Abstract
An optimal midcourse guidance law is presented that maximizes the final speed for missiles against a target at far distance or at low attitude in which the final speed is a prime factor. An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terms of thrust, lift, drag, and intercept boundary condition. The optimal guidance law can be implemented either in airframe coordinates or inertia coordinates. It is shown that the acceleration commands with constant control gain are adequate when the range is relatively short; during midcourse guidance, however, the optimal control gains are required to enhance the performance.
| Original language | English |
|---|---|
| Pages (from-to) | 419-425 |
| Number of pages | 7 |
| Journal | IEEE Transactions on Aerospace and Electronic Systems |
| Volume | 32 |
| Issue number | 1 |
| DOIs | |
| Publication status | Published - 1996 Dec 1 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Electrical and Electronic Engineering
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Analysis of optimal midcourse guidance law. / Yang, Shih-Ming.
In: IEEE Transactions on Aerospace and Electronic Systems, Vol. 32, No. 1, 01.12.1996, p. 419-425.Research output: Contribution to journal › Article
TY - JOUR
T1 - Analysis of optimal midcourse guidance law
AU - Yang, Shih-Ming
PY - 1996/12/1
Y1 - 1996/12/1
N2 - An optimal midcourse guidance law is presented that maximizes the final speed for missiles against a target at far distance or at low attitude in which the final speed is a prime factor. An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terms of thrust, lift, drag, and intercept boundary condition. The optimal guidance law can be implemented either in airframe coordinates or inertia coordinates. It is shown that the acceleration commands with constant control gain are adequate when the range is relatively short; during midcourse guidance, however, the optimal control gains are required to enhance the performance.
AB - An optimal midcourse guidance law is presented that maximizes the final speed for missiles against a target at far distance or at low attitude in which the final speed is a prime factor. An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terms of thrust, lift, drag, and intercept boundary condition. The optimal guidance law can be implemented either in airframe coordinates or inertia coordinates. It is shown that the acceleration commands with constant control gain are adequate when the range is relatively short; during midcourse guidance, however, the optimal control gains are required to enhance the performance.
UR - http://www.scopus.com/inward/record.url?scp=0029769827&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0029769827&partnerID=8YFLogxK
U2 - 10.1109/7.481282
DO - 10.1109/7.481282
M3 - Article
AN - SCOPUS:0029769827
VL - 32
SP - 419
EP - 425
JO - IEEE Transactions on Aerospace and Electronic Systems
JF - IEEE Transactions on Aerospace and Electronic Systems
SN - 0018-9251
IS - 1
ER -