CN103983801A - Method for positioning virtual velocity vector symbol of head up display of airplane - Google Patents
Method for positioning virtual velocity vector symbol of head up display of airplane Download PDFInfo
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- CN103983801A CN103983801A CN201410182556.7A CN201410182556A CN103983801A CN 103983801 A CN103983801 A CN 103983801A CN 201410182556 A CN201410182556 A CN 201410182556A CN 103983801 A CN103983801 A CN 103983801A
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Abstract
The invention discloses a method for positioning and calculating a virtual velocity vector symbol of head up display of an airplane and belongs to onboard avionics systems. The method is characterized in that a predicted inertia attack angle alpha[p] obtained through inertial navigation output is read and the pitch angle of the shadow symbol is determined; an inertia sideslip angle beta [I] obtained through inertial navigation output is read, and the azimuth angle of the shadow symbol is determined; the display time of the shadow symbol is determined. According to the method, display of the virtual velocity vector symbol of the airplane is reliably and accurately positioned and calculated and the method can be coordinated with optimal attack angle frame dynamic positioning and guarantee that the airplane is landed along a standard glide slope.
Description
Technical field
The invention belongs to airborne avionics system, particularly the flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft.
Background technology
Pseudo-velocity vector symbol (also referred to as " shadow ") is presented at flat aobvious upper, and velocity symbol supports the use.Velocity symbol is driven by the inertia angle of attack and inertia yaw angle, if aerial crosswind is larger when landing, the inertia yaw angle of aircraft also can be larger, and at this moment velocity symbol will be displaced to flat aobvious edge.And best angle of attack frame is presented at flat aobvious centre, align best angle of attack frame with velocity symbol so very difficult.In order to address this problem, velocity symbol is presented at ± 2 ° within, but can bring another one problem: pilot cannot learn the real velocity reversal of aircraft.For this reason, introduce a kind of brand-new displaying symbol---pseudo-velocity vector symbol, namely " shadow ", with its replacement velocity symbol, provides aircraft real velocity reversal to pilot.
Summary of the invention
The object of the invention is: this invention provides a kind of pseudo-velocity vector symbol and shows method for calculating and locating, for aircraft landing downslide process, in the time that bias current is larger (velocity symbol is presented at ± 2 ° within, be convenient to aim at best angle of attack frame), provide aircraft real velocity reversal to pilot.Pseudo-velocity vector symbol is aimed to landing point, can control aircraft and fly to landing point, assisting in flying person successfully lands.
Technical scheme of the present invention is: the flat aobvious pseudo-velocity symbol of a kind of aircraft shows method for calculating and locating, it is characterized in that, comprises the steps:
Step 1:
Read the prediction inertia angle of attack of inertial navigation output
p, determine " shadow " symbol angle of pitch according to formula (1):
E
L＝-α
p (1)
Step 2:
Read the inertia yaw angle β of inertial navigation output
i, determine " shadow " symbol position angle according to formula (2):
A
Z＝β
I (2)
Step 3:
Determine " shadow " demonstration opportunity:
1) while " not cutting partially ", as inertia yaw angle ︱ β
iwhen 2 ° of ︱ >, show;
2) while " cutting partially ", as inertia yaw angle ︱ β
iwhen 1 ° of ︱ >, show.
Advantage of the present invention is: use the method to show and position calculating the flat aobvious pseudo-velocity symbol of aircraft, accurately and reliably, can coordinate mutually with best angle of attack frame Kinematic Positioning, guarantee that aircraft is along standard glide path landing.
Brief description of the drawings
Fig. 1 is " shadow " dimension definitions schematic diagram
Fig. 2 is that on flat aobvious picture, " " symbol shows schematic diagram to shadow
Embodiment
Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.
The first step: determine " shadow " symbol angle of pitch
If the prediction inertia angle of attack reading from inertial navigation
p=3 °
" shadow " symbol angle of pitch: E
l=-α
p=-3 °
Second step: determine " shadow " symbol position angle
If the inertia yaw angle β reading from inertial navigation
i=1 °
" shadow " symbol position angle A
z=1 °
The 3rd step: determine demonstration opportunity
Due to β
i=1 °, now " shadow " do not show.
While repeating above step, if the inertia yaw angle β reading from inertial navigation
i=3 ° of ︱ β
i2 ° of ︱ >, now show " shadow " symbol.
Claims (1)
1. the flat aobvious pseudo-velocity symbol of aircraft shows a method for calculating and locating, it is characterized in that, comprises the steps:
Step 1:
Read the prediction inertia angle of attack of inertial navigation output
p, determine " shadow " symbol angle of pitch according to formula (1):
E
L＝-α
p (1)
Step 2:
Read the inertia yaw angle β of inertial navigation output
i, determine " shadow " symbol position angle according to formula (2):
A
Z＝β
I (2)
Step 3:
Determine " shadow " demonstration opportunity:
1) while " not cutting partially ", as inertia yaw angle ︱ β
iwhen 2 ° of ︱ >, show;
2) while " cutting partially ", as inertia yaw angle ︱ β
iwhen 1 ° of ︱ >, show.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410182556.7A CN103983801B (en) | 2014-04-27 | 2014-04-27 | The flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410182556.7A CN103983801B (en) | 2014-04-27 | 2014-04-27 | The flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103983801A true CN103983801A (en) | 2014-08-13 |
| CN103983801B CN103983801B (en) | 2016-10-26 |
Family
ID=51275849
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410182556.7A Active CN103983801B (en) | 2014-04-27 | 2014-04-27 | The flat aobvious pseudo-velocity vector symbol localization method of a kind of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103983801B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111060709A (en) * | 2019-12-06 | 2020-04-24 | 江西洪都航空工业集团有限责任公司 | Speed vector indicator driving method for unmanned aerial vehicle human-in-loop head-up display |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1358755A (en) * | 1970-07-30 | 1974-07-03 | Thomson Csf | Flight parameter display instruments |
| CN101713654A (en) * | 2009-11-18 | 2010-05-26 | 南京航空航天大学 | Fusing method of atmospheric attack angle and inertia attack angle in transonic flight stage |
| EP2196810A1 (en) * | 2008-12-11 | 2010-06-16 | Alenia Aeronautica S.P.A. | A method of estimating an angle of attack and an angle of sideslip of an aircraft |
| US20130317691A1 (en) * | 2012-03-21 | 2013-11-28 | Airbus Operations (Sas) | Method of verifying the consistency of values given by an incidence probe of an aircraft |
| CN103693203A (en) * | 2013-12-01 | 2014-04-02 | 太原航空仪表有限公司 | Small-size self-balancing type weather vane |
-
2014
- 2014-04-27 CN CN201410182556.7A patent/CN103983801B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1358755A (en) * | 1970-07-30 | 1974-07-03 | Thomson Csf | Flight parameter display instruments |
| EP2196810A1 (en) * | 2008-12-11 | 2010-06-16 | Alenia Aeronautica S.P.A. | A method of estimating an angle of attack and an angle of sideslip of an aircraft |
| CN101713654A (en) * | 2009-11-18 | 2010-05-26 | 南京航空航天大学 | Fusing method of atmospheric attack angle and inertia attack angle in transonic flight stage |
| US20130317691A1 (en) * | 2012-03-21 | 2013-11-28 | Airbus Operations (Sas) | Method of verifying the consistency of values given by an incidence probe of an aircraft |
| CN103693203A (en) * | 2013-12-01 | 2014-04-02 | 太原航空仪表有限公司 | Small-size self-balancing type weather vane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111060709A (en) * | 2019-12-06 | 2020-04-24 | 江西洪都航空工业集团有限责任公司 | Speed vector indicator driving method for unmanned aerial vehicle human-in-loop head-up display |
| CN111060709B (en) * | 2019-12-06 | 2021-10-15 | 江西洪都航空工业集团有限责任公司 | Speed vector indicator driving method for unmanned aerial vehicle human-in-loop head-up display |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103983801B (en) | 2016-10-26 |
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Effective date of registration: 20201028 Address after: Building B, building 28, Jiangsu information service industry base, Guangling New Town, Yangzhou City, Jiangsu Province, 225002 Patentee after: Shenyang Aircraft Design Institute Yangzhou Collaborative Innovation Research Institute Co., Ltd Address before: Thavorn street in Huanggu District of Shenyang city of Liaoning Province, No. 40 110035 Patentee before: SHENYANG AIRCRAFT DESIGN INSTITUTE, AVIATION INDUSTRY CORPORATION OF CHINA |
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