mounting bracket 6 comprises a transducer rod mounting portion 61 extending outwardly from a body of the transducer mounting bracket 6 in approximately horizontal direction and used for pivotally connecting to a transducer rod 41, and a mounting flange 62 extending in approximately vertical direction from the body of the mounting bracket 6.
  • the mounting flange 62 is formed with a plurality of mounting holes 64 (three in this embodiment).
  • the mounting flange 6 is fixed on the fitting 5 of the vertical tails 1. More specifically, the fitting 5 is formed with an upper lug 51, a lower lug 52 and a stiffener 53 for enhancing the strength of the fitting 5, the stiffener 53 is approximately perpendicular to the upper lug 51 and lower lug 52 of the fitting 5.
  • the vertically formed mounting flange 62 of the mounting bracket 6 is fixed to a side surface of the stiffener 53, thus the unique vertical mounting configuration of this invention is achieved.
  • mounting bracket 63 may be mounted on the other side surface of the stiffener 53 which faces the other adjacent stiffener, since the distance between two adjacent stiffeners 53 is far greater than the gap between the upper and lower fitting lug 51 and 52.
  • the stiffener 53 is provided with a plurality of through holes (not shown) corresponding to the mounting holes of the mounting flange.
  • the mounting bracket 6 is secured to one side of the stiffener 53 by a plurality of screw fastener 63 passing through the mounting holes 64 and the through holes.
  • a transducer 4 and a transducer rod 41 are components to be mounted.
  • the transducer rod 41 is pivotally connected at one end thereof to the transducer rod mounting portion 61 via a first hinge 42 and is pivotally connected at the other end thereof to the transducer 4 via a second hinge 44.
  • the mounting flange 62 is formed in approximate triangle shape by expanding itself laterally while extending vertically.
  • the portion of the stiffener 53 which fits with the mounting flange 62 has corresponding shape, facilitating the attachments of the mounting bracket while ensuring high structure strength.
  • the central area of the mounting flange 62 where the mounting holes 64 are formed recesses by a certain distance with respect to the periphery of thereof, so that heads of the screw fastener 63 would not expose outside of the mounting bracket 6 when being mounted into the mounting holes 64.
  • the mounting bracket 6 can be secured to the fitting 5 by screw fastener, persons skilled in this art may use other conventional fixing means, such as riveting.
  • the number of the fastener is not limited to three, but can be any number capable of ensuring connecting strength.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Plates (AREA)

Abstract

A transducer mounting structure for a vertical tail of an aircraft comprises a mounting bracket (6) which comprises a transducer rod mounting bracket (6) which comprises a transducer rod mounting portion (61) extending outwardly from a body of the mounting bracket, the transducer rod mounting portion being pivotally connected to a rod (41) of a transducer (4); and a mounting flange (62) extending outwardly form the body of the mounting bracket (6), the mounting flange (620 being secured to a fitting (5) of the vertical tail; wherein said mounting flange (62) extends outwardly in an approximately vertical direction, and is secured to a side surface of a stiffener (53) of the fitting (5). With the vertical mounting configuration, no intervention will occur during the process of drilling holes and mounting the transducer, thus the productivity is improved greatly.

Description

Transducer Mounting Structure For a Vertical Tail of
Aircraft
FIELD OF INVENTION
This invention relates to a mounting structure in an aircraft, especially to a transducer mounting structure used for mounting a transducer in a vertical tail of the aircraft.
BACKGROUND OF THE INVENTION
It has been well known that a rudder for implementing the control of orientation of the aircraft in horizontal direction is disposed in a vertical tail of an aircraft. For accurately sensing and controlling a horizontal angle of the rudder, a transducer is provided in the manner of being mounted on a fitting of the vertical tail so as to sense the horizontal angle of the rudder in real time and transmit it to a control system of the aircraft, thereby accurate control of rudder can be achieved.
As shown in Fig.l, a vertical tail is located in the rear portion of a conventional aircraft. A rudder 2 shown in Fig.2 is mounted in the vertical tail 1. Fig.3 shows a conventional mounting bracket for rudder transducer 3, which comprises a transducer rod mounting portion 31 and a mounting flange 32 formed horizontally. As shown in Fig.4, the transducer rod mounting portion 31 is pivotally connected to a rod 41 of the transducer 4, and the mounting flange 32 is used to fix the mounting bracket 3 to an upper lug 51 of the fitting 5 in the vertical tail via screw fasteners, so that transducer 4 is capable of moving with respect to mounting bracket 3. In this conventional mounting configuration, since the gap LI between the upper lug 51 and lower lug 52 of the vertical tail is only about 29mm, besides the vertical distance L2 between the transducer rod mounting portion 31 and the horizontally configured mounting flange 32 is only about 48mm, there is insufficient space for drilling tools and mounting tools to perform drilling and mounting operation when fixing the mounting bracket, thus the conventional mounting structure is not convenient and causes a low efficiency/productivity.
SUMMARY OF THE INVENTION
The object of this invention is to eliminate the above shortcomings of the conventional technique, and provide a novel transducer mounting structure which is convenient to mount without compromise in mounting strength.
To accomplish the above object, a transducer mounting structure for a vertical tail of an aircraft is provided in an embodiment of this invention, which comprises a mounting bracket which includes a transducer rod mounting portion extending outwardly from a body of the mounting bracket, the transducer rod mounting portion being pivotally connected to a rod of a transducer, and a mounting flange extending outwardly from the body of the mounting bracket, the mounting flange being secured to a fitting of the vertical tail; wherein said mounting flange extends outwardly in an approximately vertical direction, and is secured to a side surface of a stiff ener of the fitting.
Preferably, said mounting flange is formed in an substantially triangle shape by expanding laterally while extending in the vertical direction, and the portion of the stiffener which fits with the mounting flange is formed in the corresponding shape.
Preferably, a plurality of mounting holes are formed in the mounting flange, and corresponding through holes are formed in the stiffener, the mounting flange being secured to the stiffener by a plurality of screw fasteners passing through said mounting holes and said through holes. Preferably, the central area of the mounting flange where the mounting holes are formed recesses by a certain distance with respect to the periphery thereof such that heads of the screw fasteners would not expose outside of the mounting flange when the screw fastener is mounted.
Preferably, one end of the rod is pivotally connected to the transducer rod mounting portion via a first hinge, and the other end thereof is pivotally connected to said transducer via a second hinge.
Preferably, the mounting flange is secured to the stiffener of the fitting by riveting.
Preferably, the side surface of the stiffener where the mounting bracket is secured faces away an adjacent stiffener.
Preferably, the side surface of the stiffener where the mounting bracket is secured faces an adjacent stiffener.
In comparison with the conventional technique, this invention has following advantageous effect: a spacious mounting space is achieved thanks to the vertically formed mounting flange of the mounting bracket which thus can be secured to the stiffener vertically, thereby no intervention between the tools and other components will occur during the operation of drilling hole and fastening screw fasteners, and productivity can be improved significantly.
BRIEF DESCRIPTION OF THE DRAWINGS
Fig.l shows a rear portion of an aircraft with a vertical tail;
Fig.2 show a rudder provided in the vertical tail;
Fig.3 shows a conventional transducer mounting bracket; Fig.4 show transducer mounting configuration by use of the conventional transducer mounting bracket;
Fig.5 a transducer mounting bracket according to an embodiment of the invention;
Fig.6 show transducer mounting configuration by use of the transducer mounting bracket according to the embodiment of the invention; and
Fig.7 is the transducer mounting configuration of Fig.6 viewed in another point of view.
Numerals in figures:
Figure imgf000005_0001
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Below embodiments of this invention are described in detail with reference to the accompanying drawings. Fig.5 shows a transducer mounting bracket 6 according to an embodiment of this invention. Fig.6 shows transducer mounting configuration by use of the transducer mounting bracket 6 according to the embodiment of the invention. As shown in Fig.5, the transducer mounting bracket 6 comprises a transducer rod mounting portion 61 extending outwardly from a body of the transducer mounting bracket 6 in approximately horizontal direction and used for pivotally connecting to a transducer rod 41, and a mounting flange 62 extending in approximately vertical direction from the body of the mounting bracket 6. The mounting flange 62 is formed with a plurality of mounting holes 64 (three in this embodiment).
As shown in Fig.6, the mounting flange 6 is fixed on the fitting 5 of the vertical tails 1. More specifically, the fitting 5 is formed with an upper lug 51, a lower lug 52 and a stiffener 53 for enhancing the strength of the fitting 5, the stiffener 53 is approximately perpendicular to the upper lug 51 and lower lug 52 of the fitting 5. The vertically formed mounting flange 62 of the mounting bracket 6 is fixed to a side surface of the stiffener 53, thus the unique vertical mounting configuration of this invention is achieved. Generally, there are two stiff eners 53 in each fitting 5. To achieve maximum mounting space, the mounting bracket 6 is secured to such a side surface of the stiffener which is not facing the other adjacent stiffener.
With above configuration of the embodiment of this invention, since one side of the side surface of the stiffener 53 where the mounting bracket 6 is mounted is an open space, drilling tools and mounting tools would not intervene with other components during the process of drilling the through holes and mounting the bracket 6. Thus the configuration facilitates the operation of mounting the transducer significantly, and improves greatly the productivity in terms of drilling holes and mounting screw fasteners 63.
On the other hand, it can be readily envisaged that mounting bracket 63 may be mounted on the other side surface of the stiffener 53 which faces the other adjacent stiffener, since the distance between two adjacent stiffeners 53 is far greater than the gap between the upper and lower fitting lug 51 and 52.
The stiffener 53 is provided with a plurality of through holes (not shown) corresponding to the mounting holes of the mounting flange. The mounting bracket 6 is secured to one side of the stiffener 53 by a plurality of screw fastener 63 passing through the mounting holes 64 and the through holes.
As can be seen from Fig.6, a transducer 4 and a transducer rod 41 are components to be mounted. In the mounted configuration, the transducer rod 41 is pivotally connected at one end thereof to the transducer rod mounting portion 61 via a first hinge 42 and is pivotally connected at the other end thereof to the transducer 4 via a second hinge 44.
Preferably, the mounting flange 62 is formed in approximate triangle shape by expanding itself laterally while extending vertically. The portion of the stiffener 53 which fits with the mounting flange 62 has corresponding shape, facilitating the attachments of the mounting bracket while ensuring high structure strength.
Desirably, the central area of the mounting flange 62 where the mounting holes 64 are formed recesses by a certain distance with respect to the periphery of thereof, so that heads of the screw fastener 63 would not expose outside of the mounting bracket 6 when being mounted into the mounting holes 64. While the mounting bracket 6 can be secured to the fitting 5 by screw fastener, persons skilled in this art may use other conventional fixing means, such as riveting. In addition, the number of the fastener is not limited to three, but can be any number capable of ensuring connecting strength.
The detailed description of the embodiments as described above is illustrative, and is not intended to limit this invention. Any modification and improvement that can be made by persons skilled in the art without involving creative effort falls within the scope of this invention as defined by the claims appended.

Claims

1. A transducer mounting structure for a vertical tail of an aircraft, comprising a mounting bracket (6) which comprises:
A transducer rod mounting portion (61) extending outwardly from a body of the mounting bracket, the transducer rod mounting portion being pivotally connected to a rod (41) of a transducer (4); and
A mounting flange (62) extending outwardly from the body of the mounting bracket (6), the mounting flange (62) being secured to a fitting (5) of the vertical tail;
Characterized in that said mounting flange (62) extends outwardly in an approximately vertical direction, and is secured to a side surface of a stiffener (53) of the fitting (5).
2. The transducer mounting structure as claimed in claim 1, characterized in that said mounting flange (62) is formed in an approximate triangle shape by expanding laterally while extending in the vertical direction, and the portion of the stiffener which fits with the mounting flange is formed in the corresponding shape.
3. The transducer mounting structure as claimed in claim 1 or 2, characterized in that a plurality of mounting hole (64) are formed in the mounting flange (62), and corresponding through holes are formed in the stiffener, the mounting flange being secured to the stiffener by a plurality of screw fasteners passing through said mounting holes and said through holes.
4. The transducer mounting structure as claimed in claim 3, characterized in that a central area of the mounting flange where the mounting holes are formed recesses by a certain distance with respect to a periphery thereof such that heads of the screw fasteners would not expose outside of the mounting flange when the screw fastener is mounted.
5. The transducer mounting structure as claimed in claim 1, characterized in that one end of the rod (41) is pivotally connected to the transducer rod mounting portion via a first hinge (42), and the other end thereof is pivotally connected to said transducer (4) via a second hinge (44).
6. The transducer mounting structure as claimed in claim 1, characterized in that the mounting flange (62) is secured to the stiffener (53) of the fitting (5) by riveting.
7. The transducer mounting structure as claimed in claim 1, characterized in that the side surface of the stiffener where the mounting bracket is secured faces away an adjacent stiffener.
8. The transducer mounting structure as claimed in claim 1, characterized in that the side surface of the stiffener where the mounting bracket is secured faces an adjacent stiffener.
PCT/CN2010/076384 2010-08-26 2010-08-26 Transducer mounting structure for a vertical tail of an aircraft WO2012024838A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/CN2010/076384 WO2012024838A1 (en) 2010-08-26 2010-08-26 Transducer mounting structure for a vertical tail of an aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2010/076384 WO2012024838A1 (en) 2010-08-26 2010-08-26 Transducer mounting structure for a vertical tail of an aircraft

Publications (1)

Publication Number Publication Date
WO2012024838A1 true WO2012024838A1 (en) 2012-03-01

Family

ID=45722820

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2010/076384 WO2012024838A1 (en) 2010-08-26 2010-08-26 Transducer mounting structure for a vertical tail of an aircraft

Country Status (1)

Country Link
WO (1) WO2012024838A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150360768A1 (en) * 2014-06-12 2015-12-17 Troy A. Woodland Mounting assembly for fully automatic slat

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB722842A (en) * 1952-06-12 1955-02-02 Northrop Aircraft Inc Aileron, flap, and dive brake
US6299108B1 (en) * 1997-12-12 2001-10-09 Jeffrey V. Lindstrom Method and apparatus for detecting skew and asymmetry of an airplane flap
DE102008041259A1 (en) * 2008-08-14 2010-02-25 Airbus Deutschland Gmbh Adhesive holder for connecting lightweight component, particularly sensor or electrical component, to trunk cell structure of airplane, particularly to stringer or frame, has main body, which has three lugs

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB722842A (en) * 1952-06-12 1955-02-02 Northrop Aircraft Inc Aileron, flap, and dive brake
US6299108B1 (en) * 1997-12-12 2001-10-09 Jeffrey V. Lindstrom Method and apparatus for detecting skew and asymmetry of an airplane flap
DE102008041259A1 (en) * 2008-08-14 2010-02-25 Airbus Deutschland Gmbh Adhesive holder for connecting lightweight component, particularly sensor or electrical component, to trunk cell structure of airplane, particularly to stringer or frame, has main body, which has three lugs

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150360768A1 (en) * 2014-06-12 2015-12-17 Troy A. Woodland Mounting assembly for fully automatic slat

Similar Documents

Publication Publication Date Title
WO2012024838A1 (en) Transducer mounting structure for a vertical tail of an aircraft
EP2983057A2 (en) Vehicle pedal arm
CN108626230A (en) C-type steel connects locking device
CN204368408U (en) For being fixedly connected with the mounting structure of model plane fuselage and wing
CN106194844B (en) Combination type fan
CN203925190U (en) A kind of door/window corner portion connecting structure
CN206292028U (en) A kind of fusiformis model in wind tunnel radome fairing
WO2007130653A3 (en) Flying toy vehicle
CN102649453A (en) Mounting bracket of vehicle head hood
CN201380244Y (en) Bridge type booster riveting equipment
CN209274883U (en) A kind of baby plane active face adjustment chip architecture
CN109383757A (en) A kind of plane spoiler integral joint
CN104191837B (en) The interface guide body structure of bill printer
CN208541249U (en) A kind of multidirectional regulating system of handhold
CN207292384U (en) A kind of plane spoiler integral joint
CN205727094U (en) A kind of maize harvesting machine cutter assembly
CN210681135U (en) Control surface centralized counterweight structure of small aircraft
CN210416954U (en) Auxiliary installation device for aircraft component
CN211389860U (en) Unloading swash plate and injection molding machine of injection molding machine
CN205622854U (en) Balanced armature type receiver
CN211240636U (en) Cabinet air conditioner box
CN104097769A (en) Helicopter rotor head propeller clamping device
CN104260657B (en) Armrest frame of mini-tiller and multifunctional panel assembly
CN204297063U (en) A kind of actuator joint
CN210980307U (en) Air conditioner aluminium section bar panel lid

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10856291

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 10856291

Country of ref document: EP

Kind code of ref document: A1