JPH03112498U - - Google Patents
Info
- Publication number
- JPH03112498U JPH03112498U JP2148290U JP2148290U JPH03112498U JP H03112498 U JPH03112498 U JP H03112498U JP 2148290 U JP2148290 U JP 2148290U JP 2148290 U JP2148290 U JP 2148290U JP H03112498 U JPH03112498 U JP H03112498U
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- ventral fin
- rear fuselage
- ventral
- fin
- 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
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
第１図は本考案の第１の実施例の側面図、第２
図は同実施例のベントラルフインの作動系統図、
第３図は本考案の第２の実施例の側面図、第４図
は従来のベントラルフインの側面図、第５図及び
第６図はそれぞれ従来のベントラルフインの例を
示す後面図、第７図は迎角と方向安定の関係を示
すグラフ、第８図は航空機の離陸状態を示す説明
図、第９図は航空機の横すべり状態を示す説明図
、第１０図は航空機の仰角を示す説明図である。
１……後部胴体、２……垂直尾翼、３……ベン
トラルフイン、５……航空機、８……アクチユエ
ータ、９……ヒンジ、１０……地面、１１……迎
角計、１２……コンピユータ。
Figure 1 is a side view of the first embodiment of the present invention;
The figure shows the operating system diagram of the ventral fin in the same example.
FIG. 3 is a side view of the second embodiment of the present invention, FIG. 4 is a side view of a conventional ventral fin, and FIGS. 5 and 6 are rear views showing examples of the conventional ventral fin, respectively. Figure 7 is a graph showing the relationship between angle of attack and directional stability, Figure 8 is an explanatory diagram showing the takeoff state of the aircraft, Figure 9 is an explanatory diagram showing the sideslip state of the aircraft, and Figure 10 is the elevation angle of the aircraft. It is an explanatory diagram. DESCRIPTION OF SYMBOLS 1... Rear fuselage, 2... Vertical stabilizer, 3... Ventral fin, 5... Aircraft, 8... Actuator, 9... Hinge, 10... Ground, 11... Angle of attack meter, 12... Computer .
Claims (1)
トラルフイン、及びベントラルフインを前記後部
胴体に出入させる駆動装置を備えたことを特徴と
する航空機のベントラルフイン装置。 1. A ventral fin device for an aircraft, comprising: a ventral fin that is removably mounted on a rear fuselage of an aircraft; and a drive device that moves the ventral fin into and out of the rear fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2148290U JPH03112498U (en) | 1990-03-05 | 1990-03-05 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2148290U JPH03112498U (en) | 1990-03-05 | 1990-03-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH03112498U true JPH03112498U (en) | 1991-11-18 |
Family
ID=31524524
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2148290U Pending JPH03112498U (en) | 1990-03-05 | 1990-03-05 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH03112498U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010280252A (en) * | 2009-06-02 | 2010-12-16 | Keiji Shigemiya | Vertical tail of aircraft |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6467497A (en) * | 1987-09-08 | 1989-03-14 | Nec Corp | Yaw flight stabilizer for high elevation missile |
-
1990
- 1990-03-05 JP JP2148290U patent/JPH03112498U/ja active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6467497A (en) * | 1987-09-08 | 1989-03-14 | Nec Corp | Yaw flight stabilizer for high elevation missile |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010280252A (en) * | 2009-06-02 | 2010-12-16 | Keiji Shigemiya | Vertical tail of aircraft |
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