US5765778A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Flight vehicle with a safety device
Assignee: Individual
•
Filing: 1996-04-15
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Granted: 1998-06-16
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Expires: 2016-04-15
Abstract
Abstract An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.
Inventors
- 👤 Ayako Otsuka
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 01:31
CPC Classifications
B; B64; B64D; B64D25/00; B64C; B64C25/00; B64C25/32; B64C25/54; B64C25/56; B64D1/00; B64D1/02; B64D1/08; B64D1/14; B64D2201/00
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
230 words
An airplane having a safety device, said airplane comprising: an airplane body; a main wing extending from opposing sides of said airplane body; a tail unit connected to an end of said airplane body; at least two auxiliary engines movably mounted on a lower portion of said main wing so as to be symmetrically disposed with respect to a longitudinal axis of said airplane body, each of said auxiliary engines on said main wing having a thrust axis which can be variably positioned between a substantially horizontal direction and a substantially vertical direction; at least two auxiliary engines movably mounted on a lower portion of said tail unit so as to be symmetrically disposed with respect to the longitudinal axis of said airplane body, each of said auxiliary engines on said tail unit having a thrust axis which can be variably positioned between a substantially horizontal direction and a substantially vertical direction; first and second gas bags disposed, in a contracted state, at a lower portion of said airplane body; and third and fourth gas bags symmetrically disposed, relative to the longitudinal axis of said airplane body, in a contracted state along a lower portion of said main wing, wherein said first, second, third and fourth gas bags can each be instantly expanded into a spherical form in order to absorb landing shock in the event of an emergency landing.
Claim 2
Dependent Claim
230 words
An airplane having a safety device, said airplane comprising: an airplane body; a main wing extending from opposing sides of said airplane body; a tail unit connected to an end of said airplane body; at least two auxiliary engines movably mounted on a lower portion of said main wing so as to be symmetrically disposed with respect to a longitudinal axis of said airplane body, each of said auxiliary engines on said main wing having a thrust axis which can be variably positioned between a substantially horizontal direction and a substantially vertical direction; at least two auxiliary engines movably mounted on a lower portion of said tail unit so as to be symmetrically disposed with respect to the longitudinal axis of said airplane body, each of said auxiliary engines on said tail unit having a thrust axis which can be variably positioned between a substantially horizontal direction and a substantially vertical direction; first and second gas bags disposed, in a contracted state, at a lower portion of said airplane body; and third and fourth gas bags symmetrically disposed, relative to the longitudinal axis of said airplane body, in a contracted state along a lower portion of said main wing, wherein said first, second, third and fourth gas bags can each be instantly expanded into a spherical form in order to absorb landing shock in the event of an emergency landing.
Claim 3
Dependent Claim
35 words
The airplane as claimed in claim 1, wherein each of said auxiliary engines comprises an engine guard which is projectable in a direction along a central axis of said auxiliary engine to absorb landing shock.
Claim 4
Dependent Claim
30 words
The airplane as claimed in claim 2, wherein each of said engine guards comprises a plurality of bar elements disposed about the thrust axis and interconnected by an annular element.
Claim 5
Dependent Claim
203 words
A helicopter having a safety device, said helicopter comprising: a helicopter body having a longitudinal axis; a first pair of auxiliary engines symmetrically supported on a lower front portion of said helicopter body relative to the longitudinal axis of said helicopter body, each of said first pair of auxiliary engines having a thrust axis and being movably mounted so as to vary a thrust axis direction between a substantially horizontal direction and a substantially vertical direction; a second pair of auxiliary engines symmetrically supported on a lower rear portion of said helicopter body relative to the longitudinal axis of said helicopter body, each of said second pair of auxiliary engines having a thrust axis and being movably mounted so as to vary a thrust axis direction between a substantially horizontal direction and a substantially vertical direction; a first inflatable gas bag positioned, in a contracted state, at a lower front portion of said helicopter body; and a second inflatable gas bag positioned, in a contracted state, at a lower rear portion of said helicopter body, wherein said first and second gas bags can be instantly inflated into a spherical form in order to absorb landing shock in the event of an emergency landing.
Claim 6
Dependent Claim
203 words
A helicopter having a safety device, said helicopter comprising: a helicopter body having a longitudinal axis; a first pair of auxiliary engines symmetrically supported on a lower front portion of said helicopter body relative to the longitudinal axis of said helicopter body, each of said first pair of auxiliary engines having a thrust axis and being movably mounted so as to vary a thrust axis direction between a substantially horizontal direction and a substantially vertical direction; a second pair of auxiliary engines symmetrically supported on a lower rear portion of said helicopter body relative to the longitudinal axis of said helicopter body, each of said second pair of auxiliary engines having a thrust axis and being movably mounted so as to vary a thrust axis direction between a substantially horizontal direction and a substantially vertical direction; a first inflatable gas bag positioned, in a contracted state, at a lower front portion of said helicopter body; and a second inflatable gas bag positioned, in a contracted state, at a lower rear portion of said helicopter body, wherein said first and second gas bags can be instantly inflated into a spherical form in order to absorb landing shock in the event of an emergency landing.
Claim 7
Dependent Claim
35 words
The helicopter as claimed in claim 4, wherein each of said auxiliary engines comprises an engine guard which is projectable in a direction along a central axis of said auxiliary engine to absorb landing shock.
Claim 8
Dependent Claim
30 words
The helicopter as claimed in claim 5, wherein each of said engine guards comprises a plurality of bar elements disposed about the thrust axis and interconnected by an annular element.
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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) | 2001-06-15 | 2001-12-15 | 2002-06-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2005-06-15 | 2005-12-15 | 2006-06-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2009-06-15 | 2009-12-15 | 2010-06-16 | $7700.00 | Window Closed / Lapsed |