US 3,958,165 AGrant
Cargo Transfer Shutoff System
Issue Date:1976-05-18
•6 Claims
•5 Drawing Sheets
Abstract
A cargo loading and unloading shutoff system is used to control transfer of loads between a cargo aircraft and a loading dock. Control logic means compares commands entered on a control console and the existing conditions in the aircraft and on the dock during a loading or unloading operation. On loading, the logic means shuts off the dock conveyor drive immediately when all loads are transferred to selected aircraft positions and then shuts off the aircract conveyor drive a predetermined period later. On unloading, the logic means shuts off both the aircraft and dock conveyor drives simultaneously when all loads are transferred to selected dock positions. The logic means also prevents energization of the aircraft and dock conveyor drives when the number of load positions selected in the aircraft is different from the number of load positions selected on the dock.
Metadata
Assignee
- McDonnell Douglas Corporation
Inventor
- Roger Boy de la Tour
Application Information
Application Number:US 5281709
Filing Date:1974-11-29
Priority Date:1974-11-29
Art Unit:217
Classifications
IPC:
H02P 300
Field of Search:
318340214244467;574147 R;332;213 Q;213.1;163516;75137 R
Patent Drawings (5 sheets)
Description
Background of the Invention
My present invention relates generally to cargo transfer systems. More particularly, the invention relates to a cargo loading and unloading shutoff system for controlling the transfer of loads between a cargo aircraft and a loading dock.
One type of cargo transfer system for transferring loads between an aircraft and a dock comprises an aircraft cargo loading system operating with a similar dock cargo loading system. The aircraft cargo loading system can be like that shown, described and claimed in the U.S. Pat. No. 3,612,316 of Floyd G. Baldwin and Raymond P. Brenner for Cargo Loading and Restraint System patented Oct. 12, 1971, for example, and the dock cargo loading system can be substantially identical thereto. The aircraft cargo loading system involves pertinent latching, locking and unlatching functions, with corresponding monitoring lamps. The dock cargo loading system involves pertinent inflatable bags or tubes functioning as clutches for its conveyor, these clutches being also monitored by lamps.
In the above cargo transfer system, it is possible for an operator to make time-consuming errors and select operations which could result in dangerous situations. Although there are monitoring lamps to indicate the conditions of the various components and the functioning thereof, a large number of lamps with different and varying indications are usually involved. Coupled with other required actions and observations, the monitoring lamps could be more distracting than helpful and may easily lead to errors or failure to notice improper conditions indicated by some of the lamps. Thus, control logic means working with the cargo transfer system and which would eliminate some of the other required actions and observations is desirable and needed to prevent or minimize all such errors and incorrect selections.
Summary of the Invention
Briefly, and in general terms, my invention is preferably accomplished by providing a cargo loading and unloading shutoff system including control logic means for comparing commands entered on the control console of a cargo transfer system with the existing conditions in an aircraft and on the associated dock during a loading or unloading operation, and appropriately controlling the transfer of loads according to the fulfillment of certain conditions. During a loading operation, the logic means produced a dock drive inhibit signal to shut off the dock conveyor drive immediately when all of the loads are transferred to their selected aircraft positions and latched. At the same time, the logic means also produces another signal which is delayed to shut off the aircraft conveyor drive a short predetermined period after shutoff of the dock conveyor drive.
During an unloading operation, however, the logic means produces an aircraft drive inhibit signal and an undelayed signal to shut off both the aircraft and dock conveyor drives simultaneously when all of the loads are transferred to their selected dock positions and disengaged from the dock conveyor. The logic means further functions to produce an error signal which acts to prevent energization of the aircraft and dock conveyor drives when the number of load positions selected in the aircraft is different from the number of load positions selected on the dock, and also provide an indication for the operator to make a re-selection of such load positions in this event.
Brief Description of the Drawings
My invention will be more fully understood, and other advantages and features thereof will become apparent, from the following description of an exemplary embodiment of the invention. The description is to be taken in conjunction with the accompanying drawings, in which:
FIG. 1 is an elevational view, shown partly in section and simplified form, of a cargo aircraft being loaded with cargo from a loading dock;
FIG. 2 is a front elevational view of a console control panel including means for selecting and controlling the transfer of cargo between the aircraft and dock;
FIG. 3 is a schematic block diagram of an illustrative cargo loading and unloading shutoff system constructed according to this invention;
FIG. 4 is a circuit diagram of one of the channel modules used in the aircraft logic input means of the shutoff system;
FIG. 5 is a circuit diagram of one of the channel modules used in the dock logic input means of the shutoff system;
FIG. 6 is a circuit diagram of an exemplary aircraft logic module including aircraft logic means, delay means and output means used in the shutoff system;
FIG. 7 is a circuit diagram of an exemplary dock logic module including dock logic means and output means used in the shutoff system;
FIG. 8 is a circuit diagram of an exemplary drive and comparator means module including counter/comparator means and drive means used in the shutoff system; and
FIG. 9 is a circuit diagram of an exemplary embodiment of the comparator logic and re-select output means used in the shutoff system.
Description of the Present Embodiment
In the following description and accompanying drawings of an exemplary embodiment of my invention, some specific values and types of components are disclosed. It is to be understood, of course, that such values and types of components are given as examples only and are not intended to limit the scope of this invention in any manner.
FIG. 1 is an elevational view, shown partly in section and simplified form, of an aircraft 20 being loaded with cargo or loads 22 from a dock 24. The aircraft 20 can be suitably positioned by a towing device 26 against the outer end of the dock 24 which can be vertically adjusted by aligning jacks 28. The aircraft 20 preferably includes a cargo loading system 30 which is similar to that shown, described and claimed in the U.S. Pat. No. 3,612,316 of Floyd G. Baldwin and Raymond P. Brenner for Cargo Loading and Restraint System patented Oct. 12, 1971. Reference can be made to this patent for any details of its system as required. The dock 24 also preferably includes a cargo loading system 32 which is substantially identical to the aircraft cargo loading system 30.
FIG. 2 is a front elevational view of a console control panel 34 for selecting and controlling the loading or unloading of cargo 22 between the aircraft 20 and dock 24. There are, for example, a first row 36 of twelve indicator lamps 38, a second row 40 of twelve push-button switches 42, a third row 44 of twelve indicator lamps 46, and a fourth row 48 of twelve push-button switches 50. The first row 36 is labeled "Aircraft Position Unlatched", the second row 40 is labeled "Aircraft Position Select", the third row 44 is labeled "Dock Position Deflated", and the fourth row 48 is labeled "Dock Position Select". The aircraft positions 1 through 12 correspond to forward to aft positions for cargo pellets or containers in the aircraft 20. The dock positions 1 through 12 correspond to outer to inner positions for cargo pellets or containers on the dock 24.
When an indicator lamp 38 is lit in the first row 36, the corresponding aircraft cargo pallet position is unlatched. The push-button switches 42 in the second row 40 can be of the push-to-close and push-to-open type. When a push-button switch 42 is closed, the corresponding aircraft cargo pallet position is selected. When an indicator lamp 46 in the third row 44 is lit, the inflatable clutch bag or tube (of the nature as described in the U.S. Pat. No. 3,612,316 of Floyd G. Baldwin and Raymond P. Brenner) at the corresponding dock cargo pallet position is energized (clutch engaged at that position). The push-button switches 50 in the fourth row 48 are similar to the push-button switches 42 in the second row 40. When a push-button switch 50 is closed, the corresponding dock cargo pallet position is selected. It may be noted that the number of cargo pallet positions selected in the aircraft 20 should be the same as the number of cargo pallet positions selected on the dock 24.
The console control panel 34 further includes a power on-off switch 52, a three-position mode switch 54, a two-position function switch 56, and a three-position drive control switch 58. The control panel 34 also includes a re-select indicator lamp 60, dock cargo loading drive motor indicator lamp 62, and aircraft cargo loading motor indicator lamp 64. The motor lamps 62 and 64 are lit when the dock and aircraft drive motors (not shown) are energized. To load the aircraft 20 with cargo pallets or loads 22, the power switch 52 is placed in its "on" position and the dock cargo pallet positions are set in the fourth row 48 by closing the corresponding push-button switches 50. The appropriate aircraft cargo pallet positions to be loaded are set in the second row 40 by closing the corresponding push-button switches 42. If the number of closed aircraft position switches 42 is not the same as the number of closed dock position switches 50, the reselect lamp 60 will be energized to indicate that correction is necessary.
The function switch 56 is then placed in its "load" position. When the selected aircraft position "unlatched" lamps 38 are lit to indicate that their corresponding latches are unlatched, the drive control switch 58 is placed in its "fast" position. The selected cargo pallets are automatically transported to their pre-selected positions in the aircraft 20 in a manner generally similar or analogous to that illustratively described in the U.S. Pat. No. 3,612,316 of Floyd G. Baldwin and Raymond P. Brenner. As described therein, limit switches in the aircraft 20 sense the presence (latched) or the absence (unlatched) of loads 22 at the different cargo pallet positions in the aircraft. The aircraft "unlatched" lamps 38 for the selected cargo pallet positions will display the latching of the pallets by becoming unlit as it occurs. When the last cargo pallet reaches its aircraft position and the latch function thereof is displayed, the drive control switch 58 is placed in its "off" position to complete the loading operation. The unloading sequence of operation is the same as the loading one except that the function switch 56 is placed in its "unload" position which causes reversal of the aircraft and dock drive mechanism (conveyors) and energizes the unlatch relay of the aircraft cargo loading system 30. The overall control circuit for the aircraft and dock loading systems 30 and 32 is straightforward but not pertinent to this invention and need not be further described or shown.
FIG. 3 is a schematic block diagram of an illustrative cargo loading and unloading shutoff system 66 constructed in accordance with my invention. The shutoff system 66 includes aircraft logic input means 68 having input signals obtained from the aircraft "unlatched" lamps 38 and "select" switches 42 (shown in FIG. 2), and dock logic input means 70 having input signals obtained from the dock "deflated" lamps 46 and "select" switches 50 (also shown in FIG. 2). The output from aircraft input means 68 on lead 72 ("A" line) is applied to aircraft logic means 74 and through delay means 76 and aircraft logic output means 78 to control the aircraft drive power relay (not shown). The output from dock input means 70 on lead 80 ("B" line) is applied to dock logic means 82 and through dock logic output means 84 to control the dock drive power relay (also not shown). A lead 86 from the aircraft logic means 74 to the dock logic output means 84 can provide a dock drive inhibit signal B thereto. Similarly, lead 88 from the dock logic means 82 to the aircraft logic output means 78 can provide an aircraft drive inhibit signal "A" thereto.
Lead or bus 100 ("C" line) from the aircraft and dock logic input means 68 and 70 to counter/comparator means 92 provides a signal for comparison with a reference signal in the comparator means 92. The comparator means 92 is driven or modulated by drive means 94 which can be a square wave oscillator. The output of the comparator means 92 is applied to counter/comparator logic and re-select output means 96 which can also produce dock and aircraft drive inhibit signals "B" and "A" that are respectively provided to the leads 86 and 88 which are connected to the dock and aircraft logic output means 84 and 78.
On loading, the dock drive mechanism is shut off immediately by the dock drive inhibit signal "B" on lead 86 from the aircraft logic means 74 to the dock logic output means 84 when all "unlatched" lamps 38 (FIG. 2) corresponding to selected cargo pallet positions in the aircraft 20 are off, indicating that all latches at the selected positions are latched to the cargo pallets or containers. When all of the loads 22 are placed in the aircraft 20 and are latched in the required positions, there is no further need for a dock drive. The aircraft drive mechanism is shut off, for example, 10 seconds later because of the action of the delay means 76 connecting with the output of aircraft logic means 74. Although the loads 22 are latched, they are not yet locked. The locking process takes, for example, 2 to 3 seconds.
On unloading, however, the aircraft and dock drive mechanisms are both shut off simultaneously by the aircraft drive inhibit signal "A" on lead 88 from the dock logic means 82 to the aircraft logic output means 78 controlling the aircraft drive power relay and by the output signal from the dock logic means 82 to the dock logic output means 84 controlling the dock drive power relay. This action occurs when all "deflated" lamps 46 (FIG. 2) corresponding to selected dock cargo pallet positions on the dock 24 are on, indicating that all clutch bags or tubes at the selected positions are deflated or disengaged. The clutch bags or tubes are stationary in position and are inflated (clutches are engaged) to lift the conveyor against any load 22 so that it can be carried along with movement of the conveyor as described in the U.S. Pat. No. 3,612,316 of Floyd G. Baldwin and Raymond P. Brenner. When a clutch bag or tube is deflated, the conveyor is lowered at that position to disengage it from the load which is not moved further by movement of the conveyor. If all of the selected clutches are disengaged, there is no further need for a drive.
When the number of cargo pallet positions selected in the aircraft 20 is different from the number of cargo pallet positions (loads 22) on the dock 24, the aircraft and dock drive mechanisms will remain inactive. This is accomplished by the dock and aircraft drive inhibit signals "B" and "A" which are respectively provided on the leads 86 and 88 that are connected from comparator logic and re-select output means 96 to the dock and aircraft logic output means 84 and 78. The comparator means 92 in FIG. 3 is essentially a voltage comparator containing a reference voltage which is, for example, half the supply voltage. All loads 22 selected on the dock 24 and set in the dock switches 50 put in the comparator circuit corresponding precision resistances from bus 100 to ground, and all selected positions in the aircraft 20 and set in the aircraft switches 42 connect equal precision resistances from the supply voltage to the bus. When the number of resistances is equal on both sides of bus 100, the bus voltage is equal to the reference voltage and inhibit signals "B" and "A" are not provided from the comparator logic and re-select output means 92 to the leads 86 and 88 which are respectively connected to the dock and aircraft logic output means 84 and 78. Energization of the dock and aircraft drive power relays is, however, prevented when the bus voltage is not equal to the reference voltage.
FIG. 4 is a circuit diagram of an exemplary channel module 98 which can be used in the aircraft logic input means 68 (FIG. 3). Of course, twelve of these channel modules 98 are used in the input means 68 since twelve aircraft cargo pallet positions are illustratively indicated. Each module 98 includes a first diode CR1 connected in series with a first resistor R1 which is connected to the aircraft +28 volts, a second diode CR2 connected in series with a third diode CR3 that is connected to lead 72 ("A" line), and a fourth diode CR4 connected in series with a second resistor R2 which is connected to lead or bus 100 ("C" line). The cathode of diode CR1 is connected to a terminal 102 and its anode is connected to the anodes of the diodes CR2 and CR3. The cathode of diode CR2 and the anode of diode CR4 are connected to terminal 104. The resistor R1 has a resistance of 27 kilohms and the resistor R2 has a precision resistance of 14.7 kilohms, for example.
The channel terminal 102 is connected to ground through a corresponding aircraft position "unlatched" indicator lamp 38 (FIG. 2) and to +28 volts through a corresponding switch 106. This switch 106 can be a limit switch associated with a given or particular aircraft cargo pallet position. The aircraft position switch 106 is closed to energize its related lamp 38 to indicate an "unlatched" condition at the corresponding aircraft cargo pallet position. The aircraft position switch 106 is opened to de-energize its related lamp 38 to indicate a "latched" condition at the corresponding aircraft cargo pallet position.
The channel terminal 104 is connected to +28 volts through a corresponding aircraft position "select" push-button switch 42 (FIG. 2) and to ground through its associated indicator lamp 108. This aircraft "select" lamp 108 is energized when its related position switch 42 is closed, to indicate that its corresponding aircraft cargo pallet position has been selected to receive a load 22. The indicator lamps 38 and 108 are, for example, of the tungsten filament type which has a very low resistance when off or not lit. Thus, the terminals 102 and 104 are effectively connected to ground when the switches 106 and 42 are open and their associated lamps 38 and 108 are off. It can, therefore, be seen that the voltage on lead 72 ("A" line) goes to zero when loading is completed; i.e., when all of the aircraft switches 106 at the selected cargo pallet positions are opened to turn off their associated "unlatched" lamps 38 and indicate latching of their corresponding loads 22 at those selected aircraft positions.
FIG. 5 is a circuit diagram of an exemplary channel module 110 which can be used in the dock logic input means 70 (FIG. 3). Of course, twelve of these channel modules 110 are used in the input means 70 since twelve dock cargo pallet positions are at least required to correspond to the twelve aircraft positions. Each module 110 includes a transistor Q1 having its emitter connected to ground, a first resistor R3 connecting the transistor collector to lead or bus 100 ("C" line), a second resistor R4 connecting the transistor base to a terminal 112, a first diode CR5 connected to lead 80 ("B" line), a third resistor R5 connecting the terminal 112 to the anode of the first diode CR5, and a second diode CR6 connecting the anode of the diode CR5 to another terminal 114. The resistor R3 has a precision resistance of 14.7 kilohms, the resistor R4 has a resistance of 270 kilohms and the resistor R5 has a resistance of 27 kilohms, for example.
The channel terminal 112 is connected to +28 volts through a corresponding dock position "select" push-button switch 50 (FIG. 2) and to ground through its associated indicator lamp 116. This dock "select" lamp 116 is energized when its related position switch 50 is closed, to indicate that its corresponding dock cargo pallet position has been selected to receive a load 22. The channel terminal 114 is connected to ground through a corresponding dock position "deflated" indicator lamp 46 (FIG. 2) and to +28 volts through its associated switch 118. This switch 118 can be a switch which is actuated by a link suitably connected to a latching pawl associated with a given or particular dock cargo pallet position. The dock position switch 118 is closed when its corresponding load is being latched. This closed switch 118 energizes its related lamp 46 to indicate a "deflated" or clutch disengaged condition at the corresponding dock cargo pallet position.
The indicator lamps 46 and 116 are, for example, of the tungsten filament type which has a very low resistance when off or not lit. Thus, the terminals 112 and 114 are effectively connected to ground when the switches 50 and 118 are open and their associated lamps 116 and 46 are off. When the switch 50 is closed, the transistor Q1 conducts to connect the resistor R3 from lead or bus 100 ("C" line) to ground. If the switch 118 is also closed, the anode of the diode CR5 then will not be grounded through the diode CR6 and an off lamp 46. It can, therefore, be seen that the voltage on lead 80 ("B" line) goes from zero to positive after an unloading operation is completed; i.e., when all of the dock switches 118 at the selected cargo pallet positions are closed to turn on their associated "deflated" lamps 46 and indicate clutch disengagement of their corresponding loads 22 at those selected dock positions.
FIG. 6 is a circuit diagram of an exemplary aircraft logic module 120 including aircraft logic means 74, delay means 76 and aircraft logic output means 78. Lead 72 ("A" line) is connected to input terminal 122 which is, in turn, connected to ground terminal 124 through a zener diode CR7 that has a breakdown voltage of, for example, 20 volts. The input terminal 122 is connected through another zener diode CR8 with a breakdown voltage of, for example, 6 volts to a grounded resistor R6. The anode of the zener diode CR8 is connected by resistor R7 to the base of transistor Q2 which has its emitter grounded and its collector connected to dock +28 volts on terminal 126 through resistor R8. The collector of the transistor Q2 is also connected through resistor R9 and series diode CR9 to terminal 128 which can provide a dock drive inhibit signal "B" therefrom. When the "A" line exceeds +6 volts, the transistor Q2 conducts so that there is no dock drive inhibit signal "B" from the terminal 128; however, when the "A" line voltage goes below +6 volts (to zero), the transistor is turned off and the positive voltage on terminal 126 is provided to the terminal 128 for the inhibit signal "B" to control the dock drive mechanism.
The anode of the zener diode CR8 is also connected to a grounded capacitor C1 through resistor R10 and series diode CR10. The capacitor C1 is connected by resistor R11 to a first input of comparator amplifier 130 which is supplied with +24 volts regulated by the circuit of transistor Q3. The second input of the amplifier 130 is connected by resistor R12 to the wiper of a potentiometer R13. The wiper of the potentiometer R13 is used to set the delay voltage that the capacitor C1 must reach or drop to before the output of the amplifier 130 flips from negative to positive or vice versa. The output of the amplifier 130 is connected by resistor R14 to the collector of a transistor Q4 having its emitter grounded and base connected to terminal 132. An aircraft drive inhibit signal "A" can be provided on the terminal 132 and, when present, would cause the transistor Q4 to conduct and reduce a positive output from resistor R14 to zero.
The resistor R14 is also connected by a 6 volts breakdown zener diode CR11 to output terminal 134. This terminal 134 is connected by transistor Q5 to the aircraft drive power relay (not shown). A two-diode varistor unit CR12 can be connected between the collector and emitter of the transistor Q5 to absorb the inductive kickback from the power relay. Of course, other absorption means such as a capacitor or suitably oriented diode can be used instead of the varistor unit CR12 between the collector and emitter of the transistor Q5. When a positive signal appears from the diode CR10, the capacitor C1 is promptly charged to produce a positive output signal from the amplifier 130. When, however, the positive signal from diode CR10 is removed as when aircraft loading is completed, the capacitor C1 discharges through the resistor R11 and the first input of the amplifier 130 at a rate such that it takes approximately ten seconds before the amplifier output signal flips from positive to negative. Of course, the transistor Q2 is turned off when the positive signal from the diode CR10 was removed. Thus, the aircraft drive output signal at terminal 134 is removed after a predetermined delay following the appearance of the dock drive inhibit signal "B" at terminal 128.
FIG. 7 is a circuit diagram of an exemplary dock logic module 136 including dock logic means 82 and dock logic output means 84. Lead 80 ("B" line) is connected to input terminal 138 which is, in turn, connected by a 6 volts breakdown zener diode CR13 to terminal 140 through resistor R15 and series diode CR14. The terminal 140 is connected to terminal 132 (FIG. 6) and the lead 80 goes positive after an unloading operation to provide an aircraft drive inhibit signal "A" on terminals 140 and 132 to remove power from the aircraft drive power relay at such time. The zener diode CR13 is also connected to the base of transistor Q6 through resistor R16. The emitter of the transistor Q6 is grounded and its collector is connected to +28 volts by resistor R17. The collector of the transistor Q6 is connected by a 6 volts breakdown zener diode CR15 to output terminal 142. This terminal 142 is connected by transistor Q7 to the dock drive power relay (not shown). A two-diode varistor CR16 or other means can be connected between the collector and emitter of the transistor Q7 to absorb the inductive kickback from the power relay.
When the lead 80 ("B" line) goes positive, the transistor Q6 conducts to turn off the transistor Q7 and remove power from the dock drive power relay. Terminal 144 is connected to the base of transistor Q8 which has its emitter grounded and its collector connected to the collector of the transistor Q6. The terminal 144 is connected to the terminal 128 (FIG. 6). When the dock drive inhibit signal "B" is produced at the terminal 128 and connected to the terminal 144, transistor Q8 conducts to turn off the transistor Q7 and remove power from the dock drive power relay. The dock drive mechanism is thus de-energized when aircraft loading or unloading is completed.
FIG. 8 is a circuit diagram of an exemplary drive and comparator means module 146 including counter/comparator means 92 and drive means 94. Lead or bus 100 ("C" line) is connected to input terminal 148 which is connected to the negative or inverting input of comparator amplifier 150 through series resistors R18 and R19. The positive or non-inverting input of the amplifier 150 is connected to the wiper of a potentiometer R20 which provides a reference voltage to the positive input. Diodes CR17 and CR18 are provided as voltage limiters. The amplifier 150 is, for example, an operational amplifier having the usual very high gain to produce a normally saturated output signal. The potentiometer R20 is connected to aircraft +28 volts on terminal 152 through resistor R21, and to ground through resistor R22 and series transistor Q9. The base of the transistor Q9 is connected to dock +28 volts on terminal 154 through resistor R23.
A saturable core transformer 156 is connected in a conventional square wave oscillator 158 having a dual emitter transistor Q10 connected to provide square wave output signals at the positive and negative inputs of the amplifier 150. Thus, modulated input signals are provided to the amplifier 150 which produces a square wave output signal at its output terminal 160 according to any difference between the input signals to the amplifier. When the number of aircraft cargo pallet positions selected by closing the corresponding switches 42 (FIGS. 2 and 4) is equal to the number of dock cargo pallet position switches 50 (FIGS. 2 and 5) likewise selected, the resistances of the precision resistors R2 and R3 are equal on both sides of the lead or bus 100 ("C" line) so that the bus voltage to the negative input of the amplifier 150 is equal to the reference voltage to the positive input thereof. The output signal on terminal 160 is zero when the input signals to the positive and negative inputs of the amplifier 150 are equal.
When, however, the number of aircraft positions selected by closing their corresponding switches 42 is not equal to the number of dock positions selected by closing their corresponding switches 50, the resistances of the precision resistors R2 and R3 on the two sides of the lead or bus 100 ("C" line) are unequal so that the bus voltage to the negative input of the amplifier 150 will not be equal to the reference voltage to the positive input thereof. A square wave error signal is then produced at the output terminal 160 of the amplifier 150. A significant change of aircraft and/or dock +28 volts at the terminals 152 and 154 will decrease or increase the reference voltage on the positive input of amplifier 150 and also produce a resultant square wave error signal at the output terminal 160.
FIG. 9 is a circuit diagram of an exemplary embodiment of the comparator logic and re-select output means 96. The output terminal 160 (FIG. 8) of the amplifier 150 is connected to input terminal 162 which is coupled to the base of a transistor Q11 by capacitor C2. The emitter of transistor Q11 is connected to aircraft +28 volts on terminal 164 through another transistor Q12 which has its base connected through resistor R24 to dock +28 volts on terminal 166. The collector of the transistor Q11 is connected to ground by resistor R25 and parallel capacitor C3. The collector of transistor Q11 is also connected through a 6 volts breakdown zener diode CR19 to the base of transistor Q13 by resistor R26, aircraft drive inhibit output terminal 168 by diode CR20 and series resistor R27, and dock drive inhibit output terminal 170 by diode CR21 and series resistor R28. The emitter of the transistor Q13 is connected to ground, and its collector is connected to aircraft +28 volts by resistor R29 and to the base of transistor Q14 by resistor R30. The emitter of transistor Q14 is connected to aircraft +28 volts and its collector is connected to output terminal 172 which is connected to ground through re-select indicator lamp 60.
When a square wave error signal from amplifier 150 is provided on the input terminal 162, the transistor Q11 conducts and a positive voltage is applied to the base of transistor Q13 so that it also conducts. This reduces the potential on the base of transistor Q14 such that it conducts and energizes the re-select lamp 60 indicating that re-selection of the aircraft and dock position switches 42 and 50 (FIGS. 2, 4 and 5) should be made. At the same time, an aircraft drive inhibit signal "A" is provided on terminal 168 and a dock drive inhibit signal "B" is provided on terminal 170. The terminal 168 is connected to terminal 132 (FIG. 6) of the aircraft logic output means 78 and the terminal 170 is connected to terminal 144 (FIG. 7) of the dock logic output means 84. Thus, the aircraft and dock drive mechanisms will be deenergized until a proper selection of the aircraft and dock position switches 42 and 50 is made.
While an exemplary embodiment of this invention has been described above and shown in the accompanying drawings, it is to be understood that such embodiment is merely illustrative of, and not restrictive on, the broad invention. In FIG. 4, for example, all of the diodes can be reversed in orientation and negative voltages used instead of positive ones. This can be similarly done in FIG. 5 along with the use of a PNP transistor instead of a NPN one. Obviously, other variations can be correspondingly made elsewhere. Thus, I do not desire to be limited in my invention to the specific arrangements, circuits or structures described and shown, for various modifications thereof may be made without departing from the principles involved in this invention.
Claims
I claim:
1. For use in a vehicle cargo loading system and a cooperating dock cargo loading system, a cargo transfer shutoff system comprising: vehicle logic input means for comparing at least one command signal representative of a corresponding at least one load position selected to be loaded in said vehicle with at least one status signal representative of existing conditions at said at least one load position selected in said vehicle, and producing a first output signal when said existing conditions at all load positions selected in said vehicle are indicative of a loaded status at each of said load positions selected in said vehicle; vehicle logic means for receiving said first output signal and adapting it into a vehicle drive control signal; vehicle logic output means responsive to said vehicle drive control signal to shut off drive means of said vehicle cargo loading system when said vehicle logic output means receives said vehicle drive control signal from said vehicle logic means; dock logic input means for comparing at least one command signal representative of a corresponding at least one load position selected to be loaded on said dock with at least one status signal representative of existing conditions at said at least one load position selected on said dock, and producing a second output signal when existing conditions at all load positions selected on said dock are indicative of a loaded status at each of said load positions selected on said dock; dock logic means for receiving said second output signal and adapting it into a dock drive control signal; and dock logic output means responsive to said dock drive control signal to shut off drive means of said dock cargo loading system when said dock logic output means receives said dock drive control signal from said dock logic means, whereby said vehicle drive means is shut off when all loads have been transferred to their selected vehicle positions during a vehicle loading operation and said dock drive means is shut off when all loads have been transferred to their selected dock positions during a vehicle unloading operation.
2. The invention as defined in claim 1 further comprising comparator logic means for comparing the number of load positions selected in said vehicle and the number of load positions selected on said dock for transfer of loads therebetween, and preventing energization of said vehicle and dock drive means when said selected numbers are different.
3. The invention as defined in claim 1 wherein said vehicle logic means for receiving said first output signal adapts it additionally into a dock drive inhibit signal and said dock logic output means is responsive also to said dock drive inhibit signal to shut off said drive means of said dock cargo loading system, and said dock logic means for receiving said second output signal adapts it additionally into a vehicle drive inhibit signal and said vehicle logic output means is responsive also to said vehicle drive inhibit signal to shut off said drive means of said vehicle cargo loading system, whereby said vehicle and dock drive means are both shut off when all loads have been transferred to their selected vehicle positions during a vehicle loading operation and said dock and vehicle drive means are both shut off when all loads have been transferred to their selected dock positions during a vehicle unloading operation.
4. The invention as defined in claim 3 further comprising comparator logic means for comparing the number of load positions selected in said vehicle and the number of load positions selected on said dock for transfer of loads therebetween, and preventing energization of said vehicle and dock drive means when said selected numbers are different.
5. The invention as defined in claim 3 further comprising vehicle logic delay means for delaying transmittal of said vehicle drive control signal to said vehicle logic output means, whereby said dock drive means is shut off when all loads have been transferred to their selected vehicle positions during a vehicle loading operation and said vehicle drive means is shut off a predetermined period after said dock drive means has been shut off during such operation.
6. The invention as defined in claim 5 further comprising comparator logic means for comparing the number of load positions selected in said vehicle and the number of load positions selected on said dock for transfer of loads therebetween, and preventing energization of said vehicle and dock drive means when said selected numbers are different.
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