Lateral Nozzle Steering System with Single Obturator
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Solution Overview
Problem
Existing guidance systems for missiles using lateral gaseous jets are complex, bulky, and generate significant stresses and vibrations due to the need for multiple obturating devices, which complicates production and adjustment, and results in suboptimal dynamic performance and precision control.
Innovation Solution
A system with pairs of lateral nozzles aligned along the same axis, each controlled by a single controllable obturating device capable of modulating thrust in two senses, eliminating the need for mechanical connections between valves and simplifying production, allowing for direct-thrust and attitude-control along multiple axes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If multiple obturating devices are used for each nozzle, then precise thrust control in multiple orientations is achieved, but device complexity and bulkiness increase
Solution Approach 1:
The patent combines two obturating functions into a single obturating device that can control thrust in two opposite directions along the same axis. This single device replaces what would traditionally require two separate obturating devices, thereby reducing system complexity while maintaining the capability for precise thrust control in multiple orientations.
Solution Approach 2:
The obturating device is designed with multi-functionality, enabling it to control gas flow to multiple nozzles and regulate thrust in opposite directions along a single axis. This universal design allows one device to perform multiple functions that would otherwise require separate components, reducing overall system complexity.
2Ease of operation
If rectilinear needle-like movement of obturator is used, then thrust modulation is achieved, but high dynamic performance cannot be achieved with reasonable mass and spatial requirements
Solution Approach 1:
Instead of using rectilinear needle-like movement of the obturator, the patent inverts the approach by using rotational movement of a single obturating device to control multiple nozzles. This rotational mechanism achieves thrust modulation while providing superior dynamic performance with reduced mass and spatial requirements compared to traditional rectilinear actuation systems.
3Stability of the object's composition
If mechanical connections between valves are made to ensure constant flow rate, then flow stability is achieved, but production complexity and adjustment difficulty increase
Solution Approach 1:
The patent merges the flow control functions of multiple valves into a single obturating device that inherently maintains constant flow rate to multiple nozzles through its unified design. This eliminates the need for complex mechanical connections between separate valves, significantly simplifying production while maintaining flow stability.
4Ease of operation
If electromagnetic actuators with reduction gear are used, then thrust control is achieved, but device bulkiness and power requirements increase
Solution Approach 1:
The patent replaces traditional electromagnetic actuators with reduction gear with a streamlined obturating device that uses rotational movement directly controlled by electromagnetic actuators without mechanical reduction gears. This substitution eliminates bulky mechanical components while maintaining precise thrust control capability, significantly reducing actuator mass.
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 system achieves simplified production, reduced stress, and improved dynamic performance by using a single obturating device per nozzle pair, enabling precise thrust modulation and efficient guidance along roll, pitch, and yaw axes with reduced complexity and weight.
Implementation Method 1
a gas generator (5) capable of being connected to lateral nozzles (7) by means of movable obturating devices (8)... control the flow of the gases from the generator through said nozzles
Implementation Method 2
lateral nozzles which are provided on board the missile and can be supplied with gas from either a gas generator of the main rocket motor or a gas generator specially provided for this purpose. Thus, this results in lateral gas jets which generate transverse propulsive forces
Implementation Method 3
movable obturating devices which are provided between the generator and the nozzles, and control the flow of the gases from the generator... alter the cross section of flow for the gases flowing through the lateral nozzles
Implementation Method 4
the lines of action of such transverse forces pass through the centre of gravity of the missile... and in this instance the missile is said to be direct-thrust-controlled... the lines of action of said transverse forces may pass the axis of the missile at points other than the centre of gravity. Similarly to conventional aerodynamic motivators, said transverse forces, then, create torques allowing the missile to be attitude-controlled
Data Source
AI summary
System for steering a flying object using pairs of lateral nozzles—It comprises a gas generator (5) capable of being connected to lateral nozzles (7) via moveable plug devices (8), controlling the flow of gases coming from the generator through said nozzles. The lateral nozzles (7) are associated with at least one pair (P1, P2, P3, P4) such that the nozzles of the pair are aligned in a given axis (A1) and arranged opposite to each other, and, between the two aligned nozzles of the pair, a single controllable plug device (8) is provided, connected to said generator (5) and capable of controlling the flow of gases through said nozzles (7) in both directions.