CN104890897A - Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground - Google Patents
Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground Download PDFInfo
- Publication number
- CN104890897A CN104890897A CN201510277496.1A CN201510277496A CN104890897A CN 104890897 A CN104890897 A CN 104890897A CN 201510277496 A CN201510277496 A CN 201510277496A CN 104890897 A CN104890897 A CN 104890897A
- Authority
- CN
- China
- Prior art keywords
- test
- aircraft
- angle
- surface angle
- oil surface
- 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
Abstract
The invention provides a test method for simulating an oil surface angle of a fuel oil of an aircraft during dynamic flight on the ground. The test method comprises the following steps: firstly fixing a fuel oil system of the aircraft to a test table, wherein the test table can rotate around a Z axis and an X axis; then according to overloading parameters given by overall design staffs of the aircraft during the flight, converting the given overloading parameters into an oil surface angle theta and an oil surface angle gamma through formulas; finally inputting the oil surface angle theta and the oil surface angle gamma into a computer, so that the test table is controlled to rotate by the computer during a dynamic flight test according to the corresponding oil surface angle so as complete the test. The test method disclosed by the invention is used for simulating the oil surface angle of the fuel oil system of the aircraft instead of simulating a flight attitude angle, so that the conditions of the dynamic flight are more really simulated, and besides, the maneuverability is also very high.
Description
Technical field
The present invention relates to a kind of test method of the fuel oil surface angle when ground simulation aircraft dynamic flying, belong to Ground modelling technique field.
Background technology
According to the regulation of aircraft industry standard (HB7169-1995), aircraft fuel system, in development process, must carry out ground simulation test.Ground simulation test is divided into envelope test and dynamic flying analogue test.Envelope test is mainly for detection of the principle correctness of each system, and whether dynamic flying analogue test meets requirement in aircraft flight envelope curve for detecting each system.
Envelope test is fairly simple, generally only needs to build static test stand.Dynamic flight test needs to build the dynamic test stand with rotary freedom, and on test cell, build the fuel oil system of a complete set of 1:1.The rotational angle of test cell and confession oil transportation flow are by computer controlled.The technical barrier of dynamic flight test be how real simulated aircraft dynamic flying time fuel level and the real angle on ground, computer modeling real-time Control experiment platform rotational angle can be used.Current known test method is generally using attitude angle during aircraft flight as control angle, namely during aircraft flight and the attitude angle of earth axes.This test method has certain accuracy when the little overload flight of aircraft, but when aircraft is in large overload state of flight, carries out dynamic analog test have very large error with attitude angle now.
Summary of the invention
For solving the problem, the present invention proposes a kind of test method of the fuel oil surface angle when ground simulation aircraft dynamic flying, in the theoretical basis of this method establishment level change after liquid is transshipped.
The present invention is realized by following technical proposals, and a kind of test method of the fuel oil surface angle when ground simulation aircraft dynamic flying, is characterized in that:
First aircraft fuel system is fixed on test cell, test cell can rotate around Z axis and X-axis;
Overload parameters when then providing aircraft flight according to preliminary design of aircraft personnel, becomes pasta angle θ and γ by formula scales; Namely θ, γ angle can be used as test cell rotational angle during ground simulation dynamic flying;
Finally one-tenth pasta angle θ and γ is inputted computing machine, the test cell that make to computerized control during test during dynamic flying can complete test by corresponding pasta angle angular turn.
Described pasta angle refers to that fuel oil in fuel tanker transships the relative angle of pasta and airframe coordinate axle in the fuel tank that causes by flight.The pasta angle of simulated aircraft fuel oil system of the present invention is no longer simulated flight attitude angle.
The present invention has failure-free theoretical foundation, facts have proved that accuracy is very high, simulates the state of dynamic flying more really, and operability is also very high simultaneously.
Accompanying drawing explanation
Fig. 1 body axis system schematic diagram;
Fig. 2 is simulation dynamic flight test platform schematic diagram.
Detailed description of the invention
As depicted in figs. 1 and 2, first aircraft fuel system 2 is fixed on test cell 1, test cell 1 can rotate around Z axis and X-axis; Aircraft can be simplified to the rotation of test cell 1 around Z axis (housing) and X-axis (inside casing) along moving in X-axis and Z-direction; Aircraft only has influence on around Z axis and the size with X-axis rotational angle along moving in Y direction; Aircraft is very little to aircraft fuel system 2 work influence time (as aircraft approaching side is sliding) when Y-axis is rotated, moreover in practical flight, is again avoid producing this to rotate as far as possible, can carries out this simulation.So, as long as test cell 1 have the groundwork situation that the two-freedom rotated around Z axis (housing) and X-axis (inside casing) just can meet simulated aircraft awing fuel oil system 2.
Overload parameters when providing aircraft flight by preliminary design of aircraft personnel, then becomes pasta angle by formula scales.
Its computing formula is pressed:
Nx (J)=Nx (F)×Cosα+Ny (F)×Sinα
Ny(J)=-Nx(F)×Sinα×Cosβ＋Ny(F)×Cosα×Cosβ＋Nz(F)×Sinβ
Nz(J)=Nz(F)×Sinα×Sinβ－Ny(F)×Cosα×Sinβ＋Nz(F)×Cosβ
θ（J）＝（arctg.Nx(J)/Ny(J)）/PI
γ（J）＝（arctg.Nz(J)/Ny(J)）/PI
PI=3.141593/180
In formula:
Nx (J), Ny (J), Nz (J) are arbor all directions overload factor
Nx (F), Ny (F), Nz (F) are wind axis (speed) all directions overload factor
α, β are pitching and the angle of heel (°) of aircraft flight attitude
θ, γ are pasta angle (°)
Namely θ, γ angle now can be used as test cell rotational angle during ground simulation dynamic flying.
Finally by the numerical value of pasta angle θ and γ input computing machine, rotated by computer controlled test cell can complete test by respective angles.
Claims (2)
1. the test method at fuel oil surface angle when ground simulation aircraft dynamic flying, is characterized in that:
First aircraft fuel system is fixed on test cell, test cell can rotate around Z axis and X-axis;
Overload parameters when then providing aircraft flight according to preliminary design of aircraft personnel, becomes pasta angle θ and γ by formula scales;
Finally one-tenth pasta angle θ and γ is inputted computing machine, the test cell that make to computerized control during test during dynamic flying can complete test by corresponding pasta angle angular turn.
2. the test method at a kind of fuel oil surface angle when ground simulation aircraft dynamic flying according to claim 1, is characterized in that: pasta angle is by following formulae discovery:
Nx (J)=Nx (F)×Cosα+Ny (F)×Sinα
Ny(J)=-Nx(F)×Sinα×Cosβ＋Ny(F)×Cosα×Cosβ＋Nz(F)×Sinβ
Nz(J)=Nz(F)×Sinα×Sinβ－Ny(F)×Cosα×Sinβ＋Nz(F)×Cosβ
θ（J）＝（arctg.Nx(J)/Ny(J)）/PI
γ（J）＝（arctg.Nz(J)/Ny(J)）/PI
PI=3.141593/180
In formula:
Nx (J), Ny (J), Nz (J) are arbor all directions overload factor;
Nx (F), Ny (F), Nz (F) are wind axis all directions overload factor;
α, β are pitching and the angle of heel of aircraft flight attitude;
θ, γ are pasta angle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510277496.1A CN104890897A (en) | 2015-05-28 | 2015-05-28 | Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510277496.1A CN104890897A (en) | 2015-05-28 | 2015-05-28 | Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104890897A true CN104890897A (en) | 2015-09-09 |
Family
ID=54023966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510277496.1A Pending CN104890897A (en) | 2015-05-28 | 2015-05-28 | Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104890897A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105947231A (en) * | 2016-05-31 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Method for designing emergency fuel surface of plane pressure refueling system |
| CN106628244A (en) * | 2016-09-19 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Ground flight control test device and method |
| CN107273557A (en) * | 2016-04-06 | 2017-10-20 | 哈尔滨飞机工业集团有限责任公司 | A kind of unavailable fuel oil test method of high wing airplane |
| CN110895201A (en) * | 2019-12-04 | 2020-03-20 | 中国直升机设计研究所 | Helicopter fuel system normal overload ground simulation device and method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030061876A1 (en) * | 2001-10-02 | 2003-04-03 | Smiths Group Plc | Acoustic fluid-gauging system |
| CN104296829A (en) * | 2014-09-30 | 2015-01-21 | 四川泛华航空仪表电器有限公司 | Body axis system based oil level measuring method |
-
2015
- 2015-05-28 CN CN201510277496.1A patent/CN104890897A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030061876A1 (en) * | 2001-10-02 | 2003-04-03 | Smiths Group Plc | Acoustic fluid-gauging system |
| CN104296829A (en) * | 2014-09-30 | 2015-01-21 | 四川泛华航空仪表电器有限公司 | Body axis system based oil level measuring method |
Non-Patent Citations (1)
| Title |
|---|
| 杨振祥等: "直升机燃油系统地面模拟试验中油面角的计算", 《直升机技术》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107273557A (en) * | 2016-04-06 | 2017-10-20 | 哈尔滨飞机工业集团有限责任公司 | A kind of unavailable fuel oil test method of high wing airplane |
| CN107273557B (en) * | 2016-04-06 | 2020-08-11 | 哈尔滨飞机工业集团有限责任公司 | Method for testing unavailable fuel oil of upper single-wing aircraft |
| CN105947231A (en) * | 2016-05-31 | 2016-09-21 | 中国航空工业集团公司西安飞机设计研究所 | Method for designing emergency fuel surface of plane pressure refueling system |
| CN105947231B (en) * | 2016-05-31 | 2018-04-13 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Airplane Pressure Fueling System is met an urgent need pasta design method |
| CN106628244A (en) * | 2016-09-19 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Ground flight control test device and method |
| CN110895201A (en) * | 2019-12-04 | 2020-03-20 | 中国直升机设计研究所 | Helicopter fuel system normal overload ground simulation device and method |
| CN110895201B (en) * | 2019-12-04 | 2021-07-09 | 中国直升机设计研究所 | Helicopter fuel system normal overload ground simulation device and method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101794523B (en) | Aircraft hardware-in-the-loop simulation device | |
| CN102928846B (en) | Extreme-low-altitude laser radar digital terrain mapping system and extreme-low-altitude laser radar digital terrain mapping method of small-sized unmanned helicopter | |
| CN104890897A (en) | Test method for simulating oil surface angle of fuel oil of aircraft during dynamic flight on ground | |
| CN106933104A (en) | A kind of quadrotor attitude based on DIC PID and the mixing control method of position | |
| CN110471313B (en) | Flight simulation subsystem of simulation aircraft | |
| CN104792347B (en) | Indoor simulation method for space target optical characteristic actual measurement conditions | |
| CN105270650B (en) | A kind of six degree of freedom UAV Attitude controls test device | |
| CN108204879B (en) | A kind of measuring method and system of rotary inertia | |
| CN105270639B (en) | A kind of UAV Attitude control test device | |
| CN104155538A (en) | Comprehensive experiment testing system for small satellite antenna | |
| CN105242679A (en) | Method for designing control system of four rotor aircraft | |
| CN103673976A (en) | Method and system for converting and unifying composite type precision measuring coordinate system | |
| CN102323759B (en) | Parafoil autonomous homing semi-physical simulation system | |
| CN112541225B (en) | Virtual-real combined simulation method for rocket recovery large-attitude overturning | |
| CN103868648A (en) | Barycenter measuring method for three-axis air floatation simulation experiment platform | |
| CN104102216A (en) | Small satellite control system simulation and test integration system based on process and method thereof | |
| CN103737433A (en) | Composite type precision measurement method for large components | |
| CN109446742A (en) | Semisubmersible drilling platform pipe processing equipment grab pipe machine Dynamics Simulation method | |
| CN104536448A (en) | Backstepping based control method for unmanned-plane attitude system | |
| CN105241427A (en) | Single-camera vision measurement method using concentric circle target for measuring position posture and rotating angle of object | |
| CN106896738A (en) | A kind of various dimensions quadrotor gesture stability Simulation Experimental Platform | |
| CN103759922B (en) | A kind of space remote sensor scan mirror pointing accuracy measuring method | |
| CN103033209B (en) | Three-dimensional motion testing device | |
| CN106707793A (en) | Helicopter semi-physical simulation test system | |
| CN105270640A (en) | Attitude control test device with external frame, for unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150909 |