Aircraft glide slope coupler system
阅读：128发布：2021-04-03
专利汇可以提供Aircraft glide slope coupler system专利检索，专利查询，专利分析的服务。并且A glide slope coupler adaptable to both Autopilot and Flight Director modes for guiding an aircraft to a landing along a radio defined glide slope beam. An integrator common to both modes effectively memorizes the aircraft descent rate and provides a signal representative thereof for summation with glide slope beam displacement and altitude rate signals in respective amplifiers coupled to drive the pitch actuators and Flight Director Indicator bar. A synchronizing mode is included for coupling the pitch actuator driver amplifier output to the integrator input to obtain a desired descent rate signal while flying in a cruise mode prior to intercepting the glide slope beam. Upon intercepting the beam either the Autopilot or Flight Director mode is activated as chosen by the pilot and the selected system then operates to reduce the beam displacement signal to zero with flight path damping being provided by the altitude rate signal. During the descent the beam displacement signal is modified as a function of altitude to compensate for the convergence of the glide slope beam. At a predetermined flare altitude the beam displacement signal is rendered ineffective and thereafter the integrator output signal is modified as a function of altitude to control the flare in accordance with the memorized value of the descent rate at the commencement of the flare maneuver.，下面是Aircraft glide slope coupler system专利的具体信息内容。
1. Apparatus for guiding a craft to a landing along a radio defined glide slope beam, comprising an integrator for storing a signal representative of a desired descent rate along the glide slope beam, means for providing a signal representative of the craft displacement from the center line of the glide slope beam, means for providing a signal representative of the actual descent rate of the craft, means for algebraically summing the stored signal of said integrator with the actual descent rate and beam displacement signals, and means for selectively coupling the output of said summing means to the input of said integrator prior to the craft intercepting a predetermined radial of the glide slope beam for controlling the output signal level of the integrator in accordance with the instantaneous amplitude of the beam displacement and actual descent rate signals whereby upon the craft intercepting said predetermined radial at a given velocity in a level flight condition a desired descent rate signal is produced at the output of said integrator to cauSe pitch down of the craft for capturing the glide slope beam.
2. The apparatus of claim 1 wherein the selective coupling means is further operative upon disconnecting the output of said summing means from the input of said integrator for applying either the displacement signal or the combination of the actual descent rate signal and the integrator output signal to the integrator input for varying the desired descent rate signal so as to wash out the steady state actual descent rate signal whereby the output signal of said summing means is indicative of the craft displacement from the center line of the glide slope beam.
3. The apparatus of claim 2 including means for reducing the magnitude of the beam displacement signal in proportion to decreasing craft altitude below a predetermined altitude to compensate for convergence of the glide slope beam approaching ground level.
4. The apparatus of claim 3 further including means for deactivating the beam displacement signal at a second lower predetermined altitude and simultaneously continuously modifying the desired descent rate signal as a function of altitude from said second predetermined altitude to touchdown such that the touchdown descent rate is a prescribed fraction of the instantaneous descent rate prevailing at a predetermined altitude.
5. The apparatus of claim 1 wherein the selective coupling means is further operative upon disconnecting the output of said summing means from the input of said integrator for connecting the integrator output to its input and simultaneously applying the actual descent rate signal thereto so that the integrator output signal is driven to a level equal to that of the steady state actual descent rate signal whereby the displacement signal provides the predominant control for guiding the craft down the glide slope beam.
6. The apparatus of claim 5 wherein the output of said integrator is connected to its input through an impedance of sufficient value to convert the integrator to a long time constant lag network.
7. The apparatus of claim 5 further including means for deactivating the beam displacement signal at a second lower predetermined altitude and simultaneously continuously modifying the desired descent rate signal as a function of altitude from said second predetermined altitude to touchdown such that the touchdown descent rate is a prescribed fraction of the instantaneous descent rate prevailing at the predetermined altitude.
8. The apparatus of claim 1 wherein the selective coupling means is operative upon disconnecting the output of said summing means from the input of said integrator for connecting the displacement signal means to the integrator input so that the integrator output is driven to a level equal to that of the steady state actual descent rate signal whereby the displacement signal provides the predominant control for guiding the craft along the center line of the glide slope beam.
9. The apparatus of claim 8 further including means for deactivating the beam displacement signal at a second lower predetermined altitude and simultaneously continuously modifying the desired descent rate signal as a function of altitude from said second predetermined altitude to touchdown such that the touchdown descent rate is a prescribed fraction of the instantaneous descent rate prevailing at the predetermined altitude.
10. An integrated Autopilot/Flight Director glide slope coupler system for guiding a craft to a landing along a radio defined glide slope beam, comprising means for providing a signal representative of the craft displacement from the center line of the beam, switching means enabling said system to be set initially in a synchronizing mode and thereafter in either an Autopilot or Flight Director mode, means for providing a signal representative of the actual descent rate of the craft, an integrator for storing a signal representative of a desired descent rate, means for algebraically summing the integrAtor output signal with the displacement and actual altitude rate signals, and said switching means being operative in a first condition corresponding to the synchronizing mode, prior to the craft intercepting a predetermined radial of the glide slope beam, to connect the output of said summing means to the input of said integrator for controlling the output signal level thereof in accordance with the instantaneous amplitude of the beam displacement and actual descent rate signals whereby upon the craft intercepting said predetermined radial in a level flight condition at a prescribed velocity the signal at the output of said integrator is representative of a desired descent rate to cause a craft pitch down to fly along the center line of the glide slope beam.
11. The apparatus of claim 10 further including additional algebraic summing means connected to receive the actual descent rate, displacement and desired descent rate signals to produce a resultant flight director indicator control signal, and means for summing the actual descent rate and desired descent rate signals and applying them to the input of said integrator during a second condition of said switching means corresponding to the flight director mode so that the steady state effect of the actual rate of descent signal is effectively nullified in said additional summing means.
12. The apparatus of claim 11 further including means for continuously modifying the displacement signal in accordance with the instantaneous altitude of the craft from a first predetermined altitude down to a second predetermined altitude to compensate for convergence of the glide slope beam, and means for continuously modifying the output signal of said integrator in accordance with the instantaneous craft altitude from the second predetermined altitude to touchdown such that the touchdown descent rate is a prescribed fraction of the instantaneous descent rate prevailing at the second predetermined altitude.
13. The apparatus of claim 10 wherein the switching means is operative upon completion of the synchronizing mode to disconnect the output of the algebraic summing means from the integrator input and to connect thereto the output of said beam displacement means in a third condition of said switching means corresponding to the autopilot mode such that the effect of the steady state actual rate of descent signal is effectively nullified in said algebraic summing means.
14. The apparatus of claim 13 including means for continuously modifying the displacement signal in accordance with the instantaneous altitude of the craft from a first predetermined altitude down to a second predetermined altitude to compensate for convergence of the glide slope beam, and means for continuously modifying the output signal of said integrator in accordance with the instantaneous craft altitude from the second predetermined altitude to touchdown such that the touchdown descent rate is a prescribed fraction of the instantaneous descent rate prevailing at the second predetermined altitude.
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