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Found results for
 patents
1.
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Shockwave mitigation system for supersonic aircraft
| Application Number |
16813718 |
| Grant Number |
11834154 |
| Status |
In Force |
| Filing Date |
2020-03-09 |
| First Publication Date |
2020-09-10 |
| Grant Date |
2023-12-05 |
| Owner |
NCTAR, LLC (USA)
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| Inventor |
Schlaerth, Jr., John B.
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Abstract
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
IPC Classes ?
- B64C 23/04 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating shock waves
- B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
- B64C 3/16 - Frontal aspect
- B64C 30/00 - Supersonic type aircraft
- B64C 3/38 - Adjustment of complete wings or parts thereof
- B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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2.
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SHOCKWAVE MITIGATION SYSTEM FOR SUPERSONIC AIRCRAFT
| Application Number |
US2017053006 |
| Publication Number |
2018/067329 |
| Status |
In Force |
| Filing Date |
2017-09-22 |
| Publication Date |
2018-04-12 |
| Owner |
NCTAR, LLC (USA)
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| Inventor |
Schlaerth, John B., Jr.
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Abstract
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume (522) having a first average velocity from an engine (500), and expelling a bypass exhaust plume (532) having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave (536).
IPC Classes ?
- B64C 3/10 - Shape of wings
- B64C 30/00 - Supersonic type aircraft
- B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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3.
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SHOCKWAVE MITIGATION SYSTEM FOR SUPERSONIC AIRCRAFT
| Document Number |
03037876 |
| Status |
Pending |
| Filing Date |
2017-09-22 |
| Open to Public Date |
2018-04-12 |
| Owner |
NCTAR, LLC (USA)
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| Inventor |
Schlaerth, John B., Jr.
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Abstract
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume (522) having a first average velocity from an engine (500), and expelling a bypass exhaust plume (532) having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave (536).
IPC Classes ?
- B64C 3/16 - Frontal aspect
- B64C 23/04 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating shock waves
- B64C 30/00 - Supersonic type aircraft
- B64D 27/00 - Arrangement or mounting of power plants in aircraftAircraft characterised by the type or position of power plants
- B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
- F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
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4.
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Shockwave mitigation system for supersonic aircraft
| Application Number |
15272908 |
| Grant Number |
10618638 |
| Status |
In Force |
| Filing Date |
2016-09-22 |
| First Publication Date |
2018-01-04 |
| Grant Date |
2020-04-14 |
| Owner |
NCTAR, LLC (USA)
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| Inventor |
Schlaerth, Jr., John B.
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Abstract
A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.
IPC Classes ?
- B64C 23/00 - Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C 30/00 - Supersonic type aircraft
- B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
- B64C 3/16 - Frontal aspect
- B64C 3/38 - Adjustment of complete wings or parts thereof
- B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
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