SU912040A3 - Система управлени створкой дл подачи дополнительного воздуха в воздухозаборник двигател - Google Patents
Система управлени створкой дл подачи дополнительного воздуха в воздухозаборник двигател Download PDFInfo
- Publication number
- SU912040A3 SU912040A3 SU762314855A SU2314855A SU912040A3 SU 912040 A3 SU912040 A3 SU 912040A3 SU 762314855 A SU762314855 A SU 762314855A SU 2314855 A SU2314855 A SU 2314855A SU 912040 A3 SU912040 A3 SU 912040A3
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- point
- link
- flap valve
- pivotally connected
- air intake
- Prior art date
Links
- 238000013016 damping Methods 0.000 claims description 2
Classifications
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0253—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft
- B64D2033/026—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of aircraft for supersonic or hypersonic aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T137/00—Fluid handling
- Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Characterised By The Charging Evacuation (AREA)
- Valve-Gear Or Valve Arrangements (AREA)
- Lift Valve (AREA)
- Axle Suspensions And Sidecars For Cycles (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
Description
гом 8 и демпфером 1 - шарниром 9. Рычаг 8 соединен со створкой А шарниром 10, а с демпфером. шарниром 1 I
Система работает следующим образом .
Дл открывани створки 4 выдвигаетс шток демпфера 1, При этом рычаг в поворачиваетс вокруг оси шарнира 10,а штанга 6 - вокруг оси шарнира 10. При демпфировании возмущенно-го потока воздуха усилие от створки 4 передаетс на рычаг 8, который работа как рычаг вторрго рода, раст гива и поворачива штангу 6 нагружает дополнительным усилием демпфер 1.
Уменьшение износа конструкции воздухозаборника в процессе эксплуатации происходит за счет динамического упора.
Claims (2)
1. Система управлени створкой дл подачи дополнительного воздуха
в воздухозаборник двигател , содержаща шарнирно соединенный со створкой демпфер и рычажно-передаточный механизм, отличающа с
тем-, что, с целью обеспечени эффективности демпфировани , створка снабжена штангой, один конец которой соединен с корпусом воздухозаборника,а другой - с рычагом, шарнирно закрепленным на створке, при этом другой конец рычага шарнирно соединен с демпфером.
2. Система по п.I, о т л и ч а ющ а с тем, что демпфер шарнирно
соединен с рычагом в месте креплени рычага со штангой. .
Источники информации, прин тые внимание при экспертизе 1. Авторское свидетельство СССР № 67530, кл. В 64 D 33/00, 1940.
2. Авторское свидетельство СССР № 158182, кл. В.64 D 33/02, 1962. (прототип).
7 f
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2511468A DE2511468C3 (de) | 1975-03-15 | 1975-03-15 | Triebwerkseinlauf mit einer Hilfseinlaufklappe |
Publications (1)
Publication Number | Publication Date |
---|---|
SU912040A3 true SU912040A3 (ru) | 1982-03-07 |
Family
ID=5941525
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SU762314855A SU912040A3 (ru) | 1975-03-15 | 1976-01-09 | Система управлени створкой дл подачи дополнительного воздуха в воздухозаборник двигател |
Country Status (7)
Country | Link |
---|---|
US (1) | US3991782A (ru) |
CA (1) | CA1041308A (ru) |
DE (1) | DE2511468C3 (ru) |
FR (1) | FR2304514A1 (ru) |
GB (1) | GB1530712A (ru) |
IT (1) | IT1063949B (ru) |
SU (1) | SU912040A3 (ru) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4397431A (en) * | 1981-11-02 | 1983-08-09 | Avco Corporation | Fail-safe, anti-icing system for aircraft engines |
US4579300A (en) * | 1981-12-14 | 1986-04-01 | Carr Robert J | Internal wing aircraft |
GB2140090B (en) * | 1982-12-23 | 1986-10-01 | Rolls Royce | Air intakes of helicopter mounted gas turbine engines |
US4587803A (en) * | 1983-08-15 | 1986-05-13 | Rolls-Royce Inc. | Valve for diverting fluid flows in turbomachines |
FR2640685B1 (fr) * | 1988-12-15 | 1991-02-08 | Snecma | Vanne de decharge de compresseur de turboreacteur |
FR2763098B1 (fr) * | 1997-05-07 | 1999-06-11 | Snecma | Systeme d'admission d'air dans une veine de turbomachine |
DE10361722B4 (de) * | 2003-12-30 | 2009-06-10 | Airbus Deutschland Gmbh | Stauluftkanal zur Umgebungsluftzufuhr in einem Flugzeug |
US7600713B2 (en) * | 2005-03-04 | 2009-10-13 | Honeywell International Inc. | Pre-hung inlet door system |
US7575014B2 (en) * | 2005-07-29 | 2009-08-18 | Aerospace Filtration Systems, Inc. | Control of engine intake door |
US20120318083A1 (en) * | 2011-06-15 | 2012-12-20 | First Dome Corporation | Rotary shaft device for sliding module |
US9429071B2 (en) * | 2011-06-23 | 2016-08-30 | Continuum Dynamics, Inc. | Supersonic engine inlet diffuser with deployable vortex generators |
US9656760B2 (en) * | 2013-11-07 | 2017-05-23 | Sikorsky Aircraft Corporation | Variable geometry helicopter engine inlet |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US634596A (en) * | 1899-01-30 | 1899-10-10 | George W Warner | Door-check. |
US1875593A (en) * | 1930-07-31 | 1932-09-06 | Randolph F Hall | Airplane |
US3664612A (en) * | 1969-12-22 | 1972-05-23 | Boeing Co | Aircraft engine variable highlight inlet |
GB1452267A (en) * | 1972-10-14 | 1976-10-13 | Rolls Royce | Jet propulsion powerplant frames |
-
1975
- 1975-03-15 DE DE2511468A patent/DE2511468C3/de not_active Expired
-
1976
- 1976-01-09 SU SU762314855A patent/SU912040A3/ru active
- 1976-02-17 US US05/658,260 patent/US3991782A/en not_active Expired - Lifetime
- 1976-02-19 CA CA246,089A patent/CA1041308A/en not_active Expired
- 1976-03-04 IT IT2084676A patent/IT1063949B/it active
- 1976-03-15 FR FR7607365A patent/FR2304514A1/fr active Granted
- 1976-03-15 GB GB1028976A patent/GB1530712A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
CA1041308A (en) | 1978-10-31 |
GB1530712A (en) | 1978-11-01 |
FR2304514A1 (fr) | 1976-10-15 |
DE2511468C3 (de) | 1980-11-13 |
DE2511468B2 (de) | 1980-03-20 |
IT1063949B (it) | 1985-02-18 |
FR2304514B1 (ru) | 1979-08-24 |
DE2511468A1 (de) | 1976-09-16 |
US3991782A (en) | 1976-11-16 |
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