Missile Steering and Drag Reduction via Lateral Thrusters
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Solution Overview
Problem
Current missile designs face limitations in steerability for short-range missions and drag reduction for long-range missions, with existing systems failing to effectively address these issues simultaneously, necessitating a unified solution for improved performance and adaptability across various firing platforms.
Innovation Solution
A combined steering and drag reduction device featuring a pressurized-gas generator with lateral thrusters, including nozzles and stabilizing chambers, and a directional-control system, allowing for modular attachment to missiles to enhance trajectory control and reduce drag, comprising four lateral thrusters arranged on the base of the missile to control pitch, yaw, and roll, and inject gas downstream to minimize aerodynamic disturbances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If lateral thrusters are used to improve steerability for short-range missions, then trajectory control capability is improved, but drag increases due to additional components and aerodynamic disturbances
Solution Approach 1:
The device dynamically switches between two operational modes: for short-range missions, lateral thrusters are activated to provide enhanced steerability during acceleration phase; for long-range missions, the thrusters remain inactive and the afterbody configuration optimizes for reduced drag. This dynamic adaptation resolves the contradiction by optimizing performance for specific mission types rather than compromising both.
Solution Approach 2:
The propulsion system is segmented into two independent subsystems: the main rocket motor for primary propulsion and the lateral thrusters for auxiliary steering control. This segmentation allows each subsystem to be optimized independently - the main motor for efficiency and range, while the lateral thrusters provide targeted steering enhancement only when needed, minimizing their drag penalty impact.
2Duration of action of moving object
If aerodynamic control surfaces are used to reduce drag for long-range missions, then range is improved, but steerability deteriorates during the acceleration phase
Solution Approach 1:
The control system dynamically selects between aerodynamic control surfaces and lateral thrusters based on flight phase. During acceleration phase where aerodynamic surfaces are ineffective, lateral thrusters provide superior steerability. For cruise phase in long-range missions, aerodynamic surfaces take over for efficient drag-reduced control, maximizing range while maintaining steerability throughout the mission profile.
Solution Approach 2:
The missile control system achieves multi-functionality by integrating both aerodynamic control surfaces and lateral thrusters, allowing it to perform both drag-reduced cruise control and high-agility acceleration-phase steering with a single unified system. This universal approach eliminates the need to choose between range optimization and steerability enhancement.
3Reliability
If dedicated systems are designed for either short-range or long-range missions, then mission-specific performance is optimized, but system complexity and number of equipment types increase
Solution Approach 1:
The missile platform employs a universal control system that integrates both lateral thrusters and aerodynamic control surfaces, enabling a single equipment type to perform both short-range high-agility missions and long-range efficient cruise missions. This multi-functional design eliminates the need for separate dedicated systems, reducing overall equipment complexity while maintaining optimized performance for both mission types.
Solution Approach 2:
The system dynamically adapts its operational characteristics based on mission requirements through software control, switching between thruster-dominated mode for short-range missions and aerodynamic-surface-dominated mode for long-range missions. This dynamic reconfiguration allows one physical system to replace multiple dedicated systems, reducing complexity while preserving mission-specific optimization.
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 device achieves enhanced steerability for short-range missions with high agility and extended range for long-range missions by controlling the missile's trajectory and reducing drag, making it suitable for diverse mission profiles and platforms.
Implementation Method 1
at least one nozzle, configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis
Implementation Method 2
at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis
Data Source
AI summary
A combined steering and drag reduction device for a missile is disclosed. The device includes a base and an upper part which are arranged in succession along a main axis of navigation of the missile. Advantageously, the device also includes a pressurized-gas generator and at least one lateral thruster having at least one nozzle configured to deliver a thrust, by expanding gas transmitted by the generator and oriented along an axis substantially perpendicular to the main axis. The at least one lateral thruster also has at least one stabilizing chamber configured to expand the gas transmitted by the generator and expel it through an outlet section of the base substantially perpendicular to the main axis.