A Variable Parameter Guidance Method with Large Fall Angle Constraint Based on Measurement Information
A technology for measuring information and falling angle, applied in the field of guided aircraft, can solve the problems that the project cannot be realized, and the adaptive change of the parameters of the guidance law is not considered, so as to achieve the effect of improving the fault tolerance of information
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[0086] An adaptive variable structure terminal guidance method with drop angle constraints based on measurement information, the implementation method is as follows figure 1 As shown, the specific implementation steps are as follows:
[0087] 1. Taking the air-to-ground strike guided aircraft as an example, the implementation process of the present invention is introduced. It is known that the altitude of the target point is 1000m, the target is located at a horizontal distance of 12000m from the guided aircraft, and the expected fall angle is -70°. The two methods shown in Table 1 are used for comparison.
[0088] Table 1 Serving Conditions
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[0090]
[0091] 2. Use the integrated navigation system to measure the velocity V of the missile in three directions in the navigation coordinate system in real time e ,V n ,V s , position x n ,y n ,z n , yaw angle Pitch angle and roll angle γ.
[0092] 3. Utilize the real-time measurement of missile position, ...
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