Patent US3836100A successfully refreshed from Google Patents.
US3836100A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Engine mounting arrangement
Assignee: RTX Corp
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Filing: 1973-06-13
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Granted: 1974-09-17
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Expires: 1993-06-13
Abstract
Abstract Aircraft engine mounting arrangement in which a rear lower mount has near zero lateral restraint and an elastic vertical restraint and rear upper mount has near zero vertical restraint and an elastic lateral restraint, and an imaginary straight line drawn through the horizontal line of restraint for the front mounting and the rear upper mount locations will pass through the engine installation center of gravity to uncouple engine roll response from airframe lateral input motions.
Inventors
- 👤 Hardenberg P Von
- 👤 G Molnar
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 12:52
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/001
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
78 words
An aircraft engine mounting arrangement including front and rear mountings; said rear mounting including a lower mount having near zero lateral restraint and an elastic vertical restraint, and an upper mount having near zero vertical restraint and an elastic lateral restraint; said upper mount being located vertically such that its horizontal line of restraint intersects an imaginary straight line passing through the horizontal line of restraint for said front mounting and the center of gravity of the engine.
Claim 2
Dependent Claim
78 words
An aircraft engine mounting arrangement including front and rear mountings; said rear mounting including a lower mount having near zero lateral restraint and an elastic vertical restraint, and an upper mount having near zero vertical restraint and an elastic lateral restraint; said upper mount being located vertically such that its horizontal line of restraint intersects an imaginary straight line passing through the horizontal line of restraint for said front mounting and the center of gravity of the engine.
Claim 3
Dependent Claim
25 words
An aircraft engine mounting arrangement in accordance with claim 1 in which the restraining device for the upper and lower mounts includes a vibration isolator.
Claim 4
Dependent Claim
33 words
An aircraft engine mounting arrangement in accordance with claim 2 in which the vibration isolator for the lower mount is vertically positioned and the vibration isolator for the upper mount is horizontally positioned.
Claim 5
Dependent Claim
24 words
An aircraft engine mounting arrangement in accordance with claim 3 in which the vibration isolators are each connected to the engine at two points.
Claim 6
Dependent Claim
35 words
An aircraft engine mounting arrangement in accordance with claim 2 in which one portion of each isolator is pivotably connected to the engine and another portion of each isolator is pivotably connected to the aircraft.
Claim 7
Dependent Claim
26 words
An aircraft engine mounting arrangement in accordance with claim 5 in which the pivotable connection of eacH isolator to the engine includes a pair of links.
Claim 8
Dependent Claim
25 words
An aircraft engine mounting arrangement in accordance with claim 2 in which the lower mount vibration isolator is located directly below the engine center line.
Claim 9
Dependent Claim
27 words
An aircraft engine mounting arrangement in accordance with claim 2 in which the lower vibration isolator is tangentially connected to the engine by a pair of links.
Claim 10
Dependent Claim
97 words
An engine mounting arrangement for a helicopter; said mounting arrangement including front and rear mountings; said rear mounting including lower and upper mounts; said lower mount including a vibration isolator one portion of which is connected to the fuselage of said helicopter and another portion of which is connected to said engine; said lower mount being directly below the center line of said engine and providing vertical stiffness and a near zero lateral spring rate; and said upper mount being at the side of said engine and providing lateral stiffness and a near zero vertical spring rate.
Claim 11
Dependent Claim
97 words
An engine mounting arrangement for a helicopter; said mounting arrangement including front and rear mountings; said rear mounting including lower and upper mounts; said lower mount including a vibration isolator one portion of which is connected to the fuselage of said helicopter and another portion of which is connected to said engine; said lower mount being directly below the center line of said engine and providing vertical stiffness and a near zero lateral spring rate; and said upper mount being at the side of said engine and providing lateral stiffness and a near zero vertical spring rate.
Claim 12
Dependent Claim
50 words
An engine mounting arrangement for a helicopter in accordance with claim 9 in which the upper mount is located vertically such that its horizontal line of restraint intersects an imaginary line passing through the horizontal line of restraint for said front mounting and the center of gravity of the engine.
Claim 13
Dependent Claim
50 words
An engine mounting arrangement for a helicopter in accordance with claim 9 in which the connection of the lower mount isolator includes two links; one end of each link having a common connection with said isolator; and the other end of each link having a tangential connection with said engine.
References Cited (Backward Citations)
US2380274A
Cited
US2753140A
Cited
US3056569A
Cited
US2936978A
Cited
US3217490A
Cited
US3288404A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-09-16 | 1978-03-18 | 1978-09-17 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-09-16 | 1982-03-18 | 1982-09-17 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-09-16 | 1986-03-18 | 1986-09-17 | $7700.00 | Window Closed / Lapsed |