An Integrated Design Method for Semi-Strapdown Guidance and Control Considering Angle of Attack and Field of View Constraints
A design method, semi-strapdown technology, applied in the aerospace field, can solve problems such as misalignment of the seeker, failure to consider the restriction of the attack angle of the missile end, and the target's departure from the seeker's field of view, so as to achieve the effect of improving the attack efficiency
Active Publication Date: 2021-04-23
HARBIN INST OF TECH
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Problems solved by technology
Due to the strong dynamic coupling between the missile body and the semi-strapdown seeker, the adjustment of the attitude of the missile body can easily cause the misadjustment angle of the seeker to exceed the allowable range, resulting in the target leaving the seeker's field of view
At the same time, this literature does not consider the problem of the restricted attack angle of the missile terminal
Method used
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[0094] The guidance and control integration algorithm designed by the present invention considering the terminal attack angle and the field of view constraint of the seeker is applied to the semi-strapdown guidance and control system of the missile in the longitudinal plane as shown below:
[0095]
[0096] In the formula, the drag X, lift Y and pitching moment M of the missile z The calculation formula is: Among them, c x0 is the zero-lift drag coefficient, Respectively drag coefficient relative to α, δ z partial derivative of .
[0097] In the simulation, the structural and aerodynamic parameters of the missile are set as: S=0.42m 2 , L=0.68m, m=1200Kg, J z =5600Kg·m 2 , P=5000N, Let the target be a ground moving target, and the velocity is V t =20m / s, target ballistic inclination angle is θ t = 0°; the initial value of the velocity of the missile is V = 250m / s, and the initial value of the pitch angle is The initial value of pitch angular velocity is ω z =...
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The invention discloses a semi-strapdown guidance and control integrated design method considering the attack angle and field of view constraints. The method includes the following steps: step 1, establishing a semi-strapdown guidance and control integrated design model; Strapdown guidance and control integration design model, design the semi-strapdown guidance and control integration algorithm considering the attack angle and field of view constraints, so that the line of sight angular velocity line of sight angle ε and the desired end line of sight angle ε d Difference ε‑ε d And the seeker misalignment angle η converges to near zero as soon as possible, while satisfying the seeker field of view constraints: where it represents the maximum allowable value of η; Step 3, simulation test considers the integration of semi-strapdown guidance and control of attack angle and field of view constraints performance of the algorithm. The method of the present invention explicitly considers the constraints of the field of view of the seeker in the design, so it can theoretically ensure that the misadjustment angle of the seeker is always kept within the allowable range, and overcomes the lack of the existing semi-strapdown guidance and control integrated design method. Consider deficiencies in seeker field of view constraints.
Description
technical field [0001] The invention belongs to the field of aerospace technology, and relates to an integrated guidance and control design method, in particular to a semi-strapdown guidance and control integrated design method considering the restriction of the terminal attack angle and the field of view of the seeker. Background technique [0002] Compared with the traditional guidance and control independent design method, the guidance and control integrated design method can actively use the coupling relationship between the guidance loop and the control loop to improve the performance of the overall system. It has more advantages in terms of improving stability and reliability. However, most of the existing guidance and control integrated design results do not consider the physical characteristics of the seeker itself. With the miniaturization and cost reduction of guided weapons, the full / semi-strapdown guidance with full / semi-fixed installation of detectors and proje...
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IPC IPC(8): F42B15/01
CPCF42B15/01
Inventor 侯明哲周彬段广仁
Owner HARBIN INST OF TECH