Multi-Pulse Rocket Motor Radial Propellant Arrangement
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Solution Overview
Problem
Existing two-pulse rocket motors face limitations in propellant length, initial thrust, and structural weight due to axial arrangement of propellants and igniters, which affect maneuverability and durability, especially when targeting remote targets.
Innovation Solution
The design incorporates a multi-pulse rocket motor with internal-burning type propellants, a barrier membrane system for heat protection, and independent igniters, allowing for improved design flexibility and manufacturability by unitizing each pulse into modular units connected via forward and rearward joints, enabling efficient thrust distribution and reduced structural weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of stationary object
If the first propellant and second propellant are arranged axially in the rocket motor, then the rocket motor length is reduced for equipment and storage, but the first propellant cannot have enough length and initial thrust cannot be obtained
Solution Approach 1:
The patent transitions from axial arrangement to radial arrangement of propellant grains. The first and second propellant grains are positioned radially outward from a central axis, with burn surfaces facing each other across the axis. This dimensional change allows sufficient propellant length/area for initial thrust while keeping the motor compact in overall length.
Solution Approach 2:
The patent employs a nested configuration where the first and second propellant grains are arranged concentrically around a central axis, with the barrier membrane and igniters nested within the motor assembly. This nesting allows multiple functional components to occupy overlapping spatial zones, maximizing propellant area within a compact motor envelope.
2Ease of operation
If the first igniter and second igniter are arranged in series axially with long cantilever structure, then the igniters can reach their respective propellants, but the structure needs strengthening against vibration which increases structural weight
Solution Approach 1:
The igniters are repositioned from axial series arrangement to radial arrangement at the central axis. Both igniters extend radially outward from the axis to reach their respective propellant grains, eliminating the need for long axial cantilevers. This reduces structural weight while maintaining igniter functionality.
Solution Approach 2:
The patent merges the igniter mounting location to a common central axis position, where both igniters share the same mounting region rather than requiring separate axial positions. This consolidation reduces overall igniter support structure weight while ensuring both igniters can reach their target propellants.
3Adaptability or versatility
If the barrier membrane is made thin for flexibility, then it can conform to propellant shapes, but breakability and durability at the time of second igniter operation are compromised
Solution Approach 1:
The barrier membrane is constructed as a composite material combining organic polymer base material with inorganic fiber reinforcement (such as glass fiber, quartz fiber, or alumina). This composite structure provides both the flexibility needed to conform to propellant surfaces and the thermal durability required to withstand second igniter operation without breaking.
Solution Approach 2:
The barrier membrane exhibits local quality variations through its composite construction, with different regions or layers having different properties. The inorganic fiber reinforcement provides localized strength at critical stress points while the polymer matrix maintains overall flexibility and conformability to propellant geometry.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach enhances initial thrust, maintains propellant area, ensures igniter strength, and improves maneuverability by allowing for flexible design and manufacturing of multi-pulse rocket motors with reduced weight and increased propellant filling efficiency.
Implementation Method 1
a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter
Implementation Method 2
an igniter arranged at an end surface of the propellant
Data Source
AI summary
A pulse unit of a multi-pulse rocket motor has: a propellant in an internal-burning type shape or an internal-end-burning type shape that is loaded within a motor case; an igniter arranged at an end surface of the propellant; a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter; a forward joint arranged at a forward end of the motor case; and a rearward joint arranged at a rearward end of the motor case. The forward joint is formed so as to be connectable with the rearward joint of another pulse unit. The rearward joint is formed so as to be connectable with the forward joint of yet another pulse unit.