GB2461133A - Erosion-protecting devices for aircraft - Google Patents

Erosion-protecting devices for aircraft Download PDF

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Publication number
GB2461133A
GB2461133A GB0811838A GB0811838A GB2461133A GB 2461133 A GB2461133 A GB 2461133A GB 0811838 A GB0811838 A GB 0811838A GB 0811838 A GB0811838 A GB 0811838A GB 2461133 A GB2461133 A GB 2461133A
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United Kingdom
Prior art keywords
devices
aircraft
erosion
pair
shape
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Granted
Application number
GB0811838A
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GB2461133B (en
GB0811838D0 (en
GB2461133A8 (en
Inventor
George Valentino Constantinou
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Individual
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Individual
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Priority to GB0811838A priority Critical patent/GB2461133B/en
Publication of GB0811838D0 publication Critical patent/GB0811838D0/en
Publication of GB2461133A publication Critical patent/GB2461133A/en
Publication of GB2461133A8 publication Critical patent/GB2461133A8/en
Application granted granted Critical
Publication of GB2461133B publication Critical patent/GB2461133B/en
Expired - Fee Related legal-status Critical Current
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C5/00—Stabilising surfaces
    • 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
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • 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
    • 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
    • B64D2045/009—Fire detection or protection; Erosion protection, e.g. from airborne particles

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Laminated Bodies (AREA)

Abstract

Erosion-protecting devices 4 for aircraft 2 that are used in preventing parts of the outside of the aircraft 2 suffering from erosion during flights of the aircraft 2, the erosion-protecting devices 4 are made of adhesive polyurethane tape of a type approved for high altitude use on the outside of aircraft. The erosion-protecting devices are produced by cutting the adhesive polyurethane tape to pre-determined shapes 6, 8, 10, 12, 14, 16, 18, 20, 22, 24 that have a line of symmetry using a plotter programmed with a computer aided design program. The erosion-protecting devices also form pairs with one erosion-protecting device 4 of a pair being a mirror image of the other erosion-protecting device 4 of a pair; and each one of the devices has its predetermined shape defined by edges which meet with no sharp points and which meet only with parts of perfect circles. Thus when the erosion-protecting devices are stuck onto the outer surface of the aircraft they are less likely to become unstuck whilst in use.

Description

EROSION-PROTECTING DEVICES FOR AIRCRAFT
This invention relates to erosion-protecting devices for aircraft. More especially, this invention relates to erosion-protecting devices for aircraft for use in preventing parts of the outside of the aircraft suffering from erosion during flights of the aircraft.
During flights, parts of the outside of the aircraft suffer from erosion.
The erosion is caused by wind turbulence on the parts of the outside of the aircraft. In order to prevent this erosion, it is known to employ erosion-protecting devices which are made of adhesive polyurethane tape of a type approved for high altitude use on the outside of aircraft. The known erosion-protecting devices are cut by hand, for example using scissors, to the required predetermined shapes. The manual cutting causes the predetermined shapes to be defined by edges which meet with sharp points.
The known erosion-protecting devices cause two problems. The first problem is that they tend to become unstuck during aircraft flights, especially whilst the aircraft is flying at peak altitude. After each flight, the aircraft has to undergo by law a maintenance check which is performed upon arrival of the aircraft. The object of the maintenance check is to see if the aircraft has sustained any internal or external problems during its last flight. All maintenance and re-fueling reports have to be signed by the aircraft captain, at least one hour before the flight. The captain will always give the aircraft a check before he signs the report to safeguard himself or herself. Should the captain see one of the erosion protecting devices looking loose, then maintenance personnel have to change that particular erosion-protecting device before the aircraft can take off again. This can cause unwanted aircraft departure delays. When the aircraft arrives at its next destination, all of the erosion-protecting devices may then be changed. This can be expensive in times of maintenance time personnel, for example taking up to six hours.
The second problem caused by the known erosion-protecting devices is that if they become unstuck during an aircraft flight, then they fly backwards and may hit an aircraft engine. Whilst there is a low possibility that the erosion-protecting device in the form of the polyurethane tape will cause the engine to blow up, there is a high possibility that the erosion-protecting device will cause propeller shaft damage due to the erosion-protection device melting in the heat of the engine. Propeller shaft damage will hinder aircraft performance and it will cause grounding of the aircraft for repair purposes, costing many thousands of pounds in replacement parts.
It is an aim of the present invention to reduce the above mentioned problems.
Accordingly, in one non-limiting embodiment of the present invention there is provided erosion-protecting devices for aircraft for use in preventing parts of the outside of the aircraft suffering from erosion during flights of the aircraft, the erosion-protecting devices being such that: (i) they are made of adhesive polyurethane tape of a type approved for high altitude use on the outside of aircrafts; (ii) they are produced by cutting the adhesive polyurethane tape to pre-detemiined shapes using a plotter programmed with a computer aided design program; (iii) they have a line of symmetry; (iv) they form pairs with one erosion-protecting device of a pair being a mirror image of the other erosion-protecting device of a pair; and (v) each one of the devices has its predetermined shape defined by edges which meet with no sharp points and which meet only with parts of perfect circles.
The erosion-protecting devices of the present invention do not tend to become unstuck during aircraft flights, and especially at peak altitude of the aircraft flights. This is due to the fact that each one of the erosion-protecting devices has its predetermined shape defined by edges which meet with no sharp points, and which meet only with parts of perfect circles. It is believed that the sharp points on the known erosion-protecting devices cause them to come unstuck. The formation of the erosion-protecting devices of the present invention with their edges which meet only with parts of perfect circles is achieved by producing the erosion-protecting devices by cutting the adhesive polyurethane using the plotter programmed with the computer aided design program.
The erosion-protecting devices of the present invention also are such that if they do become unstuck during an aircraft flight, they tend to fly upwardly and then backwardly, rather than directly backwardly. This helps considerably to avoid the erosion-protecting devices flying into one of the engines of the aircraft and damaging the engine.
The erosion-protecting devices of the present invention fly upwards and then backwards if they become unstuck due to the fact that their shapes are defined by edges which meet with no sharp points and which meet only with parts of perfect circles.
The erosion-protecting devices of the present invention are made from the adhesive polyurethane tape that is currently used to make the known erosion-protecting devices. The erosion-protecting devices of the present invention may be made in various desired predetermined shapes.
Preferably, the erosion-protecting devices of the present invention comprise at least one of: (i) one pair of the devices of a shape for use at a pair of upper wing to fuse failing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (ii) one pair of the devices of a shape for use at a pair of wing tip fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (iii) one pair of the devices of a shape for use at a pair of outer pylon leading edge fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (iv) one pair of the devices of a shape for use at a pair of leading edge horizontal/vertical stabiliser positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (v) one pair of the devices of a shape for use at a pair of horizontal stabiliser positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; and (vi) one pair of the devices of a shape for use at a pair of inner pylon leading edge fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft.
The erosion-protecting devices of the present invention may be sold in sets, with each set including one or more of the above mentioned pairs of the devices.
Preferably, each one of the pair of devices of the shape for use at the pair of upper wing to fuse fairing positions has an arcuate shape with a circular hole near each end of the arcuate shape.
Preferably, each one of the pair of devices of the shape for use at the pair of wing tip fairing positions has an arcuate shape.
Preferably, each one of the pair of the devices of the shape for use at the pair of outer pylon leading edge fairing positions has a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending at an angle between the two longer sides.
Preferably, each one of the pair of the devices of the shape for use at the leading edge horizontal/vertical stabiliser positions has a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
Preferably, each one of the pair of the devices of the shape for use at the pair of horizontal stabiliser positions has a head and shoulder shape with the head part having a curved upper edge and parallel side edges, and the shoulder part having an arcuate shape.
Preferably, each one of the pair of the devices of the shape for use at the pair of inner pylon leading edge fairing positions has a generally rectangular shape with the two longer sides paratlel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
Preferably, the erosion-protecting devices of the present invention include a single erosion protecting device of a shape for use at a vertical stabiliser upper fairing position.
The single device of the shape for use at the vertical stabiliser upper fairing position preferably has a rectangular shape.
The present invention also extends to an aircraft when provided with the erosion-protecting devices of the invention.
Embodiments of the invention will now be described solely by way of example and with reference to the accompanying drawings in which: Figure 1 shows an aircraft with positions marked for receiving erosion-protecting devices; and Figure 2 shows a set of erosion-protecting devices for the aircraft shown in Figure 1.
Referring to Figure 1, there is shown an aircraft 2 having positions marked as shown where erosion-protecting devices are required to be placed in order to prevent these parts of the aircraft suffering from erosion during flights of the aircraft. The erosion is of a cosmetic nature which is clearly undesirable, especially from the point of view of passengers seeing the erosion.
If known adhesive polyurethane tape of a type approved from high altitude use on the outside of the aircraft 2 is employed at the positions shown in Figure 1, then the erosion is reduced. However the known adhesive polyurethane tape has a shape which is defined by edges which meet with sharp points, due to the shape of the erosion-protecting devices being cut by hand. The shapes are generally non-symmetric and they have microscopic jagged edges. The known erosion-protecting devices thus tend to lift, especially when the aircraft 2 is at high altitude. Partially unstuck erosion-protecting devices require replacement at the next stop of the aircraft. This can cause maintenance delays. If an erosion-protecting device becomes unstuck during a flight, it may fly directly backwards and into an engine of the aircraft 2. This is likely to cause damage to the aircraft, for example by the polyurethane tape melting on a propeller shaft. The cost of replacement parts may be considerable.
Figure 2 shows erosion-protecting devices 4 of the present invention.
All of the erosion-protection devices 4 are made of the same type of adhesive polyurethane tape currently used, that is adhesive polyurethane tape of a type approved for high altitude use on the outside of aircraft. The tape is self-adhesive tape. The erosion-resisting devices 4 are stuck on the metal-painted surface of the aircraft 2.
The erosion-protecting devices 4 are produced by cutting the adhesive polyurethane tape to the illustrated pre-determined shapes using a plotter programmed with a computer aided design program. The shapes are inputted using circle registration points, and they are cut on the plotter, thereby creating a perfect millimetre symmetrical shape with perfect round edges. This avoids lifting of the erosion-resisting devices 4 during flights of the aircraft 2.
As can be seen from Figure 2, the erosion-protecting devices 4 all have a line of symmetry. Also, they form pairs with one erosion-protecting device 4 of a pair being a mirror image of the other erosion-protecting device 4 of a pair. Thus one erosion-protecting device of a pair is able to be used on the left hand side of the aircraft 2, and the other erosion-protecting device 4 of the pair is able to be used on the right hand side of the aircraft 2.
Each one of the erosion-protecting devices 4 has its predetermined shape defined by edges which meet with no sharp points, and which meet only with parts of perfect circles, as mentioned above.
As can be seen from Figure 2, there is one pair of erosion-protecting devices 6 of a shape for use at a pair of upper wing to fuse fairing positions on the aircraft 2. One of the devices 6 is for use on one side of the aircraft 2, and the other one of the devices 6 is for use on the other side of the aircraft 2.
The devices 6 have an arcuate shape with a circular hole 8 near each end of the arcuate shape.
Another pair of the devices 10 is of a shape for use at a pair of wing-tip fairing positions on the aircraft 2. One of the devices 10 is for use on one side of the aircraft 4, and the other one of the devices 10 is for use on the other side of the aircraft 4. The devices 10 has an arcuate shape as shown.
One pair of the devices 12 is of a shape for use at a pair of outer pylon leading edge fairing positions on the aircraft 4. One of the devices 12 is for use on one side of the aircraft 4, and the other one of the devices 12 is for use on the other side of the aircraft 4. The devices 12 have a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending at an angle between the two longer sides.
One pair of the devices 14 is of a shape for use at a pair of leading edge horizonta'/vertical stabiliser positions on the aircraft 4. One of the devices 14 is for use on one side of the aircraft 4 and the other one of the devices 14 is for use on the other side of the aircraft 4. The devices 14 have a generally rectangular shape with two longer parallel sides, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
One pair of the devices 16 is such that the devices 16 are of a shape for use at a pair of horizontal stabiliser positions on the aircraft 2. One of the devices 16 is for use on one side of the aircraft 2, and the other one of the devices 16 is for use on the other side of the aircraft 2. The devices 16 are such that they each have a head and shoulder shape with the head part 18 having a curved upper edge and parallel sides, and the shoulder part 20 having an arcuate shape.
One pair of the devices 22 is such that the devices 22 are of a shape for use at a pair of inner pylon leading edge fairing positions of the aircraft 2.
One of the devices 22 is for use on one side of the aircraft 2, and the other one of the devices 22 is for use on the other side of the aircraft 2. The devices 22 are such that they are of a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
The erosion-protecting devices 4 include a single erosion-protecting device 24 of a shape for use at a vertical stabitiser upper fairing position. The device 24 has a rectangular shape as shown.
It is to be appreciated that the embodiments of the invention described above with reference to the accompanying drawings have been given by way of example only and that modifications may be effected. Thus, for example, the illustrated shapes of the erosion-protecting devices 4 shown in Figure 2 may be varied.

Claims (12)

  1. CLAIMS1. Erosion-protecting devices for aircraft for use in preventing parts of the outside of the aircraft suffering from erosion during flights of the aircraft, the erosion-protecting devices being such that: (i) they are made of adhesive polyurethane tape of a type approved for high altitude use on the outside of aircrafts; (ii) they are produced by cutting the adhesive polyurethane tape to pre-determined shapes using a plotter programmed with a computer aided design program; (iii) they have a line of symmetry; (iv) they form pairs with one erosion-protecting device of a pair being a mirror image of the other erosion-protecting device of a pair; and (v) each one of the devices has its predetermined shape defined by edges which meet with no sharp points and which meet only with parts of perfect circles.
  2. 2. Erosion-protecting devices according to claim I and comprising at least one of: (i) one pair of the devices of a shape for use at a pair of upper wing to fuse fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (ii) one pair of the devices of a shape for use at a pair of wing tip fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (iii) one pair of the devices of a shape for use at a pair of outer pylon leading edge fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (iv) one pair of the devices of a shape for use at a pair of leading edge horizontallvertical stabiliser positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; (v) one pair of the devices of a shape for use at a pair of horizontal stabiliser positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft; and (vi) one pair of the devices of a shape for use at a pair of inner pylon leading edge fairing positions on the aircraft, one of the devices being for use on one side of the aircraft and the other one of the devices being for use on the other side of the aircraft
  3. 3. Erosion-protecting devices according to claim 2 in which each one of the pair of devices of the shape for use at the pair of upper wing to fuse fairing positions has an arcuate shape with a circular hole near each end of the arcuate shape.
  4. 4. Erosion-protecting devices according to claim 2 or claim 3 in which each one of the pair of devices of the shape for use at the pair of wing-tip fairing positions has an arcuate shape.
  5. 5. Erosion-protecting devices according to any one of claims 2 -4 in which each one of the pair of the devices of the shape for use at the pair of outer pylon leading edge fairing positions has a generally rectangular shape with the two longest sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending at an angle between the two longer sides.
  6. 6. Erosion-protecting devices according to any one of claims 2 -5 in which each one of the pair of the devices of the shape for use at the leading edge horizontal/vertical stabiliser positions has a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
  7. 7. Erosion-protecting devices according to any one of claims 2 -6 in which each one of the pair of the devices of the shape for use at the pair of horizontal stabiliser positions has a head and shoulder shape with the head part having a curved upper edge and parallel side edges, and the shoulder part having an arcuate shape.
  8. 8. Erosion-protecting devices according to any one of claims 2 -7 in which each one of the pair of the devices of the shape for use at the pair of inner pylon leading edge fairing positions has a generally rectangular shape with the two longer sides parallel, one shorter side extending at 900 to the two longer sides, and the other shorter side extending in a curve between the two longer sides.
  9. 9. Erosion-protecting devices according to any one of the preceding claims and including a single erosion-protecting device of a shape for use at a vertical stabiliser upper fairing position.
  10. 10. Erosion-protecting devices according to claim 9 in which the single device of the shape for use at the vertical stabiliser upper fairing position has a rectangular shape.
  11. 11. Erosion-protecting devices for aircraft for use in preventing parts of the outside of the aircraft suffering from erosion during flights of the aircraft, substantially as herein described with reference to Figure 2 of the accompanying drawings.
  12. 12. An aircraft when provided with the erosion-protecting devices according to any one of the preceding claims.
GB0811838A 2008-06-27 2008-06-27 Aircraft erosion-protection devices Expired - Fee Related GB2461133B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB0811838A GB2461133B (en) 2008-06-27 2008-06-27 Aircraft erosion-protection devices

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB0811838A GB2461133B (en) 2008-06-27 2008-06-27 Aircraft erosion-protection devices

Publications (4)

Publication Number Publication Date
GB0811838D0 GB0811838D0 (en) 2008-07-30
GB2461133A true GB2461133A (en) 2009-12-30
GB2461133A8 GB2461133A8 (en) 2010-03-24
GB2461133B GB2461133B (en) 2011-05-11

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104129496A (en) * 2013-05-03 2014-11-05 波音公司 Protective finish for wing tip devices
US10035578B2 (en) 2012-11-20 2018-07-31 Saab Ab Multifunctional erosion protection strip

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008157013A1 (en) * 2007-06-13 2008-12-24 Hontek Corporation Method and coating for protecting and repairing an airfoil surface using molded boots, sheet or tape
EP2047979A1 (en) * 2007-10-09 2009-04-15 United Technologies Corporation Article and method for erosion resistant composite
US20090104438A1 (en) * 2007-10-17 2009-04-23 Jennifer Hoyt Lalli Abrasion resistant coatings

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008157013A1 (en) * 2007-06-13 2008-12-24 Hontek Corporation Method and coating for protecting and repairing an airfoil surface using molded boots, sheet or tape
EP2047979A1 (en) * 2007-10-09 2009-04-15 United Technologies Corporation Article and method for erosion resistant composite
US20090104438A1 (en) * 2007-10-17 2009-04-23 Jennifer Hoyt Lalli Abrasion resistant coatings

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10035578B2 (en) 2012-11-20 2018-07-31 Saab Ab Multifunctional erosion protection strip
CN104129496A (en) * 2013-05-03 2014-11-05 波音公司 Protective finish for wing tip devices
EP2799330A3 (en) * 2013-05-03 2014-12-17 The Boeing Company Protective finish for wing tip devices
US9845162B2 (en) 2013-05-03 2017-12-19 The Boeing Company Protective finish for wing tip devices
EP3366572A1 (en) * 2013-05-03 2018-08-29 The Boeing Company Protective finish for wing tip devices
CN104129496B (en) * 2013-05-03 2021-08-10 波音公司 Protective overcoat for wingtip devices

Also Published As

Publication number Publication date
GB2461133B (en) 2011-05-11
GB0811838D0 (en) 2008-07-30
GB2461133A8 (en) 2010-03-24

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Effective date: 20170627