CN108100227A - A kind of wing tank calculation of pressure method for considering rib and influencing - Google Patents
A kind of wing tank calculation of pressure method for considering rib and influencing Download PDFInfo
- Publication number
- CN108100227A CN108100227A CN201711172876.4A CN201711172876A CN108100227A CN 108100227 A CN108100227 A CN 108100227A CN 201711172876 A CN201711172876 A CN 201711172876A CN 108100227 A CN108100227 A CN 108100227A
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- fuel
- region
- pressure
- rib
- oil
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Measurement Of Levels Of Liquids Or Fluent Solid Materials (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The present invention relates to a kind of wing tank calculation of pressure methods for considering rib and influencing, and belong to strength of aircraft design field, including：Step 1：Fuel tank is divided into region one and region two using rib as boundary, fuel oil flows to region two by region one, and flow velocity is calculated to obtain by the fuel pressure in region two：When the plenum space volume in fuel tank area two is less than V0When, fuel tank area one and region two calculate oil pressure by an overall space region；When the plenum space volume of in fuel tank area two is more than V0When, fuel tank area one and region two calculate oil pressure by two separate space regions.The considerations of of the invention the perfect traditional wing tank computational methods of wing tank calculation of pressure method that influence of rib, the structure being calculated is more accurate, wing tank structure efficiency, the construction weight for mitigating aircraft wing can be improved, it is significant to improving structure efficiency and mitigation construction weight in airplane design.
Description
Technical field
The invention belongs to strength of aircraft design field more particularly to a kind of wing tank pressure for considering rib and influencing
Computational methods.
Background technology
Wing tank is a part for wing structure, it is made of the material identical with wing structure, and seam crossing is used anti-
The sealing compound sealing of oil.The selection of Oiltank structure material is depending on the type of aircraft and the purposes of aircraft.
When aircraft has overload n, wing tank pressure P calculating calculates as follows：P=ρ × g × h × n
Wherein, ρ is fuel density；G accelerates for gravity；H is the oil column length determined along overload n directions；N overloads for fuel tank
Coefficient.
It is the most by calculation formula as it can be seen that determining the oil column length along overload n directions in fuel pressure Traditional calculating methods
A crucial step.For being disposed with the integral wing tank of rib, if without considering influence of the rib to fuel pressure, it is calculated
Fuel pressure it is higher, higher than actual fuel pressure, structure is not fully utilized the oil tank fuel pressure for causing to calculate.
The content of the invention
It is existing for solving the object of the present invention is to provide a kind of wing tank calculation of pressure method for considering rib and influencing
Wing tank calculation of pressure method there is rib in fuel tank in the case of calculate the problem of inaccurate.
In order to achieve the above objectives, the technical solution adopted by the present invention is：A kind of wing for considering rib and being influenced on fuel tank
Fuel pressure calculates method, and the wing fuel pressure calculates method and fuel tank is divided into two regions suitable for rib, described
Wing fuel pressure, which calculates method, to be included
Step 1：Fuel states judge
Fuel tank is divided into region one and region two using rib as boundary, fuel oil flows to region two by region one, and flow velocity is by area
The fuel pressure in domain two calculates to obtain：
0.5×ρ×υ2=ρ × g × h1×n1
V0=A0×υ×t
In formula：υ is by the fuel flow rate of rib, n under fuel pressure effect1And h1It is rib for fuel oil free flow
The oil column length of overload and overload direction at position；
V0The fuel bulk in region two, A are flowed to from fuel tank area one for fuel oil in duration of overload t0Be rib for combustion
The area of oily free flow；
When the plenum space volume in fuel tank area two is less than V0When, an overall space is pressed in fuel tank area one and region two
Region calculates oil pressure；
When the plenum space volume of in fuel tank area two is more than V0When, fuel tank area one and region two are independent empty by two
Between region calculate oil pressure；
Step 2：When calculating oil pressure by an overall space region, the lower fuel pressure P=ρ of overload n effects are calculated as follows
×g×h×n
Oil column length h is that direction fuel oil column length is overloaded on the edge influenced without considering rib in formula；
Step 3：When calculating oil pressure by two separate space regions, using rib as boundary, subregion is calculated as follows overload and makees
With lower fuel pressure:
Region one：P1=ρ × g × h1×n
Region two：P2=ρ × g × h2×n
When fuel tank is full oily, rib both sides fuel pressure is equal, and rib is not subject to fuel pressure at this time；During half oil of fuel tank, the wing
The fuel pressure that rib is born is both sides fuel pressure P1And P2Difference.
Further, fuel oil is set when fuel tank is full oily with incompressible characteristic.
Further, in step 3, if the fuel pressure P in region one1More than the fuel pressure P in region one2, then rib hold
The Impact direction received is directed toward region two, pressure value P=P by region one1-P2。
Further, in step 3, if the fuel pressure P in region one1Less than the fuel pressure P in region one2, then rib hold
The Impact direction received is directed toward region one, pressure value P=P by region two2-P1。
The perfect traditional wing tank calculating side of wing tank calculation of pressure method that influences of the considerations of of the invention rib
Method, the structure being calculated is more accurate, can improve wing tank structure efficiency, the construction weight for mitigating aircraft wing,
It is significant to improving structure efficiency and mitigation construction weight in airplane design.
Description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the implementation for meeting the present invention
Example, and the principle for explaining the present invention together with specification.
Fig. 1 is the fuel tank schematic diagram of one embodiment of the invention.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
Fuel tank schematic diagram as shown in Figure 1, wing tank calculation of pressure method at present, among fuel tank without rib
Fuel tank is more applicable in and result is accurate；There is the wing tank of rib for fuel tank intermediate arrangement, obtained result of calculation is too conservative,
Structure efficiency cannot be fully utilized.For this purpose, the present invention proposes a kind of wing tank pressure gauge for considering rib and influencing
Calculation method, for solving above-mentioned enquirement.
The considerations of of the invention rib influence wing tank calculation of pressure method specifically include：
First：First, wing tank calculation of pressure is divided into fuel tank full of fuel oil (referred to as full oil) and underfill fuel oil
(referred to as half oil) two kinds of situations consider respectively.Wing tank is full oily and half oil is judged by method：
0.5×ρ×υ2=ρ × g × h1×n1
V0=A0×υ×t
In formula：υ is by the fuel flow rate of rib, n under fuel pressure effect1And h1It is rib for fuel oil free flow
The oil column length of overload and overload direction at position；V0For fuel oil in duration of overload t region is flowed to from fuel tank area one
Two fuel bulk, A0It is rib for the area of fuel oil free flow.
Using rib as boundary, it is region one that overload, which generates the smaller fuel tank area of fuel pressure, and pressure is larger for region two.
When the plenum space volume in fuel tank area two is less than V0When, an overall space is pressed in fuel tank area one and region two
Region calculates oil pressure (expiring oil condition)；When the plenum space volume of in fuel tank area two is more than V0When, one He of fuel tank area
Region two calculates oil pressure (i.e. half oil condition) by two separate space regions.
Second：When fuel tank is full oily, fuel tank overall space region is considered, the lower fuel pressure of overload n effects is calculated as follows：P
=ρ × g × h × n
Oil column length h is that direction fuel oil column length is overloaded on the edge influenced without considering rib in formula.
3rd：Oil pressure is calculated by two separate space regions during half oil of fuel tank, using rib as boundary, subregion is calculated as follows
The lower fuel pressure of overload effect.
For region one：P1=ρ × g × h1×n
For region two：P2=ρ × g × h2×n
h1For the oil column length in region one, h2For the oil column length in region two.
4th：The fuel pressure that rib is born, fuel tank should set fuel oil with incompressible characteristic when full oily, in this situation
Under, the fuel pressure of rib both sides is equal, and rib is not subject to fuel pressure at this time；
During half oil of fuel tank, the fuel pressure that rib is born is then the fuel pressure P of both sides1And P2Difference.
The tank pressure having in wing tank in the case of rib can be acquired by the above method.
The perfect traditional wing tank calculating side of wing tank calculation of pressure method that influences of the considerations of of the invention rib
Method, the structure being calculated is more accurate, can improve wing tank structure efficiency, the construction weight for mitigating aircraft wing,
It is significant to improving structure efficiency and mitigation construction weight in airplane design.
The above is only the optimal specific embodiment of the present invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, the change or replacement that can be readily occurred in,
It should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of the claim
Subject to enclosing.
Claims (4)
- A kind of 1. wing tank calculation of pressure method for considering rib and influencing, which is characterized in that the wing fuel pressure calculates Method is suitable for rib and fuel tank is divided into two regions, and the wing fuel pressure, which calculates method, to be includedStep 1：Fuel states judgeFuel tank is divided into region one and region two using rib as boundary, fuel oil flows to region two by region one, and flow velocity is by region two Fuel pressure calculate to obtain：0.5×ρ×υ2=ρ × g × h1×n1V0=A0×υ×tIn formula：υ is by the fuel flow rate of rib, n under fuel pressure effect1And h1It is rib for fuel oil free flow position The overload at place and the oil column length for overloading direction；V0The fuel bulk in region two, A are flowed to from fuel tank area one for fuel oil in duration of overload t0For rib for fuel oil from By the area to circulate；When the plenum space volume in fuel tank area two is less than V0When, an overall space region is pressed in fuel tank area one and region two Calculate oil pressure；When the plenum space volume of in fuel tank area two is more than V0When, Liang Ge separate spaces area is pressed in fuel tank area one and region two Domain calculates oil pressure；Step 2：When calculating oil pressure by an overall space region, the lower fuel pressure P=ρ × g of overload n effects are calculated as follows ×h×nOil column length h is that direction fuel oil column length is overloaded on the edge influenced without considering rib in formula；Step 3：When calculating oil pressure by two separate space regions, using rib as boundary, subregion is calculated as follows under overload effect Fuel pressure:Region one：P1=ρ × g × h1×nRegion two：P2=ρ × g × h2×nWhen fuel tank is full oily, rib both sides fuel pressure is equal, and rib is not subject to fuel pressure at this time；During half oil of fuel tank, rib is held The fuel pressure received is both sides fuel pressure P1And P2Difference.
- 2. the wing tank calculation of pressure method according to claim 1 for considering rib and influencing, which is characterized in that fuel tank is full Fuel oil is set when oily with incompressible characteristic.
- 3. the wing tank calculation of pressure method according to claim 1 for considering rib and influencing, which is characterized in that step 3 In, if the fuel pressure P in region one1More than the fuel pressure P in region one2, then the Impact direction that rib is born is directed toward by region one Region two, pressure value P=P1-P2。
- 4. the wing tank calculation of pressure method according to claim 1 for considering rib and influencing, which is characterized in that step 3 In, if the fuel pressure P in region one1Less than the fuel pressure P in region one2, then the Impact direction that rib is born is directed toward by region two Region one, pressure value P=P2-P1。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711172876.4A CN108100227B (en) | 2017-11-22 | 2017-11-22 | Wing oil tank pressure calculation method considering wing rib influence |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711172876.4A CN108100227B (en) | 2017-11-22 | 2017-11-22 | Wing oil tank pressure calculation method considering wing rib influence |
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| Publication Number | Publication Date |
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| CN108100227A true CN108100227A (en) | 2018-06-01 |
| CN108100227B CN108100227B (en) | 2021-01-08 |
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| CN201711172876.4A Active CN108100227B (en) | 2017-11-22 | 2017-11-22 | Wing oil tank pressure calculation method considering wing rib influence |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550676A (en) * | 2020-12-04 | 2021-03-26 | 苏州流昴飞行器技术有限公司 | Unmanned aerial vehicle stability keeps system |
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| CN201566839U (en) * | 2009-12-30 | 2010-09-01 | 陕西飞机工业（集团）有限公司 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
| RU2403179C1 (en) * | 2009-07-21 | 2010-11-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | Method for balancing fuel reserve in aircraft wing tanks during ground operation (versions) |
| FR3012419A1 (en) * | 2013-10-25 | 2015-05-01 | Herakles | METHOD AND DEVICE FOR INERTING A FUEL BODY OF AN AIRCRAFT |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Oil tank assembly oil leading devices and airplane with same |
| CN105205267A (en) * | 2015-09-24 | 2015-12-30 | 江西洪都航空工业集团有限责任公司 | Method for calculating load of wing integral fuel tank |
| US9399395B2 (en) * | 2013-03-22 | 2016-07-26 | Airbus Helicopters | Tank provided with an over-pressure valve |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
-
2017
- 2017-11-22 CN CN201711172876.4A patent/CN108100227B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2403179C1 (en) * | 2009-07-21 | 2010-11-10 | Закрытое акционерное общество "Гражданские самолеты Сухого" | Method for balancing fuel reserve in aircraft wing tanks during ground operation (versions) |
| CN201566839U (en) * | 2009-12-30 | 2010-09-01 | 陕西飞机工业（集团）有限公司 | Balancing technique configuration for fuel quantity of multiple aeroplanes |
| US9399395B2 (en) * | 2013-03-22 | 2016-07-26 | Airbus Helicopters | Tank provided with an over-pressure valve |
| FR3012419A1 (en) * | 2013-10-25 | 2015-05-01 | Herakles | METHOD AND DEVICE FOR INERTING A FUEL BODY OF AN AIRCRAFT |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Oil tank assembly oil leading devices and airplane with same |
| CN105205267A (en) * | 2015-09-24 | 2015-12-30 | 江西洪都航空工业集团有限责任公司 | Method for calculating load of wing integral fuel tank |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550676A (en) * | 2020-12-04 | 2021-03-26 | 苏州流昴飞行器技术有限公司 | Unmanned aerial vehicle stability keeps system |
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| CN108100227B (en) | 2021-01-08 |
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