Aircraft instrument landing system
阅读：336发布：2021-09-06
专利汇可以提供Aircraft instrument landing system专利检索，专利查询，专利分析的服务。并且Precision guidance of aircraft throughout a great volume of positions, and with spectrum economy, is achieved with coordinated scanning of coarse and fine coverage localizer antennas and coarse and fine glide-path antennas. The scan coordination is predetermined for sequential traversals of the useful scan sectors, microwave transmission through the several antennas being effected in the sequence of the scans. Each such transmission includes modulation not only in accordance with the antenna scan angle but also with the direction of movement in the scan sector. The aircraft receiver means detects the aircraft position by the detected modulation and/or reception timing of each directionally transmitted beam. General position is determinable from reception of the wide-angle (coarse) scanning beams. Precise guidance in the vicinity of a predetermined lowangle glide path is derivable from the beams transmitted through the narrow scan antennas.，下面是Aircraft instrument landing system专利的具体信息内容。
1. An aircraft instrument landing system comprising: plural localizer directional scanning antennas; plural glide path directional scanning antennas; the plural localizer directional scannIng antennas including at least two antenna means scanned through two sectors of different angular scan amplitudes, and the plural glide path directional scanning antennas including at least two antenna means scanned through two sectors of different angular scan amplitudes; means including at least one source of microwave energy for causing said localizer and glide path directional scanning antennas to transmit microwave energy in a predetermined time sequence, whereby energy may be received from one of said antennas at a time; means for modulating the microwave energy being transmitted by each antenna, at least one component of the modulation being varied in a predetermined relation to its direction of transmission; and radio receiving equipment for receiving microwave energy transmitted from said antennas, said radio receiving equipment comprising means for identifying the one of said antennas which is transmitting by a characteristic of its radiated energy, and means responsive to the variation in at least one modulation component of the received energy for denoting the position of the receiving means relative to the useful scan sector of the antenna from which the energy is being received.
2. An aircraft instrument landing system as defined in claim 1, said instrument landing system including means for synchronizing the scanning of said antennas in a predetermined time-relationship of their useful scan sectors within which they transmit microwave energy.
3. An aircraft instrument landing system as defined in claim 2, wherein said narrow azimuth scanning antenna and said narrow elevation scanning antenna transmit microwave energy more frequently than their respective wide scanning antennas.
4. An aircraft instrument landing system as defined in claim 2, at least one of said scanning antennas comprising a resiliently suspended directive antenna, means for imparting to said antenna oscillatory movement wherein the resilience and mass of the suspended system are relied upon, and means for limiting the times at which microwave energy is transmitted through said antenna to those times when said antenna is traversing a predetermined useful scan sector substantially narrower than the angle traversed by said oscillatory movement.
5. An aircraft landing system as defined in claim 1, wherein said scanning of each beam is oscillatory, and said means for modulating the microwave energy being transmitted by each antenna, at least one component of the modulation being varied in a predetermined relation to its direction of transmission, comprises means for imparting to the microwave energy a modulation component distinguishing one direction of swing in its oscillation from the opposite direction of swing, whereby aircraft positional information is unambiguously derivable from the symmetry or assymmetry with respect to time of the occurrences of reception of the beam resulting from the opposite swings thereof.
6. An aircraft instrument landing system as defined in claim 2, said means for causing said localizer and glide path directional scanning antennas to transmit microwave energy including means for imparting to the energy transmitted through each of said antennas a predetermined distinguishing characteristic whereby said energy is distinguishable from the energy transmitted through the other antennas.
7. An aircraft instrument landing system as defined in claim 6, said means for imparting a predetermined distinguishing characteristic comprising means for impressing on the microwave energy a beam-identity modulation component having a modulation frequency different from the beam-identity modulation components impressed on the microwave energy transmitted through the other antennas, said beam identity modulation components being distinguishable in at least one respect from the modulation components varied according to antenna transmitting direction.
8. An aircraft instrument landing system as defined in clAim 6, said means for modulating the microwave energy being transmitted by each antenna with at least one component of the modulation being varied in predetermined relation to its direction of transmission comprising means for impressing upon the microwave energy to be transmitted a phase reference modulation component and a variable phase modulation component, the phase displacement between said variable phase component and said reference phase component being varied in predetermined relation to the direction of radiation of said antenna.
9. An aircraft instrument landing system as defined in claim 8, wherein the frequency of said reference phase component and the frequency of said variable phase component are so related to each other that the products obtained by multiplication of some of said frequencies by integral factors, are of equal frequency whereby they may be phase compared at such frequency after multiplication.
10. An aircraft instrument landing system as defined in claim 6, said identifying means in said receiving system comprising means selectively responsive to the beam identity modulation component being received at any given time for conditioning the receiving system to interpret unambiguously the changing modulation component of the scanning antenna denoted by said beam identity modulation component.
11. An aircraft instrument landing system as defined in claim 10, said means in the radio receiving means for denoting the position of the receiving means relative to the useful scan sector of the antenna from which the energy is being received comprising means for measuring and averaging the phase variations of said one component of the modulation as it varies in its predetermined relation to the direction of transmission.
12. An aircraft receiver for an instrument landing system wherein synchronized recurrently scanning transmitting antennas are provided for scanning their guidance beams through predetermined useful sectors of elevation angles and azimuthal angles from a runway heading, at least two antennas of different beam widths and different scan angular amplitudes being provided for guidance within at least one of said sectors, one scan width being greater than the other, microwave energy being transmitted through one after another of said scanning transmitting antennas within successive predetermined time periods respectively allocated thereto, the energy transmitted through each of said scanning antennas being modulated with a modulation component varying according to the angular direction of its directive beam axis, and the transmitted energy being so varied as to impart thereto a characteristic distinguishing it from the other guidance beams, said aircraft receiver comprising: means for selecting and amplifying energy received from any one of said synchronized recurrently scanning transmitting antennas, means for automatically controlling the amplification of said selecting and amplifying means and producing a detected output variation from a predetermined threshold strength to a predetermined maximum strength and back to said threshold strength as the directive radiation pattern traverses the aircraft''s position, means for determining the average of the antenna axis directions traversed while the detected output varies from the threshold strength up to maximum strength and back to said threshold strength, and means for readjusting the amplification of said selecting and amplifying means upon receiving energy from a different one of the scanning transmitting antennas and producing detected output variations resulting from the microwave energy received therefrom which are substantially equal to the variations of detected output strength from the antenna from which the energy was previously received.
13. An aircraft receiver for an instrument landing system wherein plural directional beams of microwave energy are scanned through predetermined useful scan sectors encompassing landing paths of various desired glide angles for aircraft, the plural beams, each distinguishable from the others, being transmitted in different time slots, and the energy of each beam being continuous-wave modulated according to the angular position of the beam, said plural beams including at least two beams of unequal angular scans scanned in the same scan aspect, said receiver comprising: means for receiving, amplifying and demodulating the continuous-wave modulated energy from each beam during its impingement on the aircraft, a plurality of sets of circuits each including means for storing and utilizing electrical signals representing beam angles, one such set of circuits being provided for each of the plural directional beams to be received successively during an aircraft approach and landing on a predetermined runway served by the plural directional beams, means responsive to the distinguishing characteristics of each beam for selectively activating, during the reception of that beam, the respective one of said sets of circuits, means for selectively responding to the received and detected output of said receiving, amplifying and demodulating means only during part of the time when one beam is being received, that part of the time being when the signal strength of reception of that beam is within a predetermined ratio to the maximum signal strength reached as the beam''s maximum radiation direction passes over the aircraft and its receiver, and means responsive to said selectively responding means for supplying to the respective signal storing and utilizing means signals representative of the angular position of the received beam.
14. An aircraft receiver for an instrument landing system as defined in claim 13, said means responsive to the distinguishing characteristics of each beam for selectively activating the respective one of said sets of circuits comprising a selective filter for accepting a demodulation component denoting the beam received, and circuit activating means responsive to the output of said filter.
15. An aircraft receiver for an instrument landing system as defined in claim 13, said means for selectively responding to the received and detected output only during part of the time when one beam is being received comprising means so regulating the gain of said receiving, amplifying and demodulating means as to cause a detected output resulting from the received beam to rise to a maximum strength substantially equal to a predetermined maximum signal level, and means for passing demodulated components derived from the beam into said means for supplying signals representative of the angular position of the received beam only when the strength of said detected output is above a threshold value which is a predetermined substantial fraction of said predetermined maximum signal level.
16. An aircraft instrument landing system comprising: at least one localizer directional scanning antenna; at least one glide path directional scanning antenna; means coupled to each of said antennas for generating a directive beam of microwave energy and sweeping it alternately in one sense and the opposite sense through a predetermined useful scan sector; at least one further directional scanning antenna scanned in the same directional aspect as one of said localizer and glide path directional scanning antennas but having a different angular scan therefrom; means for establishing a time-shared transmitting relation between the beams transmitted by said antennas; means for imparting to the microwave energy transmitted by each of said antennas a distinctive character by which to indicate whether the beam thereof is being swept in one direction or the opposite direction through said predetermined useful scan sector thereof, and radio receiving equipment for receiving microwave energy transmitted from said antennas, said equipment comprising means responsive to the time delay from a microwave energY impingement on the aircraft as a beam swing swings in a first direction to the microwave energy impingement as the same beam swings the opposite way, and responsive to the comparative time delay to the microwave energy impingement as the same beam again swings in the first direction.
17. An aircraft radio receiver for an instrument landing system wherein at least one localizer directional scanning beam is oscillatorily scanned through a predetermined scan sector many times as wide as said beam and at least one glide path directional scanning beam is oscillatorily scanned through a predetermined scan sector many times as wide as said beam, each beam having imparted thereto a modulation signifying its direction of swing through its scan sector, at least one further directional scanning beam having a different width of scan and being scanned in the same directional sense as at least one of said localizer and glide path directional scanning beams, said receiver comprising: means for receiving and detecting energy from the localizer beam each time it impinges on the aircraft as it swings clockwise in plan view and each time it impinges on the aircraft as it swings the opposite way, first means in the receiver for providing a signal varying in a predetermined relation to differential between the interval from the localizer beam impingement in the clockwise swing to its impingement in the counter-clockwise swing and the interval between the counter-clockwise swinging beam impingement and the succeeding clockwise swinging beam impingement, means for receiving and detecting energy from the glide path beam each time it impinges on the aircraft as it swings upward and each time it impinges on the aircraft as it swings downward, and second means in the receiver for providing a signal varying in a predetermined relation to the differential between the interval from the glide path beam impingement in the upward swing to its impingement in the downward swing and the interval between the downward swinging beam impingement and the succeeding upward swinging beam impingement.
18. An aircraft radio receiver as defined in claim 17, further including means responsive to said first and second signal providing means for providing a measure of aircraft position as it varies in relation to said beams with resultant variation of the differential delays between the beam impingement intervals.
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