CA2101903C - Directional hf antenna for a helicopter - Google Patents
Directional hf antenna for a helicopterInfo
- Publication number
- CA2101903C CA2101903C CA 2101903 CA2101903A CA2101903C CA 2101903 C CA2101903 C CA 2101903C CA 2101903 CA2101903 CA 2101903 CA 2101903 A CA2101903 A CA 2101903A CA 2101903 C CA2101903 C CA 2101903C
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- Canada
- Prior art keywords
- electrical conductors
- conductors
- antenna
- directional antenna
- electrical
- 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.)
- Expired - Lifetime
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Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Details Of Aerials (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
Disclosed is a combined directional antenna and rotor blade 101 for a helicopter 100. The antenna comprises three or more electrically non-conductive rotor blades 200, each having an electrical conductor 210 positioned parallel to the major axis of a respective rotor blade 200. Two of the electrical conductors 210, having angular positions nearer to a predetermined angular position are connected via a connections means 700 to apparatus for transmission or reception of radio waves. The remaining conductors may either be connected to the body of the helicopter or supplied with a signal out of phase compared to that supplied to the two electrical conductors. Also disclosed is a communications system including apparatus for the transmission or reception of radio waves.
Description
~" UK9-92-045 2 ~ D ~
DIRECTIONAL HF 1~ FOR A HELI~
Eield of the Invention The inVention relates to transmission and reception of radio waves in the HF spectrum and more specifically to use of rotor blades on a helicopter (or rotary winged aircraft) as an efficient directional antenna.
R~Ck.J.~l~ of the Invention Conventionally antennas for helicopters have been mounted clo~e to the body of the helicopter. Typically an antenna has consisted of a rigid member parallel to and spaced from the helicopter body by spacers. An alternative that has been used is where the antenna consists of a wire stretched between two spacers used to space the antenna away from the helicopter body. Insulators join the wire onto the spacers.
The spacers are usually relatively short which result in the antenna being placed close to the body of the helicopter.
Both of these alternative antennas can be made directional, but result in a shorter effective length of antenna. In addition any directionality is fixed relative to the orientation of the helicopter.
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United States patent 4,042,929 shows a navigation system in Which antennas are used at the tips of each of the blades of a helicopter rotor. The received signals are processed on the rotor blade and introduced into the body of the helicopter by means of slip rings and contact brushes. The antennas consist of a series o~ dipoles flattened along the centrel~ine of each blade, positioned proximate to the tips of the blades.
A popular band of frequencies for operation of military and commercial communications is the HF band of frequencies.
This band extends between 2 MHz and 30 MHz and has a number .'~ ;. ' ~: ~ ':
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'~ ~';.'.., : '' '~ ' 21~1903 of technical and tactical advantages over the higher frequencies that are available. In a typical modern installation, military VHF (30-170 MHz) and UHF (225-400 MHz) are used alongside the HF band for communication between the helicopter and ship~ or other helicopters and aircraft.
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Some advantages of the use of HF band frequencies are that HF band frequencies are the highest frequencies that will reflect from the ionosphere to provide long range skip communication, higher frequencies offer only line of site communication and cannot go over the horizon and propagation attenuation increases with frequency by a factor o~ 20 log frequency. The natural phenomena of range, antenna efficiency and atmospheric noise are all functions of frequency and the best compromise of the ~actors is achieved between 2 and 30 MHz. More efficient power amplifiers are available at the HF band of frequencies.
: ~., One factor that limits the HF band performance on aircraft and helicopters is the length of the antenna. For maximum efficiency, the antenna should be equal in length to the wavelength. The wavelength in metres can be calculated as the velocity of propagation of the radio waves in metres per second divided by the frequency ln Hertz. The velocity of propagation of radio waves is constant and is approximately equal to 3 x 108 metresjsecond.
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For UHF communications (typically 300 MHz), the wavelength calculated from the above equation i~ 1.0 metres. This is a practical length for an antenna, such as those types described earlier, to be mounted on a helicopter, despite intense competition for space from electronic equipment and in military helicopters also from heavy armament.
In the HF band, at a frequency of 3 MHz, the wavelength calculation shows that an antenna of length 100 metres is required. This is an impractical length for a hellcopter.
This can be overcome by using a submultiple of the ideal length obtained from the wavelength calculation. However ' ~'' ~ UK9-92-045 3 2~01~03 the antenna efficiency falls as the length of the antenna is reduced.
Another factor that limits the HF band performance on aircraft and helicopters is the difficulty of providing a directional antenna. A directional antenna has an increased ~ -gain in a direction or directions relative to the antenna.
It also has a decreased gain in other directions relative to the antenna. The lack of directionality of an antenna results in a loss of communication range compared with an antenna having directionality and can also result in the signal being received by other than the receiver for which it was intended. In order to provide optimal communication between the directional antenna and another antenna, the directional antenna needs to be oriented so that a direction of increased gain is oriented toward the desired receiving antenna. ~-~
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This orientation can be achieved by physical rotation of a ~;
directional antenna to point towards the other antenna, however this further limits its length and hence e~ficiency, :
thus offsetting any benefit from the increased gain due to directionality.
'~'"~"''' Conventional helicopters have rotor blades made primarily of ~ '~
metal. These rotor blades are fixed to the gearbox and engines via a substantial conductive path of metallic parts : .
making the blades difficult to employ as an antenna.
The new generation of helicopters are moving away from metallic rotor blades to using composite constructions. An -example is the Aerospatiale Ecureuil which has a Starflex rotor blade that is made mainly of glass fiber. Other helicopters have blades made of carbon and gla~s fibers with internal foams. -~
Di~closure of the Invention Accordingly the invention provides a directlonal antenna for use with appa~atus for transmission or reception of radio ;~:
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2101~Q3 waves in a rotary winged aircraft having a body provided with rotor b~ades, the antenna comprising three or more electrically non-conductive rotor blades, capable of being rotated with respect to the body of the rotary winged aircraft around an axis parpendicular to the blades; two first electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade and being in contact therewith; one or more second electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade, the second electrical conductors not being electrically connected to the first electrical conductors; means for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; means for dynamically selecting the first electrical conductors from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body of the rotary winged aircraft than others of the conductors, and for dynamically selecting the others of the conductors as second electrical conductors.
In a first embodiment the second electrical conductors are electrically connected to the body of the rotary winged aircraft.
In a second embodiment one or more of the second electrical conductors are provided with a signal that is out of phase with the signal provided to the first electrical conductors.
Preferably one or more of the second electrical conductors not provided with an out of phase signal are electrically connected to the body of the rotary winged aircraft.
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Preferably the connection means comprises slip rings and contact brushes. The slip rings and contact brushes are preferably also the means for dynamically selecting conductors as first conductors or as second conductors. In another embodiment the selecting means comprises electrical diodes and means for controlling the direct current biasing of the electrical diodes.
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2~019Q3 Preferably the directional antenna further comprises a control means for maintaining said first predetermined angular position with respect to a known geographic point.
The control means preferably comprises a stepping motor.
Preferably the directional antenna further comprises means for maintaining the first predetermined angular position constant with respect to a remote apparatus for transmitting or receiving radio waves.
In a preferred embodiment the directional antenna the length of each electrical conductor is substantially similar to that of the rotor blade and the radio waves transmitted or received have wavelengths in the range from 10 metres to 150 metres.
Also provided is a communications system for transmission and reception of radio waves in a rotary winged aircraft having a body provided with rotor blades, the system comprising apparatus for transmission or reception of radio waves; three or more electrically non-conductive rotor blades, capable of being rotated with respect to the body of the rotary winged aircraft around an axis perpendicular to the blades; two first electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade and being in contact therewith; one or more second electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade, the second electrical conductors not being electrically connected to the first electrical conductors;
means for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; and means for dynamically selecting the first electrical conductors ~rom all of the , ~
electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body of the rotary winged aircraft than others of the conductors, and for dynamically selecting the others of the conductors as second electrical conductors. ~ ~;
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Brief Description of the Dr~bQng~ -Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which: ~.
Figure l is schematic view of a helicopter showing the rotor ::
blades positioned above the helicopter;
Figure 2 is a section of one of the blades shown in figure l incorporating an element of an HF antenna;
Figure 3 is a polar diagram of radiation from or to an ~ : .
omnidirectional antenna such as one formed from the elements of figure 2; ;~
Figure 4 is a view of a prior art system using omnidirectional antennas such as that of figure 2; .t:
' Figure 5 is a polar diagram of radiation from or to a directional antenna such as is used in the present invention;
Figure 6 is a view of a communications system using at least ;.
one directional antennas such as that of the present invention; ;i~
Figure 7 is a perspective view of a commutator used in the present invention;
Figure 8 is a diagram used to illustrate the connection via .
the commutator of figure 7 of the electrical conductors in the invention; . . ;
Figure 9 is a schematic diagram ~howing the selection of ~.'''i individual coils used as an alternative to the commutator of '~
figure 7 in the invention.
Detailed Description of the Invention .. .
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Figure 1 shows a helicopter 100 with rotor blades 101 positioned above the fuselage 102 of the helicopter 100. The helicopter 100 is approximately 15 metres long and carries various equipment 103 fixed to the exterior of the fuselage 102. The fuselage 102 of the helicopter 100 is a ground plane for the frequencies used for radio reception and transmission. Because of the difficulty of finding an area of the fuselage 102 that is not a ground plane and does not already have other equipment 103 attached to it, HF antennas are usually short antennas with resultant low efficiency.
This gives a reduction in system performance that is difficult to overcome without increasing the transmitter power. In addition, because of the difficulty of providing a rotatable antenna, HF antennas are usually omnidirectional.
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The efficiency of an antenna can be shown to approximate as follows in an isotropic radiator;
Efficiency = 2.5 _______________________ :::
1.5 2.5 -~ ---------------(2 * PI * h)3 wavelength where h = the length of the antenna in metres wavelength = the wavelength of the transmitted or received i~
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signal in metres ' ~:
PI = the constant 3.1415926 approx.
From the above equation, it can be seen that at 3 MHz a 100 metre~long antenna could have an efficiency of 1, whilst a 2 metre long antenna, working at the same fre~uency, could ~ ;
have an efficiency of only 0.0033. This degradation of ; i efficiency due to the reduced length exists when the antenna is used both in the transmit mode and in the receive mode. --~
The receive antenna gain is dependent on the efficiency and the directionality of the antenna as well as other factors. ~'~
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The relationship between an~ ~nQ~g9aQn and the overall system performance can be represented by the following equation:
Pr = Pt + Gt ~ Gr - 20 loq f - 20 log R - 32.4 - La where Pr = Received power (dBm) Pt = Peak transmitter power (dBm) Gt = Transmit antenna gain (dB) "
Gr = Receive antenna gain (dB) f = Frequency (MHz) -~
R = Range (Nautical miles) La = Additional losses (dB) The factor of 32.4 is a constant which reflects the units used for frequency and range.
The frequency and required range are fixed for any given scenario. Additional losses are all minimized in any good design. If a full wavelength omnidirectional antenna is used from, for example, a ship then a gain of 1 might be po~sible. Conventional helicopters are forced to use inefficient omnidirectional antennas, as measured by the equation for the antenna efficiency given above, so that the ~-only option to achieve the required performance is to increase the transmitter power. ~ , If the communication link is from helicopter to helicopter, then from the same equation we can see that the link ~ , performance Will suffer both at the transmission and reception antennas. .",,~,,,~!, ~' ' ".,''' '' "' Use of a rotor blade 200 or rotor blades of the helicopter, ;~
such as is shown in figure 2, as an antenna allows the antenna to be considerably longer and hence more efficient. -With the exception of a radiating element included in the blade, the structure of the rotor blade 200 must be i ~.' substantially electrically non-conducting. The use of the rotor blades as an antenna improve~ the system performance, particularly for helicopter to helicopter communication, '~
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where the antenna efficiency has an effect both on the transmit antenna gain and the receive antenna gain.
Figure 2 shows a rotor blade 200 which has an erosion shield 210 fitted to the leading edge. The erosion shield 210 is intended to protect the leading edge of the rotor blade 200 from damage by particles in the air such as dust particles.
It also provides some protection from such things as striking foliage, during hovering or landing, when close to the ground. The erosion shield 210 will typically be fabricated from a metal such as titanium.
The erosion shield 210 extends for the length of the rotor blade and so provides an antenna which is substantially equal to the length of the rotor blade. By making continuous simultaneous connection to more than one rotor blade, an effective antenna length of about twice the length of the rotor blade can be obtained. At 3 MHz this will provide an efficiency of around 0.7 (depending on the length of the rotor blades), compared with 1 for the ideal antenna length of 100 metres and 0.0033 for a 2 metre antenna.
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An alternative to using the erosion shield is to use a heater filament 212 that is already present at the front edge of the rotor blade 200 as an antenna. The heater filament 212 is used for deicing the leading edge of the rotor blade. The transmitted and received signals are provided to the radio apparatus in the fuselage 102 of the helicopter 100 by use of the same means used for the transferiof power to the heater filament 212. Use of the heater filament also requires a means to combine the transmitter signal with the power for the heater filament 212 as well as for separating the receiver signa} from the power. The means for achieving this are well known to those skilled in the art, and are widely applied to such areas as the dual use of windscreen elements in automobiles as both demisting elements and receiving aerials. As with the usei of the erosion shield 210, the length of the antenna will be substantially similar to the length of the rotor blade 200.
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- ' UK9-92-045 10 2 ~ Q 3 Electrical connections are made from the erosion shields 210 to the apparatus in the fuselage 10~ of the helicopter 100 by brushes and slip rings or the like. Typically, when the present invention is not implemented, bonding jumpers are used to ground the erosion shields 210 to provide protection against lightning strikes and electromagnetic pulse. This protection can be retained, if required, when the present invention is implemented, by using spark gaps of a suitable breakdown voltage as is well known to those skilled in the art. Similarly, methods known to those skilled in the art to prevent static build up caused by the motion of the rotor blades can be used (in the form of discharge wic~s, for example).
The overall system performance is improved for a negligible ~;-increase in system cost.
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If the transmitter power is kept constant, then a greater ;~
signal power is radiated, giving the transmitted signal ' greater immunity against radio jamming. ~ ~
The antenna is positioned above the helicopter fuselage so '.
that the radiation from the antenna becomes omnidirectional with no shading of the antenna due to the fuselage itself.
When the helicopter is hovering at low altitudes the antenna ;
is placed higher relative to the ground giving improved communications over an antenna placed on the fuselage of the helicopter.
The losses shown in the equation for system performance as additional losses include capacitive losses from the antenna to the airframe. These losses are reduced because of the greater distance from the fuselage to the antenna. -When compared with a conventional antenna of the type described earlier which consists of a wire antenna with insulators spaced from the helicopter, the rotor blade antenna is much more mechanically robust and less liable to damage in the ground handling process. For a helicopter that ' UK9-92-045 11 2 ~ Q 3 has a folding tail for storage in restricted spaces the rotor blade antenna is less liable to damage during this process also.
The safety of personnel is improved because the transmitting antenna is placed further away from the occupants, with the resultant decreased exposure to electromagnetic fields. The possibility of reducing the transmitter power also reduces exposure to electromagnetic fields.
Directional antennas are used to concentrate the radiated field strength either from a transmitting antenna, or to a receiving antenna. Figure 3 shows the polar diagram of radiation from or to an omnidirectional antenna 300. The radial position represents the relative field strength transmitted or received in that angular direction. The polar plot of an omnidirectional antenna using conductors affixed to all of the rotor blades of a helicopter is of this form.
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, Figure 4 shows a possible situation using omnidirectional transmissions. Helicopter 411 transmits using an omnidirectional aerial so that the signal strength received by ships 421 and 422 is dependent only on their radial distance from helicopter 411 and not on their angular position. The vessel 421 with which it is desired to communicate actually receives a lower signal strength than vessel 422. Electromagnetic radiation emissions from the transmitting helicopter can be monitored in such a situation. Signals are often encoded by an encryption device, however the fact that radio signals are detected at all may be useful information.
Figure 5 shows the polar plot of a typical directional antenna 500, in this case a Yagi type antenna. Angular portions enclosed by secondary lobes 531, 532 have a higher gain than adjacent areas 521, 522 but this gain is much lower than the gain in angular positions enclosed by the main lobe 510 or the gain from an omnidirectional antenna 300 having a polar diagram such as that of figure 3. The gain of the antenna 500 is increasèd within the angular '~ UK9-92-045 12 2~ als~3 positions enclosed by the main lobe 510 at the expense of radiation in the unwanted areas 521, 522. The increased gain can be shown to equate as follows;
Gain (ratio) = (4 * pie * Ae) / (Wl * Wl) Where Ae = effective area of the lobes, ~:
and Wl = wave length of the transmitted or ~" ;
received signal.
Increased range is achieved in the desired direction (within the angular positions enclosed by lobe 510) during both transmission and reception. Also, as described below with ;'~
reference to figures 4 and 6, increased security is achieved ~ ;~
against a signal being received by other than the receiver for which it was intended. ;
Figure 6 shows the same situation as figure 4 but helicopter -611 has a directional antenna having a polar diagram such as ~
that of figure 5. The directional antenna may be used to '-communicate with, for example, a ship, whilst minimizing the -~
risk of detection.
A coupling method is necessary to link the rotating antenna to the radio equipment. A slip ring and brushes may be ~i employed for this purpose. If a slip ring in the form of a commutator is used, then only during a portion of thé arc described by the rotating antenna as it rotates, is the antenna selectively connected to the apparatus for receiving i ~
and transmitting radio signals. Electromagnetic radiation ~ -from the antenna is only received from or transmitted to another antenna located in that portion when the antenna is connected to the apparatus for receiving and transmitting radio waves.
Figure 7 is a perspective view of a commutator 700, where some of the elements of a rotating antenna/blade assembly ~ ;
are used for transmission whilst other element~ of the antenna/blade assembly are grounded to the aircraft -~:
structure, or fed with a phase shifted signal during ~ UK9-92-045 13 21019~'3 selected segments of its sweep, in order to produce a controllable directional antenna.
The commutator 700 consists of a shell 711, which does not rotate with the rotor blades, and a part of the rotor blade shaft 712 which rotates with the rotor blades. The shell 711 contains a number of slip rings, such as 721 and 722, preferably one slip ring per rotor blade. The slip rings are connected to the apparatus for transmitting and receiving radio signals or to the helicopter body as described later.
The rotor shaft has brushes, such as 741 and 742, which are connected to one or more of the electrical conductors on the rotor blade. The brushes 741, 742 provide a connection to a corresponding slip ring 721, 722.
Each slip ring is divided into angular portions, each portion being connected to either the helicopter body or to a zero phase shift signal or to a phase shifted signal. In this way the signal provided to any one electrical conductor on the rotor blades can be made dependent on the conductors physical position relative to the helicopter body. Normally there will be a gap 731, 732 between breaking of a connection from the electrical conductor to the making of another connection to the electrical conductor.
The use of a commutator assumes and takes advantage of the capability of achieving directionality in the antenna pattern. It al~o further offers the advantage of using the commutation in various configurations to control the direction of the directed energy lobe 510. By proper selection of the connections to the electrical conductors, the main beam of the antenna can be made more directional and its direction of maximum radiation can be controlled relative to the aircraft longitudinal axis.
The directionality is achieved by feeding two or more blades with the transmitter power and utilizing one or more o~ the remaining blades either with phase shifted energy or by grounding them to reduce the radiated field intensity of the back lobe.
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Grounded configuration 2 10 1 9 Q 3 In a first embodiment, if the antenna is grounded as it rotates in the portion of the arc located at 180 degrees from the active portion, then the directivity is further enhanced. Figure 8 shows a typical composite rotor having five rotor blades. This gives an angle between the rotor blades of 72 degrees. If a commutator is arranged to connect the apparatus to the antenna conductor of two rotor blades 801, 805 at any one time, as they rotate, then this will form a 'V' configuration antenna that has directional properties without any contribution to directionality from the remaining three rotor blades. The antenna conductors of rotor blades 802, 804 are preferably grounded to act as a reflector and further add to the directivity of the antenna.
Blade 803 ma~ either be grounded or may be open circuit. As the rotor blade assembly rotates in an anticlockwise . . .
direction the rotor blade which was connected as blade 802 rotates to the position of rotor blade 801. In a preferred embodiment there is a gap in the commutator where the blade is open circuit between the times when it is connected to the apparatus and when it is grounded. ~;
A vertically staggered system is used for the commutator, as shown in figure 7. This technique ensures that the antenna conductors of two blades are always connected to the apparatus and optimum coupling is achieved.
The electrical coupling can also be achieved by inductive .
coupling or capacitor coupling using multiple coils or capacitors, one for each blade. The individual coils or capacitors can be selected at the appropriate time by means of a reversed biased diode control, for example.
Figure 9 shows such an arrangement using inductive coupling for the connection of rotor blades 805 and 801 when these rotor blades are connected to the apparatu~ for transmission and reception of radio waves. A connection 901, preferably a coaxial connection, is made from the apparatus for ., ~ :..
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transmitting and receiving radio waves to the apparatus shown in figure 9.
The following description will assume that a signal is to be transmitted by rotor blades 805 and 801. For a signal to be received the path would be reversed. The signal is inductively coupled through transformer 902 for d.c.
isolation. A signal is applied via connection 906 in order to control the bias of diode 904. This signal is a pulse synchronized with the rotor shaft position and present when it is desired for the transmitted signal to be passed on to rotor blades 805 and 801. The signal is applied through an r.f. choke 905 to prevent short circuiting of the transmitted signal through the bias supply. When the pulse is present the diode is forward biased and allows the transmitter signal to pass through to the inductive coupling mechanism 910 to the rotor blades 805 and 801. Coil 912 is on the rotor shaft and coil 911 is mounted concentric with coil 912, but is fixed to the fuselage 102. When the pulse is not present the diode is reverse biased and the transmitter signal cannot pass. The transmitted signal returns to the isolating transformer through d.c. blocking capacitor 903. The diodes must be capable of handling the radiated r.f. power and the blocking capacitor must be capable of conducting the r.f. current.
In a preferred embodiment with five such rotor blades (801, 802, 803, 804, 805), a single connection 901, isolating transformer 902 and d.c. blocking capacitor 903 are used.
For each blade there are separate diodes 904 and inductive coupling mechanisms 910. The series combinations of the diodes and inductive coupling mechanisms are connected in parallel between the isolating transformer and the d.c.
blocking capacitor. The number of series combinations is the same as the number of blades, with the coils 912 being connected between respective pairs of rotor blades.
The r.f. chokes 905 connect from each diode to a respective source of timing pulses. The timing pulses are obtained from the rotor shaft by using a magnet ~ixed to the rotor shaft ~ UK9-92-045 16 21~19Q3 and a pickup coil for each pulse required. Alternatively, an arrangement of photo-optical coupling may be used. The pulses are shaped and the amplitude processed as re~uired.
They are then passed through a delay means, the amount of the delay being capable of being controlled external to the delay means. The control of the delay may be used to effect control of the angular position of the radiating lobe with respect to a fixed geographic position. All of the pulses are delayed by the same amount.
Alternatively the pulses could be generated by a pulse generator, synchronized by one shaft position pulse. Each control pulse is displaced from the preceding one by 72 degrees in the time domain in the case of a 5 bladed rotor assembly.
Phase ~hift configuration In a second embodiment two adjacent rotor blades (801, 805) are fed in a 'V' configuration with the primary (that is, zero phase shift) radio frequency feed, which in itself results in a directional pattern in bipolar form (that is with a forwards lobe and a backwards lobe). However there is still significant radiation directed in a direction opposite to the desired direction. To reduce this rotor blades (802, 804) are driven with a phase shifted (that is, displaced from zero degrees) signal to reinforce the forward lobe and provide for some cancellation effect for the back lobe. The amount of phase shift required may be established by mathematical ~odelling, as is known to those skilled in the art of antenna theory. Rotor blade 803 can also be utilized in the same fashion (that is, fed with an out of phase signal or grounded to act as a reflector).
As the blades rotate approximately 72 degrees counterclockwise, the commutator wipers fed from the apparatus for receiving and transmitting radio waves disengage rotor blades 805 and 801 and instead engage blades 801 and 802 as the primary radiators. Blades 801 and 802 are similarly disengaged and blades 802 and 803 now engage the . ~
~'~ UK9-92-045 17 211~19Q3 ; ~
wipers with the phase controlled feed to provide reinforcement of the main lobe and a cancellation effect on the back lobe. The rotation of the commutator causes the connection of the blades, both primary feed and phase controlled feed, to change every 72 degrees of rotation.
In order to provide optimal communication between the directional antenna and another antenna, the directional antenna needs to be oriented so that a direction of increased gain is oriented toward the desired receiving antenna.
This can be achieved by rotating the commutator shell 711 that connects to the transmitting and receiving apparatus so that the electrical conductors connect to the apparatus over a dif~erent portion of the arc swept by the conductors. The rotation of the commutator can be achieved by the use of a s~epper mo~or.
All modern aircraft eguipment communicates with other equipment on the aircraft via a digital data bus. This data bus carries instructions from a central computer to the avionic equipment. The stepper motor is controlled via an suitable interface from such a data bus. The construction of sbch an inter~ace is well known to those skilled in the art of design of avionic equipment. A flight computer is given the bearing of the receiver or transmitter with which it is desired to communicate. It also has access to the present course of the aircraft. From these it is able to determine the required position of the commutator and control the stepper motor and therefore the directionality of the antenna. As the aircraft changes course, the antenna remains orlented in the appropriate direction.
In all of the variations of the invention described above, as well as in prior art antennas it is necessary to include in the system an antenna tuning unit to allow the impedance of the antenna to be matched to the impedance of the transmitter and receiver over a wide range of frequen~ies.
The design and construction of antenna tuning units is well .'~
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~- UK9-92-045 18 known to those skilled in the art and will not be discussed further.
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DIRECTIONAL HF 1~ FOR A HELI~
Eield of the Invention The inVention relates to transmission and reception of radio waves in the HF spectrum and more specifically to use of rotor blades on a helicopter (or rotary winged aircraft) as an efficient directional antenna.
R~Ck.J.~l~ of the Invention Conventionally antennas for helicopters have been mounted clo~e to the body of the helicopter. Typically an antenna has consisted of a rigid member parallel to and spaced from the helicopter body by spacers. An alternative that has been used is where the antenna consists of a wire stretched between two spacers used to space the antenna away from the helicopter body. Insulators join the wire onto the spacers.
The spacers are usually relatively short which result in the antenna being placed close to the body of the helicopter.
Both of these alternative antennas can be made directional, but result in a shorter effective length of antenna. In addition any directionality is fixed relative to the orientation of the helicopter.
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United States patent 4,042,929 shows a navigation system in Which antennas are used at the tips of each of the blades of a helicopter rotor. The received signals are processed on the rotor blade and introduced into the body of the helicopter by means of slip rings and contact brushes. The antennas consist of a series o~ dipoles flattened along the centrel~ine of each blade, positioned proximate to the tips of the blades.
A popular band of frequencies for operation of military and commercial communications is the HF band of frequencies.
This band extends between 2 MHz and 30 MHz and has a number .'~ ;. ' ~: ~ ':
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'~ ~';.'.., : '' '~ ' 21~1903 of technical and tactical advantages over the higher frequencies that are available. In a typical modern installation, military VHF (30-170 MHz) and UHF (225-400 MHz) are used alongside the HF band for communication between the helicopter and ship~ or other helicopters and aircraft.
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Some advantages of the use of HF band frequencies are that HF band frequencies are the highest frequencies that will reflect from the ionosphere to provide long range skip communication, higher frequencies offer only line of site communication and cannot go over the horizon and propagation attenuation increases with frequency by a factor o~ 20 log frequency. The natural phenomena of range, antenna efficiency and atmospheric noise are all functions of frequency and the best compromise of the ~actors is achieved between 2 and 30 MHz. More efficient power amplifiers are available at the HF band of frequencies.
: ~., One factor that limits the HF band performance on aircraft and helicopters is the length of the antenna. For maximum efficiency, the antenna should be equal in length to the wavelength. The wavelength in metres can be calculated as the velocity of propagation of the radio waves in metres per second divided by the frequency ln Hertz. The velocity of propagation of radio waves is constant and is approximately equal to 3 x 108 metresjsecond.
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For UHF communications (typically 300 MHz), the wavelength calculated from the above equation i~ 1.0 metres. This is a practical length for an antenna, such as those types described earlier, to be mounted on a helicopter, despite intense competition for space from electronic equipment and in military helicopters also from heavy armament.
In the HF band, at a frequency of 3 MHz, the wavelength calculation shows that an antenna of length 100 metres is required. This is an impractical length for a hellcopter.
This can be overcome by using a submultiple of the ideal length obtained from the wavelength calculation. However ' ~'' ~ UK9-92-045 3 2~01~03 the antenna efficiency falls as the length of the antenna is reduced.
Another factor that limits the HF band performance on aircraft and helicopters is the difficulty of providing a directional antenna. A directional antenna has an increased ~ -gain in a direction or directions relative to the antenna.
It also has a decreased gain in other directions relative to the antenna. The lack of directionality of an antenna results in a loss of communication range compared with an antenna having directionality and can also result in the signal being received by other than the receiver for which it was intended. In order to provide optimal communication between the directional antenna and another antenna, the directional antenna needs to be oriented so that a direction of increased gain is oriented toward the desired receiving antenna. ~-~
. ~, .
This orientation can be achieved by physical rotation of a ~;
directional antenna to point towards the other antenna, however this further limits its length and hence e~ficiency, :
thus offsetting any benefit from the increased gain due to directionality.
'~'"~"''' Conventional helicopters have rotor blades made primarily of ~ '~
metal. These rotor blades are fixed to the gearbox and engines via a substantial conductive path of metallic parts : .
making the blades difficult to employ as an antenna.
The new generation of helicopters are moving away from metallic rotor blades to using composite constructions. An -example is the Aerospatiale Ecureuil which has a Starflex rotor blade that is made mainly of glass fiber. Other helicopters have blades made of carbon and gla~s fibers with internal foams. -~
Di~closure of the Invention Accordingly the invention provides a directlonal antenna for use with appa~atus for transmission or reception of radio ;~:
:
2101~Q3 waves in a rotary winged aircraft having a body provided with rotor b~ades, the antenna comprising three or more electrically non-conductive rotor blades, capable of being rotated with respect to the body of the rotary winged aircraft around an axis parpendicular to the blades; two first electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade and being in contact therewith; one or more second electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade, the second electrical conductors not being electrically connected to the first electrical conductors; means for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; means for dynamically selecting the first electrical conductors from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body of the rotary winged aircraft than others of the conductors, and for dynamically selecting the others of the conductors as second electrical conductors.
In a first embodiment the second electrical conductors are electrically connected to the body of the rotary winged aircraft.
In a second embodiment one or more of the second electrical conductors are provided with a signal that is out of phase with the signal provided to the first electrical conductors.
Preferably one or more of the second electrical conductors not provided with an out of phase signal are electrically connected to the body of the rotary winged aircraft.
: ~;
Preferably the connection means comprises slip rings and contact brushes. The slip rings and contact brushes are preferably also the means for dynamically selecting conductors as first conductors or as second conductors. In another embodiment the selecting means comprises electrical diodes and means for controlling the direct current biasing of the electrical diodes.
.:..
;,. .,'''' '';
2~019Q3 Preferably the directional antenna further comprises a control means for maintaining said first predetermined angular position with respect to a known geographic point.
The control means preferably comprises a stepping motor.
Preferably the directional antenna further comprises means for maintaining the first predetermined angular position constant with respect to a remote apparatus for transmitting or receiving radio waves.
In a preferred embodiment the directional antenna the length of each electrical conductor is substantially similar to that of the rotor blade and the radio waves transmitted or received have wavelengths in the range from 10 metres to 150 metres.
Also provided is a communications system for transmission and reception of radio waves in a rotary winged aircraft having a body provided with rotor blades, the system comprising apparatus for transmission or reception of radio waves; three or more electrically non-conductive rotor blades, capable of being rotated with respect to the body of the rotary winged aircraft around an axis perpendicular to the blades; two first electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade and being in contact therewith; one or more second electrical conductors, each conductor being positioned parallel to the major axis of a respective rotor blade, the second electrical conductors not being electrically connected to the first electrical conductors;
means for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; and means for dynamically selecting the first electrical conductors ~rom all of the , ~
electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body of the rotary winged aircraft than others of the conductors, and for dynamically selecting the others of the conductors as second electrical conductors. ~ ~;
.
. ~
. ~
Brief Description of the Dr~bQng~ -Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which: ~.
Figure l is schematic view of a helicopter showing the rotor ::
blades positioned above the helicopter;
Figure 2 is a section of one of the blades shown in figure l incorporating an element of an HF antenna;
Figure 3 is a polar diagram of radiation from or to an ~ : .
omnidirectional antenna such as one formed from the elements of figure 2; ;~
Figure 4 is a view of a prior art system using omnidirectional antennas such as that of figure 2; .t:
' Figure 5 is a polar diagram of radiation from or to a directional antenna such as is used in the present invention;
Figure 6 is a view of a communications system using at least ;.
one directional antennas such as that of the present invention; ;i~
Figure 7 is a perspective view of a commutator used in the present invention;
Figure 8 is a diagram used to illustrate the connection via .
the commutator of figure 7 of the electrical conductors in the invention; . . ;
Figure 9 is a schematic diagram ~howing the selection of ~.'''i individual coils used as an alternative to the commutator of '~
figure 7 in the invention.
Detailed Description of the Invention .. .
''', :'. ~, ~ .:
Figure 1 shows a helicopter 100 with rotor blades 101 positioned above the fuselage 102 of the helicopter 100. The helicopter 100 is approximately 15 metres long and carries various equipment 103 fixed to the exterior of the fuselage 102. The fuselage 102 of the helicopter 100 is a ground plane for the frequencies used for radio reception and transmission. Because of the difficulty of finding an area of the fuselage 102 that is not a ground plane and does not already have other equipment 103 attached to it, HF antennas are usually short antennas with resultant low efficiency.
This gives a reduction in system performance that is difficult to overcome without increasing the transmitter power. In addition, because of the difficulty of providing a rotatable antenna, HF antennas are usually omnidirectional.
:
The efficiency of an antenna can be shown to approximate as follows in an isotropic radiator;
Efficiency = 2.5 _______________________ :::
1.5 2.5 -~ ---------------(2 * PI * h)3 wavelength where h = the length of the antenna in metres wavelength = the wavelength of the transmitted or received i~
. " ~
signal in metres ' ~:
PI = the constant 3.1415926 approx.
From the above equation, it can be seen that at 3 MHz a 100 metre~long antenna could have an efficiency of 1, whilst a 2 metre long antenna, working at the same fre~uency, could ~ ;
have an efficiency of only 0.0033. This degradation of ; i efficiency due to the reduced length exists when the antenna is used both in the transmit mode and in the receive mode. --~
The receive antenna gain is dependent on the efficiency and the directionality of the antenna as well as other factors. ~'~
::
The relationship between an~ ~nQ~g9aQn and the overall system performance can be represented by the following equation:
Pr = Pt + Gt ~ Gr - 20 loq f - 20 log R - 32.4 - La where Pr = Received power (dBm) Pt = Peak transmitter power (dBm) Gt = Transmit antenna gain (dB) "
Gr = Receive antenna gain (dB) f = Frequency (MHz) -~
R = Range (Nautical miles) La = Additional losses (dB) The factor of 32.4 is a constant which reflects the units used for frequency and range.
The frequency and required range are fixed for any given scenario. Additional losses are all minimized in any good design. If a full wavelength omnidirectional antenna is used from, for example, a ship then a gain of 1 might be po~sible. Conventional helicopters are forced to use inefficient omnidirectional antennas, as measured by the equation for the antenna efficiency given above, so that the ~-only option to achieve the required performance is to increase the transmitter power. ~ , If the communication link is from helicopter to helicopter, then from the same equation we can see that the link ~ , performance Will suffer both at the transmission and reception antennas. .",,~,,,~!, ~' ' ".,''' '' "' Use of a rotor blade 200 or rotor blades of the helicopter, ;~
such as is shown in figure 2, as an antenna allows the antenna to be considerably longer and hence more efficient. -With the exception of a radiating element included in the blade, the structure of the rotor blade 200 must be i ~.' substantially electrically non-conducting. The use of the rotor blades as an antenna improve~ the system performance, particularly for helicopter to helicopter communication, '~
~ ''" ''''.'~':.'' ; ~ , ,.'., 2 ~ Q '~ ~:
where the antenna efficiency has an effect both on the transmit antenna gain and the receive antenna gain.
Figure 2 shows a rotor blade 200 which has an erosion shield 210 fitted to the leading edge. The erosion shield 210 is intended to protect the leading edge of the rotor blade 200 from damage by particles in the air such as dust particles.
It also provides some protection from such things as striking foliage, during hovering or landing, when close to the ground. The erosion shield 210 will typically be fabricated from a metal such as titanium.
The erosion shield 210 extends for the length of the rotor blade and so provides an antenna which is substantially equal to the length of the rotor blade. By making continuous simultaneous connection to more than one rotor blade, an effective antenna length of about twice the length of the rotor blade can be obtained. At 3 MHz this will provide an efficiency of around 0.7 (depending on the length of the rotor blades), compared with 1 for the ideal antenna length of 100 metres and 0.0033 for a 2 metre antenna.
~ ~.
An alternative to using the erosion shield is to use a heater filament 212 that is already present at the front edge of the rotor blade 200 as an antenna. The heater filament 212 is used for deicing the leading edge of the rotor blade. The transmitted and received signals are provided to the radio apparatus in the fuselage 102 of the helicopter 100 by use of the same means used for the transferiof power to the heater filament 212. Use of the heater filament also requires a means to combine the transmitter signal with the power for the heater filament 212 as well as for separating the receiver signa} from the power. The means for achieving this are well known to those skilled in the art, and are widely applied to such areas as the dual use of windscreen elements in automobiles as both demisting elements and receiving aerials. As with the usei of the erosion shield 210, the length of the antenna will be substantially similar to the length of the rotor blade 200.
!
- ' UK9-92-045 10 2 ~ Q 3 Electrical connections are made from the erosion shields 210 to the apparatus in the fuselage 10~ of the helicopter 100 by brushes and slip rings or the like. Typically, when the present invention is not implemented, bonding jumpers are used to ground the erosion shields 210 to provide protection against lightning strikes and electromagnetic pulse. This protection can be retained, if required, when the present invention is implemented, by using spark gaps of a suitable breakdown voltage as is well known to those skilled in the art. Similarly, methods known to those skilled in the art to prevent static build up caused by the motion of the rotor blades can be used (in the form of discharge wic~s, for example).
The overall system performance is improved for a negligible ~;-increase in system cost.
, ~''':
If the transmitter power is kept constant, then a greater ;~
signal power is radiated, giving the transmitted signal ' greater immunity against radio jamming. ~ ~
The antenna is positioned above the helicopter fuselage so '.
that the radiation from the antenna becomes omnidirectional with no shading of the antenna due to the fuselage itself.
When the helicopter is hovering at low altitudes the antenna ;
is placed higher relative to the ground giving improved communications over an antenna placed on the fuselage of the helicopter.
The losses shown in the equation for system performance as additional losses include capacitive losses from the antenna to the airframe. These losses are reduced because of the greater distance from the fuselage to the antenna. -When compared with a conventional antenna of the type described earlier which consists of a wire antenna with insulators spaced from the helicopter, the rotor blade antenna is much more mechanically robust and less liable to damage in the ground handling process. For a helicopter that ' UK9-92-045 11 2 ~ Q 3 has a folding tail for storage in restricted spaces the rotor blade antenna is less liable to damage during this process also.
The safety of personnel is improved because the transmitting antenna is placed further away from the occupants, with the resultant decreased exposure to electromagnetic fields. The possibility of reducing the transmitter power also reduces exposure to electromagnetic fields.
Directional antennas are used to concentrate the radiated field strength either from a transmitting antenna, or to a receiving antenna. Figure 3 shows the polar diagram of radiation from or to an omnidirectional antenna 300. The radial position represents the relative field strength transmitted or received in that angular direction. The polar plot of an omnidirectional antenna using conductors affixed to all of the rotor blades of a helicopter is of this form.
~::
, Figure 4 shows a possible situation using omnidirectional transmissions. Helicopter 411 transmits using an omnidirectional aerial so that the signal strength received by ships 421 and 422 is dependent only on their radial distance from helicopter 411 and not on their angular position. The vessel 421 with which it is desired to communicate actually receives a lower signal strength than vessel 422. Electromagnetic radiation emissions from the transmitting helicopter can be monitored in such a situation. Signals are often encoded by an encryption device, however the fact that radio signals are detected at all may be useful information.
Figure 5 shows the polar plot of a typical directional antenna 500, in this case a Yagi type antenna. Angular portions enclosed by secondary lobes 531, 532 have a higher gain than adjacent areas 521, 522 but this gain is much lower than the gain in angular positions enclosed by the main lobe 510 or the gain from an omnidirectional antenna 300 having a polar diagram such as that of figure 3. The gain of the antenna 500 is increasèd within the angular '~ UK9-92-045 12 2~ als~3 positions enclosed by the main lobe 510 at the expense of radiation in the unwanted areas 521, 522. The increased gain can be shown to equate as follows;
Gain (ratio) = (4 * pie * Ae) / (Wl * Wl) Where Ae = effective area of the lobes, ~:
and Wl = wave length of the transmitted or ~" ;
received signal.
Increased range is achieved in the desired direction (within the angular positions enclosed by lobe 510) during both transmission and reception. Also, as described below with ;'~
reference to figures 4 and 6, increased security is achieved ~ ;~
against a signal being received by other than the receiver for which it was intended. ;
Figure 6 shows the same situation as figure 4 but helicopter -611 has a directional antenna having a polar diagram such as ~
that of figure 5. The directional antenna may be used to '-communicate with, for example, a ship, whilst minimizing the -~
risk of detection.
A coupling method is necessary to link the rotating antenna to the radio equipment. A slip ring and brushes may be ~i employed for this purpose. If a slip ring in the form of a commutator is used, then only during a portion of thé arc described by the rotating antenna as it rotates, is the antenna selectively connected to the apparatus for receiving i ~
and transmitting radio signals. Electromagnetic radiation ~ -from the antenna is only received from or transmitted to another antenna located in that portion when the antenna is connected to the apparatus for receiving and transmitting radio waves.
Figure 7 is a perspective view of a commutator 700, where some of the elements of a rotating antenna/blade assembly ~ ;
are used for transmission whilst other element~ of the antenna/blade assembly are grounded to the aircraft -~:
structure, or fed with a phase shifted signal during ~ UK9-92-045 13 21019~'3 selected segments of its sweep, in order to produce a controllable directional antenna.
The commutator 700 consists of a shell 711, which does not rotate with the rotor blades, and a part of the rotor blade shaft 712 which rotates with the rotor blades. The shell 711 contains a number of slip rings, such as 721 and 722, preferably one slip ring per rotor blade. The slip rings are connected to the apparatus for transmitting and receiving radio signals or to the helicopter body as described later.
The rotor shaft has brushes, such as 741 and 742, which are connected to one or more of the electrical conductors on the rotor blade. The brushes 741, 742 provide a connection to a corresponding slip ring 721, 722.
Each slip ring is divided into angular portions, each portion being connected to either the helicopter body or to a zero phase shift signal or to a phase shifted signal. In this way the signal provided to any one electrical conductor on the rotor blades can be made dependent on the conductors physical position relative to the helicopter body. Normally there will be a gap 731, 732 between breaking of a connection from the electrical conductor to the making of another connection to the electrical conductor.
The use of a commutator assumes and takes advantage of the capability of achieving directionality in the antenna pattern. It al~o further offers the advantage of using the commutation in various configurations to control the direction of the directed energy lobe 510. By proper selection of the connections to the electrical conductors, the main beam of the antenna can be made more directional and its direction of maximum radiation can be controlled relative to the aircraft longitudinal axis.
The directionality is achieved by feeding two or more blades with the transmitter power and utilizing one or more o~ the remaining blades either with phase shifted energy or by grounding them to reduce the radiated field intensity of the back lobe.
.. , ,' ~ ~
Grounded configuration 2 10 1 9 Q 3 In a first embodiment, if the antenna is grounded as it rotates in the portion of the arc located at 180 degrees from the active portion, then the directivity is further enhanced. Figure 8 shows a typical composite rotor having five rotor blades. This gives an angle between the rotor blades of 72 degrees. If a commutator is arranged to connect the apparatus to the antenna conductor of two rotor blades 801, 805 at any one time, as they rotate, then this will form a 'V' configuration antenna that has directional properties without any contribution to directionality from the remaining three rotor blades. The antenna conductors of rotor blades 802, 804 are preferably grounded to act as a reflector and further add to the directivity of the antenna.
Blade 803 ma~ either be grounded or may be open circuit. As the rotor blade assembly rotates in an anticlockwise . . .
direction the rotor blade which was connected as blade 802 rotates to the position of rotor blade 801. In a preferred embodiment there is a gap in the commutator where the blade is open circuit between the times when it is connected to the apparatus and when it is grounded. ~;
A vertically staggered system is used for the commutator, as shown in figure 7. This technique ensures that the antenna conductors of two blades are always connected to the apparatus and optimum coupling is achieved.
The electrical coupling can also be achieved by inductive .
coupling or capacitor coupling using multiple coils or capacitors, one for each blade. The individual coils or capacitors can be selected at the appropriate time by means of a reversed biased diode control, for example.
Figure 9 shows such an arrangement using inductive coupling for the connection of rotor blades 805 and 801 when these rotor blades are connected to the apparatu~ for transmission and reception of radio waves. A connection 901, preferably a coaxial connection, is made from the apparatus for ., ~ :..
2~0~0~
transmitting and receiving radio waves to the apparatus shown in figure 9.
The following description will assume that a signal is to be transmitted by rotor blades 805 and 801. For a signal to be received the path would be reversed. The signal is inductively coupled through transformer 902 for d.c.
isolation. A signal is applied via connection 906 in order to control the bias of diode 904. This signal is a pulse synchronized with the rotor shaft position and present when it is desired for the transmitted signal to be passed on to rotor blades 805 and 801. The signal is applied through an r.f. choke 905 to prevent short circuiting of the transmitted signal through the bias supply. When the pulse is present the diode is forward biased and allows the transmitter signal to pass through to the inductive coupling mechanism 910 to the rotor blades 805 and 801. Coil 912 is on the rotor shaft and coil 911 is mounted concentric with coil 912, but is fixed to the fuselage 102. When the pulse is not present the diode is reverse biased and the transmitter signal cannot pass. The transmitted signal returns to the isolating transformer through d.c. blocking capacitor 903. The diodes must be capable of handling the radiated r.f. power and the blocking capacitor must be capable of conducting the r.f. current.
In a preferred embodiment with five such rotor blades (801, 802, 803, 804, 805), a single connection 901, isolating transformer 902 and d.c. blocking capacitor 903 are used.
For each blade there are separate diodes 904 and inductive coupling mechanisms 910. The series combinations of the diodes and inductive coupling mechanisms are connected in parallel between the isolating transformer and the d.c.
blocking capacitor. The number of series combinations is the same as the number of blades, with the coils 912 being connected between respective pairs of rotor blades.
The r.f. chokes 905 connect from each diode to a respective source of timing pulses. The timing pulses are obtained from the rotor shaft by using a magnet ~ixed to the rotor shaft ~ UK9-92-045 16 21~19Q3 and a pickup coil for each pulse required. Alternatively, an arrangement of photo-optical coupling may be used. The pulses are shaped and the amplitude processed as re~uired.
They are then passed through a delay means, the amount of the delay being capable of being controlled external to the delay means. The control of the delay may be used to effect control of the angular position of the radiating lobe with respect to a fixed geographic position. All of the pulses are delayed by the same amount.
Alternatively the pulses could be generated by a pulse generator, synchronized by one shaft position pulse. Each control pulse is displaced from the preceding one by 72 degrees in the time domain in the case of a 5 bladed rotor assembly.
Phase ~hift configuration In a second embodiment two adjacent rotor blades (801, 805) are fed in a 'V' configuration with the primary (that is, zero phase shift) radio frequency feed, which in itself results in a directional pattern in bipolar form (that is with a forwards lobe and a backwards lobe). However there is still significant radiation directed in a direction opposite to the desired direction. To reduce this rotor blades (802, 804) are driven with a phase shifted (that is, displaced from zero degrees) signal to reinforce the forward lobe and provide for some cancellation effect for the back lobe. The amount of phase shift required may be established by mathematical ~odelling, as is known to those skilled in the art of antenna theory. Rotor blade 803 can also be utilized in the same fashion (that is, fed with an out of phase signal or grounded to act as a reflector).
As the blades rotate approximately 72 degrees counterclockwise, the commutator wipers fed from the apparatus for receiving and transmitting radio waves disengage rotor blades 805 and 801 and instead engage blades 801 and 802 as the primary radiators. Blades 801 and 802 are similarly disengaged and blades 802 and 803 now engage the . ~
~'~ UK9-92-045 17 211~19Q3 ; ~
wipers with the phase controlled feed to provide reinforcement of the main lobe and a cancellation effect on the back lobe. The rotation of the commutator causes the connection of the blades, both primary feed and phase controlled feed, to change every 72 degrees of rotation.
In order to provide optimal communication between the directional antenna and another antenna, the directional antenna needs to be oriented so that a direction of increased gain is oriented toward the desired receiving antenna.
This can be achieved by rotating the commutator shell 711 that connects to the transmitting and receiving apparatus so that the electrical conductors connect to the apparatus over a dif~erent portion of the arc swept by the conductors. The rotation of the commutator can be achieved by the use of a s~epper mo~or.
All modern aircraft eguipment communicates with other equipment on the aircraft via a digital data bus. This data bus carries instructions from a central computer to the avionic equipment. The stepper motor is controlled via an suitable interface from such a data bus. The construction of sbch an inter~ace is well known to those skilled in the art of design of avionic equipment. A flight computer is given the bearing of the receiver or transmitter with which it is desired to communicate. It also has access to the present course of the aircraft. From these it is able to determine the required position of the commutator and control the stepper motor and therefore the directionality of the antenna. As the aircraft changes course, the antenna remains orlented in the appropriate direction.
In all of the variations of the invention described above, as well as in prior art antennas it is necessary to include in the system an antenna tuning unit to allow the impedance of the antenna to be matched to the impedance of the transmitter and receiver over a wide range of frequen~ies.
The design and construction of antenna tuning units is well .'~
: ':
~- UK9-92-045 18 known to those skilled in the art and will not be discussed further.
. ;~ '' ';' ~', ~'''' ' ;'~ ~'''', ' ',' : : .:.:
.. ~" ., ,:
. :.. ::~,.,:
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Claims (12)
1. A directional antenna for use with apparatus for transmission or reception of radio waves in a rotary winged aircraft (100) having a body (102) provided with rotor blades (101), the antenna comprising:
three or more electrically non-conductive rotor blades (200), capable of being rotated with respect to the body (102) of the rotary winged aircraft (100) around an axis perpendicular to said blades;
two first electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200) and being in contact therewith;
one or more second electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200), said second electrical conductors not being electrically connected to said first electrical conductors;
means (700) for providing a connection from the plurality of first electrical conductors (210) to the apparatus for transmission or reception of radio waves;
means (721, 722, 741, 742) for dynamically selecting the first electrical conductors (210) from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body (102) of the rotary winged aircraft (100) than others of said conductors, and for dynamically selecting the others of said conductors as second electrical conductors.
three or more electrically non-conductive rotor blades (200), capable of being rotated with respect to the body (102) of the rotary winged aircraft (100) around an axis perpendicular to said blades;
two first electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200) and being in contact therewith;
one or more second electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200), said second electrical conductors not being electrically connected to said first electrical conductors;
means (700) for providing a connection from the plurality of first electrical conductors (210) to the apparatus for transmission or reception of radio waves;
means (721, 722, 741, 742) for dynamically selecting the first electrical conductors (210) from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body (102) of the rotary winged aircraft (100) than others of said conductors, and for dynamically selecting the others of said conductors as second electrical conductors.
2. A directional antenna as claimed in claim 1 wherein said second electrical conductors (210) are electrically connected to the body (102) of said rotary winged aircraft (100).
3. A directional antenna as claimed in claim 1 wherein one or more of said second electrical conductors (210) are provided with a signal that is out of phase with the signal provided to said first electrical conductors (210).
4. A directional antenna as claimed in claim 3 wherein one or more of said second electrical conductors (210) not provided with an out of phase signal are electrically connected to the body (102) of said rotary winged aircraft (100).
5. A directional antenna as claimed in claims 1 to 3 wherein the connection means comprises slip rings (721, 722) and contact brushes (741, 742).
6. A directional antenna as claimed in claims 1 to 3 wherein the means for dynamically selecting conductors (210) as first conductors or as second conductors comprises slip rings (721, 722) and contact brushes (741, 742).
7. A directional antenna as claimed in claims 1 to 3 wherein the means for dynamically selecting conductors (210) as first conductors or as second conductors comprises electrical diodes and means for controlling the direct current biasing of the electrical diodes.
8. A directional antenna as claimed in claim 1 further comprising a control means (752) for maintaining said first predetermined angular position with respect to a known geographic point.
9. A directional antenna as claimed in claim 8 wherein said control means (752) comprises a stepping motor.
10. A directional antenna as claimed in claims 1 to 3 further comprising means for maintaining said first predetermined angular position constant with respect to aremote apparatus for transmitting or receiving radio waves
11. A directional antenna as claimed in claims 1 to 3 wherein:
the length of each electrical conductor (210) is substantially similar to that of the rotor blade (200); and the radio waves transmitted or received have wavelengths in the range from 10 metres to 150 metres.
the length of each electrical conductor (210) is substantially similar to that of the rotor blade (200); and the radio waves transmitted or received have wavelengths in the range from 10 metres to 150 metres.
12. A communications system for transmission and reception of radio waves in a rotary winged aircraft (100) having a body (102) provided with rotor blades (101) the system comprising:
apparatus for transmission or reception of radio waves;
three or more electrically non-conductive rotor blades (200), capable of being rotated with respect to the body (102) of the rotary winged aircraft (100) around an axis perpendicular to said blades;
two first electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200) and being in contact therewith;
one or more second electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200), said second electrical conductors not being electrically connected to said first electrical conductors;
means (700) for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; and means (721, 722, 741, 742) for dynamically selecting the first electrical conductors (210) from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body (102) of the rotary winged aircraft (100) than others of said conductors, and for dynamically selecting the others of said conductors as second electrical conductors.
apparatus for transmission or reception of radio waves;
three or more electrically non-conductive rotor blades (200), capable of being rotated with respect to the body (102) of the rotary winged aircraft (100) around an axis perpendicular to said blades;
two first electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200) and being in contact therewith;
one or more second electrical conductors (210), each conductor being positioned parallel to the major axis of a respective rotor blade (200), said second electrical conductors not being electrically connected to said first electrical conductors;
means (700) for providing a connection from the plurality of first electrical conductors to the apparatus for transmission or reception of radio waves; and means (721, 722, 741, 742) for dynamically selecting the first electrical conductors (210) from all of the electrical conductors as those having an angular position nearer to a first predetermined angular position relative to the body (102) of the rotary winged aircraft (100) than others of said conductors, and for dynamically selecting the others of said conductors as second electrical conductors.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9223580.3 | 1992-11-11 | ||
| GB9223580A GB2272576A (en) | 1992-11-11 | 1992-11-11 | Directional HF antenna for a helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2101903A1 CA2101903A1 (en) | 1994-05-12 |
| CA2101903C true CA2101903C (en) | 1997-09-16 |
Family
ID=10724871
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA 2101903 Expired - Lifetime CA2101903C (en) | 1992-11-11 | 1993-08-04 | Directional hf antenna for a helicopter |
Country Status (2)
| Country | Link |
|---|---|
| CA (1) | CA2101903C (en) |
| GB (1) | GB2272576A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10439293B2 (en) | 2017-03-20 | 2019-10-08 | Lockheed Martin Corporation | Antenna systems using aircraft propellers |
-
1992
- 1992-11-11 GB GB9223580A patent/GB2272576A/en not_active Withdrawn
-
1993
- 1993-08-04 CA CA 2101903 patent/CA2101903C/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| CA2101903A1 (en) | 1994-05-12 |
| GB2272576A (en) | 1994-05-18 |
| GB9223580D0 (en) | 1993-03-10 |
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