Patent Description:
Sensitive technical components of aircrafts which may be exposed to environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions, must be protected against such environmental conditions when the aircrafts are parked on ground for a predetermined period of time or when they are transported from respective final assembly lines to customer centers. This may be achieved by mounting ground support equipment modules of a given ground support equipment system to the sensitive technical components. The ground support equipment modules may comprise blanks and/or covers that are e. mounted to pitot sensors, environmental control system air intakes, starter generator and air-cooled oil cooler air inlets, engine air intakes, exhaust ejectors, and/or drive shaft flanges.

By way of example, the document <CIT> describes an engine cover adaptable to fit over an aircraft engine to protect it from salt spray, ice, and water encountered on aircraft carriers. The engine cover is formed as a sectional cover of fabric combined with a brace which may be quickly and removably attached to a given engine propeller blade.

The document <CIT> describes an engine heating cover system. The system comprises a cover for an airplane engine, which can be applied to a warm engine of a plane when it returns to a station to keep the engine thereof warm, or can be applied to a cold engine to warm it up, and then keep it warm and ready for instant use. The cover can be rapidly and easily applied to an engine, can be easily adjusted to the specific engine, and can be very quickly removed.

However, in general respective ground support equipment modules must be removed from associated sensitive technical components prior to ground run and/or flight operation of an aircraft in order to avoid damages to the sensitive technical components or even an accident of the aircraft. Nevertheless, some particular ground support equipment modules may e. not be visible to a pilot of the aircraft during a pre-flight check performed by the pilot. For instance, such particular ground support equipment modules may be installed inside respective engine compartments and/or behind respective inlet barrier filters of the engines of the aircraft. Unfortunately, if not removed prior to ground run and/or flight operation of the aircraft, these particular ground support equipment modules may cause incidents such as overheating and loss of the engines.

In order to avoid any even involuntary overlooking of ground support equipment modules which are mounted to sensitive technical components of an aircraft, the ground support equipment modules may be provided with some visible alerting means, such as colored flags. However, in particular cases the pilot may not see such colored flags and, thus, not notice that respective ground support equipment modules are mounted to associated sensitive technical components. For instance, if it is raining on a helicopter during a pre-flight check performed by the pilot, respective colored flags of bleed valve covers may stick to the top of the helicopter's engine cowlings such that they are not visible to the pilot from ground.

Other visible alerting means are e. described in the document <CIT> which illustrates a tether assembly for use on a parked aircraft. The tether assembly interconnects pitot tube covers with a respective landing gear lock pin thereby assuring removal of both the covers and the lock pin as part of the aircraft pre-flight check list.

The document <CIT> describes cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, an engine cover assembly, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The second sensor component is attached to the engine cover and is configured to interact with the first sensor component. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

The document <CIT> describes an aircraft undercarriage safety pin and pitot tube sleeves detection device. The detection device comprises a detection box independent of an airplane, wherein a first sensor for sensing the movement of the airplane and slots are arranged on the detection box. The number of the slots is consistent with the number of safety pins and pitot tube sleeves of an undercarriage of each airplane. A second sensor for sensing whether the safety pins and pitot tube sleeves exist in the slots and an alarm are arranged in the detection box. When the aircraft removed, first sensor can detect whether the aircraft will take off promptly, and the second sensor can detect whether safety pin and pitot tube sleeves are retrieved to the detection case and sends alarm.

Furthermore, the document <CIT> describes an indicating marker and a method of use for removably attaching the indicating marker to an aircraft comprising an opening. The indicating marker comprises a cover device configured to removably seal the opening of the aircraft to prevent foreign contaminants from entering and getting inside the opening. At least one light is attached to the cover device. A power source is electrically connectable to the at least one light to emit a visible light from the at least one light and illuminate the cover device. Alternatively, a wireless signal emitter may be attached to the cover device and configured to receive a signal from a wireless signal receiver separate from the aircraft and transmit a wireless response signal to the wireless signal receiver. In one example, both a light and a wireless signal emitter are attached to the cover device.

Still other visible alerting means are known from completely different technical domains. For instance, it is known to provide brake disc lockers of motorbikes with so-called reminder cables.

Based on the limitations and drawbacks of the prior art, an object of the present invention is to provide a new ground support equipment system which comprises a plurality of ground support equipment modules mountable to associated aircraft components of an aircraft parked on ground, wherein respectively mounted ground support equipment modules may securely and reliably be noticed by a pilot of the aircraft during pre-flight check. It is a further object of the present invention to provide an aircraft configured for use with such a ground support equipment system, as well as a method of mounting such a ground support equipment system to an aircraft parked on ground.

This object is solved by a ground support equipment system for use on an aircraft, said ground support equipment system comprising the features of claim <NUM>. More specifically, a ground support equipment system for use on an aircraft is provided, comprising a plurality of ground support equipment modules, at least one common interconnection device, and a plurality of connecting means. The plurality of ground support equipment modules is mountable to associated aircraft components of an aircraft parked on ground for protecting the associated aircraft components from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions. The at least one common interconnection device is for rendering mounting of the plurality of ground support equipment modules to the associated aircraft components discernible for a pilot of the aircraft The plurality of connecting means connects the plurality of ground support equipment modules to the at least one common interconnection device, wherein the plurality of connecting means comprises at least one physical wire, and wherein the at least one common interconnection device comprises a suitable wire fixation that is adapted for being provided at a door handle of a cockpit access door of the aircraft for attaching the at least one physical wire.

Advantageously, by connecting the plurality of ground support equipment modules to the at least one common interconnection device, mounting of the plurality of ground support equipment modules to the associated aircraft components may securely and reliably be rendered discernible for a pilot of the aircraft, in particular during a pre-flight check of the pilot. Accordingly, ground support equipment modules which are still mounted on the aircraft during the pre-flight check of the pilot may easily and comfortably be detected. Thus, the pilots may initiate removal of such ground support equipment modules at the latest during pre-flight check such that incidents due to mounted ground support equipment modules which are not removed during such a pre-flight check of the pilot may beneficially be avoided.

For instance, all ground support equipment modules may be linked by associated physical wires or wireless connections to an analogue or digital component that is located at a position on the aircraft or close to the aircraft that may not be overlooked by the pilot in pre-flight check. Thus, the associated physical wires or wireless connections form the plurality of connecting means. Accordingly, it allows to render all ground support equipment modules which must be removed before engine start and/or take off more easily discernible. This simplifies and accelerates pre-flight check and reduces respective pilot tasks prior to ground run or flight operation.

Advantageously, following human factors analysis other cognitive senses, such as acoustic, touch, etc., and not only visual discernibility, may be considered when alerting the pilot. Thus, human failure risks may be reduced significantly.

If physical wires form the plurality of connecting means, they may e. be linked to an aircraft command, such as a door handle or, in a rotary wing aircraft, a cyclic pilots command. Furthermore, or instead, an adapter/box may enable connection of several physical wires. Thus, at least all physical wires with a "Remove before Flight" status are immediately visible in a single adapter/box to the pilots before they start ground run or flight operation of the aircraft. By way of example, a snap lock concept may be used to quickly fix or remove a connected physical wire from the adapter/box.

Moreover, the adapter/box may be equipped with an electrical detection system that is configured to provide information concerning the status of connected ground support equipment modules. Thus, the pilot may securely and reliably be informed if respective ground support equipment modules are still mounted on the aircraft and should be removed prior to ground run or flight operation, e. by means of suitable visible or acoustic alerts.

The adapter/box may be connected via a cable or by means of a wireless link to associated pilot controls. For instance, the adapter/box may be connected via a wireless link to the multi-function display panel of the pilot.

If wireless connections form the plurality of connecting means, each ground support equipment module of the plurality of ground support equipment modules may e. be provided with an associated radio frequency identification (RFID) module, such as a RFID chip. Each such RFID chip may be detectable by means of an associated RFID module detection antenna. The latter may be connected to an aircraft control system that may be configured such that e. a start of the engine(s) is prevented as long as the RFID module detection antenna still detects RFID chips.

Moreover, collected information on the respectively detected RFID chips may alternatively, or in addition, be monitored remotely. This enables big data management of a respective aircraft fleet of one or more customers.

Advantageously, all ground support equipment modules which are equipped with RFID chips may be stored in a storage pocket onboard the aircraft, e. in a respective cargo area of the aircraft, during ground run and/or flight operation. Preferably, the storage pocket comprises radio frequency isolated surfaces such that the RFID chips stored in the storage pocket may not be detected by the RFID module detection antenna. More specifically, the storage pocket may be made of one or more aluminium foils inside, e. based on credit card technology.

According to some aspects, the at least one common interconnection device comprises a collector box to which the plurality of connecting means is attachable.

Preferably, the plurality of connecting means is attachable to the collector box via a plurality of associated snap lock connections.

According to some aspects, the at least one physical wire is a cable or cord.

Preferably, the collector box is connectable to a pilot alerting system of the aircraft parked on ground, in particular to a multi-function display panel, for indicating to a pilot of the aircraft whether one or more connecting means of the plurality of connecting means are attached to the collector box.

Preferably, the collector box is connectable via a wireless signal to the pilot alerting system of the aircraft parked on ground.

According to some aspects, the plurality of connecting means comprises a plurality of wireless connectors.

Preferably, the plurality of wireless connectors comprises a plurality of radio frequency identification modules.

According to some aspects, the ground support equipment system further comprises a storage pocket that is provided for storage of the plurality of ground support equipment modules and the plurality of connecting means onboard an aircraft, in particular during flight operation, wherein the storage pocket comprises radio frequency isolated surfaces.

The present invention further relates to an aircraft comprising a ground support equipment system as described above, wherein the plurality of connecting means comprise a plurality of radio frequency identification modules; wherein the aircraft comprises a detection antenna that is configured for detecting presence of the plurality of radio frequency identification modules.

Preferably, the detection antenna is linked to an aircraft control system configured to prevent engine start of the aircraft upon detection of presence of one or more of the plurality of radio frequency identification modules.

Preferably, the aircraft further comprises a storage pocket that is provided for storage of the plurality of ground support equipment modules and the plurality of connecting means onboard an aircraft, in particular during flight operation, wherein the storage pocket comprises radio frequency isolated surfaces.

The present invention further relates to a method of mounting a ground support equipment system as described above to an aircraft parked on ground. The method comprises mounting a plurality of ground support equipment modules to associated aircraft components of the aircraft for protecting the associated aircraft components from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions; and connecting a plurality of connecting means that is connected to the plurality of ground support equipment modules to at least one common interconnection device for rendering mounting of the plurality of ground support equipment modules to the associated aircraft components discernible for a pilot of the aircraft wherein the connecting of the plurality of connecting means (<NUM>) comprises connecting at least one physical wire (<NUM>, <NUM>, <NUM>, <NUM>) to a suitable wire fixation (<NUM>) of the at least one common interconnection device (<NUM>) that is adapted for being provided at a door handle (<NUM>) of a cockpit access door (<NUM>) of the aircraft.

Preferred embodiments are outlined by way of example in the following description with reference to the attached drawings.

<FIG> shows an illustrative aircraft <NUM>. By way of example, the aircraft <NUM> is embodied as a rotary wing aircraft and, more particularly, as a helicopter. Thus, for purposes of simplicity and clarity, the aircraft <NUM> is hereinafter referred to as the "helicopter <NUM>". However, the present invention is likewise applicable to other types of aircrafts, such as airplanes, multicopters, and so on, and may even be used in spacecrafts.

The helicopter <NUM> comprises preferably at least one main rotor <NUM> with a rotor shaft <NUM>. By way of example, the at least one main rotor <NUM> is embodied as a multi-blade rotor system, for providing lift and forward or backward thrust during operation. Accordingly, the at least one main rotor <NUM> comprises a plurality of rotor blades <NUM>, <NUM> which are e. mounted at an associated rotor head <NUM> to the rotor shaft <NUM>. The at least one main rotor <NUM> is preferably powered by at least one engine <NUM>.

Illustratively, the helicopter <NUM> has a fuselage <NUM> that forms an airframe of the helicopter <NUM>. The fuselage <NUM> may be connected to a suitable landing gear <NUM> and forms, by way of example, a cabin <NUM> and a rear fuselage <NUM>. The rear fuselage <NUM> is illustratively connected to a tail boom <NUM>. The landing gear <NUM> is illustratively embodied as a wheel-type landing gear.

By way of example, the helicopter <NUM> includes at least one counter-torque device <NUM> configured to provide counter-torque during operation, i.e. to counter the torque created by rotation of the at least one main rotor <NUM> for purposes of balancing the helicopter <NUM> in terms of yaw. If desired, counter-torque device <NUM> may be shrouded as shown.

The at least one counter-torque device <NUM> is illustratively provided at an aft section of the tail boom <NUM> and comprises a tail rotor <NUM>, which may also be powered by the at least one engine <NUM>. The aft section of the tail boom <NUM> further comprises a fin <NUM>. Moreover, the tail boom <NUM> of the helicopter <NUM> is also provided with a suitable horizontal stabilizer <NUM>.

Illustratively, the helicopter <NUM> is parked on ground <NUM>. However, when being parked on ground <NUM> as illustrated, specific aircraft components of the helicopter <NUM> are preferably protected by means of a suitable ground support equipment system <NUM>. According to one aspect, the ground support equipment system <NUM> may be stored in a storage pocket <NUM> onboard the helicopter <NUM>, in particular during flight operation, wherein the storage pocket <NUM> preferentially comprises radio frequency isolated surfaces.

Preferably, the ground support equipment system <NUM> comprises a plurality of ground support equipment modules mountable to associated aircraft components of the helicopter <NUM> parked on ground <NUM> for protecting the associated aircraft components from environmental conditions, in particular rain, wind (up to <NUM> KT), snow, frost, sand, and/or salt conditions, but even from exhaustive solar irradiation (UV radiation). Illustrative ground support equipment modules are - in <FIG> - only shown by schematically indicating associated mounting positions on the helicopter <NUM>, but without illustrating the ground support equipment modules as such in greater detail, as they are well-known to the person skilled in the art.

By way of example, the plurality of ground support equipment modules comprises one or more pitot sensors covers <NUM>, one or more environmental control system air intake covers <NUM>, <NUM>, <NUM>, one or more starter generator and air-cooled oil cooler air inlet blanking caps <NUM>, one or more drive shaft flange protections <NUM>, as well as one or more engine blanks and covers <NUM>. Each one of these ground support equipment modules is preferably designed so as to require handling by not more than two operators. Moreover, they are preferably easy set-up, especially if the operator is equipped with thick gloves, e. due to winter condition.

Furthermore, an underlying weight of these ground support equipment modules preferably complies with currently applicable ergonomic standards and associated attachment means preferentially include suitable protections. Moreover, these ground support equipment modules are preferably compatible with the fully equipped helicopter <NUM> and they are water proof facing natural water runoff. More particularly, these ground support equipment modules are preferably designed in order to avoid any hazardous object to enter into a respectively protected area and to avoid any damage on associated interface parts, such that the latter do not endure premature wear, such as scratches, markings, deformation, and so on.

<FIG> shows the helicopter <NUM> of <FIG>, which is parked on ground <NUM> and provided with the ground support equipment system <NUM>. However, for simplicity and clarity of the drawing only two ground support equipment modules of the plurality of ground support equipment modules of the ground support equipment system <NUM> are, by way of example, separately labelled with the reference signs <NUM>, <NUM>.

More specifically, the ground support equipment modules <NUM>, <NUM> comprise one or more engine air intake blanks <NUM>, and one or more exhaust ejector covers <NUM>. The one or more engine air intake blanks <NUM> and the one or more exhaust ejector covers <NUM> are associated with the engine blanks and covers <NUM> of <FIG>. By way of example, one engine air intake blank <NUM> is provided for protecting an associated engine air intake <NUM> from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions, and one exhaust ejector cover <NUM> is provided for protecting an associated exhaust ejector <NUM> from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions.

Illustratively, the plurality of ground support equipment modules is connected via a plurality of connecting means <NUM> to at least one common interconnection device for rendering mounting of the plurality of ground support equipment modules discernible, in particular for a pilot of the helicopter <NUM>. By way of example, the engine air intake blank <NUM> is provided with a connecting means <NUM> and the exhaust ejector cover <NUM> is provided with a connecting means <NUM>. The connecting means <NUM>, <NUM> of the plurality of connecting means <NUM> may e. be embodied as physical wires, such as cables or cords.

The connecting means <NUM>, <NUM> of the plurality of connecting means <NUM> may e. be attached to a door handle <NUM> of a cockpit access door <NUM> of the helicopter <NUM>. In this case the door handle <NUM> forms the common interconnection device. However, other common interconnection devices may likewise be used. For instance, the connecting means <NUM>, <NUM> may e. be attached to an aircraft command of the helicopter <NUM>, in particular to a pilot command, and so on.

Furthermore, two or more common interconnection devices may be used to prevent overcharging of a single common interconnection device. Thus, the connecting means <NUM> may e. be attached to the door handle <NUM>, whereas the connecting means <NUM> is attached to a pilot command, and so on. Nevertheless, use of a single common interconnection device is preferred.

From the above described configuration, a method of mounting the ground support equipment system <NUM> to the helicopter <NUM> parked on ground <NUM> may be derived. This method preferably comprises at least the steps of: mounting the plurality of ground support equipment modules, e. the ground support equipment modules <NUM>, <NUM>, to associated aircraft components, e. the engine air intake <NUM> and the exhaust ejector <NUM>, of the helicopter <NUM> for protecting the associated aircraft components from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions; and connecting the plurality of connecting means <NUM> that is connected to the plurality of ground support equipment modules to the at least one common interconnection device, e. the door handle <NUM>, for rendering mounting of the plurality of ground support equipment modules to the associated aircraft components discernible for a pilot of the helicopter <NUM>.

<FIG> shows a section of the helicopter <NUM> of <FIG> parked on ground <NUM>, for further illustrating the engine air intake blank <NUM> that is provided for protecting the associated engine air intake <NUM> from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions. The engine air intake blank <NUM> is shown in greater detail representative for all ground support equipment modules of the ground support equipment system <NUM> of <FIG>, which is otherwise not further illustrated, for simplicity and clarity of the drawing.

As described above at <FIG>, the engine air intake blank <NUM> is connected via the connecting means <NUM> of the plurality of connecting means <NUM> to the door handle <NUM> of the cockpit access door <NUM> of the helicopter <NUM>. In order to simplify attachment of the connecting means <NUM>, which is illustratively embodied as a physical wire in the form of a cable, to the door handle <NUM>, a suitable wire fixation <NUM> may be provided at the door handle <NUM>.

<FIG> shows a section of the helicopter <NUM> of <FIG> parked on ground <NUM>, with the plurality of connecting means <NUM>, for illustrating interconnection of the plurality of connecting means <NUM> via a collector box <NUM> that, in contrast to <FIG>, now forms the common interconnection device. By way of example, the plurality of connecting means <NUM> comprises the connecting means <NUM>, <NUM> of <FIG>, and two additional connecting means <NUM>, <NUM>.

Illustratively, all connecting means <NUM>, <NUM>, <NUM>, <NUM> are embodied as physical wires in the form of cables and connected to associated ground support equipment modules of the plurality of ground support equipment modules of the ground support equipment system <NUM> of <FIG>. However, for simplicity and clarity of the drawing these ground support equipment modules are not further illustrated in <FIG> and reference is made to <FIG>.

The plurality of connection means <NUM> may be attachable to the collector box <NUM> via a plurality of associated snap lock connections <NUM>. More specifically, each one of the connecting means <NUM>, <NUM>, <NUM>, <NUM> is preferably attachable to the collector box <NUM> via a separate snap lock connection. By way of example, and representative for all connecting means <NUM>, <NUM>, <NUM>, <NUM>, the connecting means <NUM> is attached to the collector box <NUM> via an associated snap lock connection <NUM>.

<FIG> shows the section of the helicopter <NUM> parked on ground <NUM> according to <FIG>, with the plurality of connecting means <NUM> that comprises the illustrative connecting means <NUM>, <NUM>, <NUM>, <NUM> which are interconnected via the collector box <NUM>. In contrast to <FIG>, the collector box <NUM> is now connectable to a pilot alerting system of the helicopter <NUM> parked on ground <NUM>, e. to a multi-function display panel, for indicating to a pilot of the helicopter <NUM> whether one or more connecting means <NUM>, <NUM>, <NUM>, <NUM> of the plurality of connecting means <NUM> are attached to the collector box <NUM>. For instance, the collector box <NUM> may be connectable via a wireless signal <NUM> to the pilot alerting system. The wireless signal <NUM> may illustratively be emitted via a suitable communication device <NUM>.

<FIG> shows a section of the helicopter <NUM> of <FIG> parked on ground <NUM>. However, in contrast to <FIG> the plurality of connecting means <NUM> of <FIG> is now embodied by a plurality of wireless connectors <NUM> instead of the physical wires. The plurality of wireless connectors <NUM> may e. comprise, or be embodied as, a plurality of radio frequency identification (RFID) modules.

By way of example, the plurality of RIFD modules <NUM> comprises a RFID module <NUM> that is associated with, and mounted to, the engine air intake blank <NUM> of <FIG>. The engine air intake blank <NUM> and the RFID module <NUM> are shown representative for all ground support equipment modules which are provided with RFID modules, for simplicity and clarity of the drawing.

Illustratively, the helicopter <NUM> comprises a detection antenna <NUM> that is configured for detecting presence of the plurality of RFID modules <NUM>. For instance, the detection antenna <NUM> may detect presence of the plurality of RFID modules <NUM> through receipt of associated RFID signals <NUM> emitted from the plurality of RFID modules <NUM>.

Preferably, the detection antenna <NUM> is linked to an aircraft control system of the helicopter <NUM>. The aircraft control system may be configured to prevent engine start of the helicopter <NUM> upon detection of presence of one or more of the plurality of RFID modules <NUM>. In other words, as long as the aircraft control system detects RFID modules of the plurality of RFID modules <NUM>, it may be assumed that associated ground support equipment modules of the plurality of ground support equipment modules of the ground support equipment system <NUM> of <FIG> are mounted to the helicopter <NUM> and that engine start should, therefore, be prevented.

Claim 1:
A ground support equipment system (<NUM>) for use on an aircraft (<NUM>), comprising:
a plurality of ground support equipment modules (<NUM>, <NUM>) mountable to associated aircraft components (<NUM>, <NUM>) of an aircraft (<NUM>) parked on ground (<NUM>) for protecting the associated aircraft components (<NUM>, <NUM>) from environmental conditions, in particular rain, wind, snow, frost, sand, and/or salt conditions;
at least one common interconnection device (<NUM>) for rendering mounting of the plurality of ground support equipment modules (<NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>) to the associated aircraft components (<NUM>, <NUM>) discernible for a pilot of the aircraft (<NUM>); and
a plurality of connecting means (<NUM>) that connects the plurality of ground support equipment modules (<NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>, <NUM>) to the at least one common interconnection device (<NUM>), characterized in that the plurality of connecting means (<NUM>) comprises at least one physical wire (<NUM>, <NUM>, <NUM>, <NUM>), and wherein the at least one common interconnection device (<NUM>) comprises a suitable wire fixation (<NUM>) that is adapted for being provided at a door handle (<NUM>) of a cockpit access door (<NUM>) of the aircraft (<NUM>) for attaching the at least one physical wire (<NUM>, <NUM>, <NUM>, <NUM>).