CN108090248A - A kind of fuel oil in fuel tank calculation of pressure method under air maneuver state - Google Patents
A kind of fuel oil in fuel tank calculation of pressure method under air maneuver state Download PDFInfo
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- CN108090248A CN108090248A CN201711173707.2A CN201711173707A CN108090248A CN 108090248 A CN108090248 A CN 108090248A CN 201711173707 A CN201711173707 A CN 201711173707A CN 108090248 A CN108090248 A CN 108090248A
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- fuel
- aircraft
- fuel tank
- oil
- overload
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
Abstract
The present invention relates to fuel oil in fuel tank pressure Method for Accurate Calculation under a kind of air maneuver state, belong to aircraft structure strength design field, including：Step 1：(n is overloaded according to aircraft three-dimensionalx, ny, nz) when, calculate size and direction that n is overloaded in the actual synthesis of aircraft：Step 2：Aircraft fuel tank fuel oil is calculated in synthesis overload n direction oil column length h；Step 3：Calculate aircraft fuel pressure P under synthesis overload n effects：P=ρ × g × h × n.The aircraft fuel tank fuel pressure Method for Accurate Calculation of the present invention has the following advantages that：(1) consider that aircraft arbitrarily overloads, fuel tank any part fuel pressure；(2) based on traditional tank pressure computational methods, result of calculation is more accurate, can improve fuel tanker structure efficiency, mitigate aero-structure weight.
Description
Technical field
The invention belongs to fuel tanks under aircraft structure strength computing technique field more particularly to a kind of air maneuver state to fire
Oil pressure computational methods.
Background technology
Aircraft maneuver is that the flight that aircraft changes over time under state of flight (speed, height and heading) is moved
Make, the scope that flight status change is bigger, the time needed for change state is shorter, and the mobility of aircraft is better, this is
Consider one of leading indicator of military aircraft performance quality.
However when aircraft is under maneuvering condition, the fuel oil in aircraft fuel tank can generate overload so that fuel tank is held
By the additional stress in addition to fuel oil gravity in itself.
When airplane, there are three-dimensional overload (nx, ny, nz) when, traditional aircraft fuel tank fuel pressure is calculated by following
Formula Conservative estimation：P=ρ × g × (hx×nx+hy×ny+hz×nz)
In above formula：ρ is fuel density, and g accelerates for gravity, and h is the oil column length determined along overload n directions, and n is fuel tank mistake
Carry coefficient.
By calculation formula as it can be seen that the fuel pressure that fuel pressure Traditional calculating methods generate three-dimensional overload is individually counted
It calculates, then sums.In fact, when aircraft is there are during three-dimensional overload, fuel oil generates in the synthesis overloaded in three-dimensional overload direction most
Big fuel pressure.The fuel pressure that Traditional calculating methods obtain is higher, and the oil tank fuel pressure calculated is caused to be higher than actual fuel oil
Pressure, structure are not fully utilized.
The content of the invention
The object of the present invention is to provide a kind of fuel oil in fuel tank calculation of pressure method under air maneuver state, for solving mesh
Fuel tank pressure calculates the problem of more conservative under preceding maneuvering condition so that it is more accurate that fuel tank pressure calculates.
In order to achieve the above objectives, the technical solution adopted by the present invention is：Fuel oil in fuel tank pressure under a kind of air maneuver state
Power Method for Accurate Calculation, including
Step 1：(n is overloaded according to aircraft three-dimensionalx, ny, nz) when, calculate size and direction that n is overloaded in the actual synthesis of aircraft：
Step 2：Aircraft fuel tank fuel oil is calculated in synthesis overload n direction oil column length h；
Step 3：Calculate aircraft fuel pressure P under synthesis overload n effects：P=ρ × g × h × n
In above formula, ρ is fuel density, and g accelerates for gravity.
Further, when the oil column length under aircraft fuel tank overload is calculated in the computational methods of the present invention, need
It is calculated according to the geometry of fuel tank and fuel bulk.
The aircraft fuel tank fuel pressure Method for Accurate Calculation of the present invention has the following advantages that：
(1) consider that aircraft arbitrarily overloads, fuel tank any part fuel pressure；
(2) based on traditional tank pressure computational methods, result of calculation is more accurate, can improve fuel tanker structure effect
Rate mitigates aero-structure weight.
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 fuel tank pressure schematic diagram under the motor-driven overload 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.
Aircraft fuel tank pressure schematic diagram under motor-driven overload as shown in Figure 1, there are the overloads in three directions for fuel tank.
Aircraft is calculated first, and there are three-dimensional overload (nx, ny, nz) when, n sizes and direction are overloaded in the actual synthesis of aircraft；
Secondly, calculate aircraft fuel tank fuel oil and overload n direction oil column length h in synthesis, h when calculating oil column length needs root
It is calculated according to the geometry and fuel bulk of fuel tank；
The lower fuel pressure P of aircraft synthesis overload n effects is finally calculated as follows：P=ρ × g × h × n.
The aircraft fuel tank fuel pressure Method for Accurate Calculation of the present invention has the following advantages that：
(1) consider that aircraft arbitrarily overloads, fuel tank any part fuel pressure；
(2) based on traditional tank pressure computational methods, result of calculation is more accurate, can improve fuel tanker structure effect
Rate mitigates aero-structure weight.
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 (2)
- A kind of 1. fuel oil in fuel tank pressure Method for Accurate Calculation under air maneuver state, which is characterized in that the air maneuver shape Fuel oil in fuel tank pressure Method for Accurate Calculation includes under stateStep 1：(n is overloaded according to aircraft three-dimensionalx, ny, nz) when, calculate size and direction that n is overloaded in the actual synthesis of aircraft：<mrow> <mi>n</mi> <mo>=</mo> <msqrt> <mrow> <msup> <msub> <mi>n</mi> <mi>x</mi> </msub> <mn>2</mn> </msup> <mo>+</mo> <msup> <msub> <mi>n</mi> <mi>y</mi> </msub> <mn>2</mn> </msup> <mo>+</mo> <msup> <msub> <mi>n</mi> <mi>z</mi> </msub> <mn>2</mn> </msup> </mrow> </msqrt> </mrow>Step 2：Aircraft fuel tank fuel oil is calculated in synthesis overload n direction oil column length h；Step 3：Calculate aircraft fuel pressure P under synthesis overload n effects：P=ρ × g × h × nIn above formula, ρ is fuel density, and g accelerates for gravity.
- 2. fuel oil in fuel tank pressure Method for Accurate Calculation under air maneuver state according to claim 1, which is characterized in that When calculating the oil column length under aircraft fuel tank overload, it need to be calculated according to the geometry and fuel bulk of fuel tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711173707.2A CN108090248A (en) | 2017-11-22 | 2017-11-22 | A kind of fuel oil in fuel tank calculation of pressure method under air maneuver state |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711173707.2A CN108090248A (en) | 2017-11-22 | 2017-11-22 | A kind of fuel oil in fuel tank calculation of pressure method under air maneuver state |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108090248A true CN108090248A (en) | 2018-05-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711173707.2A Pending CN108090248A (en) | 2017-11-22 | 2017-11-22 | A kind of fuel oil in fuel tank calculation of pressure method under air maneuver state |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109145372A (en) * | 2018-07-17 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of hot computation modeling method of fuel tanker and its computation model |
| CN109614668A (en) * | 2018-11-23 | 2019-04-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel oil center of gravity limits method of determining range and device |
Citations (3)
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| CN101346280A (en) * | 2005-12-22 | 2009-01-14 | 空中客车英国有限公司 | Aircraft auxiliary fuel tank system and method |
| CN103775595A (en) * | 2014-02-20 | 2014-05-07 | 青岛大学 | Regenerative braking stepless transmission for vehicles |
| 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 |
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2017
- 2017-11-22 CN CN201711173707.2A patent/CN108090248A/en active Pending
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| CN101346280A (en) * | 2005-12-22 | 2009-01-14 | 空中客车英国有限公司 | Aircraft auxiliary fuel tank system and method |
| CN103775595A (en) * | 2014-02-20 | 2014-05-07 | 青岛大学 | Regenerative braking stepless transmission for vehicles |
| 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 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109145372A (en) * | 2018-07-17 | 2019-01-04 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of hot computation modeling method of fuel tanker and its computation model |
| CN109614668A (en) * | 2018-11-23 | 2019-04-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel oil center of gravity limits method of determining range and device |
| CN109614668B (en) * | 2018-11-23 | 2023-07-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and device for determining aircraft fuel center of gravity limiting range |
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Application publication date: 20180529 |
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