CN117452974B - Method and device for optimizing short-distance landing of conveyor airport - Google Patents
Method and device for optimizing short-distance landing of conveyor airport Download PDFInfo
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- CN117452974B CN117452974B CN202311781998.9A CN202311781998A CN117452974B CN 117452974 B CN117452974 B CN 117452974B CN 202311781998 A CN202311781998 A CN 202311781998A CN 117452974 B CN117452974 B CN 117452974B
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- 230000035945 sensitivity Effects 0.000 claims description 9
- 238000005457 optimization Methods 0.000 claims description 3
- 238000005201 scrubbing Methods 0.000 abstract 1
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Abstract
The application belongs to the technical field of airplane control, and relates to a method and a device for optimizing short-distance landing of a conveyor airport. The method comprises the following steps: giving a grounding speed value range of aircraft landing and an aircraft approach track angle value range; forming a plurality of input sequences for the ground speed and the aircraft approach track angle in a discrete manner; calculating a grounding attack angle of the landing grounding point and a grounding pitching attitude angle of the landing grounding point; determining a first difference value closest to the alarm attack angle, and simultaneously determining a second difference value closest to the floor scrubbing angle; when the first difference value is smaller than the second difference value, the grounding attack angle is a sensitive parameter, and a critical attack angle is calculated, otherwise, the grounding pitching attitude angle is a sensitive parameter, and a critical pitching attitude angle is calculated; and interpolating based on the critical attack angle or the critical pitching attitude angle to obtain the optimal grounding speed and the aircraft approach track angle. The method and the device can quickly determine the combination of the optimal grounding speed and the aircraft approach track angle, and shorten the landing distance.
Description
Technical Field
The application belongs to the field of aircraft flight control, and particularly relates to a method and a device for optimizing short-distance landing of a transport aircraft airport.
Background
To improve task performance, the transport needs to land at an airport at a shorter distance. Compared with the conventional landing, the short-distance landing adopts a small speed and a large glide angle approach, the landing track is a quadratic curve, a leveling section is omitted, and the landing distance can be shortened by about 13%. Landing track, landing safety, air segment flight distance are related to factors such as aircraft weight, wing loads, aerodynamic forces of the landing configuration, approach track angle, ground speed, airport altitude and temperature. The landing track is optimally designed, various design constraints must be considered to ensure the landing safety of the aircraft and shorten the landing distance.
Disclosure of Invention
In order to shorten the airport landing distance of a conveyor and improve the task execution efficiency of the airplane, the application designs a method and a device for optimizing the airport short-distance landing of the conveyor.
The first aspect of the application provides a method for optimizing short-distance landing of a transport aircraft airport, which mainly comprises the following steps:
step S1, giving a grounding speed value range of landing of an aircraft and an aircraft approach track angle value range;
s2, dispersing a plurality of speed discrete points in the grounding speed value range, dispersing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences;
step S3, for each input sequence, calculating a grounding attack angle of a landing grounding point and a grounding pitching attitude angle of the landing grounding point;
s4, determining a first difference value between the ground attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and simultaneously determining a second difference value between the ground pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle;
step S5, when the first difference value is smaller than the second difference value, the grounding attack angle is a sensitive parameter, a critical attack angle is calculated, the critical attack angle is a set multiple of an alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitive parameter, and a critical pitching attitude angle is calculated, and the critical pitching attitude angle is a set multiple of a floor wiping angle;
and S6, interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle.
Preferably, in step S1, the ground speed is in the range of Vcg-1.15Vs, vcg is the ground minimum steering speed, and Vs is the stall speed of the aircraft; the value range of the aircraft approach track angle is-5 degrees to-8 degrees.
Preferably, in step S2, at least three speed discrete points are dispersed at equal intervals in the grounding speed range, and at least three track angle discrete points are dispersed at equal intervals in the aircraft approach track angle range.
Preferably, step S3 further comprises:
step S31, according to the maximum landing grounding sinking speed V ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id =V ymax /V Id ；
Step S32, according to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：
n y =((θ ap ) 2 -(θ Id ) 2 ) (V Id ) 2 /294+1；
Step S33, according to normal overload n y Ground speed V Id Calculating the lift coefficient CL of the landing site Id ：CL Id =19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
step S34, according to the lift coefficient CL of the landing grounding point Id Determining the ground attack angle alpha of the landing ground point Id ；
Step S35, according to the grounding attack angle alpha of the grounding point Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
Preferably, in step S31, the maximum landing ground settlement speed is set to 1.5m/S.
Preferably, in step S5, the multiple is set to 0.95.
The second aspect of the present application provides a short-distance landing optimization device for a transport aircraft airport, mainly comprising:
the value range determining module is used for giving a grounding speed value range of landing of the aircraft and an aircraft approach track angle value range;
the input sequence generation module is used for discretizing a plurality of speed discrete points in the grounding speed value range, discretizing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences;
the attack angle and attitude angle calculation module is used for calculating the grounding attack angle of the landing grounding point and the grounding pitching attitude angle of the landing grounding point for each input sequence;
the difference value calculation module is used for determining a first difference value between the grounding attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and determining a second difference value between the grounding pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle;
the sensitivity parameter determining module is used for calculating a critical attack angle when the first difference value is smaller than the second difference value and the grounding attack angle is a sensitivity parameter, and the critical attack angle is a set multiple of the alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitivity parameter and the critical pitching attitude angle is a set multiple of the floor wiping angle;
and the interpolation calculation module is used for interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle.
Preferably, the attack angle and attitude angle calculation module includes:
a grounding track angle calculation unit for calculating a grounding sinking speed V according to the maximum landing ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id =V ymax /V Id ；
A normal overload calculation unit for calculating a normal overload according to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：
n y =((θ ap ) 2 -(θ Id ) 2 ) (V Id ) 2 /294+1；
A lift coefficient calculation unit for calculating a lift coefficient according to the normal overload n y Ground speed V Id Calculating the lift coefficient CL of the landing site Id ：CL Id =19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
an attack angle calculation unit for calculating a lift coefficient CL according to the landing ground point Id Determining the ground attack angle alpha of the landing ground point Id ；
A pitch angle calculation unit for calculating a ground attack angle alpha according to the landing ground point Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
The method and the device can quickly determine the combination of the optimal grounding speed and the aircraft approach track angle, and shorten the landing distance.
Drawings
FIG. 1 is a flow chart of a preferred embodiment of a method of optimizing a short landing of a conveyor airport of the present application.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The first aspect of the present application provides a method for optimizing short-distance landing of a transport aircraft airport, as shown in fig. 1, mainly including:
step S1, giving a grounding speed value range of the landing of the aircraft and an aircraft approach track angle value range.
In some alternative embodiments, the ground speed range is Vcg-1.15Vs, vcg is the ground minimum maneuver speed, and Vs is the aircraft stall speed; the value range of the aircraft approach track angle is-5 degrees to-8 degrees.
S2, dispersing a plurality of speed discrete points in the grounding speed value range, dispersing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences.
In some alternative embodiments, at least three discrete points of speed are equally spaced apart within the ground speed range and at least three discrete points of track angle are equally spaced apart within the aircraft approach track angle range.
In this embodiment, vcg is typically 1.05Vs, calculated stall speed vs=48.07 m/s, and three ground speed discrete points are equally spaced apart, each ground speed V Id =[1.05Vs，1.1Vs，1.15Vs]. Three track angle discrete points are scattered at equal intervals, and each aircraft approach track angle theta ap =[-6°，-7°，-8°]。
The three ground speeds and the three aircraft approach path angles together can form 9 input sequences.
And S3, calculating the grounding attack angle of the landing grounding point and the grounding pitching attitude angle of the landing grounding point for each input sequence.
In some alternative embodiments, step S3 further comprises:
step S31, according to the maximum landing grounding sinking speed V ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id =V ymax /V Id ；
Step S32, according to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：
n y =((θ ap ) 2 -(θ Id ) 2 ) (V Id ) 2 /294+1；
Step S33, according to normal overload n y Ground speedV Id Calculating the lift coefficient CL of the landing site Id ：CL Id =19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
step S34, according to the lift coefficient CL of the landing grounding point Id Determining the ground attack angle alpha of the landing ground point Id ；
Step S35, according to the grounding attack angle alpha of the grounding point Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
In some alternative embodiments, in step S31, the maximum landing ground settlement speed is set to 1.5m/S. For different earthing speeds V Id Angle theta with approach path of aircraft ap The formed combined sequence can calculate the corresponding grounding attack angle alpha by the mode Id Ground pitch attitude angle gamma Id . In step S34, the ground attack angle α of the landing point is determined Id Other parameters, such as airport altitude, temperature, etc., are also required, and calculating the ground angle of attack of the landing ground point is a routine calculation process in the art, and will not be described in detail in this application. Finally in step S35, the ground attack angle α of the landing ground point Id And ground track angle theta Id The grounding pitching attitude angle gamma of the landing grounding point can be obtained by adding Id 。
And S4, determining a first difference value between the ground attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and simultaneously determining a second difference value between the ground pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle.
In the step, the floor wiping angle Atd is generally 13 degrees, the alarm attack angle Ayx is generally 12.7 degrees, and the floor wiping angle Atd can be specifically designed by oneself. For example, for ground speed V Id = 52.8814m/s, ground speed V Id Combined sequence of = -7 ° calculated ground angle of attack α Id 12.7785 ° ground pitch attitude angle γ Id 11.15316, the grounding attack angle of the group of sequences exceeds the alarm attack angle and is closest to the alarm attack angle, and the first difference value is12.7785 ° -12.7 ° =0.0785 °. For the ground speed V Id = 50.4777m/s, ground speed V Id Combined sequence of = -6 ° calculated ground angle of attack α Id 17.1379 ° ground pitch attitude angle γ Id For 15.43517 °, the ground pitch attitude angle of the set of sequences exceeds and is closest to the ground angle, the second difference being 15.43517 ° -13 ° = 2.43517 °.
And S5, when the first difference value is smaller than the second difference value, the grounding attack angle is a sensitive parameter, a critical attack angle is calculated, the critical attack angle is a set multiple of the alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitive parameter, and a critical pitching attitude angle is calculated, and the critical pitching attitude angle is a set multiple of the ground wiping angle.
As can be seen from the above-mentioned embodiments, the first difference is smaller than the second difference, that is, the ground attack angle is a sensitive parameter, and when the ground attack angle is a sensitive parameter, the critical attack angle needs to be calculated. In some alternative embodiments, the multiple is set to 0.95. Accordingly, the critical angle of attack is 12.7x0.95=12.1°.
And S6, interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle.
According to the above embodiment, in the combined sequence with the same aircraft approach track angle, the ground speed is interpolated by the critical angle of attack of 12.1 ° to obtain the ground speed of 53.8m/s, at which time the aircraft approach track angle is unchanged and still is-7 °.
Similarly, if in step S5, the first difference is greater than the second difference, the ground pitch attitude angle is a sensitive parameter, a critical pitch attitude angle is calculated and obtained to be 13×0.95=12.35°, and then in the combined sequence with the same ground speed, the aircraft approach track angle is interpolated by the critical pitch attitude angle of 12.35 °, where the ground speed is unchanged and still 50.4777m/S.
The method and the device can quickly determine the combination of the optimal grounding speed and the aircraft approach track angle, and shorten the landing distance.
The second aspect of the present application provides a short-distance landing optimization device for a conveyor airport, which corresponds to the above method, and mainly includes:
the value range determining module is used for giving a grounding speed value range of landing of the aircraft and an aircraft approach track angle value range;
the input sequence generation module is used for discretizing a plurality of speed discrete points in the grounding speed value range, discretizing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences;
the attack angle and attitude angle calculation module is used for calculating the grounding attack angle of the landing grounding point and the grounding pitching attitude angle of the landing grounding point for each input sequence;
the difference value calculation module is used for determining a first difference value between the grounding attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and determining a second difference value between the grounding pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle;
the sensitivity parameter determining module is used for calculating a critical attack angle when the first difference value is smaller than the second difference value and the grounding attack angle is a sensitivity parameter, and the critical attack angle is a set multiple of the alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitivity parameter and the critical pitching attitude angle is a set multiple of the floor wiping angle;
and the interpolation calculation module is used for interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle.
In some optional embodiments, the attack angle and attitude angle calculation module includes:
a grounding track angle calculation unit for calculating a grounding sinking speed V according to the maximum landing ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id =V ymax /V Id ；
Normal overload calculation unit for rootAccording to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：
n y =((θ ap ) 2 -(θ Id ) 2 ) (V Id ) 2 /294+1；
A lift coefficient calculation unit for calculating a lift coefficient according to the normal overload n y Ground speed V Id Calculating the lift coefficient CL of the landing site Id ：CL Id =19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
an attack angle calculation unit for calculating a lift coefficient CL according to the landing ground point Id Determining the ground attack angle alpha of the landing ground point Id ；
A pitch angle calculation unit for calculating a ground attack angle alpha according to the landing ground point Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. A method for optimizing short-range landing of a conveyor airport, comprising:
step S1, giving a grounding speed value range of landing of an aircraft and an aircraft approach track angle value range;
s2, dispersing a plurality of speed discrete points in the grounding speed value range, dispersing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences;
step S3, for each input sequence, calculating a grounding attack angle of a landing grounding point and a grounding pitching attitude angle of the landing grounding point;
s4, determining a first difference value between the ground attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and simultaneously determining a second difference value between the ground pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle;
step S5, when the first difference value is smaller than the second difference value, the grounding attack angle is a sensitive parameter, a critical attack angle is calculated, the critical attack angle is a set multiple of an alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitive parameter, and a critical pitching attitude angle is calculated, and the critical pitching attitude angle is a set multiple of a floor wiping angle;
step S6, interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle;
wherein, step S3 further comprises:
step S31, according to the maximum landing grounding sinking speed V ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id ＝V ymax /V Id The method comprises the steps of carrying out a first treatment on the surface of the The maximum landing ground subsidence speed is set to 1.5m/s;
step S32, according to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：n y ＝((θ ap ) 2 -(θ Id ) 2 )(V Id ) 2 /294+1；
Step S33, according to normal overload n y Ground speed V Id Calculating the lift coefficient CL of the landing site Id ：CL Id ＝19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
step S34, according to the lift coefficient CL of the landing grounding point Id Determining the ground attack angle alpha of the landing ground point Id ；
Step S35, according to the grounding attack angle alpha of the grounding point Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
2. The method for optimizing short landing of a conveyor airport according to claim 1, wherein in step S1, the grounding speed is within a range of Vcg-1.15Vs, vcg is a ground minimum maneuvering speed, and Vs is an aircraft stall speed; the value range of the aircraft approach track angle is-5 degrees to-8 degrees.
3. The method of optimizing short landing of a conveyor airport of claim 1, wherein in step S2, at least three discrete points of speed are equally spaced apart within said ground speed range and at least three discrete points of track angle are equally spaced apart within said aircraft approach track angle range.
4. The method for optimizing short landing of a conveyor airport according to claim 1, wherein in step S5, the multiple is set to 0.95.
5. A short-range landing optimization device for a conveyor airport, comprising:
the value range determining module is used for giving a grounding speed value range of landing of the aircraft and an aircraft approach track angle value range;
the input sequence generation module is used for discretizing a plurality of speed discrete points in the grounding speed value range, discretizing a plurality of track angle discrete points in the aircraft approach track angle value range, and combining the speed discrete points and the track angle discrete points into a plurality of input sequences;
the attack angle and attitude angle calculation module is used for calculating the grounding attack angle of the landing grounding point and the grounding pitching attitude angle of the landing grounding point for each input sequence;
the difference value calculation module is used for determining a first difference value between the grounding attack angle closest to the alarm attack angle and exceeding the alarm attack angle and the alarm attack angle, and determining a second difference value between the grounding pitching attitude angle closest to the ground wiping angle and exceeding the ground wiping angle and the ground wiping angle;
the sensitivity parameter determining module is used for calculating a critical attack angle when the first difference value is smaller than the second difference value and the grounding attack angle is a sensitivity parameter, and the critical attack angle is a set multiple of the alarm attack angle, otherwise, the grounding pitching attitude angle is a sensitivity parameter and the critical pitching attitude angle is a set multiple of the floor wiping angle;
the interpolation calculation module is used for interpolating the grounding speed based on the critical attack angle or interpolating the aircraft approach track angle based on the critical pitching attitude angle to obtain the optimized grounding speed and the aircraft approach track angle;
wherein, the attack angle and attitude angle calculation module comprises:
a grounding track angle calculation unit for calculating a grounding sinking speed V according to the maximum landing ymax Ground speed V Id Calculating the grounding track angle theta Id ：θ Id ＝V ymax /V Id The method comprises the steps of carrying out a first treatment on the surface of the The maximum landing ground subsidence speed is set to 1.5m/s;
a normal overload calculation unit for calculating a normal overload according to the grounding track angle theta Id Ground speed V Id Aircraft approach track angle θ ap Calculating normal overload n of landing ground point y ：
n y ＝((θ ap ) 2 -(θ Id ) 2 )(V Id ) 2 /294+1；
A lift coefficient calculation unit for calculating a lift coefficient according to the normal overload n y Ground speed V Id Calculating the lift coefficient CL of the landing site Id ：CL Id ＝19.6n y W/(Sρ(V Id ) 2 ) The method comprises the steps of carrying out a first treatment on the surface of the Wherein W is the landing weight of the aircraft, S is the wing area, and ρ is the atmospheric density;
an attack angle calculation unit for calculating a lift coefficient CL according to the landing ground point Id Determining the ground attack angle alpha of the landing ground point Id ；
A pitch angle calculating unit for calculating a pitch angle according to landingGround angle of attack α of land Id Ground track angle θ Id Determining a ground pitch attitude angle gamma for a landing ground point Id 。
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8819093D0 (en) * | 1987-08-13 | 1988-09-14 | Grumman Aerospace Corp | Aircraft precision approach control system |
| CN1169552A (en) * | 1996-05-20 | 1998-01-07 | 波音公司 | Landing attitude modifier for airplane |
| CN102390543A (en) * | 2011-08-23 | 2012-03-28 | 北京航空航天大学 | Vertical landing track design method for unmanned aerial vehicle |
| RU2549145C1 (en) * | 2013-11-27 | 2015-04-20 | Открытое акционерное общество "Раменское приборостроительное конструкторское бюро" (ОАО "РПКБ") | Method of control of aircraft landing path at landing on programmed airfield |
| CN108255193A (en) * | 2017-12-27 | 2018-07-06 | 清华大学 | A kind of vertical/short field aircraft flight control method |
| CN110456655A (en) * | 2019-06-29 | 2019-11-15 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Microwave landing analogue simulation system |
| CN110598294A (en) * | 2019-09-03 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for determining flight trajectory stability of airplane with conventional layout |
| KR102181153B1 (en) * | 2020-06-03 | 2020-11-20 | 국방과학연구소 | Flare control method foe inproved aircraft automatic landings accuracy and safety on inclined runway |
| CN114942649A (en) * | 2022-06-06 | 2022-08-26 | 北京石油化工学院 | Airplane pitching attitude and track angle decoupling control method based on backstepping method |
| CN115639843A (en) * | 2022-10-11 | 2023-01-24 | 中国航空工业集团公司西安飞机设计研究所 | Automatic leveling control method and device for three-level landing of airplane |
| CN116050101A (en) * | 2022-12-26 | 2023-05-02 | 江西洪都航空工业集团有限责任公司 | Method for improving landing precision of aircraft under influence of ground effect |
-
2023
- 2023-12-22 CN CN202311781998.9A patent/CN117452974B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB8819093D0 (en) * | 1987-08-13 | 1988-09-14 | Grumman Aerospace Corp | Aircraft precision approach control system |
| CN1169552A (en) * | 1996-05-20 | 1998-01-07 | 波音公司 | Landing attitude modifier for airplane |
| CN102390543A (en) * | 2011-08-23 | 2012-03-28 | 北京航空航天大学 | Vertical landing track design method for unmanned aerial vehicle |
| RU2549145C1 (en) * | 2013-11-27 | 2015-04-20 | Открытое акционерное общество "Раменское приборостроительное конструкторское бюро" (ОАО "РПКБ") | Method of control of aircraft landing path at landing on programmed airfield |
| CN108255193A (en) * | 2017-12-27 | 2018-07-06 | 清华大学 | A kind of vertical/short field aircraft flight control method |
| CN110456655A (en) * | 2019-06-29 | 2019-11-15 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Microwave landing analogue simulation system |
| CN110598294A (en) * | 2019-09-03 | 2019-12-20 | 中国航空工业集团公司西安飞机设计研究所 | Method and device for determining flight trajectory stability of airplane with conventional layout |
| KR102181153B1 (en) * | 2020-06-03 | 2020-11-20 | 국방과학연구소 | Flare control method foe inproved aircraft automatic landings accuracy and safety on inclined runway |
| CN114942649A (en) * | 2022-06-06 | 2022-08-26 | 北京石油化工学院 | Airplane pitching attitude and track angle decoupling control method based on backstepping method |
| CN115639843A (en) * | 2022-10-11 | 2023-01-24 | 中国航空工业集团公司西安飞机设计研究所 | Automatic leveling control method and device for three-level landing of airplane |
| CN116050101A (en) * | 2022-12-26 | 2023-05-02 | 江西洪都航空工业集团有限责任公司 | Method for improving landing precision of aircraft under influence of ground effect |
Non-Patent Citations (2)
| Title |
|---|
| Cessna―152飞机的进近着陆过程计算分析;陈治怀;中国民航学院学报;19940212(01);全文 * |
| 大迎角自动进近短距着陆综合控制设计及仿真研究;莫文骥, 申功璋;飞机设计;20050630(02);全文 * |
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