SOLUTION OF THE PYRO-RECOCKING SYSTEM OF THE AUTOMATIC CANNON
Abstract
The paper deals with the problem of the recocking of rhe automatic cannon (e.g. in the aircraft in case of its stoppage). Pyrocartridges are utilized for this case. The theory enabling the theoretical solution of this case is presented. It consists of three periods including the only burning of the propellant, the burning combined with the flow of gases into the gas cylinder and this flow after the end of propellant burning. The losses during the gas flow are discussed. The comparison of the theoretical solution with results of experiments is shown. Problems of propellant burning have been solved by the first author, the flow of gases into the cylinder and the acceleration of the weapon mechanism by the second author.
Downloads
Published
Issue
Section
License
This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.
Authors who publish with this journal agree to the following terms:
1. Authors retain copyright and grant the journal right of first publication with the work simultaneously licensed under a Creative Commons Attribution License that allows others to share the work with an acknowledgement of the work's authorship and initial publication in this journal.
2. Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the journal's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgement of its initial publication in this journal.
3. Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work.
Users can use, reuse and build upon the material published in the journal for any purpose, even commercially.
