US4760964A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Actuator system for jet nozzle flap
Assignee: Sundstrand Corp
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Filing: 1986-10-31
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Granted: 1988-08-02
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Expires: 2006-10-31
Abstract
Abstract In order to enhance performance of an aircraft while at the same time utilizing redundant aircraft hydraulic power in an efficient manner, an actuator system for a nozzle flap of an aircraft engine is provided. The actuator system includes a power drive unit in operatively associated relation with drive transmitting gearing at a single location together with an actuator driven by the power drive unit through the drive transmitting gearing, and the actuator includes output drive gearing operatively associated with the nozzle flap for driving the nozzle flap at spaced apart locations. With this arrangement, the nozzle flap is driven at spaced apart locations by the power drive unit from a single location through the actuator to permit downsizing of components with consequent weight reduction to achieve enhanced performance.
Inventors
- 👤 Wesley A. Burandt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 16:36
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/06; F02K1/12; B; B64; B64C; B64C13/00; B64C13/24; B64C13/26; B64C13/28; B64C13/341; F02K1/1207; Y; Y02; Y02T; Y02T50/00; Y02T50/40; Y02T50/60
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
171 words
An actuator system for a nozzle flap of an aircraft engine, comprising: a pair of power drive units at a single location; a geared rotary actuator driven by said power drive units through said drive transmitting gearing, said geared rotary actuator comprising a pair of axially spaced differential planetary output stages, said differential planetary output stages being operatively associated with opposite ends of said nozzle flap; each of said differential planetary output stages having a center output ring gear in drivingly interconnected relationship with said nozzle flap, each of said differential planetary output stages also having a pair of outer fixed ring gears idsposed about said center output ring gear; said power drive units being drivingly interconnected with said differential planetary output stages through drive transmitting gearing; and means for transmitting torque from said center output ring gears across said outer fixed ring gears to said nozzle flap; whereby said nozzle flap is driven at opposite ends by said power drive units from a single location through said geared rotary actuator.
Claim 2
Dependent Claim
171 words
An actuator system for a nozzle flap of an aircraft engine, comprising: a pair of power drive units at a single location; a geared rotary actuator driven by said power drive units through said drive transmitting gearing, said geared rotary actuator comprising a pair of axially spaced differential planetary output stages, said differential planetary output stages being operatively associated with opposite ends of said nozzle flap; each of said differential planetary output stages having a center output ring gear in drivingly interconnected relationship with said nozzle flap, each of said differential planetary output stages also having a pair of outer fixed ring gears idsposed about said center output ring gear; said power drive units being drivingly interconnected with said differential planetary output stages through drive transmitting gearing; and means for transmitting torque from said center output ring gears across said outer fixed ring gears to said nozzle flap; whereby said nozzle flap is driven at opposite ends by said power drive units from a single location through said geared rotary actuator.
Claim 3
Dependent Claim
30 words
The actuator system as defined by claim 1 wherein said power drive units each comprise a hydraulic motor valve pack and said drive transmitting gearing comprises a bevel gear set.
Claim 4
Dependent Claim
48 words
The actuator system as defined by claim 2 wherein said hydraulic motor valve packs are operatively connected to an aircraft hydraulic power system, said geared rotary actuator including a pair of axially spaced input gears operatively connected to said hydraulic motor valve packs through said bevel gear set.
Claim 5
Dependent Claim
62 words
The actuator system as defined by claim 3 wherein each of said axially spaced input gears is operatively connected to one of said axially spaced differential planetary output stages for driven movement of said nozzle flap through said center output ring gears, said geared rotary actuator converting hydraulic power from said aircraft hydraulic power system to mechanical power driving said nozzle flap.
Claim 6
Dependent Claim
48 words
The actuator system as defined by claim 1 including a tubular support for said nozzle flap of said aircraft engine, said center output ring gears and said outer fixed ring gears of said geared rotary actuator defining said tubular support for said nozzle flap of said aircraft engine.
Claim 7
Dependent Claim
72 words
The actuator system as defined by claim 1 wherein each of said differential planetary output stages is driven by a simple planetary input stage, said simple planetary input stage driving each of said differential planetary output stages comprising a portion of said geared rotary actuator, said simple planetary input stage driving each of said differential planetary output stages also being operatively connected to said power drive units through said drive transmitting gearing.
Claim 8
Dependent Claim
54 words
The actuator system as defined by claim 6 wherein said drive transmitting gearing includes a bevel gear set operatively connecting said power drive units to a second simple planetary input stage, said second simple planetary input stage being operatively connected to said simple planetary input stage driving each of said differential planetary output stages.
Claim 9
Dependent Claim
82 words
The actuator system as defined by claim 7 wherein said simple planetary input stages each include a sun gear and a fixed ring gear together with a plurality of planet gears disposed therebetween, said sun gear of said simple planetary input stage being operatively connected to said planet gears of said second simple planetary input stage thrugh a planetary carrier therefor, said sun gear of said second simple planetary input stage being operatively connected to said bevel gear set through a shaft.
Claim 10
Dependent Claim
68 words
The actuator system as defined by claim 8 wherein said simple planetary input stage driving each of said differential planetary output stages includes a planetary carrier operatively connected to a sun gear of one of said differential planetry outut stages in a direct integral fashion and a planetary carrier operatively connected to a sun gear of the other of said differential planetary output stages through a torque tube.
Claim 11
Dependent Claim
129 words
The actuator system as defined by claim 9 wherein each of said differential planetary output stages also includes a plurality of planet gear shafts each carrying a center planet gear and a pair of outer planet gears, each of said center planet gears being disposed in drivingly interconnected relationship with the respective ones of said sun gears and said center output ring gears and each of said pairs of outer planet gears being disposed in drivingly interconnected relationship with the respective ones of said pairs of outer fixed ring gears, and including a support ring disposed on either side of each of said center planet gears inwardly of the respective ones of said outer planet gears to maintain said planet gears in drivingly interconnected relationship with said ring gears.
Claim 12
Dependent Claim
51 words
The actuator system as defined by claim 6 wherein said power drive units are disposed within a tube support for said nozzle flap intermediate the ends thereof and are each drivingly interconnected with one of said differential planetary output stages through a separate drive transmitting gearing and simple planetary input stage.
Claim 13
Dependent Claim
109 words
The actuator system as defined by claim 11 wherein said drive transmitting gearing includes a seperate drive gear operatively associated with each of said power drive units and a driven gear operatively associated with each of said drive gears, each of said driven gears being drivingly interconnected with a sun gear of the corresponding one of said simple planetary input stages through a torque tube, each of said simple planetary input stages also including a plurality of planet gears disposed between said sun gear and a fixed ring gear and a planetary carrier operatively connected to a sun gear of the corresponding one of said differential planetary output stages.
Claim 14
Dependent Claim
129 words
The actuator system as defined by claim 12 wherein each of said differential planetary output stages also includes a plurality of planet gear shafts each carrying a center planet gear and a pair of outer planet gears, each of said center planet gears being disposed in drivingly interconnected relationship with the respective ones of said sun gears and said center output ring gears and each of said pairs of outer planet gears being disposed in drivingly interconnected relationship with the respective ones of said pairs of outer fixed ring gears, and including a support ring disposed on either side of each of said center planet gears inwardly of the respective ones of said outer planet gears to maintain said planet gears in drivingly interconnected relationship with said ring gears.
Claim 15
Dependent Claim
30 words
The actuator system as defined by claim 11 wherein said center output ring gears and said tube support are supported relative to said outer fixed ring gears on ball bearings.
Claim 16
Dependent Claim
64 words
The actuator system as defined by claim 1 wherein each of said differential planetary output stages is formed such that one of said outer fixed ring gears and center output ring gears has an arcuate slot and the other of said outer fixed ring gears and center output ring gear has a fork extending through said arcuate slot to define said torque transmitting means.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1991-08-02 | 1992-02-01 | 1992-08-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-08-02 | 1996-02-01 | 1996-08-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-08-02 | 2000-02-01 | 2000-08-02 | $7700.00 | Window Closed / Lapsed |