Glide slope antenna system

Claim 2

In combination with an aircraft having a plurality of landing gear doors, each of said doors having a leading edge with respect to the longitudinal axis of said aircraft, antenna system comprising: a track antenna, said track antenna disposed in the leading edge of one of said landing gear doors, said track antenna remaining shielded from the exterior space surrounding said aircraft when said one of said landing gear doors is in a closed position and capable of receiving a horizontally polarized signal when said one of said landing gear doors is in an open position.

Claim 3

The combination according to claim 1 wherein said track antenna comprises a slot antenna.

Claim 4

The combination according to claim 1 including a further track antenna disposed in the leading edge of a second of said plurality of landing gear doors.

Claim 5

The combination according to claim 1 wherein said one of said landing gear doors comprises a nose gear wheel well door.

Claim 6

The combination according to claim 3 wherein said one of said landing gear doors and said second of said plurality of landing gear doors comprise opposing aircraft nose gear doors.

Claim 7

In combination with an aircraft having a landing gear and a plurality of landing gear doors which are extended in a generally vertical plane with respect to the runway surface when said landing gear is extended and in a generally horizontal plane with respect to the runway surface when said gear is retracted, an antenna system comprising a capture antenna arranged in a first of said plurality of landing gear doors and a track antenna arranged in said first of said landing gear doors, said capture and track antennas polarized in orthogonal planes so that said track antenna is horizontally polarized (and said capture antenna is vertically polarized) when said first of said plurality of landing gear doors is extended in said generally vertical plane relative to the runway surface.

Claim 8

In combination with an aircraft having a landing gear and a plurality of landing gear doors which are extended in a generally vertical plane with respect to the runway surface when said landing gear is extended and in a generally horizontal plane with respect to the runway surface when said gear is retracted, an antenna system comprising a capture antenna arranged in a first of said plurality of landing gear doors and a track antenna arranged in said first of said landing gear doors, said capture and track antennas polarized in orthogonal planes so that said track antenna is horizontally polarized (and said capture antenna is vertically polarized) when said first of said plurality of landing gear doors is extended in said generally vertical plane relative to the runway surface.

Claim 9

In an aircraft including a plurality of landing gear wheel well doors, a dual channel instrument landing system comprising a first channel having first antenna means arranged in a first of said plurality of landing gear wheel well doors and adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, first receiving means coupled to said first and second antenna outputs, and a second channel having second antenna means in a second of said plurality of landing gear wheel well doors and adapted to receive radiant energy in said first and second angularly separated planes of polarization and to supply third and fourth antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, second receiving means coupled to said third and fourth antenna outputs.

Claim 10

In an aircraft including a plurality of landing gear wheel well doors, a dual channel instrument landing system comprising a first channel having first antenna means arranged in a first of said plurality of landing gear wheel well doors and adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, first receiving means coupled to said first and second antenna outputs, and a second channel having second antenna means in a second of said plurality of landing gear wheel well doors and adapted to receive radiant energy in said first and second angularly separated planes of polarization and to supply third and fourth antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, second receiving means coupled to said third and fourth antenna outputs.

Claim 11

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and tRack antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft.

Claim 12

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and tRack antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft.

Claim 13

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna output corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and track antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft, and wherein said plurality of slots are spaced one-half wavelength apart and are fed 180* out of phase.

Claim 14

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna output corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and track antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft, and wherein said plurality of slots are spaced one-half wavelength apart and are fed 180* out of phase.

Claim 15

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and track antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft, and including further hybrid circuit means coupled to said plurality of slot elements to provide phasing and amplitude balance between said slot elements.

Claim 16

In an aircraft landing gear wheel well door, antenna means adapted to receive radiant energy in first and second angularly separated planes of polarization and to supply first and second antenna outputs corresponding respectively to radiant energy thereby received in said first and second planes of polarization, receiving means, and hybrid circuit means coupled between said antenna means and said receiver means, said antenna means comprising capture and track antennas, said capture antenna including a plurality of slot elements arranged parallel to the longitudinal axis of the aircraft, and including further hybrid circuit means coupled to said plurality of slot elements to provide phasing and amplitude balance between said slot elements.