CN109250070A - A kind of high wing airplane wing flap puts down angle mark method - Google Patents
A kind of high wing airplane wing flap puts down angle mark method Download PDFInfo
- Publication number
- CN109250070A CN109250070A CN201811119437.1A CN201811119437A CN109250070A CN 109250070 A CN109250070 A CN 109250070A CN 201811119437 A CN201811119437 A CN 201811119437A CN 109250070 A CN109250070 A CN 109250070A
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- CN
- China
- Prior art keywords
- wing flap
- mark
- wing
- angle
- flap
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000003086 colorant Substances 0.000 claims description 2
- 239000003550 marker Substances 0.000 description 2
- 230000004438 eyesight Effects 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Traffic Control Systems (AREA)
Abstract
The present invention relates to a kind of high wing airplane wing flaps to put down angle mark method, in the case where putting down angle instruction thrashing for the wing flap in cockpit, unit out of cabin point of observation along course wing flap rear can from wing flap put down angle.High mounted wing transporter, after wing flap puts down certain angle, wing flap cabin lower surface rear can be no longer be overlapped with wing flap leading edge, can not directly judge that wing flap puts down angle by the spacing of wing flap leading edge and wing flap cabin lower surface rear.The present invention is in left and right wing flap upper and lower surfaces and wing flap cabin lower surface setting flag, the different angle that wing flap is put down is represented by the relative positional relationship of these labels and the quantity of display observable, solves the problems, such as that the wing flap of high wing airplane puts down label and is not easy to arrange and observe identification.
Description
Technical field
The present invention relates to a kind of high wing airplane wing flaps to put down angle mark method, puts down angle for the wing flap in cockpit
In the case where degree instruction thrashing, unit out of cabin point of observation along course wing flap rear can from wing flap put down angle
Degree.
Background technique
There is upper and lower cover plates in wing flap cabin, and upper cover plate stretches out longer distance backward, puts down angular range in entire wing flap
Interior, upper cover plate and wing flap have an overlay region, and most of seating planes are all low wing aircrafts, and low wing aircraft is put wing flap is all
Within the scope of lower angle, wing flap cabin upper surface rear and flap upper surface still have overlay region, convenient for arranging wing flap in upper surface of the airfoil
Label, and unit be easy out of cabin downwards from, can directly indicate angular values, accurately instruction wing flap put down angle,
In the case that the wing flap of cockpit cockpit puts down angle instruction thrashing, unit out of cabin can from wing flap put down
Angle facilitates driver to control flying speed, so as to safe landing.
And high mounted wing transporter, after wing flap puts down certain angle, wing flap cabin lower surface rear can be with wing flap leading edge no longer
Overlapping, but be separated by a distance, it can not directly judge that wing flap is put by the spacing of wing flap leading edge and wing flap cabin lower surface rear
Lower angle, it is more complicated that the wing flap of high wing airplane puts down angle mark setting, and is limited by observation window position, need to pass through the flap
The location of the wing and the relative tertiary location in wing flap cabin and observer comprehensively consider.
Summary of the invention
Angle mark design arrangement is put down the present invention overcomes existing high wing airplane wing flap and is asked using observation is difficult
Topic provides a kind of method that high mounted wing wing flap puts down angle mark design arrangement and observation uses.
In order to solve the above-mentioned technical problem, the present invention is in left and right wing flap upper and lower surfaces and wing flap cabin lower surface setting mark
Note represents the different angle that wing flap is put down, observation by the relative positional relationship of these labels and the quantity of display observable
When, on 0 ° of flap configuration, the label in wing flap and wing flap cabin is overlapped, and upper marker is invisible；When wing flap is lowered into I angle,
Wing flap and the label of wing flap cabin lower surface separate, and upper marker is invisible；Wing flap is greater than the Ith angle when being lowered into II angle,
Wing flap and the marking path of wing flap cabin lower surface further increase, while the label of flap upper surface is rotated to observable position,
The label of upper and lower surfaces is visible；It is greater than the IIth angle, table on wing flap cabin lower surface and wing flap when under wing flap to III angle
Face label is as it can be seen that flap lower surface label is invisible；It is greater than the IIIth angle when under wing flap to IV angle, only table on wing flap cabin
As it can be seen that flap lower surface label is invisible, wing flap puts down angle and does not exceed 4 angle ladders face label.The size of label with
The characteristics of fuselage interior point of observation meets the requirement of 0.8 and the above eyesight to the distance of label, guarantees label [relative positional relationship
With the quantity of display observable] it is easy identification, label and the background color of surrounding are shown using strong comparison, and use unglazed fluorescence
Material has high-visible in cabin under conditions of illumination between guaranteeing round the clock.The present invention can be with: making for various remote-controlled operations
The monitoring of the working conditions such as the mechanical arm of industry indicates.
The utility model has the advantages that compared with prior art, the wing flap that the present invention solves high wing airplane puts down label and is not easy to arrange
The problem of with observation identification.
Detailed description of the invention
Fig. 1 is the wing flap label placement of the present invention shown from wing lower section and observation window position view；
Fig. 2 is the wing flap label situation of 0 ° of wing flap from observation window；
Fig. 3 is the wing flap label situation that wing flap puts down angle I from observation window；
Fig. 4 is the wing flap label situation that wing flap puts down angle II from observation window；
Fig. 5 is the wing flap label situation that wing flap puts down angle III from observation window；
Fig. 6 is the wing flap label situation that wing flap puts down angle IV from observation window.
Specific embodiment
Present invention is further described in detail with specific embodiment with reference to the accompanying drawing: according to the taboo of high wing airplane
The position of the wing specifies observation wing flap to put down the observation window of angle mark on user's manual, is mainly in the position close to fuselage
Distance controlling designs wing flap label, and arrangement mark position mainly utilizes the relative position of wing flap and wing flap cabin lower cover plate and wing flap to become
The variation relation of the spatial position of change relationship and wing flap upper and lower surface and observer, so that wing flap is when difference puts down angle,
The spatial position of label and quantity change, and the different display situations judgement wing flaps that observer is marked by wing flap put down angle
Degree, and by wing flap it is each put down angle when corresponding wing flap put down angle mark situation and enumerated out in subscriber data
Come.
Specifically, a kind of high wing airplane wing flap puts down angle mark method, this method is provided with observation in 1 side of fuselage
Window 4, the observation window 4 is in 2 rear side of wing；2 lower surface of wing is provided with the first mark 5,3 lower surface of wing flap is provided with second
Mark 6 is provided with third mark 7 in 3 upper surface of wing flap；From observation window 4, for the assembled state of each mark, respectively refer to
Show angle locating for wing flap 3 or angular range.
First mark 5 and the second mark 6 are lateral；The third mark 7 is longitudinal.
When observing the edge alignment of first mark 5 and the second mark 6, indicate wing flap 30 ° of position；
When only observing first mark 5 and the second mark 6 and separating one section of gap, indicate wing flap 3 at angle I
It sets；
When observing 5, second mark 6 of the first mark and third mark 7 simultaneously, indicate wing flap 3 at angle II
It sets；
When only observing first mark 5 and third mark 7, indicate wing flap 3 in III position of angle；
When only observing third mark 7, indicate wing flap 3 in IV position of angle.
First mark, 5, second mark 6 and third mark 7 take different shapes.
First mark, 5, second mark 6 and third mark 7 use different colors.
Claims (5)
1. a kind of high wing airplane wing flap puts down angle mark method, it is characterised in that: this method is provided in fuselage (1) side
Observation window (4), the observation window (4) is on rear side of wing (2)；Wing (2) lower surface is provided with the first mark (5), in wing flap (3)
Lower surface is provided with the second mark (6), and wing flap (3) upper surface is provided with third mark (7)；From observation window (4), for
The assembled state respectively indicated indicates respectively angle or angular range locating for wing flap (3).
2. according to the method described in claim 1, it is characterized by: first mark (5) and the second mark (6) are laterally
's；The third mark (7) is longitudinal.
3. according to the method described in claim 1, it is characterized by:
When observing the edge alignment of first mark (5) and the second mark (6), indicate wing flap (3) 0 ° of position；
When only observing first mark (5) and the second mark (6) and separating one section of gap, indicate wing flap (3) in angle I
Position；
When observing first mark (5), the second mark (6) and third mark (7) simultaneously, indicate wing flap (3) in angle
II position；
When only observing first mark (5) and third mark (7), indicate wing flap (3) in III position of angle；
When only observing third mark (7), indicate wing flap (3) in IV position of angle.
4. according to the method described in claim 1, it is characterized by: first mark (5), the second mark (6) and third mark
Show that (7) take different shapes.
5. according to the method described in claim 1, it is characterized by: first mark (5), the second mark (6) and third mark
Show that (7) use different colors.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811119437.1A CN109250070B (en) | 2018-09-25 | 2018-09-25 | Method for marking flap lowering angle of upper single-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811119437.1A CN109250070B (en) | 2018-09-25 | 2018-09-25 | Method for marking flap lowering angle of upper single-wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109250070A true CN109250070A (en) | 2019-01-22 |
| CN109250070B CN109250070B (en) | 2021-09-14 |
Family
ID=65047479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811119437.1A Active CN109250070B (en) | 2018-09-25 | 2018-09-25 | Method for marking flap lowering angle of upper single-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109250070B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114506460A (en) * | 2022-03-15 | 2022-05-17 | 中国商用飞机有限责任公司 | System and method for monitoring flap faults |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1332108A (en) * | 1971-04-16 | 1973-10-03 | Ulmic Sa | Method of checking the displacement of a movable component |
| CN102458995A (en) * | 2009-05-26 | 2012-05-16 | 空中客车营运有限公司 | Aircraft having vertical lift system |
| CN102655587A (en) * | 2011-03-02 | 2012-09-05 | 罗斯蒙特航天公司 | Airplane cockpit video system |
| CA2915618A1 (en) * | 2014-12-22 | 2016-06-22 | Airbus Operations Gmbh | Method for determining a state of a component in a high lift system of an aircraft |
| CN107074350A (en) * | 2014-09-16 | 2017-08-18 | 空中客车运作有限责任公司 | A kind of wing for aircraft and include the aircraft of this wing |
-
2018
- 2018-09-25 CN CN201811119437.1A patent/CN109250070B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1332108A (en) * | 1971-04-16 | 1973-10-03 | Ulmic Sa | Method of checking the displacement of a movable component |
| CN102458995A (en) * | 2009-05-26 | 2012-05-16 | 空中客车营运有限公司 | Aircraft having vertical lift system |
| CN102655587A (en) * | 2011-03-02 | 2012-09-05 | 罗斯蒙特航天公司 | Airplane cockpit video system |
| CN107074350A (en) * | 2014-09-16 | 2017-08-18 | 空中客车运作有限责任公司 | A kind of wing for aircraft and include the aircraft of this wing |
| CA2915618A1 (en) * | 2014-12-22 | 2016-06-22 | Airbus Operations Gmbh | Method for determining a state of a component in a high lift system of an aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114506460A (en) * | 2022-03-15 | 2022-05-17 | 中国商用飞机有限责任公司 | System and method for monitoring flap faults |
| CN114506460B (en) * | 2022-03-15 | 2024-05-10 | 中国商用飞机有限责任公司 | System and method for monitoring flap faults |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109250070B (en) | 2021-09-14 |
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