US 12,454,928 B2
Multistage variable burning rate solid rocket motor and forming method
Fengnan Guo, Liaoning (CN); Yanxiang Ren, Liaoning (CN); Fengrui Li, Liaoning (CN); Hua Zhang, Liaoning (CN); Yiming Li, Liaoning (CN); Wenyu Li, Liaoning (CN); Hongfeng Ji, Liaoning (CN); and Lin Fu, Liaoning (CN)
Assigned to DALIAN UNIVERSITY OF TECHNOLOGY, Liaoning (CN)
Filed by DALIAN UNIVERSITY OF TECHNOLOGY, Liaoning (CN)
Filed on Nov. 27, 2024, as Appl. No. 18/962,602.
Claims priority of application No. 202410018453.0 (CN), filed on Jan. 5, 2024.
Prior Publication US 2025/0084806 A1, Mar. 13, 2025
Int. Cl. F02K 9/36 (2006.01); F02K 9/12 (2006.01); B33Y 80/00 (2015.01)
CPC F02K 9/12 (2013.01) [F02K 9/36 (2013.01); B33Y 80/00 (2014.12)] 8 Claims
OG exemplary drawing
 
1. A multistage variable burning rate solid rocket motor, comprising a combustion chamber case, an insulator, a propellant grain, a fiber skeleton structure and a fixed fiber, wherein
the insulator is bonded on an inner surface of the combustion chamber case;
the fiber skeleton structure is arranged in the combustion chamber case and composed of a plurality of axial fibers perpendicular to an end surface of a main grain and radial fibers parallel to the end surface of the main grain, wherein front ends of the axial fibers are connected with the insulator, and ends of the axial fibers are connected with the fixed fiber; and the radial fibers are distributed along the plurality of axial fibers;
the propellant grain is filled in the combustion chamber case.