CN104986345B - Additional ruler method in flight test - Google Patents
Additional ruler method in flight test Download PDFInfo
- Publication number
- CN104986345B CN104986345B CN201510305327.4A CN201510305327A CN104986345B CN 104986345 B CN104986345 B CN 104986345B CN 201510305327 A CN201510305327 A CN 201510305327A CN 104986345 B CN104986345 B CN 104986345B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- flight test
- adhesive tape
- scale
- additional
- 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.)
- Active
Links
Abstract
Additional ruler method in flight test of the present invention, belongs to flight test technology field.When aircraft power and configuration determine, the whole process of operating aircraft is the change that aircraft occurs attitude first, and the aerodynamic force then acting against on aircraft changes, and then air speed changes.That is in the case that power and configuration determine, pilot by being accurately controlled and can keep aspect to reach the purpose being accurately controlled and keeping air speed to aircraft.But the fortune comprehensive aobvious posture pointing accuracy of 12F aircraft is excessively coarse, pilot cannot realize the accurate holding of aspect.For the problems referred to above, devise " additional scale ", in order to improve the comprehensive aobvious system pointing accuracy of aircraft, the method effectively raises take a flight test quality and the efficiency of taking a flight test that pitot static calibrations are taken a flight test.
Description
Technical field
Additional ruler method in flight test of the present invention, belongs to flight test technology field.
Background technology
It is desirable to pilot is accurately controlled and keeps air speed in fortune 12F aircraft airspeed calibration is taken a flight test.In conventional flight
In test, pilot's Main Basiss air speed indicates and to carry out control and the holding of air speed, the efficiency of actually this maneuverability pattern
Not high, test pilot will possess higher driving technology simultaneously, taller degree concentrates one's energy to can be only achieved requirement.
Content of the invention
The purpose of invention：The present invention keeps precision, mitigates test pilot stress mainly for improving air speed.
The technical scheme of invention：Additional ruler method in flight test, the method adopts following steps：
The first step, is accurately measured to the pitch attitude indicating graduation on aircraft, is then made corresponding high precision electro
Sub- version scale；
Second step, is designed to improve the additional scale of the comprehensive aobvious system pointing accuracy electronic edition of aircraft；
3rd step, additional for electronic edition scale is printed upon on A4 blank sheet of paper, smooth stickup transparent adhesive tape on the scale printing
Band；
4th step, after adhesive tape cements, washes the blank sheet of paper on adhesive tape off with clear water, and at this moment, adhesive tape has become can paste saturating
Bright scale, the adhesive tape after drying still has enough stickups, now just can be affixed to the comprehensive aobvious enterprising enforcement of aircraft
With.
Advantages of the present invention：The method effectively raises take a flight test quality and the efficiency of taking a flight test that pitot static calibrations are taken a flight test.Meanwhile,
This skill is also generalized to climbing performance etc. to be needed to keep the taking a flight test in project of air speed.In addition, only need to slightly change, it is fabricated to accurately
Indicate the transparent scale at inclination angle, just can be used for needing in the flight test subject accurately keeping inclination angle, such as minimum control speed, machine
Dynamic in-flight steering force of elevator etc. is taken a flight test, and has same lifting effect.In fortune 12F aircraft certification evidence obtaining is taken a flight test, should
Invention saving cost of taking a flight test exceedes million, greatly shortens the cycle of taking a flight test.
Brief description
The attitude of Fig. 1 aircraft shows (normal)
The attitude that Fig. 2 transports 12F aircraft shows (angle of pitch " additional scale ")
Specific embodiment
The principle of the present invention：When aircraft power and configuration determine, the whole process of operating aircraft is that aircraft occurs first
The change of attitude, the aerodynamic force then acting against on aircraft changes, and then air speed changes.That is aircraft is in work(
In the case that rate and configuration determine, pilot can by be accurately controlled and keep aspect reach be accurately controlled and
Keep the purpose of air speed.But the fortune comprehensive aobvious posture pointing accuracy of 12F aircraft is excessively coarse, pilot cannot realize aircraft appearance
The accurate holding of state.For the problems referred to above, devise " additional scale ", in order to improve the comprehensive aobvious system pointing accuracy of aircraft,
With reference to Figure of description, the present invention is described in detail.
Additional ruler method in flight test, the method adopts following steps：
The first step, is accurately measured to the pitch attitude indicating graduation on aircraft, is then made corresponding high precision electro
Sub- version scale；
Second step, is designed to improve the additional scale of the comprehensive aobvious system pointing accuracy electronic edition of aircraft；
3rd step, additional for electronic edition scale is printed upon on A4 blank sheet of paper, smooth stickup transparent adhesive tape on the scale printing
Band；
4th step, after adhesive tape cements, washes the blank sheet of paper on adhesive tape off with clear water, and at this moment, adhesive tape has become can paste saturating
Bright scale, the adhesive tape after drying still has enough stickups, now just can be affixed to the comprehensive aobvious enterprising enforcement of aircraft
With.
Fig. 1 and Fig. 2 is respectively the design sketch after transporting the 12F aircraft not additional scale of comprehensive aobvious system and additional scale, can be very
Significantly find out, during additional scale aircraft comprehensive aobvious on pitch attitude indicate 10 ° within precision be 2.5 °, 10 ° are in addition
Precision is 5 °, and this is unfavorable for the precise control of aspect and keeps (particularly disadvantageous in the case of High Angle of Attack).
Claims (1)
1. the additional ruler method in flight test is it is characterised in that the method adopts following steps：
The first step, is accurately measured to the pitch attitude indicating graduation on aircraft, then makes corresponding high-precision electronic version
Scale；
Second step, is designed to improve the additional scale of the comprehensive aobvious system pointing accuracy electronic edition of aircraft；
3rd step, additional for electronic edition scale is printed upon on A4 blank sheet of paper, smooth stickup adhesive tape on the scale printing；
4th step, after adhesive tape cements, washes the blank sheet of paper on adhesive tape off with clear water, and at this moment, adhesive tape has become permissible
The transparent scale pasted, the adhesive tape after drying still has enough stickups, now just can be by described adhesive tape
Be pasted onto aircraft comprehensive aobvious on employed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510305327.4A CN104986345B (en) | 2015-06-05 | 2015-06-05 | Additional ruler method in flight test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510305327.4A CN104986345B (en) | 2015-06-05 | 2015-06-05 | Additional ruler method in flight test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104986345A CN104986345A (en) | 2015-10-21 |
| CN104986345B true CN104986345B (en) | 2017-03-01 |
Family
ID=54298278
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510305327.4A Active CN104986345B (en) | 2015-06-05 | 2015-06-05 | Additional ruler method in flight test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104986345B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018058311A1 (en) * | 2016-09-27 | 2018-04-05 | 深圳市大疆创新科技有限公司 | Control method, control device, and electronic device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1050848A (en) * | 1989-10-11 | 1991-04-24 | 徐朝九 | Drawing rule additional unit |
| CN103389732A (en) * | 2012-05-11 | 2013-11-13 | 空中客车运营简化股份公司 | Piloting control method of aircraft |
| CN103708039A (en) * | 2012-10-08 | 2014-04-09 | 空中客车运营简化股份公司 | Method and device for displaying flight parameters on an aircraft |
| CN103847971A (en) * | 2012-11-30 | 2014-06-11 | 空中客车股份有限公司 | Assistance with piloting of aircraft in stall |
| CN104281149A (en) * | 2013-07-12 | 2015-01-14 | 空中客车运营简化股份公司 | Method and device for displaying in real time a pitch instruction on an aircraft during manual piloting |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008036063A2 (en) * | 2005-06-02 | 2008-03-27 | L-3 Communications Avionics Systems, Inc. | Aircraft avionic system having a pilot user interface with context dependent input devices |
-
2015
- 2015-06-05 CN CN201510305327.4A patent/CN104986345B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1050848A (en) * | 1989-10-11 | 1991-04-24 | 徐朝九 | Drawing rule additional unit |
| CN103389732A (en) * | 2012-05-11 | 2013-11-13 | 空中客车运营简化股份公司 | Piloting control method of aircraft |
| CN103708039A (en) * | 2012-10-08 | 2014-04-09 | 空中客车运营简化股份公司 | Method and device for displaying flight parameters on an aircraft |
| CN103847971A (en) * | 2012-11-30 | 2014-06-11 | 空中客车股份有限公司 | Assistance with piloting of aircraft in stall |
| CN104281149A (en) * | 2013-07-12 | 2015-01-14 | 空中客车运营简化股份公司 | Method and device for displaying in real time a pitch instruction on an aircraft during manual piloting |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104986345A (en) | 2015-10-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102680201B (en) | Buffeting wind tunnel testing method based on video measurement | |
| CN102941925B (en) | Elastic correction method of airplane lifting resistance aerodynamic characteristics | |
| CN112683446B (en) | Real-time center-of-gravity position estimation method for airplane | |
| CN104986345B (en) | Additional ruler method in flight test | |
| CN105628325A (en) | Real-time high-precision acquiring method for conical surface pneumatic pressure field | |
| CN103885453B (en) | Wide-angle is marched into the arena performance improvement and optimization | |
| CN103693203B (en) | Small-sized self-balance formula weathercock | |
| CN101881971B (en) | Method and device for controlling flight state of micro unmanned rotary wing aircraft | |
| CN105424267A (en) | Probe used for total pressure measurement of rotorcraft | |
| CN110414110B (en) | Airplane stress simulation method used in flight stall state | |
| US20150082634A1 (en) | Method and apparatus for rotor blade balance | |
| CN205246271U (en) | A probe for gyroplane total pressure measurement | |
| CN113525711B (en) | Method for identifying aerodynamic focus of aircraft through flight test | |
| CN217456388U (en) | Atmospheric data system for flying wing type airplane | |
| CN106372307B (en) | Civil aircraft airflow angle estimation method based on pneumatic model | |
| CN205300888U (en) | A test model for measuring rudder face hinge moment | |
| CN110160737B (en) | Elastic pneumatic data accurate acquisition method based on engineering surface element method | |
| CN109229368A (en) | Hidden autonomous flight miniature drone | |
| CN113094953B (en) | Finite element analysis method for hinge moment balance with wing deformation | |
| CN111717412B (en) | Flexible missile wing skin deformation load testing device | |
| CN106932164A (en) | A kind of aerodynamic data modification method based on aerodynamic derivative identification result | |
| Oehler | Measuring apparent flow vector on a flexible wing kite | |
| Spearman et al. | Longitudinal Stability and Control Characteristics at Mach Numbers of 1.41 and 2.01 of a 67 Degree Swept-wing Airplane Configuration with Canard Control Surfaces | |
| CN117892648A (en) | Method for calculating lateral wind resistance speed of conveyor | |
| CN106705948A (en) | Data communication structure for angular speed of flexible gyro system |
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 |