CN113525711B - Method for identifying aerodynamic focus of aircraft through flight test - Google Patents
Method for identifying aerodynamic focus of aircraft through flight test Download PDFInfo
- Publication number
- CN113525711B CN113525711B CN202110648124.0A CN202110648124A CN113525711B CN 113525711 B CN113525711 B CN 113525711B CN 202110648124 A CN202110648124 A CN 202110648124A CN 113525711 B CN113525711 B CN 113525711B
- Authority
- CN
- China
- Prior art keywords
- aircraft
- gravity
- center
- elevator
- deflection angle
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000005484 gravity Effects 0.000 claims abstract description 72
- 238000013016 damping Methods 0.000 claims description 4
- 238000005259 measurement Methods 0.000 description 8
- 230000001133 acceleration Effects 0.000 description 3
- IAZDPXIOMUYVGZ-UHFFFAOYSA-N Dimethylsulphoxide Chemical compound CS(C)=O IAZDPXIOMUYVGZ-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000012797 qualification Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- 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
- B64F5/60—Testing or inspecting aircraft components or systems
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Navigation (AREA)
Abstract
The invention discloses a method for identifying an aerodynamic focus of an aircraft through a flight test, which comprises the following steps: measuring the weight of the aircraft; a joint debugging test system; respectively obtaining front gravity center data and rear gravity center data required for identifying the aerodynamic focus of the aircraft through a front gravity center flight test and a rear gravity center flight test; and identifying the pneumatic focus of the airplane by adopting a formula. The method for identifying the pneumatic focus of the airplane is simple and reliable, can accurately identify the relative position of the pneumatic focus, further guides the front and rear limiting position of the center of gravity of the airplane, and plays a key role in structural configuration of the airplane.
Description
Technical Field
The invention relates to the field of aviation, and particularly provides a method for identifying an aerodynamic focus of an aircraft through aerial flat flight and pull-up flight tests.
Background
For a static aircraft, the relative position between the aerodynamic focus and the center of gravity directly affects the aircraft's flight performance. Specifically, the closer the relative position of the two is, the smaller the stability margin is, so that the stability performance of the body is worsened, and the flight safety is seriously affected; otherwise, if the relative position of the two is far, the stability margin is larger, so that the following performance of the aircraft is poor, the aerodynamic load is increased, the trim resistance is increased, and the cruising economy of the aircraft is influenced.
At present, the pneumatic focus of an airplane is obtained through wind tunnel test data identification, a model of a wind tunnel test is a rigid body, the deformation is extremely small in the test process, the obtained focus is the focus of the rigid body airplane, the airplane in flight is an elastomer, the airplane can deform in the flight process, and the position of the focus can deviate. The authenticity of the focus plays a vital role in the distribution of the center of gravity of the aircraft, and if the aircraft determines the front and rear limit positions of the center of gravity according to the rigid focus, the risk coefficient is increased, so that how to acquire the real pneumatic focus for accurately determining the front and rear limit positions of the center of gravity becomes a problem to be solved.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a method for identifying an aerodynamic focus of an aircraft by a flight test to obtain a relative position of a real aerodynamic focus.
The technical scheme provided by the invention is as follows: the method for identifying the aerodynamic focus of the aircraft through the flight test comprises the following steps:
s1: measuring the weight m of the aircraft;
s2: a joint debugging test system;
s3: the front center of gravity flight test and the rear center of gravity flight test are adopted to respectively obtain front center of gravity data and rear center of gravity data required for identifying the aerodynamic focus of the aircraft, wherein the front center of gravity data comprises the front center of gravity position of the initially selected aircraftCorresponding aircraft elevator deflection angle delta when plane flies 1 Aircraft elevator deflection angle delta corresponding to pull-up 2 And a longitudinal overload n y1 The rear gravity center data comprises the gravity center rear limit position of the initially selected airplane>Corresponding aircraft elevator deflection angle delta when plane flies 3 Aircraft elevator deflection angle delta corresponding to pull-up 4 Longitudinal overload n y2 Wherein the aircraft elevator offset angle delta is obtained 1 And aircraft elevator deflection angle delta 3 The corresponding plane flying speeds are the same;
s4: identifying an aerodynamic focus of an aircraft using equation (1)
In the formula (1), the components are as follows,for the relative position of the aerodynamic focus of the aircraft, +.>For the pitch damping derivative of an aircraft, μ=2m/ρsb A Represents the relative density of the aircraft, m represents the weight of the aircraft, ρ represents the atmospheric density, S represents the wing reference area, b A Representing the average aerodynamic chord length, delta z1 、Δδ z2 Representing elevator offset, delta z1 ＝δ 1 -δ 2 ，Δδ z2 ＝δ 3 -δ 4 ，Δn y1 、Δn y2 Represents the longitudinal overload increment delta n y1 ＝n y1 -1，Δn y2 ＝n y2 -1，/>And->Respectively representing the front limit position and the rear limit position of the gravity center of the initially selected aircraft.
Preferably, in S3, the step of obtaining front barycenter data required for identifying the aerodynamic focus of the aircraft through the front barycenter flight test specifically includes the steps of:
gravity center front limiting position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 1 ；
Front position of center of gravity of aircraft for maintaining primary selectionAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 2 Longitudinal overload n y1 。
Further preferably, in S3, the obtaining of the rear center of gravity data required for identifying the aerodynamic focus of the aircraft by the rear center of gravity flight test specifically includes the steps of:
gravity center rear limit position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 3 The plane flying speed V is the same as the plane flying speed V set in the front gravity center flight test;
aircraft center of gravity rear limit position that keeps primary electionAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 4 Longitudinal overload n y2 。
The method for identifying the aerodynamic focus of the aircraft through the flight test is simple and reliable, can accurately identify the relative position of the aerodynamic focus, further guides the front and rear limiting positions of the center of gravity of the aircraft, and plays a key role in structural configuration of the aircraft.
Drawings
The invention will be described in further detail with reference to the accompanying drawings and embodiments:
FIG. 1 is a flow chart of a method for identifying aerodynamic focus of an aircraft through a flight test provided by the present invention;
FIG. 2 is a graph showing the measurement of horizontal flight speed, elevator deflection angle and longitudinal overload for a RX4E four-seat electric aircraft in a front center of gravity flight test;
fig. 3 is a graph showing the measurement of the fly speed, elevator deflection angle and longitudinal overload of an RX4E four-seat electric aircraft during fly-flat and pull-up in a post center of gravity flight test.
Detailed Description
The invention will be further explained below in connection with specific embodiments, but is not limited to the invention.
As shown in fig. 1, the present invention provides a method for identifying an aerodynamic focus of an aircraft through a flight test, comprising the steps of:
s1: the weight m of the aircraft is measured:
before the aircraft is subjected to the flight test, in order to determine the technical state in the air flight test, the weight of the aircraft is actually measured on the ground, and the used instruments and equipment for measurement are required to be within the validity period of qualification verification and have qualification marks, and the weighing precision is not lower than: the range of the weighed weight is about 2/3 of the maximum measuring range;
s2: a joint debugging test system;
the test system comprises a flight parameter recorder, an airborne data acquisition system, a ground data processing system and a ground monitoring system, and specifically comprises: located on board: RXP 100 data record appearance, GPS antenna, voltage current transducer, absolute value formula rotary encoder, rotational speed sensor, airspeed, data transmission antenna, temperature and pole force transducer etc.. Located on the ground: GCS ground station, dual-frenquency double star antenna, data transmission antenna. The RXAP100 data recorder integrates a high-precision IMU combination module, a high-precision dynamic-static pressure sensor, a high-precision magnetic sensor and a high-precision differential GPS positioning module. The speed measurement accuracy error is not more than 0.05kts, the longitudinal overload measurement accuracy error is not more than 0.2%, and the rudder deflection angle measurement error is not more than 0.2%;
s3: the front center of gravity flight test and the rear center of gravity flight test are adopted to respectively obtain front center of gravity data and rear center of gravity data required for identifying the aerodynamic focus of the aircraft, wherein the front center of gravity data comprises the front center of gravity position of the initially selected aircraftCorresponding aircraft elevator deflection angle delta when plane flies 1 Aircraft elevator deflection angle delta corresponding to pull-up 2 And a longitudinal overload n y1 The rear gravity center data comprises the gravity center rear limit position of the initially selected airplane>Corresponding aircraft elevator deflection angle delta when plane flies 3 Aircraft elevator deflection angle delta corresponding to pull-up 4 Longitudinal overload n y2 Wherein the aircraft elevator offset angle delta is obtained 1 And aircraft elevator deflection angle delta 3 The corresponding plane flying speeds are the same;
the method for acquiring the front gravity center data required for identifying the aerodynamic focus of the airplane through the front gravity center flight test specifically comprises the following steps of:
gravity center front limiting position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 1 ；
Front position of center of gravity of aircraft for maintaining primary selectionAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 2 Longitudinal overload n y1 ；
The method for acquiring the rear gravity center data required for identifying the aerodynamic focus of the aircraft through the rear gravity center flight test specifically comprises the following steps of:
gravity center rear limit position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 3 The plane flying speed V is the same as the plane flying speed V set in the front gravity center flight test;
aircraft center of gravity rear limit position that keeps primary electionAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 4 Longitudinal overload n y2 ；
S4: identifying an aerodynamic focus of an aircraft using equation (1)
In the formula (1), the components are as follows,for the relative position of the aerodynamic focus of the aircraft, +.>For the pitch damping derivative of an aircraft, μ=2m/ρsb A Represents the relative density of the aircraft, m represents the weight of the aircraft, ρ represents the atmospheric density, S represents the wing reference area, b A Representing the average aerodynamic chord length, delta z1 、Δδ z2 Representing elevator offset, delta z1 ＝δ 2 -δ 1 ，Δδ z2 ＝δ 4 -δ 3 ，Δn y1 、Δn y2 Represents the longitudinal overload increment delta n y1 ＝n y1 -1，Δn y2 ＝n y2 -1，/>And->Respectively representing the front limit position and the rear limit position of the gravity center of the initially selected aircraft.
The derivation of equation (1) is given below:
simultaneous equations (2) to (7) to obtain equation (8)
μ＝2m/ρSb A (5)
Δc y ＝Δn y gc ypf ＝(n y -1)gc ypf (6)
And solving the equations from the simultaneous equations (2) to (7) to obtain:
in the formulas (2) to (8),for the static margin Δc y Representing lift coefficientIncrement (S)/(S)>Indicating elevator efficiency, delta z Representing elevator offset value,/->Representing the pitch damping derivative of an aircraft,>represents the dimensionless pitch rate, b A The average aerodynamic chord length of the aircraft is represented by V, the set aircraft flat flying speed is represented by g, the gravitational acceleration is represented by n y Indicating a pull-up longitudinal overload, < >>Representing the position of the centre of gravity of the aircraft->Represents the relative position of the aerodynamic focus of the aircraft, m represents the weight of the aircraft, S represents the wing reference area, ρ represents the atmospheric density, Δn y Indicating the longitudinal overload increment c ypf The lift coefficient of an aircraft during flat flight is shown.
Front gravity center limiting position of initially selected airplane in front gravity center flight testAircraft elevator offset angle delta 1 Aircraft elevator offset angle delta 2 Longitudinal overload delta deltan y1 And (8) into formula to obtain
In the formula, delta z1 ＝δ 2 -δ 1 ，Δn y1 ＝n y1 -1；
Limiting the gravity center of a primary aircraft in a rear gravity center flight testAircraft elevator offset angle delta 3 Aircraft elevator offset angle delta 4 Longitudinal overload delta deltan y2 And (8) into formula to obtain
In the formula, delta z2 ＝δ 4 -δ 3 ，Δn y2 ＝n y2 -1；
And (3) combining the formulas (9) and (10) to obtain the formula (1).
The method for identifying the aerodynamic focus of the aircraft through the flight test provided by the invention comprises the steps of initially selecting the front limit position of the center of gravity of the aircraft and the rear limit position of the center of gravity, calculating the elevator deviation value and the longitudinal overload of the plane in the two positions, and utilizing a formulaThe method has the advantages that the aerodynamic focus of the airplane can be identified, the number of parameters required by the method is small, the method is easy to realize, and compared with the method for identifying the aerodynamic focus of the airplane by adopting CFD calculation or wind tunnel test, the method can obtain the real relative position of the aerodynamic focus of the airplane.
The following gives a comparative example of identifying the aerodynamic focus of an aircraft using the method provided by the invention and using wind tunnel tests for RX4E four electric aircraft:
FIG. 2 shows the horizontal flight speed (in m/s), elevator deflection angle (in degrees) and longitudinal overload (i.e., Z-axis acceleration in m/s) of an RX4E four-seat electric aircraft in front center of gravity flight test 2 ) Is a measurement curve of (2); FIG. 3 shows the horizontal flight speed (in m/s), elevator deflection angle (in degrees) and longitudinal overload (i.e., Z-axis acceleration in m/s) of an RX4E four-seat electric aircraft in the post-center-of-gravity flight test 2 ) Is a measurement curve of (a).
Table 1 shows a comparison of the results of the method provided by the invention and the identification of the aerodynamic focus of an aircraft by wind tunnel test
TABLE 1 flight test focus vs. wind tunnel test focus
The wind tunnel test model is a rigid body and is a scaling model, and the deformation of the whole machine is small in the wind tunnel test process. In actual flight, the RX4E four electric aircrafts are elastic bodies, wings, a fuselage and a tail wing are all made of carbon fiber composite materials, and the elastic deformation is large in flight, so that the focus is more forward than the focus of a wind tunnel test, and the focus is the actual aerodynamic focus of the aircrafts during actual flight.
Claims (1)
1. The method for identifying the aerodynamic focus of the aircraft through the flight test is characterized by comprising the following steps of:
s1: measuring the weight m of the aircraft;
s2: a joint debugging test system;
s3: the front center of gravity flight test and the rear center of gravity flight test are adopted to respectively obtain front center of gravity data and rear center of gravity data required for identifying the aerodynamic focus of the aircraft, wherein the front center of gravity data comprises the front center of gravity position of the initially selected aircraftCorresponding aircraft elevator deflection angle delta when plane flies 1 Aircraft elevator deflection angle delta corresponding to pull-up 2 And a longitudinal overload n y1 The rear gravity center data comprises the gravity center rear limit position of the initially selected airplane>Corresponding aircraft elevator deflection angle delta when plane flies 3 Aircraft elevator deflection angle delta corresponding to pull-up 4 Longitudinal overload n y2 Wherein the aircraft elevator offset angle delta is obtained 1 And aircraft elevator deflection angle delta 3 The corresponding plane flying speeds are the same;
s4: identifying an aerodynamic focus of an aircraft using equation (1)
In the formula (1), the components are as follows,for the relative position of the aerodynamic focus of the aircraft, +.>For the pitch damping derivative of an aircraft, μ=2m/ρsb A Represents the relative density of the aircraft, m represents the weight of the aircraft, ρ represents the atmospheric density, S represents the wing reference area, b A Representing the average aerodynamic chord length, delta z1 、Δδ z2 Representing elevator offset, delta z1 ＝δ 1 -δ 2 ，Δδ z2 ＝δ 3 -δ 4 ，Δn y1 、Δn y2 Represents the longitudinal overload increment delta n y1 ＝n y1 -1，Δn y2 ＝n y2 -1，/>And->Respectively representing the front limit position and the rear limit position of the gravity center of the initially selected aircraft;
in S3, the front center of gravity data required for identifying the aerodynamic focus of the aircraft is obtained through a front center of gravity flight test, which specifically includes the following steps:
gravity center front limiting position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 1 ；
Maintaining the fore-limit of the center of gravity of a first selected aircraftPosition ofAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 2 Longitudinal overload n y1 ；
In S3, through a rear center of gravity flight test, the method for obtaining the rear center of gravity data required for identifying the aerodynamic focus of the aircraft specifically comprises the following steps:
gravity center rear limit position of primary aircraftSetting the plane flying speed V of the airplane and measuring the deflection angle delta of the elevator of the airplane 3 The plane flying speed V is the same as the plane flying speed V set in the front gravity center flight test;
aircraft center of gravity rear limit position that keeps primary electionAnd the set plane flying speed V of the aircraft is unchanged, the aircraft elevator is rapidly pulled, and the aircraft elevator deflection angle delta is measured 4 Longitudinal overload n y2 。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110648124.0A CN113525711B (en) | 2021-06-10 | 2021-06-10 | Method for identifying aerodynamic focus of aircraft through flight test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110648124.0A CN113525711B (en) | 2021-06-10 | 2021-06-10 | Method for identifying aerodynamic focus of aircraft through flight test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113525711A CN113525711A (en) | 2021-10-22 |
| CN113525711B true CN113525711B (en) | 2024-04-02 |
Family
ID=78124780
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110648124.0A Active CN113525711B (en) | 2021-06-10 | 2021-06-10 | Method for identifying aerodynamic focus of aircraft through flight test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113525711B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114491808B (en) * | 2022-01-17 | 2024-03-15 | 成都飞机工业（集团）有限责任公司 | Aircraft pneumatic focus adjustment method, device, equipment and storage medium |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105373647A (en) * | 2015-09-30 | 2016-03-02 | 成都飞机工业（集团）有限责任公司 | A Method for Identifying Aerodynamic Focus Through Ground Rolling Test |
| CN110027728A (en) * | 2019-04-17 | 2019-07-19 | 辽宁通用航空研究院 | Pass through the method for the pneumatic focus of airflight test identification aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10239635B2 (en) * | 2017-06-08 | 2019-03-26 | The Boeing Company | Methods for balancing aircraft engines based on flight data |
-
2021
- 2021-06-10 CN CN202110648124.0A patent/CN113525711B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105373647A (en) * | 2015-09-30 | 2016-03-02 | 成都飞机工业（集团）有限责任公司 | A Method for Identifying Aerodynamic Focus Through Ground Rolling Test |
| CN110027728A (en) * | 2019-04-17 | 2019-07-19 | 辽宁通用航空研究院 | Pass through the method for the pneumatic focus of airflight test identification aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 《电动飞机气动焦点辨识及飞行试验研究》;李亚东 等;《航空工程进展》;第12卷(第3期);1-7 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113525711A (en) | 2021-10-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Kimberlin | Flight testing of fixed wing aircraft | |
| CN109710961B (en) | High-altitude unmanned aerial vehicle limit rising data processing method based on GPS data | |
| CN112683446A (en) | Real-time center-of-gravity position estimation method for airplane | |
| Mitchell et al. | An NACA Vane-Type Angle-of-Attack Indicator for Use at Subsonic and Supersonic Speeds | |
| CN113525711B (en) | Method for identifying aerodynamic focus of aircraft through flight test | |
| RU2663315C2 (en) | Method and device for calculating current value of angular attacks and gliding of aerial vehicle | |
| CN106372307B (en) | Civil aircraft airflow angle estimation method based on pneumatic model | |
| CN107132376A (en) | A kind of acquisition methods of aircraft angle of attack fair curve | |
| CN110027728B (en) | A Method of Identifying Aerodynamic Focus of Aircraft by Air Flight Test | |
| Kanistras et al. | UC2AV: Unmanned circulation control aerial vehicle for short takeoff and enhanced payload | |
| CN215893640U (en) | Follow-up probe system with rotor wing downwash influence correction function | |
| Curry et al. | Ground-effect characteristics of the Tu-144 supersonic transport airplane | |
| Siu et al. | Flight test results of an angle of attack and angle of sideslip calibration method using Output-Error optimization | |
| Ranaudo et al. | Effects of horizontal tail ice on longitudinal aerodynamic derivatives | |
| Kufeld et al. | UH-60A helicopter rotor airloads measured in flight | |
| CN113609771A (en) | Airplane atmospheric parameter model calculation method based on MBSE | |
| Jain et al. | Calibration and accuracy determination of airdata system for a modern fighter aircraft | |
| Weishaeupl et al. | Flight Test Driven Development of Low Cost UAVs-Pitfalls and Opportunities | |
| Li et al. | A comparative study of airspeed calibration using GPS method and tower fly by method | |
| Benyamen et al. | Effects of propwash on horizontal tail aerodynamics of pusher UASS | |
| Meissner Jr | A flight instrumentation system for acquisition of atmospheric turbulence data | |
| Rolls et al. | An Investigation of the Drag Characteristics of a Tailless Delta-Wing Airplane in Flight, Including Comparison With Wind-Tunnel Data | |
| Rohde-Brandenburger | Inflight Measurements of Rudder Deflections in Circling Flight | |
| Bellman et al. | Preliminary Drag Measurements of the Consolidated Vultee XF-92A Delta-Wing Airplane in Flight Tests to a Mach Number of 1.01 | |
| Neuhart et al. | Flight Data Collection for General Aviation Aircraft Simulation Validation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |