Deception Antenna System Using Vertical Separation
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Solution Overview
Problem
Existing methods for generating deception signals to counter monopulse radars are ineffective on small aircraft due to the requirement for a minimum distance between antennae to create a cross-eye base, which is not feasible on helicopters and other small aircraft.
Innovation Solution
A method and apparatus using two antennae mounted with a relative height difference of at least 2 meters, converting RF signals to IF, storing and compensating phase and amplitude differences, and introducing controlled imbalances and phase shifts to simulate a cross-eye effect, allowing effective deception signals to be generated even with antennae closer than 10 meters apart.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If two deception antennae are mounted at a large distance to create a cross-eye base, then the deception effect is improved, but the device cannot be mounted on small aircraft
Solution Approach 1:
The patent transitions from a horizontal arrangement of antennae (planar dimension) to a vertical arrangement (elevation dimension). By mounting antennae at different heights rather than separating them horizontally, the system creates a cross-eye base effect without requiring large horizontal distances, thus enabling installation on small aircraft with limited wing span.
Solution Approach 2:
The patent changes the geometric parameters of the antenna configuration by introducing height difference as a new dimension. Instead of relying solely on horizontal separation distance, the system uses vertical separation (height difference) to create the necessary cross-eye base effect, thereby achieving the same deception performance with smaller overall dimensions.
2Reliability
If two deception antennae are mounted at a large distance to create a cross-eye base, then the deception effect is improved, but the device complexity increases
Solution Approach 1:
By utilizing the vertical dimension for antenna placement, the patent eliminates the need for complex horizontal mounting structures that would be required to maintain large separations between antennae on the aircraft wings. The vertical arrangement can be achieved using standard height-differentiated mounting points on the aircraft fuselage or vertical stabilizer.
3Adaptability or versatility
If the distance between antennae is reduced for small aircraft, then the device can be mounted on small aircraft, but the cross-eye base effect is weakened
Solution Approach 1:
The patent compensates for the reduced horizontal distance by introducing vertical separation between antennae. This dimensional transition allows the system to maintain an effective cross-eye base configuration even when the overall antenna separation is limited by the small dimensions of helicopters and other compact aircraft.
Solution Approach 2:
The system changes the spatial parameters by prioritizing height difference over horizontal separation. By adjusting the vertical positioning of antennae, the patent maintains the necessary geometric relationship for cross-eye base effect while accommodating the size constraints of small aircraft platforms.
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 solution effectively deceives monopulse radars by creating a virtual cross-eye base comparable to a longer physical base, disrupting target locking and tracking, while being robust, cost-effective, and easily mountable on existing aircraft.
Implementation Method 1
The so-called 'bounce effect' technique is also known, this consisting in directing these deception signals towards the ground, making use of their reflection
Data Source
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AI summary
Method for generating and transmitting deception signals to location devices consisting of tracking monopulse radars and associated apparatus to be installed on aircraft in particular of the rotary-blade type. The deception signals generated and sent to the tracking radar cause an angular deception, namely the aircraft is viewed by the radar in a direction different from the real direction.