An interdependent estimation and guidance design approach for interceptors is presented by enforcing a stable zero-effort-miss dynamics. The output of the estimator is the demanded lateral acceleration, which serves as the guidance command. A dynamic inversion based inner-loop autopilot design facilitates extensive six degree-of-freedom simulation studies, which shows that the proposed interdependent approach gives improved performance compared to the conventional approach where estimation and guidance are done separately
A defense system against ballistic threat is a very complex system from the engineering point of vie...
A partial integrated guidance and control design for an interception with terminal impact angle cons...
Abstract — In this paper, guidance law (GL) and autopilot system, the decision parts of an airframe,...
This paper addresses the problem of intercepting highly maneuverable threats using seeker-less inter...
To address the concern of classical guidance and control designs (where guidance and control loops a...
A new partial integrated guidance and control design approach is proposed in this paper, which combi...
Using the recently developed computationally efficient model predictive static programming and a clo...
The authors propose an autopilot based on partial integrated guidance and control for missiles to ac...
The paper proposes a time scale separated partial integrated guidance and control of an interceptor ...
An integrated guidance integrated estimation/guidance law is designed for exoatmospheric interceptor...
In this thesis, the problem of intercepting highly manoeuvrable threats using seeker-less intercepto...
There have been attempts at obtaining robust guidance laws to ensure zero miss distance (ZMD) for i...
An important limitation of the existing IGC algorithms, is that they do not explicitly exploit the i...
ABSTRACT: Bird's formation flight is one of the best types of cooperation in nature. The bird's flig...
This article covers the design of an L1-adaptive Incremental Nonlinear Dynamic Inversion (INDI) auto...
A defense system against ballistic threat is a very complex system from the engineering point of vie...
A partial integrated guidance and control design for an interception with terminal impact angle cons...
Abstract — In this paper, guidance law (GL) and autopilot system, the decision parts of an airframe,...
This paper addresses the problem of intercepting highly maneuverable threats using seeker-less inter...
To address the concern of classical guidance and control designs (where guidance and control loops a...
A new partial integrated guidance and control design approach is proposed in this paper, which combi...
Using the recently developed computationally efficient model predictive static programming and a clo...
The authors propose an autopilot based on partial integrated guidance and control for missiles to ac...
The paper proposes a time scale separated partial integrated guidance and control of an interceptor ...
An integrated guidance integrated estimation/guidance law is designed for exoatmospheric interceptor...
In this thesis, the problem of intercepting highly manoeuvrable threats using seeker-less intercepto...
There have been attempts at obtaining robust guidance laws to ensure zero miss distance (ZMD) for i...
An important limitation of the existing IGC algorithms, is that they do not explicitly exploit the i...
ABSTRACT: Bird's formation flight is one of the best types of cooperation in nature. The bird's flig...
This article covers the design of an L1-adaptive Incremental Nonlinear Dynamic Inversion (INDI) auto...
A defense system against ballistic threat is a very complex system from the engineering point of vie...
A partial integrated guidance and control design for an interception with terminal impact angle cons...
Abstract — In this paper, guidance law (GL) and autopilot system, the decision parts of an airframe,...