Composite impact vector control based on Apollo descent guidance

ERER K. S., TEKIN R., ÖZGÖREN M. K.

Chinese Journal of Aeronautics, cilt.35, sa.7, ss.67-74, 2022 (SCI-Expanded) identifier identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 35 Sayı: 7
  • Basım Tarihi: 2022
  • Doi Numarası: 10.1016/j.cja.2021.07.009
  • Dergi Adı: Chinese Journal of Aeronautics
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Aerospace Database, Communication Abstracts, Compendex, INSPEC, Metadex, Directory of Open Access Journals, Civil Engineering Abstracts
  • Sayfa Sayıları: ss.67-74
  • Anahtar Kelimeler: Impact angle, Impact plane, Impact vector, Three-dimensional missile guidance, Trajectory shaping
  • Orta Doğu Teknik Üniversitesi Adresli: Evet

Özet

© 2021 Chinese Society of Aeronautics and AstronauticsA new three-dimensional missile guidance law to control the impact vector against a stationary target is proposed. The composite guidance law has two well-known components: Apollo descent guidance and trajectory shaping guidance. These respectively linear and planar guidance laws are combined to achieve a specified impact direction. The main idea is to define an impact plane and to steer the missile onto this plane using Apollo descent guidance while concurrently performing trajectory shaping with reference to the impact plane. The resulting guidance law is expressed by a single equation in vector form, which is straightforward to implement. Because it originates from an optimal formulation, the performance of the proposed technique is expected to be satisfactory. This is confirmed by comparative simulation runs, which also involve the method known as generalized explicit guidance.