GB2027403A - Controlling dirigibles - Google Patents
Controlling dirigibles Download PDFInfo
- Publication number
- GB2027403A GB2027403A GB7919387A GB7919387A GB2027403A GB 2027403 A GB2027403 A GB 2027403A GB 7919387 A GB7919387 A GB 7919387A GB 7919387 A GB7919387 A GB 7919387A GB 2027403 A GB2027403 A GB 2027403A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressurised fluid
- propulsion
- control valve
- propulsion control
- dirigible
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
- B64B1/36—Arrangement of jet reaction apparatus for propulsion or directional control
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supercharger (AREA)
Abstract
A propulsion control valve 15 suitable for a dirigible 10 is provided with nozzles 48, 49, 50, 51 Fig. 3 (not shown) and contains a flexible duct 22 which is adapted to receive a portion of the efflux from a remote gas turbine engine and direct that efflux to one or more of the nozzles 48, 49, 50, 51. Suitable positioning of a number of such valves 15 on a dirigible 10 ensures that propulsion and directional control of the dirigible 10 is achieved by appropriate alterations of the efflux flow through the nozzles 48, 49, 50, 51. <IMAGE>
Description
SPECIFICATION
Propulsion control valve suitable for a dirigible
This invention relates to dirigibles and in particular to a propulsion control valve suitable for a dirigible.
Dirigibles are usually difficult to control with any degree of accuracy. They are conventionally provided with propulsion engines which are satisfactory under cruising conditions but relatively insensitive when accurate, low speed manoeuvring is necessary.
It is an object of the present invention to provide a propulsion control valve suitable for a dirigible whereby more precise dirigible control is possible.
According to one aspect of the present invention, a propulsion control valve suitable for a dirigible comprises duct means adapted in operation to be supplied with a pressurised fluid, and a plurality of propulsion nozzles, said duct means being directionally controllable so as to selectively supply any one of said propulsion nozzles with said pressurised fluid, said propulsion nozzles being aligned in differing directions so as to be capable of directing said pressurised fluid in said differing directions.
Preferably said duct means is so directionally controllable that said pressurised fluid may be proportionally distributed between at least two of said propulsion nozzles.
Said propulsion control valve is preferably provided with four of said propulsion nozzles aligned so as to be capable of directing said pressurised fluid in mutually perpendicular directions.
Said duct means may comprise first and second rigid duct members interconnected by a flexible duct member, said first rigid duct member being adapted in operation to be supplied with said pressurised fluid and the second rigid duct member being mounted for movement relative to said first rigid duct member, actuation means being provided to control and direct said second rigid duct member to selectively supply any one or more of said propulsion nozzles with said pressurised fluid.
Said second rigid duct member may be mounted for translation along two relatively movable mutually perpendicular guides, said actuation means being adapted to translate said second rigid duct along said perpendicular guides.
Said actuation means may comprise an assembly of cables, pulleys and drive means arranged such that said second rigid duct member may be simultaneously driven along both of said perpendicular guides so as to move in a direction which is the resultant of its directions of movement along each of said perpendicular guides.
Said pressurised fluid is preferably derived from the efflux of a gas turbine engine.
According to a further aspect of the present invention, a dirigible is provided with a source of pressurised fluid and a plurality of propulsion control valves in accordance with the present invention, the source of pressurised fluid being adapted to supply pressurised fluid to each of said propulsion control valves.
Said dirigible may be substantially disc-shaped and provided with four of said propulsion control valves equally spaced apart around its periphery.
Said source of pressurised fluid is preferably a gas turbine engine.
The invention will now be described, by way of example, with reference to the accompanying drawings in which;
Fig 1 is a side view of a dirigible provided with a propulsion control valve in accordance with the present invention,
Fig 2 is a plan view of the dirigible shown in Fig
1,
Fig 3 is a perspective view of a propulsion control valve in accordance with the present invention,
Fig. 4 is a partially sectioned side view of the propulsion control valve shown in Fig 3,
Fig. 5 is a view of the actuation mechanism of the propulsion control valve shown in Figs 3 and 4.
With reference to Fig 1 a dirigible indicated at
10 comprises a generally disc-shaped gas envelope 11 having a gondola 12 suspended below it. The gondola 12 contains a gas turbine engine (not shown) the efflux of which is in operation passed through a duct 13 which extends into the interior of the gas envelope 11.
The duct 1 3 divides within the gas envelope 11 into four perpendicular ducts 14 (Fig 2) which extend to the periphery of the gas envelope 11.
Each duct 14 terminates in a propulsion control valve 15.
Each propulsion control valve 1 5, one of which can be seen in Fig 3, comprises a first rigid duct 1 6 of circular cross section which interconnects the propulsion control valve 1 5 and its associated engine efflux duct 14. Within the first rigid duct 1 6 there is provided a substantially V-shaped pylon 1 7 (Fig 4) which carries a boss 1 8. The boss 1 8 is positioned at the apex of the pylon 17 and is adapted to receive the spherical end 19 of a rod 20. The other end of the rod 20 is attached to a second rigid duct 21 of square cross section.The first and second ducts 16 and 21 are interconnected by a flexible duct 22 so that the engine efflux passed in operation into the first rigid duct 1 6 from the engine efflux duct 14 is subsequently passed through the flexible duct 22 and into the second rigid duct 21.
The boss 18 and spherical rod end 19 constitute a ball joint which permits movement of the second rigid duct 21 relative to the first rigid duct 1 6. The range of movement of the second
rigid duct 1 6 is such that it may be aligned with any one of four square cross-section nozzle inlets 23, 24, 25 and 26 positioned within the propulsion control valve 1 5 and arranged such that any one nozzle inlet is adjacent two other nozzle inlets. Two of the nozzle inlets 23 and 25 can be seen in Fig 4 whilst all four nozzle inlets 23, 24, 25 and 26 can be seen in Fig 5.
The actuating mechanism for directionally controlling the second rigid duct 21 is generally indicated at 27 in Fig 5 but in the interests of clarity has been omitted from Fig 4. With reference to Fig 5, the second rigid duct 21 is provided on each of its four side faces with pulleys 28, 29, 30 and 31 respectively. The opposite pulleys 28 and 30 are interconnected by a cable 32 which is attached to the propulsion control valve 15 at 33 and 34. The cable 32 extends from its attachment position 33 to a first pulley assembly 35 where it passes around the pulley 28. It then passes around pulleys 36 and 37 mounted on the propulsion control valve 15 to a second pulley assembly 38 where it passes around the opposite pulley 30 whereupon it extends to other attachment position 34.The first and second pulley assemblies 35 and 38 are interconnected by a guide 39 which passes through appropriate holes (not shown) in the second rigid duct 21.
The opposite pulleys 29 and 31 are
interconnected by a cable 40 which is attached to the propulsion control valve 15 at 41 and 42. The
cable 40 interconnects the pulleys 29 and 31 in the same fashion as the cable 32 interconnects the pulleys 28 and 30 with pulley assemblies 43 and 44 corresponding to pulley assemblies 35 and 38. The pulley assemblies 43 and 44 are interconnected by a guide 45 which is similar to the guide 39 and also passes through appropriate holes (not shown) in the second rigid duct 21. The guides 39 and 45 are perpendicular to each other.
Motor drives 46 and 47 are adapted to drive the cables 32 and 40 respectively.
The arrangement of pulleys and cables is such that the second rigid duct 21 may be simultaneously driven along each of the guides 39 and 45 by the motor drives 46 and 47. Thus the second rigid duct 21 may be translated in directions which are the resultants of its directions of movement along each of the guides 39 and 45.
Consequently the second rigid duct 21 may be positioned so that it is aligned with any one of the four cross-section nozzle inlets 23, 24, 25 and 26 or alternatively it may be positioned so as to straddle two or all four of the nozzle inlets 23, 24, 25 and 26.
The nozzle inlets 23, 24, 25 and 26 lead to propulsion nozzles 48,49, 50 and 51 respectively (see Fig 3) on the exterior of the propulsion control valve 1 5. The propulsion nozzles 48, 49, 50 and
51 are aligned in mutually perpendicular directions so that engine efflux emanating from the second rigid duct 21 may be directed in those directions. Since the second rigid duct 21 may be either aligned with each of the nozzle inlets 23, 24, 25 and 26 or positioned so as to straddle two or all four of them, the engine efflux may be directed in any one of the four mutually perpendicular directions or simultaneously distributed between two or four of those directions.
In operation, the efflux from gas turbine engine contained within the gondola 12 is fed through the duct 13 and 14 to each of the four propulsion control valves 1 5. The actuating mechanisms 27 of each of the control valves 1 5 are then operated so as to direct the engine efflux to propel the dirigible in the desired direction. Alterations in the direction of motion of the dirigible may be achieved by appropriate operation of the actuating mechanisms 27 so as to re-distribute the flow of engine efflux through the propulsion nozzles 23, 24, 25 and 26 of each propulsion control valve 1 5.If it is desired that the net propulsive thrust from any particular propulsion control valve 1 5 should be nil then the actuating mechanism 27 may be operated so as to position the second rigid duct 21 conta-ined within that valve 15 so as to direct equal amounts of engine efflux through each of the nozzles 23,24,25 and 26.
Consequently by suitable operation of the actuating mechanisms 27 of the propulsion control valves 15, the dirigible 10 may hover or be propelled in a given direction whilst its gas turbine engine operates at a constant speed.
It will be seen therefore that the present invention provides a dirigible with a source of propulsion which permits accurate directional control. Such control enables dirigibles to perform tasks previously considered unsuitable for them such as the picking up and setting down of loads whilst the dirigible is hovering.
Claims (11)
1. A propulsion control valve suitable for a dirigible comprising duct means adapted in operation to be supplied with a pressurised fluid, and a plurality of propulsion nozzles, said duct means being directionally controllable so as to selectively supply any one of said propulsion nozzles with said pressurised fluid, said propulsion nozzles being aligned in differing directions so as to be capable of directing said pressurised fluid in said differing directions.
2. A propulsion control valve as claimed in claim 1 wherein said duct means is so directionally controllable that said pressurised fluid may be proportionally distributed between at least two of said propulsion nozzles.
3. A propulsion control valve as claimed in claim 1 or claim 2 wherein said propulsion control valve is provided with four of said propulsion nozzles so as to be capable of directing said pressurised fluid in mutually perpendicular directions.
4. A propulsion control valve as claimed in any one preceding claim wherein said duct means 'comprises first and second rigid duct members
interconnected by a flexible duct member, said first rigid duct member being adapted in operation to be supplied with said pressurised fluid and the
second rigid duct member being mounted for movement relative to said first rigid duct member,
actuation means being provided to control and
direct said second rigid duct member to selectively
supply any one or more of said propulsion nozzles
with said pressurised fluid.
5. A propulsion control valve as claimed in claim 4 wherein said second rigid duct member is mounted for translation along two relatively movable mutually perpendicular guides, said actuation means being adapted to translate said second rigid duct along said perpendicular guides.
6. A propulsion control valve as claimed in claim 4 or claim 5 wherein said actuation means comprises an assembly of cables, pulleys and drive means arranged such that said second rigid duct member may be simultaneously driven along both of said perpendicular guides so as to move in a direction which is the resultant of its directions of movements along each of said perpendicular guides.
7. A propulsion control valve as claimed in any one preceding claim wherein said pressurised fluid is derived from the efflux of a gas turbine engine.
8. A dirigible with a source of pressurised fluid
and a plurality of propulsion control valves as claimed in any one preceding claim, the source of pressurised fluid being adapted to supply pressurised fluid to each of said propulsion control valves.
9. A dirigible as claimed in claim 8 wherein said dirigible is substantially disc-shaped and provided with four of said propulsion control valves equally spaced apart around its periphery.
10. A dirigible as claimed in claim 8 or claim 9 wherein said source of pressurised fluid is a gas turbine engine.
11. A dirigible substantially as hereinbefore described with reference to and as shown in
Figures 1 and 2 of the accompanying drawings.
11. A propulsion control valve substantially as
hereinbefore described with reference to and as
shown in the accompanying drawings.
12. A dirigible substantially as hereinbefore
described with reference to and as shown in
Figures 1 and 2 of the accompanying drawings.
New claims or amendments to claims filed on
16 October 1979.
Superseded Claims
New or amended claims
1. A propulsion control valve suitable for a
dirigible comprising duct means adapted in
operation to be supplied with a pressurised fluid
and a plurality of propulsion nozzles, said duct
means comprising first and second rigid duct
members interconnected by a flexible duct
member, said first rigid duct member being
adapted in operation to be supplied with said
pressurised fluid and said second rigid duct
member being mounted for movement relative to
said first rigid duct member, actuation means
being provided to control and direct said second rigid duct member to selectively supply any one or more of said propulsion nozzles with said pressurised fluid, said propulsion nozzles being aligned in differing directions so as to be capable of directing said pressurised fluid in said differing directions.
2. A propulsion control valve as claimed in claim 1 wherin said duct means is so directionally controllable that said pressurised fluid may be proportionally distributed between at least two of said propulsion nozzles.
3. A propulsion control valve as claimed in claim 1 or claim 2 wherein said propulsion control valve is provided with four of said propulsion nozzles so as to be capable of directing said pressurised fluid in mutually perpendicular directions.
4. A propulsion control valve as claimed in any one of claims 1 to 3 wherein said second rigid duct member is mounted for translation along two relatively movable mutually perpendicular guides, said actuation means being adapted to translate said second rigid duct along said perpendicular guides.
5. A propulsion control valve as claimed in any one preceding claim wherein said actuation means comprises an assembly of cables, pulleys and drive means arranged such that said second rigid duct member may be simultaneously driven along both of said perpendicular guides so as to move in a direction which is the resultant of its directions of movements along each of said perpendicular guides.
6. A propulsion control valve as claimed in any one preceding claim wherein said pressurised fluid is derived from the efflux of a gas turbine engine.
7. A dirigible with a source of pressurised fluid and a plurality of propulsion control valves as claimed in any one preceding claim, the source of pressurised fluid being adapted to supply pressurised fluid to each of said propulsion control valves.
8. A dirigible as claimed in claim 8 wherein said dirigible is substantially disc-shaped and provided with four of said propulsion control valves equally spaced apart around its periphery.
9. A dirigible as claimed in claim 8 or claim 9 wherein said source of pressurised fluid is a gas turbine engine.
10. A propulsion control valve substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB7919387A GB2027403B (en) | 1978-07-25 | 1979-06-04 | Controlling dirigibles |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB7831022 | 1978-07-25 | ||
| GB7919387A GB2027403B (en) | 1978-07-25 | 1979-06-04 | Controlling dirigibles |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2027403A true GB2027403A (en) | 1980-02-20 |
| GB2027403B GB2027403B (en) | 1982-06-16 |
Family
ID=26268336
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB7919387A Expired GB2027403B (en) | 1978-07-25 | 1979-06-04 | Controlling dirigibles |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2027403B (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2144817A (en) * | 1983-08-12 | 1985-03-13 | David Victor Mills | Pipe coupling-diverter valves |
| US4606515A (en) * | 1984-05-29 | 1986-08-19 | Hickey John J | Hybrid annular airship |
| US5147429A (en) * | 1990-04-09 | 1992-09-15 | James Bartholomew | Mobile airborne air cleaning station |
| FR2712128A1 (en) * | 1993-07-30 | 1995-05-12 | Int Multi Media Corp | Sub-orbital, high-altitude communication system |
| US5755402A (en) * | 1994-01-03 | 1998-05-26 | Henry; Roy | Discoid airship |
| US7844218B2 (en) | 1993-07-30 | 2010-11-30 | International Multi-Media Corporation | Sub-orbital, high altitude communications system |
| WO2012118731A3 (en) * | 2011-03-01 | 2012-12-27 | Ciampa John A | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| US8505847B2 (en) | 2011-03-01 | 2013-08-13 | John Ciampa | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| CN114313203A (en) * | 2022-01-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Unmanned floating airship |
| CN114313203B (en) * | 2022-01-27 | 2024-05-24 | 中国航发沈阳发动机研究所 | Unmanned floating airship |
-
1979
- 1979-06-04 GB GB7919387A patent/GB2027403B/en not_active Expired
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2144817A (en) * | 1983-08-12 | 1985-03-13 | David Victor Mills | Pipe coupling-diverter valves |
| US4606515A (en) * | 1984-05-29 | 1986-08-19 | Hickey John J | Hybrid annular airship |
| US5147429A (en) * | 1990-04-09 | 1992-09-15 | James Bartholomew | Mobile airborne air cleaning station |
| US7567779B2 (en) | 1993-07-30 | 2009-07-28 | International Multi-Media Corporation | Sub-orbital, high altitude communications system |
| EP0711476A1 (en) * | 1993-07-30 | 1996-05-15 | International Multi-Media Corporation | Sub-orbital, high altitude communications system |
| EP0711476A4 (en) * | 1993-07-30 | 1996-07-10 | Int Multi Media Corp | Sub-orbital, high altitude communications system |
| ES2113814A1 (en) * | 1993-07-30 | 1998-05-01 | Int Multi Media Corp | Sub-orbital, high altitude communications system |
| FR2712128A1 (en) * | 1993-07-30 | 1995-05-12 | Int Multi Media Corp | Sub-orbital, high-altitude communication system |
| US7844218B2 (en) | 1993-07-30 | 2010-11-30 | International Multi-Media Corporation | Sub-orbital, high altitude communications system |
| US5755402A (en) * | 1994-01-03 | 1998-05-26 | Henry; Roy | Discoid airship |
| WO2012118731A3 (en) * | 2011-03-01 | 2012-12-27 | Ciampa John A | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| US8505847B2 (en) | 2011-03-01 | 2013-08-13 | John Ciampa | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| US8622338B2 (en) | 2011-03-01 | 2014-01-07 | John Ciampa | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| US9126669B2 (en) | 2011-03-01 | 2015-09-08 | John Ciampa | Lighter-than-air systems, methods, and kits for obtaining aerial images |
| CN114313203A (en) * | 2022-01-27 | 2022-04-12 | 中国航发沈阳发动机研究所 | Unmanned floating airship |
| CN114313203B (en) * | 2022-01-27 | 2024-05-24 | 中国航发沈阳发动机研究所 | Unmanned floating airship |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2027403B (en) | 1982-06-16 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |