CA1240048A - Helicopter weight and torque advisory system - Google Patents
Helicopter weight and torque advisory systemInfo
- Publication number
- CA1240048A CA1240048A CA000498862A CA498862A CA1240048A CA 1240048 A CA1240048 A CA 1240048A CA 000498862 A CA000498862 A CA 000498862A CA 498862 A CA498862 A CA 498862A CA 1240048 A CA1240048 A CA 1240048A
- Authority
- CA
- Canada
- Prior art keywords
- helicopter
- weight
- display unit
- hook
- load
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000000446 fuel Substances 0.000 claims abstract description 21
- 230000005484 gravity Effects 0.000 claims abstract description 14
- 238000013479 data entry Methods 0.000 claims description 6
- 230000003466 anti-cipated effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241000202867 Helicops Species 0.000 description 1
- 208000003251 Pruritus Diseases 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 238000004380 ashing Methods 0.000 description 1
- 230000004397 blinking Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Toys (AREA)
- Jib Cranes (AREA)
- Component Parts Of Construction Machinery (AREA)
- Cosmetics (AREA)
Abstract
A HELICOPTER WEIGHT AND TORQUE ADVISORY SYSTEM
ABSTRACT OF THE DISCLOSURE
A helicopter weight and torque advisory system connected to external cargo hook load sensors, fuel gauge, air temperature and altitude indicating systems of a helicopter to provide the flight crew, in real time, the helicopter's engine torque margins, gross weight, gross weight center of gravity and the weight supported by each external cargo hook as an external sling load is raised and sup-ported by the helicopter.
ABSTRACT OF THE DISCLOSURE
A helicopter weight and torque advisory system connected to external cargo hook load sensors, fuel gauge, air temperature and altitude indicating systems of a helicopter to provide the flight crew, in real time, the helicopter's engine torque margins, gross weight, gross weight center of gravity and the weight supported by each external cargo hook as an external sling load is raised and sup-ported by the helicopter.
Description
A HELICOPTER WEIGHT AND TORQUE ADVISORY SYSTEM
BACKGRO ND OF THE INVENTION
This invention relates to a helicopter advisory system and more particularly, but not by way of limitation, to a system for 5 providing real time engine torque margin (the difference between available torque and required torque), gross weight, gross weight center of gravity and weight supported by the helicopter's cargo hooks to helicopter personnel for external load carriage missions.
Heretofore, helicopter pilots did not have modern auto-10 mated means of knowing required engine torque relative to availabletorque as a function of actual external cargo load. The present process is to manually refer to performance look-up tables and charts to determine torque margin for an actual external load which is time consuming, cumberso~le and always subject to error. This 15 manual system may cause helicopter structural damage, inability to complete missions and unfortunate accidents.
Prior attempts to determine the helicopters conditlon after lifting external cargo'did not incorporate the real time input of al-titude, temperature and fuel weight data necessary to determine 20 engine torque margins.
The subject helicopter weight and torque advisory system ellminates the above mentioned problems and provides unique features and advantages heretofore not available during helicopter flight.
SUMMARY OF THE INVENTION
According to one aspect of the invention there is provided a helicopter wei0ht and torque advisory system connected to a helicopter's i'uel gauge, outside air temperature and altitude indi-cating system and hook load sensor and operated by one of the heli-\~
copter's personnel, the system comprising: a control panel and processor unit connected to the aircraft's power source, hook load sensor, fuel gauges, outside air temperature and altitude system, the control panel processor unit including a compu-ter and necessary 5 memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and indivi-dual weight suppcrted by a cargo hook as an external load is raised by the helicopter; and a remote display unit connected to the pro cessor unit, the display unit displaying the helicopter's fuel weight, 10 outside air temperature and altitude.
~ ccording to another aspect of the invention there is pro-vided a helicopter weight and torque advisory system connected to a helicopter's fuel gauge, outside air temperature and altitude indi-cating system and hook load sensors and operated by one oE the 15 helicopter's personnel, the system comprising: a control panel and processor unit connected to the aircraft's power source, hook load sensor, fuel flow indicating system, outside air temperature gauge, pressure altitude gauge and anti-ice system, the control panel and processor unit including a computer and necessary memory for storing 20 and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each of the helicopter's cargo hooks as an external load is raised by each of the hooks of the helicopter; and a remote display unit connected to the processor unit, the display unit displaying ~he 25 helicopter's fuel weight, outside air temperature and altitude.
The subject helicopter weight and torque advisory system displays in real time the helicopter's engine torqua margin, gross weight, gross weight center of gravity and wei5h-t supported by each cargo hook as an external load is raised and carried by the 30 helicop ter .
~,.
The system display also alerts the flight crew when re-quired torque approaches available torque. Also, it displays the helicopter gross weiyht and gross weight center of gravity (CG) which flash when a (CG) limit is exceeded. Also, it displays the 5 weight lifted by a cargo hook and flashes when the hook weigh t load limit is reached.
The system may also be used to compute engine torque margins at a destination location based on actual external load and processor unit. The display unll and control panel may be mounted 10 in the cockpit of the helicopter and may be read in direct sunlight and with or without nlght vision goggles. The control panel por-tion of the control panel and processor unit consists of an ON/OFF
switch, three mode switches, i . e ., internal cargo load switch INTERNAL LOAD, sling load switch SLING LOAD and engine torque 15 margin at destination switch DEST. ~lso, it contains a recall key RCL, a test key TEST and a calibration key CALB. Further, it includes three data keys, CHANGE, SGROLL and ENTER~ and a display brightness control knob. The remote display unit consists of three lines with each line capable of displaying four alpha-numeric 20 characters.
The remote display untt and control panel and processor unlt are small Eor potential installation ln existing space without dis-turbing existing equiprnent in the helicopter's cocl~pit.
BRIEF DESCRIPTION OF THE DRAWINGS
-Fig. 1 illustrates the rernote display unit.
Fig. 2 illustrate.s the control panel of the control panel and processor unit .
Fig. 3 illustrates a cockpit of a heltcopter for receiving i the remote display unit and control panel and processor unit.
Figs. 4A and 4B illustrate a system diagram of the advisory system and processor unit components.
Figs. 5A, 5B, 5C and 5D illustrate the display formats when 5 the on/off switch is engaged.
Figs. 6A, 6B, 6C and 6D illustrate example displays when the on/off switch is engaged~
Figs. 7A and 7B illustrate the display formats when the internal load switch is engaged.
Figs. 8A, 8B and 8C illustrate example displays when the internal load switch is engaged.
Figs. 9A and 9B illustrate the display formats when the sling load switch is engaged.
Figs. lOA, lOB and lOC illustrate example displays when the 1~ sling load s~itch is engaged.
Flgs. llA and llB illustrate display formats when the Destlnation (DEST ) switch is engaged .
Figs. 12A and 12B illustrate example displays w~len the Destination (DEST) switch is engaged.
Fig. 13 illustrates the location of the cargo compartments in an example CH-~7D helicopter.
Fig. 14 illustrates the location of the external cargo hooks on the example CH-47D helicopter.
DETAILED DESCRIPTION OF THE DRAWINGS
In Fig. 1 the remote display unit is designated by general reference numeral 10. The unit 10 includes three lines 12, 14 and 16 each capable of displaying four alpha-numeric characters.
In Fig. 2, the control panel and proce~sor unit is shown and designated by general reference 18. The unit 18 includes an on/off switch 20 and three display mode keys, internal load 22, sling load 24 and destination (DEST) 26.
A second line includes a recall (RCL) key 28, test key 30 and calibration (CALB) key 32. Further a -third line includes three àata entry keys, change 34, scroll 36 and enter 38. On the unit 18 a display brightness control knob 40 is included for regulating the brightness of the light to the remote display unit 10.
Shown in Fig. 3 is a cockpit for a CH-47D helicopter showlng 15 where typically, the remote display unit 10 and control panel and processor unit 18 can be mounted~ The remote display unit 10 and control panel processor unit 1~ are small enough for potential instal-lation in e~cisting space without disturbing the equip~nent used with:
various types of helicopters.
In Fig. 4A a system diagram is shown whlch illustrates the interface between the helicopter weight and torque advisory system designated by general reference numeral 42 and other helicopter sys-tems. In this diagram, the remote display unit 10: shown is connected to the control panel and processor unit 18 via lead 43. The unit l8 25 iS connected via lead 44 to lead 45 which is connected to the fuel gauging system oi the helicopter. Lead 44 is also connected to lead 46 cbnnected to the outside air temperature sensor system of the heli-copter and to lead 48 connected to the altitude indicating system of the helicopter.
In Fig. 4B the computer and necessary memory of the pro-cessor unit 18 is shown for storing and calculating the helicopter engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each individual external cargo 5 hook. The load sensors, fuel gauge and outside air temperature system are connected to analog to digital converter with multiplexer 56 via leads 45, 46 and 50. The converter 56 is connected to a single chip processor 58 which in turn is connected to drivers 60.
A keyboard 62 of the unit 18 is connected to an encoder 64 which 10 in turn is connected to the processor 58. The drivers 60 interface with receivers 66 which are connected to a digit multiplexing control 68 and serial parallel connector 70. The control 68 is connected to digit drivers 72 and the connector 70 is connected to segment drivers 74. The drivers 72 and 74 are connected to the remote display unit 15 10.
Referring now to Fig. 5A and prior to the start of a mis-sion, the operator turns the system on using the onloff switch 20.
The display 10 will indicate the total fuel weight on the first line 12, pressure altitude on the second line 14, and outside air temperature 20 on the third line 16. The values should be the same as those shown on the helicopters total fuel gauge and the altitude and outside air temperature indicators. The operator ~ould press the SCROLL key 36 on the control panel 18 to view the helicopters operating weight, Fig. 5B, operating weight CG, Fig. 5C, and type of engines, Fig. 5D, 25 which are stored in the processor memory. The data entry keys on the control panel 18, i.e., CHANGE 34, SCROLL 36, and ENTER 38 are used to change the displayed data. The process for entering or updating data consists of pressing the change key 34 which starts -the cursor of the display unit 10 blinking at the first data character 30 position. If no change is required at this position, the operator then presses the enter key 38 and the cursor will shift to the next charac-ter position. If a character is to be entered or updated, the opera-tor then presses the SCROLL key 36 to bring up the desired :
character and then the ENTER key 3~ is pressed. The cursor will then automatically shift to the next character and at the end of the line, skip to the first data character on the next line. Figs. 6A, 6B, 6C and 6D are examples of the display formats that would appear 5 when the system is turned on and the SCROLL key is used to bring up displays. The original display format 5A will appear after the SGROLL key is used when Fi0ure 5D is displayed.
The operator must manually enter the internal cargo load weight into the system processor prior to the lifting of the external 10 sling load, Thls is accomplished by first engaging the INTERNAL LOAD
switch 22 on the control panel 18 which brings up format Fig. 7P, and then using the data entry keys CHG 34, SCROLL 36 and ENTER 38.
The system automatically distributes the displayed internal cargo load weight evenly over the internal cargo compartments C, D and E
15 which are shown in Fig. 13. This weight distribution may be viewed by pressing the SCROLL key and the display format would be as shown in 7B. If the internal cargo load weight is not distributed evenly, the operator would enter the unevenly distributed load into the processor using the Fig. 7B format and the data entry keys CHG
20 34, SCROLL 36 and ENTER 38. Figs. 8A and 8B illustrate an exam-ple of a 16,000 pound internal payload evenly distributed and non-evenly distributed in Fig. 8C.
Prior to lifting an external load, the operator would engage the SLI~lG LOAD switch 24. The display format that will appear is 25 shown in Fig. 9A. As the external sling load is raised, the helicopter gross weight shown in the first line 12 of the display 10 would in-crease, as well as the total sling load weight shown in the second line 14 of the display 10. Also, as the external sling load is raised, the torque margin for two engines and single engine operation would 30 decrease and would be displayed in the third line 16 of the display 10. An example of an actual display is shown in Fig. 10A.
.
.:
If the helicopter gross weight limit is exceeded as a result of an adverse balance (center of gravity) condition, a "F" for forward CG limit condition or an "A" for aft CG limit condition would appear in the first position of line 12 oi the display 10 and the entire 5 line would start i~ashing. If the weight limit of external cargo hooks, 76, 78 or 80 shown in Fig. 14 is exceeded, the hook that is over-loaded will appear in the first position of line 14 of the display 10 and the entire line 14 of the display 10 will i~ash. An "A" in the first position would indicate forward hook 76, "C" the center hook 78 and 10 "D" the aft hook 80. If a torque margin (available torque minus required torque) for either a two engine or single engine operation is exceeded, the torque margin displayed which was exceeded in line 16 of display 10 would start flashing. This is shown in Fig. 10B~
If the operator wants to view the individual sling load 15 weights, he would press the scroll key 36 and the display format 9B displaying the individual sling loads supported by rack hook would be displayed. The hook position and the sling weight it is supporting are displayed and ii any of the hook load limit weights exceeded their load limit, its weight value and hook identification symbol (F, C, A) 20 would flash. An example is shown in Fig. 10C. The operator would press either SCROLL 36 or SLING LOAD 2~ to return to the original sling load format display 9A.
The desitnation (DEST) switch 26 is used to determine the engine torque margins at the mission destination point based on 25 actual sling load and the internal load and anticipated remaining fuel weight, altitude and temperature at the mission destination point~
When the destination switch 26 is engaged, the anticipated destination, altitude and air temperature would be displayed as shown in Fig. llA
and an example in Fig. 12A. These values may be updated by the 30 operator using the data entry keys. Next, the operator would press the scroll key 36 to display and update the anticipated remaining ~l2~
g fuel at destination. The destination remaining fuel value is shown on the second line of Fig. llB and an example in Fig. 12B. The resulting torqu~ margins at destination are displayed on the third line of Fig. llB and will flash if they are exceeded.
The recall key RCL 28, on the control panel 18 is used to display the same data that appears when the system is turned on (Fig. 5). The test key TEST, 30, is used for built-in-test pur-poses. The calibration key CALB 32, is used to calibrate the system processor with the discretes from the external cargo hooks, fuel 10 gauge and altitude and air temperature indicators.
Changes may be made in the construction and arrangement of the parts or elements of the embodiments as described herein without departing from the spirit or scope of the invention defined in the following claims.
BACKGRO ND OF THE INVENTION
This invention relates to a helicopter advisory system and more particularly, but not by way of limitation, to a system for 5 providing real time engine torque margin (the difference between available torque and required torque), gross weight, gross weight center of gravity and weight supported by the helicopter's cargo hooks to helicopter personnel for external load carriage missions.
Heretofore, helicopter pilots did not have modern auto-10 mated means of knowing required engine torque relative to availabletorque as a function of actual external cargo load. The present process is to manually refer to performance look-up tables and charts to determine torque margin for an actual external load which is time consuming, cumberso~le and always subject to error. This 15 manual system may cause helicopter structural damage, inability to complete missions and unfortunate accidents.
Prior attempts to determine the helicopters conditlon after lifting external cargo'did not incorporate the real time input of al-titude, temperature and fuel weight data necessary to determine 20 engine torque margins.
The subject helicopter weight and torque advisory system ellminates the above mentioned problems and provides unique features and advantages heretofore not available during helicopter flight.
SUMMARY OF THE INVENTION
According to one aspect of the invention there is provided a helicopter wei0ht and torque advisory system connected to a helicopter's i'uel gauge, outside air temperature and altitude indi-cating system and hook load sensor and operated by one of the heli-\~
copter's personnel, the system comprising: a control panel and processor unit connected to the aircraft's power source, hook load sensor, fuel gauges, outside air temperature and altitude system, the control panel processor unit including a compu-ter and necessary 5 memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and indivi-dual weight suppcrted by a cargo hook as an external load is raised by the helicopter; and a remote display unit connected to the pro cessor unit, the display unit displaying the helicopter's fuel weight, 10 outside air temperature and altitude.
~ ccording to another aspect of the invention there is pro-vided a helicopter weight and torque advisory system connected to a helicopter's fuel gauge, outside air temperature and altitude indi-cating system and hook load sensors and operated by one oE the 15 helicopter's personnel, the system comprising: a control panel and processor unit connected to the aircraft's power source, hook load sensor, fuel flow indicating system, outside air temperature gauge, pressure altitude gauge and anti-ice system, the control panel and processor unit including a computer and necessary memory for storing 20 and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each of the helicopter's cargo hooks as an external load is raised by each of the hooks of the helicopter; and a remote display unit connected to the processor unit, the display unit displaying ~he 25 helicopter's fuel weight, outside air temperature and altitude.
The subject helicopter weight and torque advisory system displays in real time the helicopter's engine torqua margin, gross weight, gross weight center of gravity and wei5h-t supported by each cargo hook as an external load is raised and carried by the 30 helicop ter .
~,.
The system display also alerts the flight crew when re-quired torque approaches available torque. Also, it displays the helicopter gross weiyht and gross weight center of gravity (CG) which flash when a (CG) limit is exceeded. Also, it displays the 5 weight lifted by a cargo hook and flashes when the hook weigh t load limit is reached.
The system may also be used to compute engine torque margins at a destination location based on actual external load and processor unit. The display unll and control panel may be mounted 10 in the cockpit of the helicopter and may be read in direct sunlight and with or without nlght vision goggles. The control panel por-tion of the control panel and processor unit consists of an ON/OFF
switch, three mode switches, i . e ., internal cargo load switch INTERNAL LOAD, sling load switch SLING LOAD and engine torque 15 margin at destination switch DEST. ~lso, it contains a recall key RCL, a test key TEST and a calibration key CALB. Further, it includes three data keys, CHANGE, SGROLL and ENTER~ and a display brightness control knob. The remote display unit consists of three lines with each line capable of displaying four alpha-numeric 20 characters.
The remote display untt and control panel and processor unlt are small Eor potential installation ln existing space without dis-turbing existing equiprnent in the helicopter's cocl~pit.
BRIEF DESCRIPTION OF THE DRAWINGS
-Fig. 1 illustrates the rernote display unit.
Fig. 2 illustrate.s the control panel of the control panel and processor unit .
Fig. 3 illustrates a cockpit of a heltcopter for receiving i the remote display unit and control panel and processor unit.
Figs. 4A and 4B illustrate a system diagram of the advisory system and processor unit components.
Figs. 5A, 5B, 5C and 5D illustrate the display formats when 5 the on/off switch is engaged.
Figs. 6A, 6B, 6C and 6D illustrate example displays when the on/off switch is engaged~
Figs. 7A and 7B illustrate the display formats when the internal load switch is engaged.
Figs. 8A, 8B and 8C illustrate example displays when the internal load switch is engaged.
Figs. 9A and 9B illustrate the display formats when the sling load switch is engaged.
Figs. lOA, lOB and lOC illustrate example displays when the 1~ sling load s~itch is engaged.
Flgs. llA and llB illustrate display formats when the Destlnation (DEST ) switch is engaged .
Figs. 12A and 12B illustrate example displays w~len the Destination (DEST) switch is engaged.
Fig. 13 illustrates the location of the cargo compartments in an example CH-~7D helicopter.
Fig. 14 illustrates the location of the external cargo hooks on the example CH-47D helicopter.
DETAILED DESCRIPTION OF THE DRAWINGS
In Fig. 1 the remote display unit is designated by general reference numeral 10. The unit 10 includes three lines 12, 14 and 16 each capable of displaying four alpha-numeric characters.
In Fig. 2, the control panel and proce~sor unit is shown and designated by general reference 18. The unit 18 includes an on/off switch 20 and three display mode keys, internal load 22, sling load 24 and destination (DEST) 26.
A second line includes a recall (RCL) key 28, test key 30 and calibration (CALB) key 32. Further a -third line includes three àata entry keys, change 34, scroll 36 and enter 38. On the unit 18 a display brightness control knob 40 is included for regulating the brightness of the light to the remote display unit 10.
Shown in Fig. 3 is a cockpit for a CH-47D helicopter showlng 15 where typically, the remote display unit 10 and control panel and processor unit 18 can be mounted~ The remote display unit 10 and control panel processor unit 1~ are small enough for potential instal-lation in e~cisting space without disturbing the equip~nent used with:
various types of helicopters.
In Fig. 4A a system diagram is shown whlch illustrates the interface between the helicopter weight and torque advisory system designated by general reference numeral 42 and other helicopter sys-tems. In this diagram, the remote display unit 10: shown is connected to the control panel and processor unit 18 via lead 43. The unit l8 25 iS connected via lead 44 to lead 45 which is connected to the fuel gauging system oi the helicopter. Lead 44 is also connected to lead 46 cbnnected to the outside air temperature sensor system of the heli-copter and to lead 48 connected to the altitude indicating system of the helicopter.
In Fig. 4B the computer and necessary memory of the pro-cessor unit 18 is shown for storing and calculating the helicopter engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each individual external cargo 5 hook. The load sensors, fuel gauge and outside air temperature system are connected to analog to digital converter with multiplexer 56 via leads 45, 46 and 50. The converter 56 is connected to a single chip processor 58 which in turn is connected to drivers 60.
A keyboard 62 of the unit 18 is connected to an encoder 64 which 10 in turn is connected to the processor 58. The drivers 60 interface with receivers 66 which are connected to a digit multiplexing control 68 and serial parallel connector 70. The control 68 is connected to digit drivers 72 and the connector 70 is connected to segment drivers 74. The drivers 72 and 74 are connected to the remote display unit 15 10.
Referring now to Fig. 5A and prior to the start of a mis-sion, the operator turns the system on using the onloff switch 20.
The display 10 will indicate the total fuel weight on the first line 12, pressure altitude on the second line 14, and outside air temperature 20 on the third line 16. The values should be the same as those shown on the helicopters total fuel gauge and the altitude and outside air temperature indicators. The operator ~ould press the SCROLL key 36 on the control panel 18 to view the helicopters operating weight, Fig. 5B, operating weight CG, Fig. 5C, and type of engines, Fig. 5D, 25 which are stored in the processor memory. The data entry keys on the control panel 18, i.e., CHANGE 34, SCROLL 36, and ENTER 38 are used to change the displayed data. The process for entering or updating data consists of pressing the change key 34 which starts -the cursor of the display unit 10 blinking at the first data character 30 position. If no change is required at this position, the operator then presses the enter key 38 and the cursor will shift to the next charac-ter position. If a character is to be entered or updated, the opera-tor then presses the SCROLL key 36 to bring up the desired :
character and then the ENTER key 3~ is pressed. The cursor will then automatically shift to the next character and at the end of the line, skip to the first data character on the next line. Figs. 6A, 6B, 6C and 6D are examples of the display formats that would appear 5 when the system is turned on and the SCROLL key is used to bring up displays. The original display format 5A will appear after the SGROLL key is used when Fi0ure 5D is displayed.
The operator must manually enter the internal cargo load weight into the system processor prior to the lifting of the external 10 sling load, Thls is accomplished by first engaging the INTERNAL LOAD
switch 22 on the control panel 18 which brings up format Fig. 7P, and then using the data entry keys CHG 34, SCROLL 36 and ENTER 38.
The system automatically distributes the displayed internal cargo load weight evenly over the internal cargo compartments C, D and E
15 which are shown in Fig. 13. This weight distribution may be viewed by pressing the SCROLL key and the display format would be as shown in 7B. If the internal cargo load weight is not distributed evenly, the operator would enter the unevenly distributed load into the processor using the Fig. 7B format and the data entry keys CHG
20 34, SCROLL 36 and ENTER 38. Figs. 8A and 8B illustrate an exam-ple of a 16,000 pound internal payload evenly distributed and non-evenly distributed in Fig. 8C.
Prior to lifting an external load, the operator would engage the SLI~lG LOAD switch 24. The display format that will appear is 25 shown in Fig. 9A. As the external sling load is raised, the helicopter gross weight shown in the first line 12 of the display 10 would in-crease, as well as the total sling load weight shown in the second line 14 of the display 10. Also, as the external sling load is raised, the torque margin for two engines and single engine operation would 30 decrease and would be displayed in the third line 16 of the display 10. An example of an actual display is shown in Fig. 10A.
.
.:
If the helicopter gross weight limit is exceeded as a result of an adverse balance (center of gravity) condition, a "F" for forward CG limit condition or an "A" for aft CG limit condition would appear in the first position of line 12 oi the display 10 and the entire 5 line would start i~ashing. If the weight limit of external cargo hooks, 76, 78 or 80 shown in Fig. 14 is exceeded, the hook that is over-loaded will appear in the first position of line 14 of the display 10 and the entire line 14 of the display 10 will i~ash. An "A" in the first position would indicate forward hook 76, "C" the center hook 78 and 10 "D" the aft hook 80. If a torque margin (available torque minus required torque) for either a two engine or single engine operation is exceeded, the torque margin displayed which was exceeded in line 16 of display 10 would start flashing. This is shown in Fig. 10B~
If the operator wants to view the individual sling load 15 weights, he would press the scroll key 36 and the display format 9B displaying the individual sling loads supported by rack hook would be displayed. The hook position and the sling weight it is supporting are displayed and ii any of the hook load limit weights exceeded their load limit, its weight value and hook identification symbol (F, C, A) 20 would flash. An example is shown in Fig. 10C. The operator would press either SCROLL 36 or SLING LOAD 2~ to return to the original sling load format display 9A.
The desitnation (DEST) switch 26 is used to determine the engine torque margins at the mission destination point based on 25 actual sling load and the internal load and anticipated remaining fuel weight, altitude and temperature at the mission destination point~
When the destination switch 26 is engaged, the anticipated destination, altitude and air temperature would be displayed as shown in Fig. llA
and an example in Fig. 12A. These values may be updated by the 30 operator using the data entry keys. Next, the operator would press the scroll key 36 to display and update the anticipated remaining ~l2~
g fuel at destination. The destination remaining fuel value is shown on the second line of Fig. llB and an example in Fig. 12B. The resulting torqu~ margins at destination are displayed on the third line of Fig. llB and will flash if they are exceeded.
The recall key RCL 28, on the control panel 18 is used to display the same data that appears when the system is turned on (Fig. 5). The test key TEST, 30, is used for built-in-test pur-poses. The calibration key CALB 32, is used to calibrate the system processor with the discretes from the external cargo hooks, fuel 10 gauge and altitude and air temperature indicators.
Changes may be made in the construction and arrangement of the parts or elements of the embodiments as described herein without departing from the spirit or scope of the invention defined in the following claims.
Claims (16)
1. A helicopter weight and torque advisory system con-nected to a helicopter's fuel gauge, outside air temperature and altitude indicating system and hook load sensor and operated by one of the helicopter's personnel, the system comprising:
a control panel and processor unit connected to the air-craft's power source, hook load sensor, fuel gauges, outside air temperature and altitude system, the control panel processor unit including a computer and neces-sary memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by a cargo hook as an external load is raised by the helicopter; and a remote display unit connected to the processor unit, the display unit displaying the helicopter's fuel weight, outside air temperature and altitude.
a control panel and processor unit connected to the air-craft's power source, hook load sensor, fuel gauges, outside air temperature and altitude system, the control panel processor unit including a computer and neces-sary memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by a cargo hook as an external load is raised by the helicopter; and a remote display unit connected to the processor unit, the display unit displaying the helicopter's fuel weight, outside air temperature and altitude.
2. The system as described in Claim 1 wherein the control panel and processor unit includes an on/off switch, internal load key, sling load key, destination key, recall key, calibration key and test key along with three data entry keys such as change, scroll and enter.
3. The system as described in Claim 2 wherein the control panel and processor unit includes a brightness control knob for providing light to the remote display unit.
4. The system as described in Claim 1 wherein the remote display unit displays operation weight, operation weight balance and center of gravity.
5. The system as described in Claim 1 wherein the remote display unit displays payload and individual weight in cargo compart-ments of the helicopter.
6. The system as described in Claim 1 wherein the re-mote display unit displays individual loads on a forward, a center and an aft hook mounted on the helicopter.
7. The system as described in Claim 6 wherein the remote display visually displays when the forward hook, center hook or aft hook reaches its load limits.
8. The system as described in Claim 1 wherein the remote display unit visually flashes when the torque margin, gross weight, gross weight center of gravity and individual hook load reaches its limit.
9. A helicopter weight and torque advisory system con-nected to a helicopter's fuel gauge, outside air temperature and altitude indicating system and hook load sensors and operated by one of the helicopter's personnel, the system comprising:
a control panel and processor unit connected to the air-craft's power source, hook load sensor, fuel flow in-dicating system, outside air temperature gauge, pressure altitude gauge and anti-ice system, the control panel and processor unit including a computer and necessary memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each of the helicopter's cargo hooks as an external load is raised by each of the hooks of the helicopter; and a remote display unit connected to the processor unit, the display unit displaying the helicopter's fuel weight, out-side air temperature and altitude.
a control panel and processor unit connected to the air-craft's power source, hook load sensor, fuel flow in-dicating system, outside air temperature gauge, pressure altitude gauge and anti-ice system, the control panel and processor unit including a computer and necessary memory for storing and calculating the helicopter's engine torque margin, gross weight, gross weight center of gravity and individual weight supported by each of the helicopter's cargo hooks as an external load is raised by each of the hooks of the helicopter; and a remote display unit connected to the processor unit, the display unit displaying the helicopter's fuel weight, out-side air temperature and altitude.
10. The system as described in Claim 9 wherein the control panel and processor unit includes an on/off switch, internal load key, sling load key, destination key, recall key, calibration key and test key along with three data entry keys such as change, scroll and enter.
11. The system as described in Claim 10 wherein the control panel and processor unit includes a brightness control knob for providing light to the remote display unit.
12. The system as described in Claim 10 wherein the remote display unit displays operation weight, operation weight balance and center of gravity.
13. The system as described in Claim 9 wherein the remote display unit displays payload and individual weight in cargo compart-ments of the helicopter.
14. The system as described in Claim 9 wherein the remote display unit displays individual loads on a forward, a center and an aft hook mounted on the helicopter.
15. The system as described in Claim 14 wherein the remote display unit visually displays when the forward hook, center hook or aft hook reaches its load limits.
16. The system as described in Claim 9 wherein the remote display unit visually flashes when the torque margin, gross weight, gross weight center of gravity and individual hook load reaches its limit.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US68853385A | 1985-01-03 | 1985-01-03 | |
| US688,533 | 1985-01-03 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1240048A true CA1240048A (en) | 1988-08-02 |
Family
ID=24764804
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000498862A Expired CA1240048A (en) | 1985-01-03 | 1986-01-02 | Helicopter weight and torque advisory system |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS61211199A (en) |
| CA (1) | CA1240048A (en) |
| FR (1) | FR2575550B1 (en) |
| GB (1) | GB2169572B (en) |
| IT (1) | IT1188221B (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH671555A5 (en) * | 1986-09-10 | 1989-09-15 | Zermatt Air Ag | |
| JPH064439B2 (en) * | 1987-09-01 | 1994-01-19 | 防衛庁技術研究本部長 | Aircraft center of gravity measuring device |
| US5229956A (en) * | 1991-03-06 | 1993-07-20 | United Technologies Corporation | Helicopter weight measurement |
| FR2866109B1 (en) * | 2004-02-05 | 2006-04-07 | Airbus France | METHOD AND DEVICE FOR VERIFYING A TEMPERATURE VALUE AT AN ALTITUDE OF DESTINATION OF AN AIRCRAFT |
| WO2008018912A2 (en) * | 2006-02-23 | 2008-02-14 | Sikorsky Aircraft Corporation | Radio frequency emitting hook system for a rotary-wing aircraft external load handling |
| FR2936491B1 (en) | 2008-09-26 | 2010-10-08 | Eurocopter France | METHOD FOR LARGING AN EXTERNAL LOAD CARRIED BY AN AIRCRAFT AND ASSOCIATED DEVICE |
| FR2953493B1 (en) | 2009-12-08 | 2012-01-27 | Eurocopter France | AIRCRAFT PROVIDED WITH A STEERING ASSISTING DEVICE WHEN IT FEATURES AN EXTERNAL LOAD WITH A SLING, AND A METHOD USED THEREBY |
| FR2977565B1 (en) | 2011-07-07 | 2013-07-12 | Eurocopter France | DEVICE FOR FIXING AND CONTROLLING THE INCLINATION OF A SLING, AND AIRCRAFT |
| JP5832352B2 (en) * | 2012-03-29 | 2015-12-16 | 三菱重工業株式会社 | Vertical take-off and landing aircraft torque estimation device, vertical take-off and landing aircraft, vertical take-off and landing aircraft torque estimation program, and vertical take-off and landing aircraft torque estimation method |
| JP5960019B2 (en) * | 2012-10-02 | 2016-08-02 | 三菱重工業株式会社 | Flight management support device, flight management support system, flight management support method, and display device |
| WO2016007796A1 (en) | 2014-07-10 | 2016-01-14 | Breeze-Eastern Corporation | Helicopter hoist systems, devices, and methodologies |
| GB2533584A (en) * | 2014-12-22 | 2016-06-29 | Airbus Operations Ltd | Aircraft fuel tank inerting arrangement, method of inerting one or more aircraft fuel tanks, aircraft and software product |
| FR3142461A1 (en) | 2022-11-30 | 2024-05-31 | Airbus Helicopters | method of setting the mass of a load to be transported by an aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1416344A (en) * | 1964-02-04 | 1965-11-05 | United Aircraft Corp | Remaining power indicator |
| NL7905278A (en) * | 1979-07-06 | 1981-01-08 | Philips Nv | APPARATUS FOR RECORDING AND READING SIGNALS IN TRACKS ON A MAGNETIC TAPE. |
-
1985
- 1985-12-19 GB GB08531319A patent/GB2169572B/en not_active Expired
- 1985-12-26 JP JP60292406A patent/JPS61211199A/en active Pending
-
1986
- 1986-01-02 CA CA000498862A patent/CA1240048A/en not_active Expired
- 1986-01-03 FR FR868600057A patent/FR2575550B1/en not_active Expired
- 1986-01-03 IT IT19008/86A patent/IT1188221B/en active
Also Published As
| Publication number | Publication date |
|---|---|
| JPS61211199A (en) | 1986-09-19 |
| GB2169572B (en) | 1988-02-10 |
| FR2575550B1 (en) | 1989-12-15 |
| GB8531319D0 (en) | 1986-01-29 |
| FR2575550A1 (en) | 1986-07-04 |
| IT1188221B (en) | 1988-01-07 |
| IT8619008A0 (en) | 1986-01-03 |
| GB2169572A (en) | 1986-07-16 |
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