CN104401494A - Ventilation structure for aircraft gun - Google Patents
Ventilation structure for aircraft gun Download PDFInfo
- Publication number
- CN104401494A CN104401494A CN201410664430.3A CN201410664430A CN104401494A CN 104401494 A CN104401494 A CN 104401494A CN 201410664430 A CN201410664430 A CN 201410664430A CN 104401494 A CN104401494 A CN 104401494A
- Authority
- CN
- China
- Prior art keywords
- gun
- cabin
- air
- aircraft
- aircraft gun
- 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.)
- Granted
Links
Landscapes
- Electric Suction Cleaners (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to the field of fighter aircraft body structure design and relates to a ventilation structure for an aircraft gun. The ventilation structure is characterized in that a plurality of air inlets and air outlets, which are vertical to the heading of an aircraft are formed in an outer skin or covering cap of an aircraft gun cabin; the air inlets, the air outlets and the skin or covering cap of the aircraft gun cabin are integrally formed; the air inlets are arranged in the front of the heading, the air outlets are arranged in the rear of the heading, the sum of products of the length of the air inlets and the number of the air inlets is required to be consistent with that of products of the length of the air outlets and the number of the air outlets, and thus, excessive pneumatic pressure cannot be formed in the aircraft gun cabin; the air inlets are formed by main air inlet zones, transition zones and crack stop holes, wherein an angle of certain degrees is formed between the skin or covering cap of the aircraft gun cabin and each main air inlet zone, the transition zones are located at the two sides, and the crack stop holes are formed in the two extreme ends; the air outlets are formed by main air outlet zones, transition zones and crack stop holes, wherein an angle of negative certain degrees is formed between the skin or covering cap of the aircraft gun cabin and each main air outlet zone, the transition zones are located at the two sides, and the crack stop holes are formed in the two extreme ends. According to the ventilation structure, air in the aircraft gun cabin can be kept flowing, so that the accumulation of smoke and dust resulting from the gun firing of the aircraft gun is avoided.
Description
Technical field
The invention belongs to fighter plane housing construction design field, relate to a kind of aeration structure for gun.
Background technology
Fighter plane gun is generally placed in custom-designed gun cabin, and gun cabin is except local, gun muzzle place is exposed, and all the other are all positioned at internal body.Because gun can produce volume of smoke when launching, be all designed to physical isolation between gun cabin and other cabins of aircraft, avoid flue dust to enter in other cabins, cause equipment pollution, damage.Gun cabin itself does not allow volume of smoke to accumulate yet simultaneously, so need a kind of new version of design to make flue dust can drain into rapidly out of my cabin when gun is launched.
Summary of the invention
Technical matters to be solved by this invention is: provide a kind of version being carried ventilation function by design, the flue dust realized on aircraft in gun cabin drains into engine body exterior rapidly.
For an aeration structure for gun, it is characterized in that: on gun out of my cabin covering or lid, some admission ports 1 perpendicular to vector and exhausr port 2 are set; Admission port 1, exhausr port 2 and gun cabin covering or lid 3 integrally formed; Admission port 1 is arranged in front, course, and exhausr port 2 is arranged in rear, course, admission port 1 length multiplier amount long-pending and with the long-pending of exhausr port 2 multiplier amount and should be consistent, ensure not form unnecessary Pneumatic pressure in gun cabin; Admission port 1 by pressing from both sides the main air inlet area 4 at 25 ° of angles with gun cabin covering or lid 3, the stop hole 6 at the transition region 5 of both sides and most two ends forms; Exhausr port 2 by pressing from both sides the main exhaust district 7 at negative 25 ° of angles with gun cabin covering or lid 3, the stop hole 6 at the transition region 5 of both sides and most two ends forms.
The invention has the beneficial effects as follows: the present invention is by arranging some admission ports perpendicular to vector and exhausr port, when aircraft flight, air-flow can enter gun cabin by admission port, because of gun cabin and other cabin physical isolations, after air-flow circulates in cabin, can only be discharged by exhausr port, make the air in gun cabin keep flowing, thus the flue dust brought when avoiding gun to set off firecrackers accumulate.
Accompanying drawing explanation
Fig. 1 is aeration structure overall schematic;
Fig. 2 is the enlarged drawing of Fig. 1 partial admission mouth;
Fig. 3 is the enlarged drawing of Fig. 1 local exhaust inlet;
Wherein, 1-admission port, 2-exhausr port, 3-gun cabin covering or lid, the main air inlet area of 4-, 5-transition region, 6-stop hole, 7-main exhaust district.
Detailed description of the invention
Be described further below in conjunction with the detailed description of the invention of accompanying drawing to this method.
Gun out of my cabin covering or lid arrange some admission ports 1 perpendicular to vector and exhausr port 2, sees accompanying drawing 1.When aircraft flight, air-flow can enter gun cabin by admission port 1, because of gun cabin and other cabin physical isolations, after air-flow circulates in cabin, can only be got rid of by exhausr port 2, make the air in gun cabin keep flowing, thus the flue dust brought when avoiding gun to set off firecrackers accumulates.
Admission port 1 and exhausr port 2 and covering or lid integrally formed.Admission port 1 design plan is shown in accompanying drawing 2, and by pressing from both sides the main air inlet area 4 at 25 ° of angles with gun cabin covering or lid 3, the stop hole 6 at the transition region 5 of both sides and most two ends forms.Exhausr port 2 design plan is shown in accompanying drawing 3, and by pressing from both sides the main exhaust district 7 at negative 25 ° of angles with gun cabin covering or lid 3, the stop hole 6 at the transition region 5 of both sides and most two ends forms.When main air inlet area 4 and main exhaust district 5 angle 25 degree, good fanning effect can be reached, can angle be increased if needed, but must material stretch ratio be considered.Transition region 5 is positioned at main air inlet area 4 or both sides, main exhaust district 7, should accomplish smooth transition during design as far as possible, reduces the extension that material is unnecessary.Stop hole 6 is positioned at the most two ends of admission port 1 and exhausr port 2, and size recommends Φ 3mm, and the too small stress that easily causes is concentrated, and crosses conference and causes stop hole 6 place to form eddy current.
Claims (1)
1. for an aeration structure for gun, it is characterized in that: on gun out of my cabin covering or lid, some admission ports perpendicular to vector (1) and exhausr port (2) are set; Admission port (1), exhausr port (2) and gun cabin covering or lid (3) integrally formed; Admission port (1) is arranged in front, course, exhausr port (2) is arranged in rear, course, admission port (1) length multiplier amount long-pending and with the long-pending of exhausr port (2) multiplier amount and should be consistent, ensure not form unnecessary Pneumatic pressure in gun cabin; Admission port (1) by pressing from both sides the main air inlet area (4) at 25 ° of angles with gun cabin covering or lid (3), the stop hole (6) at the transition region (5) of both sides and most two ends forms; Exhausr port (2) by pressing from both sides the negative main exhaust district (7) at 25 ° of angles with gun cabin covering or lid (3), the stop hole (6) at the transition region (5) of both sides and most two ends forms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664430.3A CN104401494B (en) | 2014-11-19 | 2014-11-19 | A kind of aeration structure for aircraft gun |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410664430.3A CN104401494B (en) | 2014-11-19 | 2014-11-19 | A kind of aeration structure for aircraft gun |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104401494A true CN104401494A (en) | 2015-03-11 |
| CN104401494B CN104401494B (en) | 2017-12-12 |
Family
ID=52639187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410664430.3A Active CN104401494B (en) | 2014-11-19 | 2014-11-19 | A kind of aeration structure for aircraft gun |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104401494B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184778A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | A kind of gun pod waste gas flow guiding device |
| CN110844042A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Flap integrating ventilation and drainage functions |
| CN111432589A (en) * | 2020-04-30 | 2020-07-17 | 中国直升机设计研究所 | Avionics equipment cabin with ventilation loop |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007114831A2 (en) * | 2005-11-03 | 2007-10-11 | Harding David K | Jungle fighter aircraft conversion kit |
| CN203612062U (en) * | 2013-07-30 | 2014-05-28 | 北汽福田汽车股份有限公司 | Top cover heat radiation structure and automobile |
-
2014
- 2014-11-19 CN CN201410664430.3A patent/CN104401494B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007114831A2 (en) * | 2005-11-03 | 2007-10-11 | Harding David K | Jungle fighter aircraft conversion kit |
| CN203612062U (en) * | 2013-07-30 | 2014-05-28 | 北汽福田汽车股份有限公司 | Top cover heat radiation structure and automobile |
Non-Patent Citations (1)
| Title |
|---|
| 保罗·艾登: "《当代主力战机：数据和结构图》", 31 July 2013 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106184778A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | A kind of gun pod waste gas flow guiding device |
| CN106184778B (en) * | 2016-09-23 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of gun pod waste gas flow guiding device |
| CN110844042A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Flap integrating ventilation and drainage functions |
| CN111432589A (en) * | 2020-04-30 | 2020-07-17 | 中国直升机设计研究所 | Avionics equipment cabin with ventilation loop |
| CN111432589B (en) * | 2020-04-30 | 2021-06-18 | 中国直升机设计研究所 | Avionics equipment cabin with ventilation loop |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104401494B (en) | 2017-12-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| BR112015020698A2 (en) | dirt separator assembly for a gas turbine engine, dirt separator for a gas turbine engine and two stage particle separator for a gas turbine engine | |
| RU2016134087A (en) | GAS-TURBINE ENGINE WITH COMPRESSED AIR FLOW | |
| EP2711297A3 (en) | Heat exchanger systems and methods for controlling airflow cooling | |
| WO2014114653A3 (en) | Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity | |
| WO2018017172A3 (en) | Ceramic matrix composite airfoil cooling | |
| EP2784267A3 (en) | A gas turbine engine cooling arrangement | |
| EP2481893A3 (en) | Heated booster splitter plenum | |
| WO2015187653A3 (en) | Air intake water separator | |
| WO2015012919A3 (en) | Aircraft engine with multi-nozzle flow diverter | |
| CN104401494A (en) | Ventilation structure for aircraft gun | |
| WO2016126986A3 (en) | Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation | |
| CN105151307B (en) | Method for cutting Mach surface of hypersonic aircraft with forebody/air inlet pipeline in integrated design | |
| WO2012098321A3 (en) | Nacelle for an aircraft bypass turbojet engine | |
| CN102249004A (en) | Aircraft using submerged intake | |
| JP2014092157A5 (en) | ||
| WO2015126489A3 (en) | Exhaust section for an aircraft gas turbine engine | |
| JP2014234824A5 (en) | ||
| CN104088704B (en) | A kind of have the aeroengine hot air anti-icing chamber device conformal with anti-icing wall | |
| CN103587704A (en) | Combined subsonic air intake device of aircraft | |
| CN104590569B (en) | Helicopter with engine intake | |
| CN110304267A (en) | Hypersonic aircraft design method and system | |
| WO2009024662A3 (en) | Coupling system connecting an internal structure and an external structure of a jet engine nacelle | |
| MY190376A (en) | Intake manifold with surge tank | |
| WO2014113444A3 (en) | Aircraft supplemental thrust device and method of operating the same | |
| WO2014198655A3 (en) | An air-to-air heat exchanger |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |