CN103057692A - Airplane suspension beam - Google Patents
Airplane suspension beam Download PDFInfo
- Publication number
- CN103057692A CN103057692A CN2012105537470A CN201210553747A CN103057692A CN 103057692 A CN103057692 A CN 103057692A CN 2012105537470 A CN2012105537470 A CN 2012105537470A CN 201210553747 A CN201210553747 A CN 201210553747A CN 103057692 A CN103057692 A CN 103057692A
- Authority
- CN
- China
- Prior art keywords
- linear portion
- drop
- straight line
- angle
- line segment
- 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.)
- Pending
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Classifications
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- 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
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
Abstract
The invention relates to an airplane suspension beam. The front end face of the suspension beam comprises a straight line segment (1), an arc segment (2), a straight line segment (3) and a spline curve segment (4), wherein the arc segment (2) is connected between the straight line segment (1) and the straight line segment (3), transition between the straight line segment (1) and the straight line segment (3) is smooth, the spline curve segment (4) is connected between the straight line segment (3) and a bottom surface (5) of the suspension beam and tangent to the straight line segment (3), an included angle (7) between the straight line segment (1) and the straight line segment (3) is an acute angle, an included angle (8) between a connecting line of two endpoints of the spline curve segment (4) and the bottom surface (5) is an acute angle, and an included angle (9) between the bottom surface (5) and a rear end face (6) of the suspension beam is an obtuse angle. The airplane suspension beam trims an airplane by using own weight of an external suspended object, improves the gravity center of the airplane, increases the variety of external suspended objects, and improves external suspending ability.
Description
Technical field
The present invention relates to aircraft aerodynamic arrangement design field, particularly aircraft drop in beam contour structures.
Background technology
In the middle of the employed drop in beam of current military aircraft, substantially be conventional elevator shape profile drop in beam as shown in Figure 2.This kind drop in beam for large sweepback angle, configured the aircraft of Leading-Edge Manoeuvre Flap, because the track that deflects down of Leading-Edge Manoeuvre Flap requires restriction, so that traditional echelon form drop in beam is restricted in the installation site, after store Combinations and aircraft relative position lean on, plug-in configuration situation get off the plane center of gravity partially after, and then retrained store Combinations kind quantity, can't bring into play fully the plug-in ability of aircraft.
Summary of the invention
(1) purpose of the present invention
For solve adopting large sweepback angle and with the plug-in configuration center of gravity of airplane of the motor-driven droope snoot aircraft technical matters after partially, and increase plug-in kind ability, propose a kind of novel aircraft front extensible drop in beam.
(2) technical scheme of the present invention
The technical scheme that the present invention takes is: a kind of aircraft drop in beam contour structures, the front end face of drop in beam comprises that linear portion 1, circular arc 2, linear portion 3, SPL section 4 consist of, circular arc 2 is connected between linear portion 1 and the linear portion 3, make smooth transition between linear portion 1 and the linear portion 3, SPL section 4 is connected between linear portion 3 and the drop in beam bottom surface 5, SPL 4 is tangent with linear portion 3, the line of 4 two end points of SPL section and bottom surface 5 angles 8 are acute angle, and the angle 9 between bottom surface 5 and the drop in beam aft end face 6 is the obtuse angle.
The line of two end points of described SPL section 4 and the angle between the bottom surface 58 are 25 °～45 °, and the angle 9 between bottom surface 5 and the drop in beam aft end face 6 is 120 °～145 °.
Gap between described drop in beam front end face linear portion 1 and the lower inclined to one side droope snoot 12 is 5mm～30mm.
(3) beneficial effect of the present invention:
Technical scheme of the present invention is avoided droope snoot path of motion, rationally adjusts the store Combinations installation site, improves the relative position relation of store Combinations and aircraft, utilize the weight of store Combinations self that aircraft is carried out trim, improve the center of gravity of airplane, reaching increases plug-in kind, improves plug-in ability.
Description of drawings
Fig. 1 is shape assumption diagram of the present invention.
Fig. 2 is traditional trapezoidal drop in beam shape assumption diagram.
The specific embodiment
One embodiment of the present invention are: as shown in Figure 1, the front end face of drop in beam comprises linear portion 1 and linear portion 3, between linear portion 1 and the linear portion 3 with 2 transition of smooth circular arc, angle 7 between linear portion 1 and the linear portion 3 is between 20 °～40 °, connect with Quadric spline curve 4 between linear portion 3 and the drop in beam bottom surface 5, SPL 4 is tangent with linear portion 3, the line of two end points of SPL 4 and the angle 8 between the bottom surface 5 are between 25 °～45 °, and the angle 9 between bottom surface 5 and the drop in beam aft end face 6 is between 120 °～145 °.Gap between drop in beam front end face linear portion 1 and the lower inclined to one side droope snoot 12 is at 5mm～30mm.
For the aircraft of center of gravity after partially, as adopt store Combinations to come the trim center of gravity of airplane, Fig. 1 middle distance 10 and and Fig. 2 in distance 13 can realize full machine trim when reaching certain numerical value, obviously, when the distance 10 among Fig. 1 and the distance among Fig. 2 13 equates, then the distance among Fig. 1 11 is less than the distance 14 among Fig. 2, therefore adopt the required drop in beam weight of paying of traditional trapezoidal drop in beam and bring load all large than front extensible drop in beam, therefore the front extensible drop in beam can better satisfy the operating needs of aircraft, brings the effect of loss of weight, off-load when realizing the trim of full machine center of gravity.
Claims (5)
1. aircraft drop in beam, the front end face that it is characterized in that drop in beam comprises linear portion (1), arc section (2), linear portion (3), SPL section (4) consists of, arc section (2) is connected between linear portion (1) and the linear portion (3), make smooth transition between linear portion (1) and the linear portion (3), SPL section (4) is connected between linear portion (3) and drop in beam bottom surface (5), SPL (4) is tangent with linear portion (3), angle (7) between linear portion (1) and the linear portion (3) is acute angle, line and bottom surface (5) angle (8) of (4) two end points of SPL section are acute angle, and the angle (9) between bottom surface (5) and the drop in beam aft end face (6) is the obtuse angle.
2. a kind of aircraft drop in beam according to claim 1 is characterized in that the angle (7) between linear portion (1) and the linear portion (3) is 20 °～40.
3. a kind of aircraft drop in beam according to claim 1 is characterized in that line and the angle (8) between bottom surface (5) of two end points of SPL section (4) is 25 °～45 °.
4. a kind of aircraft drop in beam according to claim 1 is characterized in that the angle (9) between bottom surface (5) and the drop in beam aft end face (6) is 120 °～145 °.
5. a kind of aircraft drop in beam according to claim 1 is characterized in that the gap between drop in beam front end face linear portion (1) and the lower inclined to one side droope snoot (12) is 5mm～30mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105537470A CN103057692A (en) | 2012-12-19 | 2012-12-19 | Airplane suspension beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105537470A CN103057692A (en) | 2012-12-19 | 2012-12-19 | Airplane suspension beam |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103057692A true CN103057692A (en) | 2013-04-24 |
Family
ID=48100656
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105537470A Pending CN103057692A (en) | 2012-12-19 | 2012-12-19 | Airplane suspension beam |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103057692A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101134508A (en) * | 2006-08-31 | 2008-03-05 | 联合工艺公司 | Fan exhaust nozzle for turbofan engine |
| CN101272951A (en) * | 2005-09-26 | 2008-09-24 | 法国空中巴士公司 | Turbofan provided with a pre-cooler |
| CN101272954A (en) * | 2005-09-28 | 2008-09-24 | 法国空中客车公司 | Monolithic framework engine mounting structure |
| CN203064200U (en) * | 2012-12-19 | 2013-07-17 | 江西洪都航空工业集团有限责任公司 | Airplane suspended beam |
-
2012
- 2012-12-19 CN CN2012105537470A patent/CN103057692A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101272951A (en) * | 2005-09-26 | 2008-09-24 | 法国空中巴士公司 | Turbofan provided with a pre-cooler |
| CN101272954A (en) * | 2005-09-28 | 2008-09-24 | 法国空中客车公司 | Monolithic framework engine mounting structure |
| CN101134508A (en) * | 2006-08-31 | 2008-03-05 | 联合工艺公司 | Fan exhaust nozzle for turbofan engine |
| CN203064200U (en) * | 2012-12-19 | 2013-07-17 | 江西洪都航空工业集团有限责任公司 | Airplane suspended beam |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130424 |