Patent US3670994A successfully refreshed from Google Patents.
US3670994A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Variable deflection thrusters for jets
Assignee: United States Department of the Navy
•
Filing: 1970-08-13
•
Granted: 1972-06-20
•
Expires: 1990-08-13
Abstract
Abstract Variable deflection thrusters center body of improved design for jets for overcoming stream detachment at high mach numbers and high pressure ratios.
Inventors
- 👤 Apostolos P Kizilos
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 16:06
CPC Classifications
B; B64; B64C; B64C9/00; B64C9/38
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
164 words
An improved variable deflection thruster at the rearward end of an airfoil for use at high subsonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a sharp trailing edge, b. said rearward sharp trailing edge being formed from one side edge of a biconvex centerbody, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said biconvex centerbody which forms said trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the surfaces of said biconvex centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streAms discharged from said apertures relative to one another.
Claim 2
Dependent Claim
164 words
An improved variable deflection thruster at the rearward end of an airfoil for use at high subsonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a sharp trailing edge, b. said rearward sharp trailing edge being formed from one side edge of a biconvex centerbody, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said biconvex centerbody which forms said trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the surfaces of said biconvex centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streAms discharged from said apertures relative to one another.
Claim 3
Dependent Claim
189 words
An improved variable deflection thruster at the rearward end of an airfoil for use at high transonic and supersonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a wedge shaped trailing edge, b. said rearward wedge shaped trailing edge being formed by a variable deflection thruster centerbody having two flat sides which intersect to form a wedge, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said variable deflection thruster centerbody having two flat sides which intersect to form said wedge shaped trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the flat surfaces of said variable deflection thruster centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.
Claim 4
Dependent Claim
189 words
An improved variable deflection thruster at the rearward end of an airfoil for use at high transonic and supersonic speeds without jet detachment, comprising: a. an airfoil having opposite first and second side surfaces substantially merging at the rearward end of the airfoil into a wedge shaped trailing edge, b. said rearward wedge shaped trailing edge being formed by a variable deflection thruster centerbody having two flat sides which intersect to form a wedge, c. first and second spanwise-extending jet discharge apertures in said airfoil, one said jet discharge aperture being on each side of said variable deflection thruster centerbody having two flat sides which intersect to form said wedge shaped trailing edge, d. each of said first and second jet discharge apertures being shaped and arranged to discharge a fluid stream as a layer rearwardly over the flat surfaces of said variable deflection thruster centerbody, e. first and second jet pressure supply and control means to provide a fluid jet stream from each said first and second jet discharge apertures, respectively, and to vary the flow of said jet streams discharged from said apertures relative to one another.
References Cited (Backward Citations)
US3467043A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-06-20 | 1975-12-20 | 1976-06-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-06-20 | 1979-12-20 | 1980-06-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-06-20 | 1983-12-20 | 1984-06-20 | $7700.00 | Window Closed / Lapsed |