CN105438446A - Cone type damping device manufactured on front portion of aircraft - Google Patents
Cone type damping device manufactured on front portion of aircraft Download PDFInfo
- Publication number
- CN105438446A CN105438446A CN201510661732.XA CN201510661732A CN105438446A CN 105438446 A CN105438446 A CN 105438446A CN 201510661732 A CN201510661732 A CN 201510661732A CN 105438446 A CN105438446 A CN 105438446A
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- bullet
- aircraft
- fairing
- forefront
- portions
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Abstract
A cone type damping device manufactured on the front portion of an aircraft is characterized in that the cone type or cone-like type damping device can be manufactured on the endpoint portions of the forefront portions of front fairings of various airplanes, guided missiles and space rockets, the point portions of the leading edges of the forefront portions of wings of airplanes and missile wings of guided missiles and space rockets, and the endpoint portions of the forefront portions of front rectifying cones of cannonballs and bullets. In addition, the damping device can be manufactured on the portions such as the front fairings of various aircrafts as well as the portions such as the wings and the missile wings of aircrafts, and has a quite good damping effect, and therefore the damping device can be quite widely applied in future.
Description
Technical field:
The present invention relates to a kind of drag reduction technology that can use at all kinds aircraft, guided missile, space rocket, shell and bullet forefront drag reduction.
Background technology:
Various aircraft, guided missile, space rocket and the forefront such as shell and bullet, the main method that will carry out drag reduction at motion process, adopt now, be exactly by the forefront outside face of these aircraft, be made as fairing or class fairing profile, but technology has been mature on the whole sizing now like this, be difficult to proceed significantly to improve raising, so at various aircraft, guided missile, space rocket and the anterior region such as shell and bullet, want to realize significantly drag reduction further, just must seek the drag reduction mechanisms of other principles.
Summary of the invention:
Target of the present invention, will propose the better practical drag reduction technology of a kind of drag-reduction effect exactly.
In order to realize such target, a kind of bullet formula fairing made in aircraft front portion proposed, it is characterized in that: at the forefront end points position of the anterior fairing of various aircraft, guided missile and space rocket, the forefront leading edge blade tip position of aircraft wing and guided missile and space rocket missile wing, shell and bullet front portion rectification centrum forefront end points position, all can the fairing of fabrication and installation bullet formula or class bullet formula.
Various aircraft, guided missile, space rocket, the aircraft such as shell or bullet is at high-speed flight motion process, from the air draught in aircraft movements front, in flow at high speed by various aircraft, guided missile, space rocket, the forefront such as shell or bullet fairing or position, rectification centrum district, with flow through aircraft wing and guided missile and space rocket missile wing forefront position, set bullet or class bullet formula fairing process, because of a large amount of positive air draught flow through at a high speed, the bullet of meeting in aircraft front or the rear outside position of class bullet formula fairing, produce stampability pile up and move outside specularity, and outside such specularity, move air draught, with just from the air draught that space, aircraft more lateral is passed through to the high speed relative motion of aircraft rear, sense of motion at that time clearly exists to a certain degree different, thus mutually the process of crossing will be moved at them, in the air draught that aircraft exterior passes through, produce very strong eddy current flow phenomenon.And the strong eddy current motive air air-flow produced like this, motion process is carried out at the position, more rear of the wing outside the position, more rear and aircraft, guided missile and space rocket of the various aircrafts at more rear, guided missile, space rocket, the fuselage such as shell or bullet, body, rocket body or missile wing, just greatly amplitude will inevitably reduce various aircraft, guided missile or space rocket, shell or bullet, the resistance of motion existing for sporting flying process.
And such bullet formula or class bullet formula fairing, can make at the fairing forefront of aircraft, guided missile and space rocket, shell and bullet and use, also use at the missile wing forefront position manufacture and installation of aircraft wing and missiles and rockets, so bullet or class bullet formula fairing field of application are very widely like this.
Accompanying drawing illustrates:
Below with regard to let us by reference to the accompanying drawings, some features of this drag reduction overcoat are conducted some supplement.
Fig. 1-3 is the wherein three kinds of anterior fairing rip cutting appearance profile schematic diagrams making bullet formula or class bullet formula fairing at forefront positions such as aircraft, guided missile, space rockets.
Fig. 4 is the rip cutting appearance profile schematic diagram at the anterior fairing positions such as aircraft, guided missile, space rocket.
Fig. 5-7 is the rip cutting appearance profile schematic diagrams when shell or bullet forefront make bullet or class bullet formula fairing.
Fig. 8 is the rip cutting appearance profile schematic diagram of the forefront such as shell or bullet part.
Fig. 9-12 is wherein two kinds of basic appearance profile schematic diagrams of aircraft wing and the appearance profile schematic diagram after its forefront makes bullet or class bullet formula fairing.
Figure 13-14 is the appearance profile schematic diagram of guided missile and space rocket postmedian missile wing and the appearance profile schematic diagram after its forefront makes bullet formula or class bullet formula fairing.
In figure; 1 bullet or class bullet formula fairing 2 bullet or class bullet formula fairing and more rear portion fairing or larger transition region outside face 5 shell of interpyramidal outside face 4 sinuousness being connected the anterior fairings such as crest line 3 aircraft, guided missile, space rocket of rectification or common aircraft wing 8 guided missile of the overcritical aircraft wing of bullet bullet 67 or space rocket missile wing.
Detailed description of the invention:
Bullet or class bullet formula fairing, can at the anterior fairing of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft, and rectification centrum forefront position makes.
Bullet or class bullet formula fairing, also can make at the forefront position of the anterior rectification centrum of various aircraft wing, guided missile and space rocket missile wing.
At anterior fairing and the rectification centrum position foremost of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft; And the position foremost, front portion of various aircraft wing, guided missile and space rocket missile wing; When making bullet or class bullet formula fairing, by the appearance profile of bullet or class bullet formula fairing, the triangular shape centrum shape structure of complete straight line can be made as.
At anterior fairing and the rectification centrum position foremost of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft; And various aircraft wing, guided missile and space rocket missile wing front portion position foremost; When making bullet or class bullet formula fairing, also can by bullet or class bullet formula fairing, the outside face being made as its triangular shape centrum is the structure of class fairing formula curved profile.
At anterior fairing and the rectification centrum position foremost of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft; And the position foremost, front portion of various aircraft wing, guided missile and space rocket missile wing; When making bullet or class bullet formula fairing, can also by the triangular shape centrum of bullet or class bullet formula fairing or class triangular knife bladed bullet, be made as can inwardly outside fore-and-aft direction suitably carry out the structure of stretching.
At various aircraft, guided missile and space rocket, the anterior fairing of shell or bullet and so on aircraft and rectification centrum position foremost; And the position foremost, front portion of various aircraft wing, guided missile and space rocket missile wing; When making bullet or class bullet formula fairing, can by the triangular shape vertebral body structure of bullet or class bullet formula fairing, be made as with Fig. 1,5 to draw profile similar, the structure that the anterior triangular shape taper angle of cut is less.
At anterior fairing and the rectification centrum position foremost of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft; And the position foremost, front portion of various aircraft wing, guided missile and space rocket missile wing; When making bullet or class bullet formula fairing, can by the triangular shape vertebral body structure of bullet or class bullet formula fairing, be made as with Fig. 2-3,6-7 to draw profile similar, the anterior triangular shape taper front part angle of cut is carried out obvious increase, or the anterior triangular shape taper front part angle of cut has been become larger structure.
At anterior fairing and the rectification centrum position foremost of various aircraft, guided missile and space rocket, shell or bullet and so on aircraft; And the position foremost, front portion of various aircraft wing, guided missile and space rocket missile wing; When making bullet or class bullet formula fairing, also can the anterior fairing of aircraft or rectification centrum, and between bullet or class bullet formula fairing, make outside ratio fairing below and the larger transition region of rectification centrum outer surface bending degree (4).
Claims (1)
1. the bullet formula fairing made in aircraft front portion, it is characterized in that: at the forefront end points position of the anterior fairing of various aircraft, guided missile and space rocket, the forefront leading edge blade tip position of aircraft wing and guided missile and space rocket missile wing, shell and bullet front portion rectification centrum forefront end points position, all can the fairing of fabrication and installation bullet formula or class bullet formula.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510661732.XA CN105438446A (en) | 2016-01-18 | 2016-01-18 | Cone type damping device manufactured on front portion of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510661732.XA CN105438446A (en) | 2016-01-18 | 2016-01-18 | Cone type damping device manufactured on front portion of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105438446A true CN105438446A (en) | 2016-03-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510661732.XA Pending CN105438446A (en) | 2016-01-18 | 2016-01-18 | Cone type damping device manufactured on front portion of aircraft |
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| Country | Link |
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| CN (1) | CN105438446A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741938A (en) * | 2016-05-11 | 2017-05-31 | 鲁正祥 | The linear hypersonic speed of stray bullet flies hole passenger plane |
-
2016
- 2016-01-18 CN CN201510661732.XA patent/CN105438446A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741938A (en) * | 2016-05-11 | 2017-05-31 | 鲁正祥 | The linear hypersonic speed of stray bullet flies hole passenger plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160330 |
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| WD01 | Invention patent application deemed withdrawn after publication |