Flight path adaptive completion method for flight attitude simulation

Abstract

The invention discloses a flight path self-adaptive complementing method for flight attitude simulation, which comprises the following steps of: according to data of related attitude angle, surface speed and flight height of an existing airplane, combining initial longitude and initial latitude, and through a longitude updating strategy and a latitude updating strategy, realizing the whole estimation and self-adaptive complementing process of the flight path of the airplane. According to the aircraft attitude information and the longitude and latitude real-time updating process, related flight path self-adaptive complementation is carried out, the attitude of the aircraft in the maneuvering process in the air is dynamically reflected, and the problem that the dynamic motion process of an aircraft body cannot be simulated only by depending on existing attitude information directly obtained by an engine is solved.

Description

Technical Field

[0001] The invention relates to a track adaptive completion method for flight attitude simulation, belonging to the technical field of aeroengines. Background Art

[0002] The attitude angles related to the aircraft attitude are mainly divided into pitch angle, roll angle and yaw angle. The above attitude angles are the relative rotation angles of the aircraft body coordinate system relative to the geographic coordinate system. If only the attitude angles are used for simulation, the dynamic characteristics of the aircraft in the air cannot be shown. Therefore, it is necessary to add longitude, latitude and other position information to simulate the dynamic characteristics of the aircraft.

[0003] Aircraft engines are installed in aircraft as power. When the engine is designed, it cannot obtain real-time track information such as longitude and latitude of the aircraft during flight, but can only obtain attitude angles related to the aircraft's attitude. In order to facilitate the engine to carry out aircraft attitude simulation and intuitively understand the engine's attitude during the aircraft maneuvering process, it is necessary to carry out relevant track adaptive completion based on the aircraft's attitude angle. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a track adaptive completion method for flight attitude simulation.

[0005] The present invention is achieved through the following technical solutions.

[0006] The present invention provides a method for adaptively completing a flight track for flight attitude simulation, comprising: based on the data of the existing aircraft-related attitude angle, indicated speed, and flight altitude, combined with the initial longitude and initial latitude, through the longitude update strategy and the latitude update strategy, the aircraft track estimation and adaptive completion process are realized.

[0007] The longitude update strategy is based on the formula:

[0008] Longitude(i)=Longitude(i-1)+Vb(i)×cos((Yaw(i) / 180)×3.14159)×0.0000001;

[0009] The latitude update strategy is based on the formula:

[0010] Latitude(i)=Latitude(i-1)+Vb(i)×sin((Yaw(i) / 180)×3.14159)×0.0000001.

[0011] The beneficial effects of the present invention are: according to the real-time update process of the aircraft attitude information and longitude and latitude, it is possible to carry out adaptive completion of the relevant track, dynamically respond to the attitude of the aircraft during the maneuvering process in the air, and solve the problem that the existing attitude information directly obtained by the engine cannot simulate the dynamic motion process of the aircraft body. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 is a flow chart of the method of the present invention; DETAILED DESCRIPTION

[0013] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0014] See also Figure 1 shown.

[0015] The present invention provides a method for adaptively completing a flight path for flight attitude simulation, comprising the following steps:

[0016] 1) Obtain aircraft attitude information, mainly attitude angles related to aircraft attitude (yaw angle, pitch angle, roll angle, sideslip angle), indicated speed, and flight altitude;

[0017] 2) Data cleaning. Remove non-flight data such as the aircraft's ground inertial navigation alignment process and ground driving. The specific implementation benchmark is to determine the indicated speed and altitude. The flight data segment is defined as the positive change of the indicated speed and altitude together. After the data segment is determined, the time is reset to zero;

[0018] 3) Yaw angle alignment. Align the obtained yaw angles by subtracting the yaw angle in the first row of data from all rows of the data so that the initial direction is consistent during simulation;

[0019] 4) Initial setting of longitude and latitude. Set the initial longitude and latitude according to user needs. For three-dimensional simulation, it should be within the longitude and latitude range of the map to which it belongs;

[0020] 5) Longitude update. The longitude is updated according to the initial longitude (Longitude), speed (Vb) and yaw angle (Yaw). The specific method is as follows:

[0021] Longitude(i)=Longitude(i-1)+Vb(i)×cos((Yaw(i) / 180)×3.14159)×0.0000001

[0022] Among them, the unit of longitude is "°", the unit of speed (Vb) is "km / h", and the unit of yaw angle (Yaw) is "°";

[0023] Note: The initial longitude can be any location on the earth and is usually determined by developing three-dimensional simulation map information.

[0024] 6) Latitude update. The latitude is updated according to the initial latitude (Latitude), speed (Vb) and yaw angle (Yaw). The specific method is as follows:

[0025] Latitude(i)=Latitude(i-1)+Vb(i)×sin((Yaw(i) / 180)×3.14159)×0.0000001

[0026] Among them, the unit of latitude (Latitude) is "°", the unit of speed (Vb) is "km / h", and the unit of yaw angle (Yaw) is "°";

[0027] Note: The initial latitude can be any location on the earth and is usually determined by developing three-dimensional simulation map information.

[0028] 7) All subsequent data are adaptively updated according to steps 5) and 6) in sequence, and the obtained track information can normally reflect the aircraft attitude and speed related information.

[0029] For example: the initial value of longitude is 108.681035°, and the initial value of latitude is 29.01743744°;

[0030] Longitude update. Update the longitude according to the initial longitude (Longitude), speed (Vb) and yaw angle (Yaw). The specific method is as follows:

[0031] Longitude(i)=Longitude(i-1)+Vb(i)×cos((Yaw(i) / 180)×3.14159)×0.0000001, where the unit of longitude (Longitude) is “°”, the unit of speed (Vb) is “km / h”, and the unit of yaw angle (Yaw) is “°”;

[0032] As in t i-1 = 74s, Longitude(i-1) = 108.7164342°,

[0033] Vb(i)=668.172km / h, Yaw(i)=-2.966°, then t i =74.1s, the longitude can be adaptively updated, Longitude(i)=108.7164342+668.172×cos((-2.966 / 180)×3.14159)×0.0000001=108.7165009°;

[0034] Latitude update. Update the latitude according to the initial latitude (Latitude), speed (Vb) and yaw angle (Yaw). The specific method is as follows:

[0035] Latitude(i)=Latitude(i-1)+Vb(i)×sin((Yaw(i) / 180)×3.14159)×0.0000001, where the unit of latitude (Latitude) is “°”, the unit of speed (Vb) is “km / h”, and the unit of yaw angle (Yaw) is “°”;

[0036] As in t i-1 = 74s, Latitude(i-1) = 29.01597839°,

[0037] Vb(i)=668.172km / h, Yaw(i)=-2.966°, then t i =74.1s, the latitude can be adaptively updated, Latitude(i)=29.01597839+668.172×sin((-2.966 / 180)×3.14159)×0.0000001=29.01597494°.

Claims

1. A method for adaptive track completion for flight attitude simulation, characterized in that: include: According to the data of the existing aircraft attitude angle, indicated speed, and flight altitude, combined with the initial longitude and initial latitude, the aircraft track estimation and adaptive completion process are realized through the longitude update strategy and latitude update strategy.

2. The method for adaptively completing a flight path for flight attitude simulation according to claim 1, characterized in that: The longitude update strategy is based on the formula: Longitude(i)=Longitude(i-1)+Vb(i)×cos((Yaw(i) / 180)×3.14159)×0.0000001.

3. The method for adaptively completing a flight path for flight attitude simulation according to claim 1, characterized in that: The latitude update strategy is based on the formula: Latitude(i)=Latitude(i-1)+Vb(i)×sin((Yaw(i) / 180)×3.14159)×0.0000001.

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