US4600449A
Expired / Lapsed
US
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Titanium alloy (15V-3Cr-3Sn-3Al) for aircraft data recorder
Assignee: Sundstrand Data Control Inc
•
Filing: 1984-01-19
•
Granted: 1986-07-15
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Expires: 2004-01-19
Abstract
Abstract An aircraft flight data recorder housing comprising a titanium alloy having a nominal composition of 15 weight percent vanadium, 3 weight percent chromium, 3 weight percent tin, and 3 weight percent aluminum with the balance being titanium and, within limitations, certain trace elements. The alloy is simultaneously hot formed and solution heat treated at temperatures on the order of 1400° F. to 1500° F. to fabricate the recorder housing.
Inventors
- 👤 Kenneth W. White
- 👤 William F. Spurr
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 21:42
CPC Classifications
H; H05; H05K; H05K5/00; H05K5/02; H05K5/0213; C; C22; C22C; C22C14/00; G; G12; G12B; G12B17/00; G12B17/08; H05K5/0209; H05K5/021
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
94 words
A flight data recorder housing comprising a titanium alloy consisting essentially of ______________________________________
Element Weight percent (wt. %)
______________________________________
V 14 to 16
Cr 2.5 to 3.5
Sn 2.5 to 3.5
Al 2.5 to 3.5
O.sub.2 0.13 max
N.sub.2 0.03 max
C 0.03 max
H.sub.2 0.015 max
Fe 0.30 max
Y 0.005 max
Residual elements, each
0.10 max
Residual elements, total
0.30 max
Ti Balance,
______________________________________ said housing having been simultaneously formed and solution heat treated at an elevated temperature, said alloy having been aged to an ultimate tensile strength less than 200 ksi.
Claim 2
Dependent Claim
94 words
A flight data recorder housing comprising a titanium alloy consisting essentially of ______________________________________
Element Weight percent (wt. %)
______________________________________
V 14 to 16
Cr 2.5 to 3.5
Sn 2.5 to 3.5
Al 2.5 to 3.5
O.sub.2 0.13 max
N.sub.2 0.03 max
C 0.03 max
H.sub.2 0.015 max
Fe 0.30 max
Y 0.005 max
Residual elements, each
0.10 max
Residual elements, total
0.30 max
Ti Balance,
______________________________________ said housing having been simultaneously formed and solution heat treated at an elevated temperature, said alloy having been aged to an ultimate tensile strength less than 200 ksi.
Claim 3
Dependent Claim
18 words
The flight data recorder of claim 1 wherein said housing is formed at elevated temperatures from sheet stock.
Claim 4
Dependent Claim
28 words
The flight data recorder housing of claim 1 wherein said elevated temperature is in the range of from the beta transus temperature of the alloy to 1500° F.
Claim 5
Dependent Claim
25 words
The flight data recorder housing of claim 3 wherein the average grain size of said alloy is finer than about 3 ASTM grain size units.
Claim 6
Dependent Claim
25 words
The flight data recorder housing of claim 4 wherein the average grain size of said alloy is finer than about 5 ASTM grain size units.
Claim 7
Dependent Claim
24 words
The flight data recorder of claim 1 wherein said alloy has been aged to an ultimate tensile strength of between 165 and 200 ksi.
Claim 8
Dependent Claim
24 words
The flight data recorder of claim 6 wherein said alloy has been aged to an ultimate tensile strength of between 180 and 200 ksi.
Claim 9
Independent Claim
136 words
A method for preparing a flight data recorder housing comprising a titanium alloy exhibiting high strength and fracture toughness wherein said alloy consists essentially of ______________________________________
Element Weight percent (wt. %)
______________________________________
V 14 to 16
Cr 2.5 to 3.5
Sn 2.5 to 3.5
Al 2.5 to 3.5
O.sub.2 0.13 max
N.sub.2 0.03 max
C 0.03 max
H.sub.2 0.015 max
Fe 0.30 max
Y 0.005 max
Residual elements, each
0.10 max
Residual elements, total
0.30 max
Ti Balance,
______________________________________ said method comprising the steps of: a. formulating said alloy and creating an ingot, b. forging said ingot and rolling sheet stock therefrom, c. simultaneously solution treating and forming a flight data recorder housing from said sheet stock at an elevated temperature, and d. aging said alloy to an ultimate tensile strength level less than 200 ksi.
Claim 10
Independent Claim
136 words
A method for preparing a flight data recorder housing comprising a titanium alloy exhibiting high strength and fracture toughness wherein said alloy consists essentially of ______________________________________
Element Weight percent (wt. %)
______________________________________
V 14 to 16
Cr 2.5 to 3.5
Sn 2.5 to 3.5
Al 2.5 to 3.5
O.sub.2 0.13 max
N.sub.2 0.03 max
C 0.03 max
H.sub.2 0.015 max
Fe 0.30 max
Y 0.005 max
Residual elements, each
0.10 max
Residual elements, total
0.30 max
Ti Balance,
______________________________________ said method comprising the steps of: a. formulating said alloy and creating an ingot, b. forging said ingot and rolling sheet stock therefrom, c. simultaneously solution treating and forming a flight data recorder housing from said sheet stock at an elevated temperature, and d. aging said alloy to an ultimate tensile strength level less than 200 ksi.
Claim 11
Dependent Claim
28 words
The method of claim 8 wherein said forming is conducted at a temperature at a range of from the beta transus temperature of the alloy to 1500° F.
Claim 12
Dependent Claim
22 words
The method of claim 9 wherein the average grain size of said alloy is finer than about 3 ASTM grain size units.
Claim 13
Dependent Claim
22 words
The method of claim 10 wherein the average grain size of said alloy is finer than about 5 ASTM grain size units.
Claim 14
Dependent Claim
26 words
The method of claim 9 wherein said flight data recorder housing is maintained at said elevated temperature for a period ranging from 3 to 30 minutes.
Claim 15
Dependent Claim
22 words
The method of claim 8, wherein said alloy is aged to an ultimate tensile strength level of between 165 and 200 ksi.
Claim 16
Dependent Claim
22 words
The method of claim 13, wherein said alloy is aged to an ultimate tensile strength level of between 180 and 200 ksi.
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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) | 1989-07-14 | 1990-01-13 | 1990-07-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-07-14 | 1994-01-13 | 1994-07-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-07-14 | 1998-01-13 | 1998-07-15 | $7700.00 | Window Closed / Lapsed |