CA2301350A1 - Universal vtol power and rotor system module - Google Patents
Universal vtol power and rotor system module Download PDFInfo
- Publication number
- CA2301350A1 CA2301350A1 CA002301350A CA2301350A CA2301350A1 CA 2301350 A1 CA2301350 A1 CA 2301350A1 CA 002301350 A CA002301350 A CA 002301350A CA 2301350 A CA2301350 A CA 2301350A CA 2301350 A1 CA2301350 A1 CA 2301350A1
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- drive shaft
- rotor
- main drive
- module
- component support
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- 230000005540 biological transmission Effects 0.000 claims abstract description 21
- 230000003416 augmentation Effects 0.000 claims description 20
- 230000008878 coupling Effects 0.000 claims description 5
- 238000010168 coupling process Methods 0.000 claims description 5
- 238000005859 coupling reaction Methods 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 3
- 239000002131 composite material Substances 0.000 claims description 2
- 230000009977 dual effect Effects 0.000 claims description 2
- 238000012546 transfer Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000005355 Hall effect Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/291—Detachable rotors or rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U60/00—Undercarriages
- B64U60/30—Undercarriages detachable from the body
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Transmission Devices (AREA)
Abstract
A universal power drive and lifting rotor system module for single and multiple rotor type VTOL aircraft having a component support airframe module hawing a plurality of quick disconnect fasteners for detachably connecting components thereto. A train drive shaft is supported for rotation within the component support airframe and is adapted for detachable connection to an engine. A lifting rotor assembly and transmission are mounted on the component support airframe using quick disconnect fasteners. The rotor transmission has a power input shaft adapted for detachable connection to the main drive shaft for transferring power between the main drive shaft and the power input shaft.
Description
UNIVERSAL VTOL POWER AND
ROTOR SYSTEM MODULE ..
This application is related to and claims priority from U.S. Patent Application Serial No. 09!045,991 filed March 23, 1998 which is incorporated .
herein by reference.
BACKGROUND
This invention broadly relates to aerial vehicles having vertical takeoff/landing (VTOL) capability, of which helicopters are a common type, ! 0 and of which the described VTOL aircraft has a particularly useful capability as an unmanned aerial vehicle (UAV) , sometimes referred to as a "drone"
aircraft.
More particularly, the invention is a common universal power drive and lifting rotor system module from which various types of single and multiple ! 5 rotor VTOL aircraft can be produced. The simplicity and versatility of the power drive and lifting rotor system module of the invention is such that it has a particular adaptation to providing VTOL UAV aircraft of several types that are highly suitable to carrying out military and commercial surveillance missions.
There is a particular need for a portable, remotely controlled VTOL
UAV platform carrying visual and sensing recording devices for performing a.
variety of military and commercial missions including transmitting or recording visual and other ground data information that is not readily available or possible by other means. The capability of recently developed, simple and lightweight devices for recording and transmitting a wide variety of visual and other data is such that their usefulness can be greatly expanded by mounting them on a portable and remotely controlled VTOL UAV aircraft platform. Typical missions for such VTOL UAV units would be aerial intelligence gathering and reconnaissance, commercial cinematography, news coverage, aerial mapping, law enforcement and anti-terrorism augmentation, border patrol, disaster..
assessment, environmental assessment, utility inspection and maintenance, etc.
SUMMARY OF THE INVENTION
The invention provides a universal power drive and lifting rotor system unit or module suitable for powering a variety of types of VTOL aircraft including both single and multiple rotor type VTOL aircraft, and both single rotor convention and compound helicopters.
The invention further provides a system capable of rapid assembly and disassembly into small modules for man portable transport andlor rapid maintenance without the use of hand tools.
The invention incorporates VTOL power producing and lifting rotor systems and their interconnections on and within a component support airframe.
I 5 The component support airframe is configured for the detachable attachment of an engine and VTOL augmentation framework. The lifting rotor assembly and transmission are mounted on the component support airframe and receive power from a power train comprising a main drive shaft detachably coupled to the engine and extending within the component support airframe. The main drive O shaft and transmission are adapted for detachable connection to a drive shaft of a rotor torque compensating means mounted on any one of the VTOL.
conversion auxiliary frameworks affixed to the module component support airframe. Thus, a variety of types of VTOL aircraft can be powered by attaching the versatile power drive and rotor system module to an auxiliary ?s framework on which is mounted the particular type of rotor torque compensating system utilized on the specific type of VTOL aircraft being produced.
ROTOR SYSTEM MODULE ..
This application is related to and claims priority from U.S. Patent Application Serial No. 09!045,991 filed March 23, 1998 which is incorporated .
herein by reference.
BACKGROUND
This invention broadly relates to aerial vehicles having vertical takeoff/landing (VTOL) capability, of which helicopters are a common type, ! 0 and of which the described VTOL aircraft has a particularly useful capability as an unmanned aerial vehicle (UAV) , sometimes referred to as a "drone"
aircraft.
More particularly, the invention is a common universal power drive and lifting rotor system module from which various types of single and multiple ! 5 rotor VTOL aircraft can be produced. The simplicity and versatility of the power drive and lifting rotor system module of the invention is such that it has a particular adaptation to providing VTOL UAV aircraft of several types that are highly suitable to carrying out military and commercial surveillance missions.
There is a particular need for a portable, remotely controlled VTOL
UAV platform carrying visual and sensing recording devices for performing a.
variety of military and commercial missions including transmitting or recording visual and other ground data information that is not readily available or possible by other means. The capability of recently developed, simple and lightweight devices for recording and transmitting a wide variety of visual and other data is such that their usefulness can be greatly expanded by mounting them on a portable and remotely controlled VTOL UAV aircraft platform. Typical missions for such VTOL UAV units would be aerial intelligence gathering and reconnaissance, commercial cinematography, news coverage, aerial mapping, law enforcement and anti-terrorism augmentation, border patrol, disaster..
assessment, environmental assessment, utility inspection and maintenance, etc.
SUMMARY OF THE INVENTION
The invention provides a universal power drive and lifting rotor system unit or module suitable for powering a variety of types of VTOL aircraft including both single and multiple rotor type VTOL aircraft, and both single rotor convention and compound helicopters.
The invention further provides a system capable of rapid assembly and disassembly into small modules for man portable transport andlor rapid maintenance without the use of hand tools.
The invention incorporates VTOL power producing and lifting rotor systems and their interconnections on and within a component support airframe.
I 5 The component support airframe is configured for the detachable attachment of an engine and VTOL augmentation framework. The lifting rotor assembly and transmission are mounted on the component support airframe and receive power from a power train comprising a main drive shaft detachably coupled to the engine and extending within the component support airframe. The main drive O shaft and transmission are adapted for detachable connection to a drive shaft of a rotor torque compensating means mounted on any one of the VTOL.
conversion auxiliary frameworks affixed to the module component support airframe. Thus, a variety of types of VTOL aircraft can be powered by attaching the versatile power drive and rotor system module to an auxiliary ?s framework on which is mounted the particular type of rotor torque compensating system utilized on the specific type of VTOL aircraft being produced.
BRIEF DESCRIPTION OF THE DRAWINGS
Figure 1 is a side elevation of one embodiment of the invention. ..
Figure 2 is a side elevation of a second embodiment of the invention.
Figure 3 is a side elevation of a third embodiment of the invention.
Figure 4 is an illustration of an embodiment of a quick disconnect fastener for use with the invention.
Figure 5 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 6 is an illustration of another embodiment of a quick disconnect I c~ fastener for use with the invention.
Figure 7 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 8 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 9 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 10 is a side elevation of one embodiment of a coupling for use with the invention.
DETAILED DESCRIPTION OF THE INVENTION
The module 10 utilized to power various types of VTOL aircraft.
subsequently described is illustrated in Figure 1, in which a lifting rotor assembly 11 and transmission 12 are mounted onto a component support airframe 13 on which the components of the module are supported.
Components of module 10 are preferably connected using quick disconnect fasteners 22. Fasteners 22 preferably provide a self aligning interface for the components of module 10 and allow quick connection and removal without use of hand tools.
The rotor assembly 11 is preferably of a conventional nature with rotor blades 14, 15 supported thereon. Rotor assembly 11 may also be multibladed, may be bearingless, or may employ a hollow main rotor shaft or other apparatus commonly known or used in the art. The main rotor interface of rotor assembly 11 is preferably easily adaptable to accommodate a variety of rotor head designs (including fully articulated, bearingless, teetering, off-set teetering, and co-axial designs) capable of providing variable rigidity in flapping and movement. This flexible design has a direct impact on the I c> suitability of rotary wing aircraft to perform successful launch and retrieval in heaving, pitching, and rolling conditions on a boat landing or when landing on ground inclines. The pitch of the rotor blades 14, 15 is preferably controlled by a linkage arrangement of a swash plate assembly 19 actuated by servo motors 20 and of which the details will not be described as being well known I S in the art. Rotor assembly 11 is also preferably configured for quick disconnection and connection at point 16 using quick disconnect fasteners.
The rotor transmission 12 is preferably driven by a power input shaft 21 which preferably extends from the transmission 12. The power input shaft 21 is preferably adapted for detachable connection to the main power drive shaft ~c~ 34 and for receiving an external rotatable shaft (not shown). The component supporting airframe 13 of the module on which the lifting rotor assembly 11.
and transmission 12 and other components of the module are supported is preferably a cylindrical composite airframe structure which provides fuel storage as well as allows for increased space for payloads. This provides an s innovative solution to the traditional design compromise over the location of the fuel tank vis-a-vis other supporting structures by actually making the fuel tank the airframe. Engine 30 is preferably mounted on airframe 13 using quick disconnect fasteners 22.
The support airframe 13 is preferably provided with bolt holes (not shown) and other facilities for attaching augmentation auxiliary framework using quick disconnect fasteners 22. The rotor assembly 11 and transmission 12 are preferably supported by a base plate 33 fastened to the lower side of the .
transmission housing 23 and to the component support airframe 13 using quick disconnect fasteners 22. The component support airframe 13 preferably provides space in which various control and operational components required for operation of a VTOL may be stowed and for which the consumption of fuel o does not adversely affect the balance of the aircraft during operation.
A main power drive shaft 34 extending longitudinally of the component support airframe 13 is preferably supported for rotation in the airframe structure. One end of the drive shaft 34 is preferably detachably connected to the engine 30 by a flexible coupling (not shown) that de-links axially.
A preferred powering unit mounted on the component support airframe 13 is a two-stroke air cooled engine with twin opposed cylinders. A more preferable powering unit is a diesel engine, but other engines suitable for mounting on the front end of the airframe 13 could be utilized. Preference for a two-stroke engine is discussed below with respect to module 10 being used to p) power a dual rotor configured VTOL aircraft. Auxiliary power for the module may be provided using one or more generators (not shown). It is preferred that a combination starterlgenerator is used to provide both auxiliary power and starter capability. Use of a combination starterlgenerator also provides benefits in terms of reduced weight.
Rotational power of the main drive shaft 34 is preferably transferred to the transmission power input shaft 21 by means of a pulley and belt drive arrangement 39. The pulley-belt drive arrangement 39 is one preferred embodiment as being light and effective. Gear trains and other well known power transfer apparatus may be utilized for power transmission. The maim drive shaft 34 is also preferably adapted for detachable connection to an external rotatable shaft of a VTOL augmentation auxiliary framework. This s can be accomplished using a splined coupling (not shown) to allow for quick connection and disconnection to the transmission power input shaft 21 or other external rotatable shafts. A centrifugal clutch (not shown) may be incorporated with the main drive shaft 34 for selectively connecting and disconnecting the main drive shaft 34 from the transmission power input shaft 21.
p The versatility of the above described module 10 for powering a variety of types of VTOL aircraft, particularly VTOL UAV aircraft (drone helicopters) is demonstrated in the following descriptive matter relating to the illustrations of Figures 2 and 3. Figure 2 illustrates the module of the invention powering a VTOL aircraft having a tail mounted torque compensating rotor. Referring I 5 now to Figure 2, a main drive shaft clutch assembly extension 60 is detachably attached to the module component supporting airframe 13 by quick disconnect fasteners 22 or other attaching components. VTOL augmentation framework 45 is connected to clutch assembly extension 60 using quick disconnect fasteners 22. The augmentation framework 45 contains a torque compensating c) rotor (counter torque rotor) 49. A counter torque rotor drive shaft 50 is preferably supported for rotation within the augmentation framework 45 and is.
.
operatively connected to rotate the counter torque rotor 49. Counter torque rotor drive shaft 50 is preferably also detachably connected to the main power drive shaft 34. The counter torque rotor drive shaft 50 is preferably a floating ?s thin-walled drive shaft. Augmentation framework 45 preferably comprises a tail boom section 45a detachably connected to a tail section 45b with quick disconnect fasteners 22.
Figure 1 is a side elevation of one embodiment of the invention. ..
Figure 2 is a side elevation of a second embodiment of the invention.
Figure 3 is a side elevation of a third embodiment of the invention.
Figure 4 is an illustration of an embodiment of a quick disconnect fastener for use with the invention.
Figure 5 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 6 is an illustration of another embodiment of a quick disconnect I c~ fastener for use with the invention.
Figure 7 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 8 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 9 is an illustration of another embodiment of a quick disconnect fastener for use with the invention.
Figure 10 is a side elevation of one embodiment of a coupling for use with the invention.
DETAILED DESCRIPTION OF THE INVENTION
The module 10 utilized to power various types of VTOL aircraft.
subsequently described is illustrated in Figure 1, in which a lifting rotor assembly 11 and transmission 12 are mounted onto a component support airframe 13 on which the components of the module are supported.
Components of module 10 are preferably connected using quick disconnect fasteners 22. Fasteners 22 preferably provide a self aligning interface for the components of module 10 and allow quick connection and removal without use of hand tools.
The rotor assembly 11 is preferably of a conventional nature with rotor blades 14, 15 supported thereon. Rotor assembly 11 may also be multibladed, may be bearingless, or may employ a hollow main rotor shaft or other apparatus commonly known or used in the art. The main rotor interface of rotor assembly 11 is preferably easily adaptable to accommodate a variety of rotor head designs (including fully articulated, bearingless, teetering, off-set teetering, and co-axial designs) capable of providing variable rigidity in flapping and movement. This flexible design has a direct impact on the I c> suitability of rotary wing aircraft to perform successful launch and retrieval in heaving, pitching, and rolling conditions on a boat landing or when landing on ground inclines. The pitch of the rotor blades 14, 15 is preferably controlled by a linkage arrangement of a swash plate assembly 19 actuated by servo motors 20 and of which the details will not be described as being well known I S in the art. Rotor assembly 11 is also preferably configured for quick disconnection and connection at point 16 using quick disconnect fasteners.
The rotor transmission 12 is preferably driven by a power input shaft 21 which preferably extends from the transmission 12. The power input shaft 21 is preferably adapted for detachable connection to the main power drive shaft ~c~ 34 and for receiving an external rotatable shaft (not shown). The component supporting airframe 13 of the module on which the lifting rotor assembly 11.
and transmission 12 and other components of the module are supported is preferably a cylindrical composite airframe structure which provides fuel storage as well as allows for increased space for payloads. This provides an s innovative solution to the traditional design compromise over the location of the fuel tank vis-a-vis other supporting structures by actually making the fuel tank the airframe. Engine 30 is preferably mounted on airframe 13 using quick disconnect fasteners 22.
The support airframe 13 is preferably provided with bolt holes (not shown) and other facilities for attaching augmentation auxiliary framework using quick disconnect fasteners 22. The rotor assembly 11 and transmission 12 are preferably supported by a base plate 33 fastened to the lower side of the .
transmission housing 23 and to the component support airframe 13 using quick disconnect fasteners 22. The component support airframe 13 preferably provides space in which various control and operational components required for operation of a VTOL may be stowed and for which the consumption of fuel o does not adversely affect the balance of the aircraft during operation.
A main power drive shaft 34 extending longitudinally of the component support airframe 13 is preferably supported for rotation in the airframe structure. One end of the drive shaft 34 is preferably detachably connected to the engine 30 by a flexible coupling (not shown) that de-links axially.
A preferred powering unit mounted on the component support airframe 13 is a two-stroke air cooled engine with twin opposed cylinders. A more preferable powering unit is a diesel engine, but other engines suitable for mounting on the front end of the airframe 13 could be utilized. Preference for a two-stroke engine is discussed below with respect to module 10 being used to p) power a dual rotor configured VTOL aircraft. Auxiliary power for the module may be provided using one or more generators (not shown). It is preferred that a combination starterlgenerator is used to provide both auxiliary power and starter capability. Use of a combination starterlgenerator also provides benefits in terms of reduced weight.
Rotational power of the main drive shaft 34 is preferably transferred to the transmission power input shaft 21 by means of a pulley and belt drive arrangement 39. The pulley-belt drive arrangement 39 is one preferred embodiment as being light and effective. Gear trains and other well known power transfer apparatus may be utilized for power transmission. The maim drive shaft 34 is also preferably adapted for detachable connection to an external rotatable shaft of a VTOL augmentation auxiliary framework. This s can be accomplished using a splined coupling (not shown) to allow for quick connection and disconnection to the transmission power input shaft 21 or other external rotatable shafts. A centrifugal clutch (not shown) may be incorporated with the main drive shaft 34 for selectively connecting and disconnecting the main drive shaft 34 from the transmission power input shaft 21.
p The versatility of the above described module 10 for powering a variety of types of VTOL aircraft, particularly VTOL UAV aircraft (drone helicopters) is demonstrated in the following descriptive matter relating to the illustrations of Figures 2 and 3. Figure 2 illustrates the module of the invention powering a VTOL aircraft having a tail mounted torque compensating rotor. Referring I 5 now to Figure 2, a main drive shaft clutch assembly extension 60 is detachably attached to the module component supporting airframe 13 by quick disconnect fasteners 22 or other attaching components. VTOL augmentation framework 45 is connected to clutch assembly extension 60 using quick disconnect fasteners 22. The augmentation framework 45 contains a torque compensating c) rotor (counter torque rotor) 49. A counter torque rotor drive shaft 50 is preferably supported for rotation within the augmentation framework 45 and is.
.
operatively connected to rotate the counter torque rotor 49. Counter torque rotor drive shaft 50 is preferably also detachably connected to the main power drive shaft 34. The counter torque rotor drive shaft 50 is preferably a floating ?s thin-walled drive shaft. Augmentation framework 45 preferably comprises a tail boom section 45a detachably connected to a tail section 45b with quick disconnect fasteners 22.
An undercarriage 51 is preferably configured with a landing support 52 connected thereto using quick disconnect fasteners 22. The undercarriage 51 is attached to the module 13 using the quick disconnect fasteners 22. The undercarriage illustrated in Fig. 2 is one suitable for a VTOL UAV type aircraft. If the module 10 is of a size and power suitable for powering pilot controlled aircraft, the undercarriage structure and configuration would conform more closely to a conventional VTOL fuselage.
In a preferred embodiment of the invention an exhaust boom support structure is used to reduce the thermal heat signature and muffle the exhaust I () sound signature. The augmentation framework 45 (and 59 discussed below) structure provides valuable space aboard the aircraft which can reduce noise pollution in commercial environments and increase survivability and stealth in war or near war environments. Accordingly, the augmentation framework 45 is preferably used for exhaust baffling to reduce the sound signature.
~ 5 A particularly useful VTOL configuration utilizing a pair of the modules of the invention for powering a twin rotor VTOL aircraft is illustrated in Figure 3. By interconnecting a pair of modules 10 of the invention in a back-to-back arrangement, the payload is considerably more than can be carried by a single module configuration, the lifting rotor torque generated by one module o being counteracted by the other module. This configuration is also preferable when one engine fails to operate, for whatever reason, as the other engine can still apply power to both rotor systems permitting safe recovery of the aircraft.
Referring to Figure 3, an augmentation framework 59 is configured for rapid detachable connection to the module component support airframe 13 via quick disconnect fasteners 22. A connecting drive shaft 61 is detachably connected to the transmission input shafts 21 of the respective modules 10. The tandem rotor configuration of the VTOL aircraft of Figure 3 requires the lifting rotors 11 of the respective back-to-back arranged modules 10 rotate in opposite directions. e.g., the engine 30 of the left side module 10 rotates clockwise as viewed from the front side of the engine and the engine 30 of the right side module 10 rotates counterclockwise as viewed from the front side of the engine.
Two-stroke engines are preferred since two-stroke engines have the characteristic of operating in either direction with no change to the timing or other operative components of the engine. A two-stroke engine operates in the same direction in which it is started. Hence, an operative configuration of the described tandem rotor VTOL aircraft of Figure 3 ,powered by a pair of I c~ modules of the invention connected back-to-back in the manner described is easily achieved by starting the respective engines of the pair of modules in opposite directions. Four-stroke~engines may be utilized, but require a different timing adjustment of each of the respective engines and other modifications.
It is preferred that engine timing is electromagrietically switched using a I s plurality of Hall effect sensors mounted on the rotating components of the engine, thereby eliminating the need for manual timing adjustments.
The embodiment shown in Figure 3 can be modified to include a third engine (not shown) mounted on or within augmentation framework 59 to provide additional payload capacity. The third engine is preferably connected 0 to the augmentation framework 59 using quick disconnect fasteners.
As previously indicated, the space provided on and around the module.
component support airframe 13 is available for installation of components involving operative control of the module lifting rotor assembly 11 and operative control of VTOL augmentation framework mounted flight control units. The present invention is adapted to powering VTOL UAV aircraft. The described VTOL embodiments of Figures 2 and 3 are of this unmanned type preferably include equipment which establishes remote control of the aircraft _g_ from the ground. An example of such equipment is disclosed in U.S. Patent 3,096,046 which is incorporated herein by reference. ..
Figures 4 _and S illustrate two embodiments of the quick disconnect fasteners 22 which can be used to connect landing support 52 to undercarriage 51. Figure 6 shows an embodiment of quick disconnect fastener 22 which can be used to connect augmentation framework 45 to main drive shaft clutch assembly extension 60. Figure 7 shows an embodiment of the quick disconnect fastener 22 which can be used to connect transmission 12 to component support air frame 13. Figures 8 and 9 show an embodiment of quick disconnect I U fastener 22 which can be used to connect tail boom section 45a to main drive shaft clutch assembly extension. 60. Figure 10 shows an embodiment of a coupling which may be used to~ connect main drive shaft 34 to transmission power input shaft 21 or counter torque rotor drive shaft 50.
It should be understood that the foregoing disclosure involves preferred I 5 embodiments of the invention and that numerous modifications or alterations therein may be made without departing from the spirit and scope of the invention as set forth in the appendant claims.
In a preferred embodiment of the invention an exhaust boom support structure is used to reduce the thermal heat signature and muffle the exhaust I () sound signature. The augmentation framework 45 (and 59 discussed below) structure provides valuable space aboard the aircraft which can reduce noise pollution in commercial environments and increase survivability and stealth in war or near war environments. Accordingly, the augmentation framework 45 is preferably used for exhaust baffling to reduce the sound signature.
~ 5 A particularly useful VTOL configuration utilizing a pair of the modules of the invention for powering a twin rotor VTOL aircraft is illustrated in Figure 3. By interconnecting a pair of modules 10 of the invention in a back-to-back arrangement, the payload is considerably more than can be carried by a single module configuration, the lifting rotor torque generated by one module o being counteracted by the other module. This configuration is also preferable when one engine fails to operate, for whatever reason, as the other engine can still apply power to both rotor systems permitting safe recovery of the aircraft.
Referring to Figure 3, an augmentation framework 59 is configured for rapid detachable connection to the module component support airframe 13 via quick disconnect fasteners 22. A connecting drive shaft 61 is detachably connected to the transmission input shafts 21 of the respective modules 10. The tandem rotor configuration of the VTOL aircraft of Figure 3 requires the lifting rotors 11 of the respective back-to-back arranged modules 10 rotate in opposite directions. e.g., the engine 30 of the left side module 10 rotates clockwise as viewed from the front side of the engine and the engine 30 of the right side module 10 rotates counterclockwise as viewed from the front side of the engine.
Two-stroke engines are preferred since two-stroke engines have the characteristic of operating in either direction with no change to the timing or other operative components of the engine. A two-stroke engine operates in the same direction in which it is started. Hence, an operative configuration of the described tandem rotor VTOL aircraft of Figure 3 ,powered by a pair of I c~ modules of the invention connected back-to-back in the manner described is easily achieved by starting the respective engines of the pair of modules in opposite directions. Four-stroke~engines may be utilized, but require a different timing adjustment of each of the respective engines and other modifications.
It is preferred that engine timing is electromagrietically switched using a I s plurality of Hall effect sensors mounted on the rotating components of the engine, thereby eliminating the need for manual timing adjustments.
The embodiment shown in Figure 3 can be modified to include a third engine (not shown) mounted on or within augmentation framework 59 to provide additional payload capacity. The third engine is preferably connected 0 to the augmentation framework 59 using quick disconnect fasteners.
As previously indicated, the space provided on and around the module.
component support airframe 13 is available for installation of components involving operative control of the module lifting rotor assembly 11 and operative control of VTOL augmentation framework mounted flight control units. The present invention is adapted to powering VTOL UAV aircraft. The described VTOL embodiments of Figures 2 and 3 are of this unmanned type preferably include equipment which establishes remote control of the aircraft _g_ from the ground. An example of such equipment is disclosed in U.S. Patent 3,096,046 which is incorporated herein by reference. ..
Figures 4 _and S illustrate two embodiments of the quick disconnect fasteners 22 which can be used to connect landing support 52 to undercarriage 51. Figure 6 shows an embodiment of quick disconnect fastener 22 which can be used to connect augmentation framework 45 to main drive shaft clutch assembly extension 60. Figure 7 shows an embodiment of the quick disconnect fastener 22 which can be used to connect transmission 12 to component support air frame 13. Figures 8 and 9 show an embodiment of quick disconnect I U fastener 22 which can be used to connect tail boom section 45a to main drive shaft clutch assembly extension. 60. Figure 10 shows an embodiment of a coupling which may be used to~ connect main drive shaft 34 to transmission power input shaft 21 or counter torque rotor drive shaft 50.
It should be understood that the foregoing disclosure involves preferred I 5 embodiments of the invention and that numerous modifications or alterations therein may be made without departing from the spirit and scope of the invention as set forth in the appendant claims.
Claims (10)
1. A universal power drive and lifting rotor system module for single and multiple rotor type VTOL aircraft comprising:
a component support airframe having a plurality of quick disconnect fasteners for detachably connecting components thereto, a main drive shaft supported for rotation within said component support airframe, said main drive shaft being adapted for detachable connection to an engine, a lifting rotor assembly and transmission mounted on said component support airframe, said lifting rotor assembly and said transmission being fastened to said component support airframe using said quick disconnect fasteners, said rotor transmission having a power input shaft adapted for detachable connection to said main drive shaft for transferring power between said main drive shaft and said power input shaft.
a component support airframe having a plurality of quick disconnect fasteners for detachably connecting components thereto, a main drive shaft supported for rotation within said component support airframe, said main drive shaft being adapted for detachable connection to an engine, a lifting rotor assembly and transmission mounted on said component support airframe, said lifting rotor assembly and said transmission being fastened to said component support airframe using said quick disconnect fasteners, said rotor transmission having a power input shaft adapted for detachable connection to said main drive shaft for transferring power between said main drive shaft and said power input shaft.
2. The module of claim 1 wherein said main drive shaft further comprises a coupling for axially delinking said main drive shaft and said engine.
3. The module of either of claims 1 or 2 further comprising power transfer apparatus having a main drive shaft pulley and a power input shaft pulley; said pulleys being interconnected by a belt.
4. The module of claim 1 wherein said lifting rotor assembly is configured for detachable connection to said rotor transmission.
5. The module of claim 1, wherein said component support airframe comprises a composite structure for providing fuel storage.
6. The module of claim 5, wherein said component support airframe further provides payload capacity on and around said support airframe.
7. A VTOL aircraft comprising:
the module of any one of claims 1, 2, 4, 5 or 6, a main drive shaft clutch extension detachably connected to said component support airframe using quick disconnect fasteners.
a first augmentation framework having a counter torque rotor, said first augmentation framework being detachably connected to said main drive shaft clutch extension using quick disconnect fasteners, a counter torque rotor drive shaft within said first augmentation framework adapted for detachable connection to said main drive shaft and said counter torque rotor.
the module of any one of claims 1, 2, 4, 5 or 6, a main drive shaft clutch extension detachably connected to said component support airframe using quick disconnect fasteners.
a first augmentation framework having a counter torque rotor, said first augmentation framework being detachably connected to said main drive shaft clutch extension using quick disconnect fasteners, a counter torque rotor drive shaft within said first augmentation framework adapted for detachable connection to said main drive shaft and said counter torque rotor.
8. The VTOL aircraft of claim 7, wherein said first augmentation framework is adapted for use as exhaust baffling to provide reduced sound signature for said aircraft.
9. The VTOL aircraft of claim 7, further comprising an undercarriage detachably connected to said component support airframe.
10. A VTOL dual rotor aircraft comprising:
a pair of the modules of any one of claims 1, 2, 4, 5 or 6, a second augmentation framework detachably attached to said
a pair of the modules of any one of claims 1, 2, 4, 5 or 6, a second augmentation framework detachably attached to said
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US51505000A | 2000-02-25 | 2000-02-25 | |
| US09/515,050 | 2000-02-25 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2301350A1 true CA2301350A1 (en) | 2001-08-25 |
Family
ID=24049771
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002301350A Abandoned CA2301350A1 (en) | 2000-02-25 | 2000-03-20 | Universal vtol power and rotor system module |
Country Status (3)
| Country | Link |
|---|---|
| AU (1) | AU784766B2 (en) |
| CA (1) | CA2301350A1 (en) |
| GB (1) | GB2359533A (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2856030B1 (en) * | 2003-06-11 | 2006-09-22 | Microcopter Soc | LIGHT AND MODULAR HELICOPTER WITH A VARIABLE FRONT MODULE CONNECTED TO A MAIN MODULE CONTAINING ESSENTIAL FLIGHT ORGANISMS |
| AT413811B (en) * | 2004-07-15 | 2006-06-15 | Schiebel Ind Ag | UNMANNED HELICOPTER |
| BR112012013352A8 (en) * | 2009-12-02 | 2016-05-17 | Saab Ab | helicopter |
| WO2011068445A1 (en) * | 2009-12-02 | 2011-06-09 | Saab Ab | Dismountable helicopter |
| FR2976553A1 (en) * | 2011-06-20 | 2012-12-21 | Cassidian | SYSTEM FOR INTEGRATING A DIESEL ENGINE IN A DRONE |
| CN102774492B (en) * | 2012-06-08 | 2016-03-30 | 无锡汉和航空技术有限公司 | A kind of small-sized depopulated helicopter fuselage |
| EP2933187B1 (en) | 2014-04-15 | 2017-01-11 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Rotary wing aircraft with a multiple beam tail boom |
| CN104554720A (en) * | 2014-12-31 | 2015-04-29 | 昆明天龙经纬电子科技有限公司 | Compound power helicopter |
| CN107399423B (en) * | 2017-07-28 | 2023-05-26 | 珠海紫燕无人飞行器有限公司 | Unmanned helicopter modularization frame structure |
| EP4282754A1 (en) * | 2022-05-24 | 2023-11-29 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | An attachment assembly for attachment of a tail boom to a rear fuselage of a rotorcraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1353692A (en) * | 1919-11-25 | 1920-09-21 | Wolfe Paul Timberlake | Aeroplane |
| FR921723A (en) * | 1946-02-07 | 1947-05-16 | United Aircraft Corp | Improvements to helicopters and aircraft of this type |
| GB871050A (en) * | 1958-01-17 | 1961-06-21 | Hiller Aircraft Corp | Improvements in or relating to rotary wing aircraft |
| GB1523714A (en) * | 1971-12-13 | 1978-09-06 | Westland Aircraft Ltd | Helicopters |
-
2000
- 2000-03-20 CA CA002301350A patent/CA2301350A1/en not_active Abandoned
- 2000-03-21 GB GB0006737A patent/GB2359533A/en not_active Withdrawn
- 2000-03-22 AU AU22464/00A patent/AU784766B2/en not_active Ceased
Also Published As
| Publication number | Publication date |
|---|---|
| GB2359533A (en) | 2001-08-29 |
| AU2246400A (en) | 2001-09-27 |
| GB0006737D0 (en) | 2000-05-10 |
| AU784766B2 (en) | 2006-06-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Discontinued |