Patent US4148675A successfully refreshed from Google Patents.
US4148675A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Insulation system for rocket motors
Assignee: Natural Resources Canada
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Filing: 1978-04-20
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Granted: 1979-04-10
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Expires: 1998-04-20
Abstract
Abstract An insulation system for use in rocket motors containing solid composite propellants is disclosed. Some composite rocket propellants are based on carboxyl-terminated polybutadiene (CTPB) and others on hydroxyl-terminated polybutadiene (HTPB) binders. An important requirement of such systems is the ability of the wall insulation to adhere to the combustion chamber and of the composite propellant to adequately adhere to the insulation system. With CTPB propellants, a sheet insulant comprising chrysotile asbestos fibers and floats dispersed in a CTPB polymeric binder has been successfully employed. However, the use of a similar sheet insulant based on HTPB polymeric binder has not proved to be compatible with HTPB propellants. The present invention provides a composite sheet insulation system which is compatible with HTPB propellants including a first layer of sheet material comprising a CTPB binder having a mixture of asbestos fibers and floats dispersed in it and, bonded to it, a second layer of aluminum foil and an economical and effective method of lining a rocket casing propellant chamber, using the novel system of the present invention.
Inventors
- 👤 Jacques Ratte
- 👤 Gonzague Duchesne
- 👤 Pierre Carignan
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 19:43
CPC Classifications
B; B32; B32B; B32B19/00; B32B19/04; B32B19/041; F; F02; F02K; F02K9/00; F02K9/08; F02K9/32; F02K9/34; F02K9/346; B32B15/00; B32B15/20; B32B19/08; B32B2260/00; B32B2260/02; B32B2260/021; B32B2260/04; B32B2260/048; B32B2307/00; B32B2307/30; B32B2307/304; B32B2311/00; B32B2311/24; Y; Y10; Y10T; Y10T156/00; Y10T156/10; Y10T156/1002
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
191 words
A method of bonding a composite sheet insulant system to a rocket propellant chamber casing in a single operation, said insulant system comprising: (1) a first layer of a sheet material comprising a carboxyl-terminated polybutadiene binder and a mixture of asbestos fibers and floats dispersed therein; and (2) a second layer of aluminum foil: said method comprising: (a) attaching, but not bonding, said layer of sheet material to said aluminum foil layer along only one longitudinal edge thereof, (b) forming said insulant system into a roll and allowing said layer of sheet material and said aluminum foil layer to move relative to each other from the edge of their attachment thereby at least substantially eliminating air inclusions therebetween, (c) inserting said roll into said chamber, (d) positioning said insulant system in said chamber, said first layer in contact with said casing and the aluminum foil layer defining a facing for said chamber, and (e) simultaneously bonding said first layer to said casing and to said aluminum foil in a single step by heating and applying outward pressure from the interior of said roll to force said insulant system against said casing.
Claim 2
Independent Claim
191 words
A method of bonding a composite sheet insulant system to a rocket propellant chamber casing in a single operation, said insulant system comprising: (1) a first layer of a sheet material comprising a carboxyl-terminated polybutadiene binder and a mixture of asbestos fibers and floats dispersed therein; and (2) a second layer of aluminum foil: said method comprising: (a) attaching, but not bonding, said layer of sheet material to said aluminum foil layer along only one longitudinal edge thereof, (b) forming said insulant system into a roll and allowing said layer of sheet material and said aluminum foil layer to move relative to each other from the edge of their attachment thereby at least substantially eliminating air inclusions therebetween, (c) inserting said roll into said chamber, (d) positioning said insulant system in said chamber, said first layer in contact with said casing and the aluminum foil layer defining a facing for said chamber, and (e) simultaneously bonding said first layer to said casing and to said aluminum foil in a single step by heating and applying outward pressure from the interior of said roll to force said insulant system against said casing.
Claim 3
Dependent Claim
22 words
The method of claim 1 wherein said sheet material is stapled to said aluminum foil layer along only one longitudinal edge thereof.
Claim 4
Independent Claim
159 words
A method of bonding a composite sheet insulant system to a rocket propellant chamber casing in a single operation, said insulant system comprising: (1) a first layer of a sheet material comprising a carboxyl-terminated polybutadiene binder and a mixture of asbestos fibers and floats dispersed therein, and (2) a second layer of aluminum foil, said method comprising: (a) attaching, but not bonding, said layer of sheet material to said aluminum foil layer along only one longitudinal edge thereof, (b) forming said insulant system into a roll, (c) inserting said roll into said chamber, (d) positioning said insulant system in said chamber, said first layer in contact with said casing and the aluminum foil layer defining a facing for said chamber, and (e) simultaneously bonding said first layer to said casing and to said aluminum foil in a single step by heating and applying outward pressure from the interior of said roll to force said insulant system against said casing.
Claim 5
Independent Claim
159 words
A method of bonding a composite sheet insulant system to a rocket propellant chamber casing in a single operation, said insulant system comprising: (1) a first layer of a sheet material comprising a carboxyl-terminated polybutadiene binder and a mixture of asbestos fibers and floats dispersed therein, and (2) a second layer of aluminum foil, said method comprising: (a) attaching, but not bonding, said layer of sheet material to said aluminum foil layer along only one longitudinal edge thereof, (b) forming said insulant system into a roll, (c) inserting said roll into said chamber, (d) positioning said insulant system in said chamber, said first layer in contact with said casing and the aluminum foil layer defining a facing for said chamber, and (e) simultaneously bonding said first layer to said casing and to said aluminum foil in a single step by heating and applying outward pressure from the interior of said roll to force said insulant system against said casing.
Claim 6
Dependent Claim
58 words
The method of claim 3 which further comprises forming a sub-assembly for insertion in said chamber, said sub-assembly including the rolled composite sheet insulant system, a head-end insulator and a head-end restrictor member, and inserting and positioning said sub-assembly in said chamber, and bonding said sub-assembly to said chamber by the action of said pressure and heat alone.
Claim 7
Dependent Claim
24 words
The method of claim 3 or 4 wherein said sheet material is stapled to said aluminum foil layer along only one longitudinal edge thereof.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-04-09 | 1982-10-09 | 1983-04-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-04-09 | 1986-10-09 | 1987-04-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-04-09 | 1990-10-09 | 1991-04-10 | $7700.00 | Window Closed / Lapsed |