Projectile Guidance via Transverse Thrust for Range and Accuracy
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Artillery-fired projectiles face limitations in range and accuracy, leading to increased operational costs and risks in combat situations due to their fixed trajectory and sensitivity to atmospheric conditions, which existing systems like integrated rocket systems and control surfaces fail to adequately address.
Innovation Solution
A projectile system equipped with an auxiliary control system that includes a guidance system and a transverse propulsion system, allowing for adjustable trajectory and range extension through the activation of these systems to ensure precise targeting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of stationary object
If integrated rocket systems are added to extend range, then the range of the projectile is improved, but the accuracy is not necessarily improved and the system complexity increases
Solution Approach 1:
The system is divided into separate functional modules: a propulsion module for range extension and a guidance module for accuracy control. This segmentation allows each module to be optimized independently, resolving the contradiction between range extension and system complexity by providing modular integration rather than a monolithic system.
Solution Approach 2:
A guidance system acts as an intermediary between the propulsion system and the target, enabling precise control of the projectile's trajectory. This intermediary component allows the system to achieve both extended range through propulsion and high accuracy through active guidance, without requiring the entire system to be overly complex.
2Measurement precision
If control surfaces are added to guide the projectile, then the accuracy is improved, but the weight and complexity of the projectile increase substantially
Solution Approach 1:
The patent replaces traditional mechanical control surfaces with an active guidance system that uses thrusters or propulsion elements to control the projectile's trajectory. This substitution eliminates the need for large, heavy control surfaces while achieving comparable or superior accuracy through controlled propulsion adjustments during flight.
Solution Approach 2:
The system changes the control parameter from aerodynamic surface area (which would require large, heavy surfaces) to propulsion force magnitude and direction. By controlling the magnitude and vector of thrust from small thrusters, the system achieves accurate trajectory control without the weight penalty of large control surfaces.
3Ease of operation
If aerodynamic control surfaces are deployed to modify trajectory, then the guidance capability is improved, but the drag increases and reduces the range of the projectile
Solution Approach 1:
The patent substitutes aerodynamic control surfaces with a propulsion-based guidance system that uses small thrusters to adjust the projectile's trajectory. This replacement eliminates the continuous drag associated with deployed control surfaces, as the thrusters provide brief, targeted impulses for course correction without creating sustained aerodynamic resistance.
Solution Approach 2:
The guidance system employs periodic, impulsive thrust from small thrusters rather than continuous aerodynamic control. This periodic action provides the necessary trajectory adjustments while minimizing energy loss, as the thrusters operate only when needed for course correction rather than continuously creating drag like deployed control surfaces would.
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
The auxiliary control system enhances the range and accuracy of projectiles, reducing the need for prolonged engagements and minimizing logistical burdens by enabling precise targeting and improved trajectory control, thus enhancing combat effectiveness and safety.
Implementation Method 1
a rocket engine configured to couple to a projectile and propel the projectile to an intended target according to a guidance kit
Data Source
AI summary
Methods and apparatus for projectile systems according to various aspects of the present invention comprise a projectile attached to an auxiliary control system. The auxiliary control system may include a control system and a transverse propulsion system. The control system controls the trajectory of the projectile system, for example by activating the transverse propulsion system to adjust the trajectory.