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US4014485A
Expired / Lapsed
US
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Gas cooling system for hypersonic vehicle nosetip
Assignee: Lockheed Martin Corp
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Filing: 1975-04-14
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Granted: 1977-03-29
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Expires: 1995-04-14
Abstract
Abstract A cooled nosetip arrangement for a vehicle designed to travel at hypersonic velocities is taught herein. We provide a nosetip having one or more orifices at its forwardmost location, but instead of utilizing an arrangement for expelling a liquid coolant, which would necessitate a considerable amount of plumbing and tankage, we utilize a novel gas generator arrangement enabling a coolant gas to be selectively generated and then expelled from such nosetip orifice(s). In this manner we utilize a coolant that advantageously remains in a chemical form until it is to be actually utilized.
Inventors
- 👤 Laird D. Kinnaird
- 👤 Seth B. Moorhead, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 19:32
CPC Classifications
B; B64; B64C; B64C1/00; B64C1/38
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
89 words
An arrangement for protecting the nosecone of a vehicle during travel at hypersonic velocities, comprising a nosecone provided with a nosetip having orifice means, gas generator means in said vehicle in which comparatively large quantities of gases can be generated, said gas generator means containing a solid propellant, duct means for delivering such gases from said gas generator means to said orifice means, and means for bringing about on occasion, the generation of gases in said generator means, and consequently the flow of such gases from said orifice means.
Claim 2
Dependent Claim
89 words
An arrangement for protecting the nosecone of a vehicle during travel at hypersonic velocities, comprising a nosecone provided with a nosetip having orifice means, gas generator means in said vehicle in which comparatively large quantities of gases can be generated, said gas generator means containing a solid propellant, duct means for delivering such gases from said gas generator means to said orifice means, and means for bringing about on occasion, the generation of gases in said generator means, and consequently the flow of such gases from said orifice means.
Claim 3
Dependent Claim
37 words
The arrangement as defined in claim 1 in which the solid propellant contained in said gas generator means is caused to ignite as a result of the ram air at the nosetip rising above a preascertained temperature.
Claim 4
Dependent Claim
38 words
The arrangement as defined in claim 1 in which igniter means are utilized for selectively bringing about the generation of gases in said gas generator means, said igniter means being caused to function by a command electrical signal.
Claim 5
Dependent Claim
43 words
The arrangement as defined in claim 1 in which said means for bringing about the generation of gases in said gas generator means includes a pressure-sensitive igniter caused to function by exposure to at least some of the pressure rise at said nosetip.
Claim 6
Dependent Claim
31 words
The arrangement as defined in claim 1 in which said nosetip is made of refractory material having high strength characteristics, even when operating in the 2000° F to 5000° F range.
Claim 7
Dependent Claim
48 words
The arrangement as defined in claim 1 in which said solid propellant used in said gas generator is capable of producing gas at approximately 2000° F, such gas to be used for preventing a temperature rise at the nosetip, that is substantially above the temperature of the gas.
Claim 8
Dependent Claim
58 words
The arrangement as defined in claim 1 in which said duct means serves to communicate local pressure as well as pressure changes occurring at said nosetip to said gas generator, such pressure changes affecting the burn rate of the propellant in the gas generator, and thereby bringing about a self regulation of the burn rate of such propellant.
Claim 9
Dependent Claim
26 words
The arrangement as defined in claim 1 in which said gas generator means is a discrete vessel, disposed at a location comparatively remove from said nosetip.
Claim 10
Dependent Claim
36 words
The arrangement as defined in claim 1 in which said gas generator means is disposed comparatively close to said nosetip, and is of a configuration conforming to the shape of the interior of the missile nosecone.
Claim 11
Dependent Claim
27 words
The arrangement as defined in claim 9 in which said gas generator means serves as both a pressure vessel and as the basic structure of the nosecone.
Claim 12
Dependent Claim
36 words
The arrangement as defined in claim 1 in which a protective boot of low melting point material is normally disposed on said nosetip, which boot is melted and removed by the heat encountered during hypersonic flight.
Claim 13
Dependent Claim
117 words
An arrangement for protecting the nosecone of a vehicle when it encountered hypersonic velocities, comprising a nosecone provided with a nosetip having orifice means, gas generator means in said vehicle in which comparatively large quantities of gases can be generated, said gas generator means employing a solid propellant having the characteristic of producing gases in proportion to the pressure applied to its burning surface, duct means for delivering such gases from said gas generator means to said orifice means, said duct means serving as a communication means between the solid propellant, and the heat and pressure of the hypersonic environment, thus to provide both ignition of the propellant as well as control of the gases produced therefrom.
Claim 14
Dependent Claim
117 words
An arrangement for protecting the nosecone of a vehicle when it encountered hypersonic velocities, comprising a nosecone provided with a nosetip having orifice means, gas generator means in said vehicle in which comparatively large quantities of gases can be generated, said gas generator means employing a solid propellant having the characteristic of producing gases in proportion to the pressure applied to its burning surface, duct means for delivering such gases from said gas generator means to said orifice means, said duct means serving as a communication means between the solid propellant, and the heat and pressure of the hypersonic environment, thus to provide both ignition of the propellant as well as control of the gases produced therefrom.
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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) | 1980-03-28 | 1980-09-27 | 1981-03-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-03-28 | 1984-09-27 | 1985-03-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-03-28 | 1988-09-27 | 1989-03-29 | $7700.00 | Window Closed / Lapsed |