GB2169572A

GB2169572A - A helicopter weight and torque advisory system

Info

Publication number: GB2169572A
Application number: GB08531319A
Authority: GB
Inventors: Richard L Adelson
Original assignee: Boeing Co
Current assignee: Boeing Co
Priority date: 1985-01-03
Filing date: 1985-12-19
Publication date: 1986-07-16
Also published as: CA1240048A; GB2169572B; FR2575550B1; IT8619008A0; GB8531319D0; JPS61211199A; FR2575550A1; IT1188221B

Abstract

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 supported by the helicopter. The various parameters can be displaced selectively (Figs 5-12). <IMAGE>

Description

SPECIFICATION A helicopter weight and torque advisory system Background of the invention This invention relates to a helicopter advisory system and more particularly, but not by way of limitation, to a system for 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 automated means of knowing required engine torque relative to available torque 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, cumbersome and always subject to error. This manual system may cause helicopter structural damage, inability to complete missions and unfortunate accidents.

Prior attempts to determine the helicopters condition after lifting external cargo did not incorporate the real time input of altitude, temperature and fuel weight data necessary to determine engine torque margins.

The subject helicopter weight and torque advisory system eliminates 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 weight and torque advisory system connected to 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 aircraft's power source, hook load sensor, fuel gauges, outside air temperatue and altitude system, the control panel 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 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.

According to another aspect of the invention there is provided a helicopter weight and torque advisory system connected 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 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 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, outside air temperature and altitude.

The subject helicopter weight and torque advisory system displays in real time the helicopter's engine torque margin, gross weight, gross weight center of gravity and weight supported by each cargo hook as an external load is raised and carried by the helicopter.

The system display also alerts the flight crew when required torque approaches available torque.

Also, it displays the helicopter gross weight and gross weight center of gravity (CG) which flash when a (CG) limit is exceeded. Also, it displays the weight lifted by a cargo hook and flashes when the hook weight 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 unit and control panel may be mounted in the cockpit of the helicopter and may be read in direct sunlight and with or without night vision goggles.

The control panel portion of the control panel and processor unit consists of an ON/OFF switch, three mode switches, i.e., internal cargo load switch IN TERNAL LOAD, sling load switch SLING LOAD and engine torque margin at destination switch DEST.

Also, it contains a recall key RCL, a test key TEST and a calibration key CALB. Further, it includes three data keys, CHANGE, SCROLL 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 characters.

The remote display unit and control panel and processor unit are small for potential installation in existing space without disturbing existing equipment in the helicopter's cockpit.

Brief description of the drawings Figure 1 illustrates the remote display unit.

Figure 2 illustrates the control panel of the control panel and processor unit.

Figure 3 illustrates a cockpit of a helicopter for receiving the remote display unit and control panel and processor unit.

Figures 4A and 4B illustrate a system diagram of the advisory system and processor unit components.

Figures 5A, 5B, 5C and 5D illustrate the display formats when the on/off switch is engaged.

Figures 6A, 6B, 6C and 6D illustrate example displays when the on/off switch is engaged.

Figures 7A and 7B illustrate the display formats when the internal load switch is engaged.

Figures 8A, 8B and 8C illustrate example displays when the internal load switch is engaged.

Figures 9A and 9B illustrate the display formats when the sling load switch is engaged.

Figures lOA, 70B and 10C illustrate example dis plays when the sling load switch is engaged.

Figures 71A and 71B illustrate display formats when the Destination (DEST) switch is engaged.

Figures 12A and 12B illustrate example displays when the Destination (DEST) switch is engaged.

Figure 13 illustrates the location of the cargo compartments in an example CH-47D helicopter.

Figure 14 illustrates the location of the external cargo hooks on the example CH-47D helicopter.

Detailed description of the drawings In Figure 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 Figure 2, the control panel and processor 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 data 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 Figure 3 is a cockpit for a CH-47D helicopter showing 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 18 are small enough for potential installation in existing space without disturbing the equipment used with various types of helicopters.

In Figure 4A a system diagram is shown which illustrates the interface between the helicopter weight and torque advisory system designated by general reference numeral 42 and other helicopter systems. In this diagram, the remote display unit 10 shown is connected to the control panel and processor unit 18 via lead 43. The unit 18 is connected via lead 44 to lead 45 which is connected to the fuel gauging system of the helicopter. Lead 44 is also connected to lead 46 connected to the outside air temperature sensor system of the helicopter and to lead 48 connected to the altitude indicating system of the helicopter.

In Figure 4B the computer and necessary memory of the processor 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 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 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 10.

Referring now to Figure 5A and prior to the start of a mission, the operator turns the system on using the on/off 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 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 would press the SCROLL key 36 on the control panel 18 to view the helicopters operating weight, Figure 5B, operating weight CG, Figure 5C, and type of engines, Figure 5D, 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 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 character position. If a character is to be entered or updated, the operator then presses the SCROLL key 36 to bring up the desired character and then the ENTER key 38 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. Figures 6A, 6B, 6C and 6D are examples of the display formats that would appear 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 SCROLL key is used when Figure 5D is displayed.

The operator must manually enter the internal cargo load weight into the system processor prior to the lifting of the external sling load. This is accomplished by first engaging the INTERNAL LOAD switch 22 on the control panel 18 which brings up format Figure 7A 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 which are shown in Figure 13. This weight distribution may be viewed by pressing the SCROLL key and the display format would be as shown in 78. If the internal cargo load weight is not distributed evenly, the operator would enter the unevently distributed load into the processor using the Figure 7B format and the data entry keys CHG 34, SCROLL 36 and ENTER 38. Figures 8A and 8B illustrate an example of a 16,000 pound internal payload evenly distributed and nonevenly distributed in Figure 8C.

Prior to lifting an external load, the operator would engage the SLING LOAD switch 24. The display format that will appear is shown in Figure 9A.

As the external sling load is raised, the helicopter gross weight shown in the first line 12 of the display 10 would increase, as well as the total sling load weight shown in the second line 14 of the cis- play 10. Also, as the external sling load is raised, the torque margin for two engines and single en gine operation would decrease and would be displayed in the third line 16 of the display 10. An example of an actual display is shown in Figure 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 of the display 10 and the entire line would start flashing. If the weight limit of external cargo hooks, 76, 78 or 80 shown in Figure 14 is exceeded, the hook that is overloaded will appear in the first position of line 14 of the display 10 and the entire line 14 of the display 10 will flash. An "A" in the first position would indicate forward hook 76, "C" the center hook 78 and "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 Figure 10B.

If the operator wants to view the individual sling load weights, he would press the scroll key 36 and the display format 9B displaying the individual sling loads supported by rack hook wou!d be displayed. The hook position and the sling weight it is supporting are displayed and if any of the hook load limit weights exceeded their load limit, its weight value and hook identification symbol (F, C, A) would flash. An example is shown in Figure 10C. The operator would press either SCROLL 36 or SLING LOAD 24 to return to the original sling load format display 9A.

The destination (DEST) switch 26 is used to determine the engine torque margins at the mission destination point based on 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 Figure 11A and an example in Figure 12A. These values may be updated by the operator using the data entry keys. Next, the operator would press the scroll key 36 to display and update the anticipated remaining fuel at destination. The destination remaining fuel value is shown on the second line of Figure 11B and an example in Figure 12B. The resulting torque margins at destination are displayed on the third line of Figure 11B 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 (Figure 5). The test key TEST, 30, is used for built-in-test purposes. The calibration key CALB 32, is used to calibrate the system processor with the discretes from the external cargo hooks, fuel 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 scope of the invention defined in the fol

Claims

lowing claims. CLAIMS

1. A helicopter weight and torque advisory system connected 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 aircraft's power source, hook load sensor, fuel gauges, outside air temperature and altitude system, the control panel 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 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 compartments of the helicopter.

6. The system as described in Claim 1 wherein the remote 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 connected 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 aircraft's power source, hook load sensor. fue flow indicating system, outside air temperature gauge, pressure altitude guage 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, outside 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 compartments 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.

17. A helicopter weight and torque advisory system substantially as herein described with reference to and as shown in the accompanying drawings.