http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-104077469-B
Outgoing Links
Predicate | Object |
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classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/G06F19-00 |
filingDate | 2014-05-28-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
grantDate | 2017-09-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
publicationDate | 2017-09-01-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
publicationNumber | CN-104077469-B |
titleOfInvention | Segment iteration remaining time method of estimation based on prediction of speed |
abstract | The invention discloses a kind of segment iteration remaining time method of estimation based on prediction of speed, it is known constant value by missile flight velocity magnitude, utilize section iterative method, according to the primary condition of guided missile and target relative movement, since the starting point of the first segmentation of segmentation, the primary condition of starting point correspondence guided missile and target relative movement, obtains the corresponding states variable of each segmentation section end.The present invention can effectively solve real missile because velocity magnitude is not controlled, and the flying speed size for causing guided missile is time-varying, the problem of further resulting in remaining time and be difficult to accurate estimation;Compared with existing segment iteration remaining time method of estimation, remaining time estimated accuracy is significantly improved;Estimated accuracy is improved, preferably resolve in the case of current big angle of lead based on proportional guidance law/control the remaining time method of estimation of proportional guidance law to be only applicable to the problem of missile flight velocity magnitude is this more satisfactory situation of known constant value with angle. |
priorityDate | 2014-05-28-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 15.