Three-Thruster Divert Control for Kinetic Energy Vehicle Weight Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current kinetic energy vehicles with thruster systems lack efficient course correction mechanisms for high-speed target engagement and diversion, particularly for long-range ballistic missiles, as existing systems are costly and heavy due to multiple thrusters.
Innovation Solution
A kinetic energy vehicle equipped with a divert thruster system featuring three thrusters circumferentially spaced around the perimeter and an attitude control system in a bowtie configuration, both operatively coupled to a solid rocket motor, allowing for precise translation and orientation adjustments using pressurized gases, with a control loop and sensor system for guidance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple thrusters are used for course correction and attitude control, then control precision and versatility are improved, but vehicle weight and cost increase
Solution Approach 1:
Each thruster in the three-thruster divert system is capable of producing thrust in multiple directions through differential firing combinations. The same thrusters can be used for both divert control (course correction) and attitude control (orientation), eliminating the need for separate dedicated thruster systems and reducing overall vehicle weight while maintaining full control versatility
Solution Approach 2:
The system dynamically reconfigures thruster firing patterns based on control requirements. By selectively activating different combinations of the three thrusters, the system can achieve six independent divert thrust vectors and multiple attitude control moments, allowing a fixed physical configuration to provide dynamic, multi-directional control capability without adding physical complexity
2Adaptability or versatility
If multiple thrusters are used for course correction and attitude control, then control precision and versatility are improved, but system complexity and cost increase
Solution Approach 1:
The three thrusters serve dual purposes: they function as divert thrusters for course correction and as attitude control thrusters for orientation management. This universal usage reduces the total number of thrusters from what would traditionally be required for separate divert and attitude systems, thereby simplifying the overall system architecture and reducing complexity
Solution Approach 2:
The patent merges the divert control system and attitude control system into a single integrated thruster system. By combining these two traditionally separate functions into one unified three-thruster system, the patent reduces component count, simplifies system integration, and lowers overall system complexity while maintaining full control capability
3Device complexity
If three divert thrusters are used instead of traditional four-thruster configuration, then system complexity is reduced, but divert control capability must be maintained
Solution Approach 1:
The three thrusters are positioned asymmetrically at 120-degree intervals around the vehicle perimeter, creating an equilateral triangle configuration. This asymmetric arrangement, while simpler than a traditional cruciform, provides symmetric control authority in all radial directions through differential firing, maintaining full divert capability with fewer components
Solution Approach 2:
The system uses differential firing of the three thrusters to create six independent thrust vectors (by firing thrusters in different combinations and sequences). This partial utilization of the thruster combinations (not all firing simultaneously at full power) provides excessive control authority beyond what a single thruster per axis would provide, ensuring reliable divert capability while using fewer thrusters
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
Enables flexible and efficient translation and orientation control of the vehicle, reducing the number of thrusters while maintaining or improving performance, allowing for effective engagement and diversion of targets with reduced weight and cost.
Implementation Method 1
burning a solid rocket motor to produce pressurized gasses
Implementation Method 2
The three thrusters are configured to translationally divert the vehicle in any direction perpendicular to a longitudinal axis of the vehicle, by firing one or a combination of the thrusters
Implementation Method 3
the attitude control thrusters of each pair having radial thrust components in an outward radial direction and circumferential thrust components in opposite circumferential directions
Data Source
AI summary
A kinetic energy vehicle (or warhead) has a divert thruster system and an attitude control system, both operatively coupled to receive pressurized gasses from a solid rocket motor that is operatively coupled to both systems. The divert thruster system may have three divert thrusters evenly spaced around a circumference of the vehicle, offset 120 degrees from each other. The divert thrusters are located at a longitudinal (axial) location along the vehicle at or close to a center of gravity of the vehicle. In addition the vehicle may have an aft axial thrusters that may be used in maneuvering the vehicle.