JPH03287494A - Drag reducing device for missile with backward step - Google Patents
Drag reducing device for missile with backward stepInfo
- Publication number
- JPH03287494A JPH03287494A JP8917090A JP8917090A JPH03287494A JP H03287494 A JPH03287494 A JP H03287494A JP 8917090 A JP8917090 A JP 8917090A JP 8917090 A JP8917090 A JP 8917090A JP H03287494 A JPH03287494 A JP H03287494A
- Authority
- JP
- Japan
- Prior art keywords
- missile
- fuselage
- section
- height
- backward
- 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
Links
- 230000003247 decreasing effect Effects 0.000 abstract 1
- 238000000926 separation method Methods 0.000 description 16
- 230000007423 decrease Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、飛しよう体、航空機等の後向きの段差をもつ
飛行体の抵抗軽減装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Field of Application] The present invention relates to a drag reduction device for a flying object, an aircraft, etc., which has a step facing backward.
従来の技術をロケットを例に第３図によって説明する。 The conventional technology will be explained using FIG. 3 using a rocket as an example.
ロケットには、人工衛星等の打ち上げ物（ペイロード）
が頭部１に搭載される。その際、ペイロードのサイズが
大きくて、それを囲む衛星フェアリング１ａの断面直径
が、下部胴体２の・直径より大きくなる場合がある。A rocket carries a launch object (payload) such as an artificial satellite.
is mounted on head 1. In this case, the size of the payload is large, and the cross-sectional diameter of the satellite fairing 1a surrounding it may be larger than the diameter of the lower fuselage 2.
この場合、衛星フェアリング１ａと下部胴体の接続部分
には、第４図（ｂ）に示すように、衛星フェアリング１
ａＫ直角をなして下部胴体２へ接続する後向きのステッ
プ４ａ、又は第４図（ｅ）に示すように、後方へ向って
断面積が次第に減少する後向きのランプ４ｂが設けられ
ている（このステップ及びランプ等の断面積が気流方向
にひいて減少する部分を本明細書では総称して後向きの
段差という）、
〔発明が解決しようとする課題〕
本発明が解決しようとする課題を第４図（ｂ）、（ｃ’
）によって説明する。In this case, as shown in FIG. 4(b), the satellite fairing 1
aK A rearward facing step 4a connecting to the lower fuselage 2 at right angles or a rearward facing ramp 4b whose cross-sectional area gradually decreases rearward as shown in FIG. 4(e) is provided (this step In this specification, the portion where the cross-sectional area of a lamp, etc. decreases in the airflow direction is collectively referred to as a backward step). (b), (c'
).
前記の従来のロケットの後向きの段差、即ちその断面積
が気流Ｆ方向に訟いて減少している部分ては、気流Ｆの
機体に沿って流れる部分である境界層１０が機体から遊
離する。これを境界層の剥離１１という（第４図（ｂ）
、（ｅ）参照）。At the rearward step of the conventional rocket, that is, the portion where the cross-sectional area decreases in the direction of the airflow F, the boundary layer 10, which is the portion of the airflow F flowing along the airframe, separates from the airframe. This is called boundary layer separation 11 (Fig. 4(b)
, see (e)).
境界層の剥離１１が起ると、第４図ｔｂ）、（Ｃ）に示
すように、段差４ａ、４ｂの後方に剥離流１２が形成さ
れ、物体の抵抗は大きく増加する。そこでロケット、航
空機等では機体形状を流線形等にして剥離を抑えようと
している。When separation 11 of the boundary layer occurs, a separation flow 12 is formed behind the steps 4a and 4b, as shown in FIGS. 4(tb) and 4(C), and the resistance of the object increases greatly. Therefore, in rockets, aircraft, etc., efforts are being made to make the fuselage shape streamlined or the like in order to suppress separation.
しかし、ロケットでは、前記のように構造上または費用
の面から下部胴体の断面積より大きな断面積をもつ衛星
フェアリングが装着される場合があり、前記の境界層ｆ
＃Ｉ離が避けられない。However, as mentioned above, a satellite fairing having a cross-sectional area larger than that of the lower fuselage is sometimes installed on a rocket due to structural or cost reasons.
#I separation is inevitable.
筐た、航空機のキャノピ−又は大型前部胴体の後部にも
、同様に気流方向に断面積が減少する段差があり、前記
の境界層剥離が発生する。Similarly, in the rear part of an aircraft canopy or a large front fuselage, there is a step where the cross-sectional area decreases in the airflow direction, and the boundary layer separation described above occurs.
前記の剥離流１２ｔｉ、３次元的な速度変動を持つ乱流
となっている（言い換えると、３方向に変動の激しい流
れ場となっている）。この３次元的な速度変動のうち、
一方向の変動を抑えれば（！１流すれば）、乱流の強さ
が減少し、さらに剥離の大きさが減少して剥離領域が小
さくなって、空力抵抗が減少する。The separated flow 12ti is a turbulent flow with three-dimensional velocity fluctuations (in other words, it is a flow field with severe fluctuations in three directions). Among these three-dimensional speed fluctuations,
If the fluctuations in one direction are suppressed (!1 flow), the strength of the turbulence is reduced, and the magnitude of the separation is further reduced, the separation area becomes smaller, and the aerodynamic drag is reduced.
本発明は、この気流の変動を小さくして空力抵抗を減少
させようとするものである。The present invention aims to reduce aerodynamic drag by reducing fluctuations in airflow.
本発明の後向き段差を有する飛行体の抵抗軽減装置は、
飛行体の後向き段差にその前端部を接し、飛行体の面に
直角をなし気流方向に後方へ向うと共に、その前部が前
記段差の高さ以上の高さを有する整流装置を飛行体の面
に取付けた。The drag reduction device for an aircraft having a backward step according to the present invention includes:
A rectifier whose front end is in contact with the backward step of the aircraft, is perpendicular to the plane of the aircraft, faces rearward in the airflow direction, and whose front part has a height equal to or higher than the height of the step is attached to the plane of the aircraft. installed on.
前記したように、飛行体の後向き段差を有する部分の後
方では、境界層の剥離が起って三次元的速度変動をもつ
剥離流が発生する。しかし、本発明では、段差から後方
へ向って飛行体の面に直角を危し気流方向に後方向へ向
う整流装置が飛行体の面に取付けられ、しかも整流装置
の前部の高さは、段差の高さ以上であるために、剥離流
の横方向の流れが抑えられる。これによって、乱流の強
さが減少し、筺たその大きさが減少して剥離領域が小さ
くなって、空気抵抗が減少する。As described above, separation of the boundary layer occurs behind the portion of the flying object that has a backward step, resulting in a separated flow having three-dimensional velocity fluctuations. However, in the present invention, the rectifier is attached to the plane of the aircraft, which extends rearward from the step at right angles to the plane of the aircraft and faces backward in the airflow direction, and the height of the front part of the rectifier is Since the height is greater than the height of the step, the lateral flow of the separated flow is suppressed. This reduces the strength of the turbulence, reduces the size of the enclosure, reduces the separation area, and reduces air resistance.
本発明の第１の実施例を、第１図によって説明する。１
は、円錐状の＠部１ｂとこれに続く円筒状の衛星フェア
リング１ａからなるロケットの頭部であり、衛星フェア
リング１ａの後部は、断面積が後方に行くに従って減少
する截頭円錐状のランプ状の段差４を介して、衛星フェ
アリング１ａより断伽積の小さい円筒状の下部胴体２に
接続されている。A first embodiment of the present invention will be described with reference to FIG. 1
is the head of the rocket consisting of a conical @ part 1b and a cylindrical satellite fairing 1a following it, and the rear part of the satellite fairing 1a is a truncated conical part whose cross-sectional area decreases toward the rear. It is connected via a ramp-shaped step 4 to a cylindrical lower body 2 having a smaller cross section than the satellite fairing 1a.
この段差４に先端を接して下部胴体２から同調体２の面
に直角に放射状に、かつ、気流の方向、即ち、ロケット
の機軸方向に後方へ複数個の板状の整流装置３が、下部
胴体２の１わりに外方へ向って突出して等間隔に設けら
れている。A plurality of plate-shaped flow straighteners 3 are attached to the bottom of the step 4, radially extending from the lower fuselage 2 at right angles to the plane of the synchronizer 2 and rearward in the direction of the airflow, that is, in the rocket axis direction. They protrude outward for one part of the body 2 and are provided at equal intervals.
この整流装置３の段差４に接する前部の高さは、第１図
（Ｃ）に示すように、段差４の高さと等しいか、又は、
第１図（ｄ）に示すように、段差４の高さより高く設定
されている。また、整流装置３の上縁は、下部胴体２の
面には！平行となっている。同整流装置３の平面形状は
、第１図（ｅ３に示すように舅形状、第１図（ｆ）に示
すように細長い平行四辺形状、又は第１図（ｇ）に示す
ようにくさび（菱形）形状のもの等で、厚さの薄いもの
が採用される。The height of the front part of this rectifying device 3 in contact with the step 4 is equal to the height of the step 4, as shown in FIG. 1(C), or
As shown in FIG. 1(d), the height is set higher than the height of the step 4. Also, the upper edge of the rectifier 3 is not on the surface of the lower body 2! They are parallel. The planar shape of the rectifier 3 may be a leg shape as shown in Fig. 1 (e3), an elongated parallelogram as shown in Fig. 1 (f), or a wedge (diamond) shape as shown in Fig. 1 (g). ) shape, etc., and thin ones are used.
以上のように構成された本実施例では、整流装置３ば、
段差４から下部胴体２の面に直角をなして気流方向に後
方へ向って延びており、かつ段差４に接する前部は、段
差４の高さに等しいか、それより大きい高さを有してい
るために、段差４後方で発生する気流の境界層剥離によ
る三次元的速度変動をもつ剥離流の横方向の流れが抑え
られる。従って、乱流の強さを減少させまた剥離領域も
小さくすることができ、これによって空力抵抗を減少さ
せることができる。In this embodiment configured as described above, the rectifier 3
The front part extending rearward in the airflow direction from the step 4 at right angles to the surface of the lower fuselage 2 and in contact with the step 4 has a height equal to or greater than the height of the step 4. Therefore, the lateral flow of a separated flow having three-dimensional velocity fluctuations due to boundary layer separation of the airflow generated behind the step 4 is suppressed. Therefore, the intensity of turbulence can be reduced and the separation area can also be reduced, thereby reducing aerodynamic drag.
本発明の第２の実施例を、第２図によって説明する。A second embodiment of the invention will be described with reference to FIG.
本実施例は、パイロットを囲むキャノピ−５が胴体６よ
り突出している小型航空機２戦Ｍ機等の抵抗軽減装置で
あって、キャノピ−５後部の後向きの段差４に、その前
端を段差４に接して胴体６の面に直角に、かつ、気流の
方向に後方へ向って１個の板状の整流装置３が取付けら
れている。同整流装置３の前部の高さは、前記＠１の実
施例と同様に段差４の高さに等しいか、それより大きく
され、その平面形状も前記第１の実施例と同様のものが
採用される。This embodiment is a drag reduction device for a small aircraft such as a 2nd Fighter M aircraft in which a canopy 5 surrounding a pilot protrudes from a fuselage 6, and the front end of the canopy 5 is attached to a rearward facing step 4 at the rear of the canopy 5. A plate-shaped rectifying device 3 is attached perpendicularly to the surface of the body 6 and facing rearward in the direction of airflow. The height of the front part of the rectifying device 3 is equal to or larger than the height of the step 4 as in the @1 embodiment, and its planar shape is the same as in the first embodiment. Adopted.
本実施例に訃いても、整流装置３によって、段差４後方
で発生する気流の境界層剥離による剥離流の横方向の流
れを抑え、空力抵抗を減少させることができる。Even with this embodiment, the rectifying device 3 can suppress the lateral flow of the separated flow caused by boundary layer separation of the airflow generated behind the step 4 and reduce the aerodynamic drag.
本発明の第３の実施例を、第３図によって説明する。A third embodiment of the present invention will be described with reference to FIG.
本実施例は、大型旅客機の断面積の大きい前部胴体７と
断面積が小さい後部胴体８との間に形成される段差４に
、前記第２の実施例と同様な１個の板状の整流装置３を
設けたものである。In this embodiment, a single plate-shaped plate similar to the second embodiment is installed in the step 4 formed between the front fuselage 7, which has a large cross-sectional area, and the rear fuselage 8, which has a small cross-sectional area, of a large passenger aircraft. A rectifier 3 is provided.
本実施例にシいても、ｇ／ｌｆＭ装置３によって、段差
４で発生する気流の境界層剥離による剥離流の横方向の
流れを抑え、空力抵抗を減少させることができる。In this embodiment as well, the g/lfM device 3 can suppress the lateral flow of the separated flow due to boundary layer separation of the airflow generated at the step 4, thereby reducing aerodynamic drag.
なに１前記各実施例にかける整流装置の気流方向の長さ
は、剥離流の横方向の流れを抑えて整流を行なうことが
できるように適宜の長さに選定される。′また、整流装
置の高さは、剥離流の高さと同程度とするのが望璽しい
が、その前部の高さは、少くとも段差４の高さと等しく
し段差後方の剥離流の横方向の流れを抑えるようにされ
ている。また更に、整流装置の後方の部分の高さは、剥
離流の横方向の流れを抑えると共に、構造強度及び美観
等の観点から適宜の値に選定することができる。First, the length of the rectifying device in each of the above embodiments in the airflow direction is selected to be an appropriate length so that the flow can be rectified while suppressing the lateral flow of the separated flow. 'Also, it is preferable that the height of the rectifier be the same as the height of the separated flow, but the height of the front part should be at least equal to the height of step 4, and the height of the rectifier should be at least equal to the height of the separated flow behind the step. It is designed to suppress directional flow. Furthermore, the height of the rear portion of the rectifying device can be selected to an appropriate value from the viewpoints of suppressing the lateral flow of the separated flow, structural strength, aesthetics, and the like.
本発明は、飛行体の後向き段差にその前端部を接して、
飛行体の面に直角をなし気流方向に後方へ向うと共に、
その前部が前記段差の高さ以上の高さを有する整流装置
を飛行体の面に取付けたことによって、段差後方に形成
される剥離流の横方向の流れを抑え、これによって流れ
の乱れ強さと大きさを抑えることができ、機体に対する
空力抵抗を軽減させることができる。The present invention has a front end in contact with a backward step of an aircraft,
At right angles to the plane of the aircraft and facing backward in the direction of the airflow,
By attaching a rectifier whose front part has a height equal to or greater than the height of the step to the surface of the aircraft, it suppresses the lateral flow of the separated flow that forms behind the step, thereby increasing the turbulence of the flow. It is possible to reduce the size and size of the aircraft, and reduce aerodynamic drag on the aircraft.
第１図は本発明の第１の実施例を示し、第１図（ａ’）
はその側面図、第１図（ｂ）はその斜視図、第１図（Ｃ
）、（ｄ）はそれぞれその整流装置の例を示す側面図、
第１図（ｅ）〜（ｇ）はそれぞれその整流装置の平面形
状の例を示す断面図、第２図は本発明の第２の実施例の
斜視図、第３図は本発明の第３の実施例の斜視図、第４
図（ａ）は従来のロケットの側面図、第４図（ｂ＞、（
ｃ）は同従来のロケットの後向き段差後方の流れの状態
の説明図である。
１・・・ロケットの頭部、１ａ・・・衛星フェアリング
、°２・・・ロケットの下部胴体、３・・・整流装置、
４・・・段差、４ａ・−・ステップ、４ｂ・・・ランプ
、５・・・キャノピ−１６・・・胴体、７・・・前部胴
体、８・・・後部胴体、１０・・・境界層、１１・・・
境界層剥離、１２・・・剥離層、Ｆ・・・気流。
第１皿
Ｃａ）FIG. 1 shows a first embodiment of the present invention, and FIG. 1(a')
is its side view, Fig. 1(b) is its perspective view, and Fig. 1(C) is its side view.
) and (d) are side views showing examples of the rectifier, respectively;
FIGS. 1(e) to (g) are sectional views showing examples of planar shapes of the rectifier, FIG. 2 is a perspective view of the second embodiment of the present invention, and FIG. 3 is the third embodiment of the present invention. 4th perspective view of the embodiment of
Figure (a) is a side view of a conventional rocket, Figure 4 (b>, (
c) is an explanatory diagram of the flow state behind the backward step of the conventional rocket. 1... Head of rocket, 1a... Satellite fairing, °2... Lower body of rocket, 3... Rectifier,
4... Level difference, 4a... Step, 4b... Ramp, 5... Canopy 16... Fuselage, 7... Front fuselage, 8... Rear fuselage, 10... Boundary Layer, 11...
Boundary layer separation, 12... separation layer, F... airflow. 1st dish Ca)
Claims (1)
垂直をなし気流方向に後方へ向うと共に、その前部が前
記段差の高さ以上の高さを有する整流装置を、飛行体の
面に取付けたことを特徴とする後向き段差を有する飛行
体の抵抗軽減装置。A rectifying device that has its front end in contact with the backward step of the aircraft, is perpendicular to the plane of the aircraft, faces rearward in the airflow direction, and has a front portion with a height equal to or higher than the height of the step. A drag reduction device for an aircraft having a rearward step, characterized in that it is attached to a surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8917090A JPH03287494A (en) | 1990-04-05 | 1990-04-05 | Drag reducing device for missile with backward step |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP8917090A JPH03287494A (en) | 1990-04-05 | 1990-04-05 | Drag reducing device for missile with backward step |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH03287494A true JPH03287494A (en) | 1991-12-18 |
Family
ID=13963320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP8917090A Pending JPH03287494A (en) | 1990-04-05 | 1990-04-05 | Drag reducing device for missile with backward step |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH03287494A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010514616A (en) * | 2006-12-26 | 2010-05-06 | エアバス | Aircraft fuselage |
| CN110274525A (en) * | 2019-06-25 | 2019-09-24 | 石家庄市居高科技有限公司 | A kind of drag reduction increases the high-speed aircraft of journey |
-
1990
- 1990-04-05 JP JP8917090A patent/JPH03287494A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010514616A (en) * | 2006-12-26 | 2010-05-06 | エアバス | Aircraft fuselage |
| CN110274525A (en) * | 2019-06-25 | 2019-09-24 | 石家庄市居高科技有限公司 | A kind of drag reduction increases the high-speed aircraft of journey |
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