Automatic release of a load from a helicopter external cargo suspension system

• US 5,465,925 A
• Filed: 05/27/1994
• Issued: 11/14/1995
• Est. Priority Date: 05/27/1994
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Smith, Matthew T., Mankaukas, Joseph J., Connolly, Christopher J., Lawrence, Thomas H., Pawlowski, John J.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/250,988
• Time in Patent Office: 536 Days
• Field of Search: 244/137.1, 244/137.2, 244/137.3, 244/137.4, 244/118.2, 244/118.1, 364/567, 395/900, 414/21
• US Class Current: 244/137.1
• CPC Class Codes: B64D 1/12 Releasing

Abstract

A helicopter external cargo suspension system (12) has load sensors (19,20) at each suspension point for sensing the magnitude of a load (32) at each suspension point. A delay period (FIG. 6) is determined based on the magnitude of the load, and a load is released if one of the following failure modes occurs for a period which exceed the delay period: one of the suspension points is unloaded, the magnitude of the load exceeds a maximum threshold magnitude, or if the distribution of the load, as indicated by the difference in magnitude at each suspension point, exceeds a difference threshold magnitude. If the magnitude of the load is below a minimum threshold magnitude, the load will be carried by one of the suspension points in response to a failure of the other suspension points.

Alternatively, the load information is converted from crisp values to fuzzy inputs (700) wherein the detected values are fuzzified by assigning a membership weight at discrete points or segments on a normalized scale; a new mode fuzzy output (707) is provided by applying a compositional rule of inference (705) across each fuzzy input (702) and a composite mode selection rule base (710), the new mode fuzzy output (707) is converted into a crisp output by taking the weighted sum of the membership weight at each point on the normalized scale in excess of a threshold value (712), and new mode is determined by comparing the new mode crisp output to a set of new mode membership ranges (FIGS. 8e and 9e).

Claims

1. A helicopter external cargo suspension system, comprising:

at least one suspension point for externally suspending cargo from the helicopter;

each suspension point having a load sensor for sensing the weight exerted by cargo at each suspension point and for providing weight signals indicative thereof;

each suspension point having disconnect means responsive to the absence of a disconnect signal for maintaining a connection between the helicopter and cargo via said suspension point and responsive to the presence of said disconnect signal for disconnecting cargo from the helicopter;

signal processing means responsive to said weight signals for determining if a failure mode has occurred, and for providing a disconnect signal to all of said disconnect means if a failure mode is determined.

2. A helicopter external cargo suspension system according to claim 1 further comprising:

delay means for calculating a delay period based on the total weight of cargo as indicated by the sum of said weight signals; and

said signal processing means providing a disconnect signal to all of said disconnect means only if the duration of said failure mode exceeds said delay period.

3. A helicopter external cargo suspension system according to claim 2 wherein said failure mode is determined in response to the sum of said weight signals exceeding an overload weight limit.

4. A helicopter external cargo suspension system according to claim 2 wherein said failure mode is determined in response to the failure of one of said suspension points.

5. A helicopter external cargo suspension system according to claim 4 wherein the failure of one of said suspension points is indicated by said corresponding weight signal for said suspension point being less than a minimum weight limit.

6. A helicopter external cargo suspension system according to claim 5 wherein said minimum weight limit is approximately zero kilograms (zero pounds).

7. A helicopter external cargo suspension system according to claim 2 wherein said failure mode is determined in response to an out of balance cargo condition.

8. A helicopter external cargo suspension system according to claim 7 wherein said out of balance cargo condition is indicated by the difference between said weight signals exceeding an out of balance weight limit.

9. A helicopter external cargo suspension system according to claim 1 further comprising display means for indicating to a pilot the nature of said failure mode.

10. A helicopter external cargo suspension system according to claim 2 wherein said signal processing means does not provide a disconnect signal if the sum of said weight signals is below a minimum threshold magnitude.

11. A helicopter external cargo suspension system according to claim 2 wherein the duration of said delay period is inversely proportional to the sum of said weight signals.

12. A helicopter external cargo suspension system according to claim 11 wherein said signal processing means does not provide a disconnect signal if the sum of said weight signals is below a minimum threshold magnitude.

13. A helicopter external cargo suspension system according to claim 12 wherein said failure mode is determined in response to the sum of said weight signals exceeding an overload weight limit.

14. A helicopter external cargo suspension system according to claim 13 wherein said failure mode is determined in response to the failure of one of said suspension points.

15. A helicopter external cargo suspension system according to claim 14 wherein the failure of one of said suspension points is indicated by said corresponding weight signal for said suspension point being less than a minimum weight limit.

16. A helicopter external cargo suspension system according to claim 15 wherein said minimum weight limit is approximately zero kilograms (zero pounds).

17. A helicopter external cargo suspension system according to claim 14 wherein said failure mode is determined in response to an out of balance cargo condition.

18. A helicopter external cargo suspension system according to claim 17 wherein said out of balance cargo condition is indicated by the difference between said weight signals exceeding an out of balance weight limit.

19. A helicopter external cargo suspension system according to claim 17 further comprising display means for indicating to a pilot the nature of said failure mode.

20. A helicopter external cargo suspension system according to claim 19 wherein each of said suspension points further comprises:

support lines; and

retaining members for attachment to cargo;

said load sensors, disconnect means, support lines and retaining members acting in cooperation to provide an attachment between the helicopter and cargo.

21. A helicopter external cargo suspension system according to claim 1 further comprising:

duration means for providing a duration signal indicative of the duration of said failure mode;

fuzzification means responsive to said weight signals and said duration signal for providing fuzzy input signals indicative thereof;

rule base means for providing at least one new mode selection rule, each new mode selection rule representing a suitable new mode selection decision;

said signal processing means applying said fuzzy input signals to said new mode selection rules for providing a new mode fuzzy output signal;

defuzzification means responsive to said new mode fuzzy output signal for providing a crisp output signal indicative thereof; and

mode selection means responsive to said crisp output signal for providing a disconnect signal to all of said disconnect means in response to a release load new mode, and for retaining said cargo on said suspension points in response to a retain load new mode.

22. A helicopter external cargo suspension system according to claim 21 further comprising a composite mode selection rule base means for providing a composite mode selection signal for each possible combination of said fuzzy input signals, said composite mode selection rule base being generated as a composition of said new mode selection rules.

23. A helicopter external cargo suspension system according to claim 22 further comprising memory means for storing said composite mode selection rule base means.

24. A helicopter external cargo suspension system according to claim 21 wherein said fuzzification means comprises:

scaling means for applying a scale factor to said weight signals and said duration signals to thereby provide a corresponding scaled value signal in relation to discrete segments (u_i) on a normalized scale;

membership weight assignment means responsive to said scaled value signals for providing a membership weight (ω

_i) value at each discrete segment (u_i) on said normalized scale for each of said scaled value signals; and

each of said fuzzy input signals thereby being represented as a set of ordered pairs of discrete segments and corresponding membership weights (u_i,ω

_i).

25. A helicopter external cargo suspension system according to claim 24 wherein said defuzzification means comprises means for providing said crisp output signals as the weighted sum of each of said membership weights in excess of a threshold value for each of said segments.