Patent Abstract:
The invention relates to a device for maneuvering, on the ground, a door of an aircraft landing gear, the door being linked with door maneuvering means and uplock means for locking the door when it reaches the closed position, at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means  17  which can be operated by an operator on the ground in order to control at least:
       an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means,   a closing sequence during which the maneuvering means are actuated in order to close the door again.

Full Description:
the invention relates to a device for manoeuvring, on the ground, a door of an aircraft landing gear. 
     BACKGROUND TO THE INVENTION 
     The majority of modern aircraft are provided with retractable landing gear, with compartments for receiving this landing gear when the aircraft is in flight, and doors for closing these compartments. The doors are opened and closed using actuators for manoeuvring the doors, for example cylinders. 
     When the door reaches the closed position, it is automatically locked in this position by uplock means, for example an uplock box on which is hinged a hook which imprisons a roller fixed on the door. The hook is unhooked using an actuator, which is most often hydromechanical or electromechanical. Frequently, the uplock box includes an emergency actuator which can unlock the hook, if the main actuator can no longer be used. 
     In flight, the unhooking of this hook and the opening and closing of this door are controlled during the sequences for extending and retracting the landing gear. It should be noted that the doors are closed again and hooked when the landing gear is unfolded. 
     When the aircraft is on the ground, it is necessary to be able to open the doors, particularly to access the equipment located on the upper part of the landing gear or in the landing gear compartment. To this end, the majority of aircraft include control means that can be operated by the ground staff, for deactivating the uplock means such as to free the doors. 
     As the power required for these operations, which is generally hydraulic or electric, is not available on the ground, particularly when the engines have stopped, the aircraft includes mechanical control means arranged to deactivate the uplock means when the aircraft is on the ground. These mechanical control means generally comprise a handle connected to the uplock boxes via a linkage. 
     These mechanical control means are particularly heavy, bulky and therefore expensive for the aircraft manufacturer. 
     SUBJECT MATTER OF THE INVENTION 
     The subject matter of the invention is a device for manoeuvring, on the ground, a door of a landing gear, for reducing the weight of the existing devices without making this manoeuvre less safe. 
     BRIEF DESCRIPTION OF THE INVENTION 
     With a view to achieving this aim, a device is proposed for manoeuvring, on the ground, a door of an aircraft landing gear, the door being linked with door manoeuvring means and uplock means for locking the door when it reaches the closed position, the uplock means comprising at least one unlocking electromechanical actuator arranged to act upon the uplock means with a view to deactivating them during opening of the door in flight. According to the invention, the device comprises control means which can be operated by an operator on the ground in order to control at least:
         an opening sequence during which the unlocking electromechanical actuator is actuated in order to deactivate the uplock means,   a closing sequence during which the manoeuvring means are actuated in order to close the door again.       

     The deactivation, on the ground, of the uplock means through the control of an electromechanical actuator already fitted to the uplock box enables mechanical elements of the control mechanical means to be replaced with electrical elements, contributing to a large saving in weight. 
     According to a particular embodiment of the invention, the opening device comprises at least two control members arranged such that they must both be actuated to enable control of the unlocking actuator or control of the manoeuvring means. 
     Therefore, manoeuvring the door cannot be controlled inadvertently through the action of an operator on the ground or any other external cause. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The invention will be better understood in the light of the following description with reference to the figures of the appended drawings wherein: 
         FIG. 1  is a schematic front view of an aircraft compartment with the door thereof and the landing gear thereof in the unfolded position, 
         FIG. 2  schematically illustrates an uplock box provided with two actuators, including one electromechanical actuator, 
         FIG. 3  is a process diagram illustrating the interactions between various elements of the manoeuvring device according to a particular embodiment of the invention, 
         FIG. 4  illustrates the control means for the manoeuvring device of  FIG. 3 . 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     The aircraft  1  shown in  FIG. 1  comprises a landing gear  2  hinged on the structure between an unfolded position illustrated here and a retracted position wherein the landing gear is received in a compartment  4  that can be closed by a door  3 . A cylinder  5  connected to the door  3  enables the latter to be manoeuvred. An uplock box  6  provided with a hook  7  enables a knob  10  which is rigidly connected with the door  3  to be hooked when the door  3  reaches the closed position. To control the manoeuvring of the door  3  and the unhooking of the hook  7 , the aircraft is provided with control means  17  that can be accessed by opening a panel  15 . 
       FIG. 2  illustrates an uplock box  6 , known per se, the hook  7  being shown in the locked position, imprisoning the knob  10  of the door  3 . The hook  7  is mounted in a pivoting manner about an axis X 1  and is held in the hooked position by a lock  30  which is also pivoted about an axis X 2  which is parallel with the axis X 1  and comprises a roller  31  engaging a surface of the hook  7  to hold the latter in the hooked position. Springs  37  and  38  return the lock  30  into the locked position and the hook  7  into the unhooked position respectively. Unhooking the hook  7  is controlled, in flight, by a main actuator  39  or by an emergency actuator  40 , the two actuators acting on the lock  30  to make it pivot such that the lock  30  frees the hook  7 . In this case, the emergency actuator  40  is electromechanical. 
     The diagram shown in  FIG. 3  illustrates the operating principle of a device for opening, on the ground, a door according to a first particular embodiment of the invention. The device includes a control board  17  which can be accessed on the ground by an operator after opening a panel for accessing the control board. The control board  17  includes a certain number of control members (which will be described below) to send commands to a control box  18  which is arranged to control an electrohydraulic solenoid valve connected to the door cylinder  5  and to control the emergency electromechanical actuator  40  of the uplock box. Therefore, it is possible to control at least two sequences:
         an opening sequence during which the emergency electromechanical actuator  40  is actuated in order to free the knob of the door. The solenoid valve  16  is then activated such that the two chambers of the door cylinder  5  are connected, the resulting force opening the door  3  following the door  3  being freed,   a closing sequence during which the solenoid valve  16  is actuated such that the door cylinder  5  closes the door again. The latter is then automatically hooked when the door reaches the closed position.       

     The control board  17  is illustrated in greater detail in  FIG. 4 . It comprises:
         four push-buttons  24 ,  25 ,  26 ,  27 , called “ENABLE”, “OPEN”, “CLOSE”, “FLIGHT” respectively,   indicator lights  28 ,  29 ,  32 , called “HYD PWD OK”, “ELEC PWD OK”, “RESET” respectively,   a switch  33  for activating or deactivating the push-buttons,   an electrical input  34  for connecting an external power source,   a push-to-test button  36  for checking, via a pressing action, that the control board  17  operates correctly,   a state indicator  35 .       

     In the door opening device of the present invention, the control board  17  is located in the space  8  closed by the access panel  15 . Door opening control requires pressing of the “ENABLE” push-button  24  then of the “OPEN” push-button  25 , which causes the transmission of an electrical order to the control box  18 , which then implements the opening sequence. 
     Door closing control requires pressing of the “ENABLE” push-button  24 , then of the “CLOSE” push-button  26 , which causes the transmission of an electric order to the electronic box  18  which then implements the closing sequence. 
     A third sequence called, in this case, an isolation sequence is carried out in the door manoeuvring device; it is controlled by pressing on the “ENABLE” push-button  24 , then on the “FLIGHT” push-button  27 , and causes electrical isolation between the control board  17  and the rest of the aircraft electrical circuit, for ensuring that no manoeuvre of the door  3  will be triggered in an untimely manner. 
     The control box  18  can be a box dedicated to controlling the device for manoeuvring the doors on the ground of the invention, or on the contrary, be used simultaneously by another device, for example an in-flight door and/or landing gear manoeuvring device. Therefore, the operations carried out by the control box linked with the ground door manoeuvring device of the present invention are carried out without addition of equipment. 
     Pressing on the “ENABLE” push-button  24  also enables “HYD PWD OK”, “ELEC PWD OK” indicator lights to be activated, which enable the operator to check the availability of the hydraulic and electric power, respectively, which are necessary for the device to operate well. 
     According to one advantageous aspect of the invention, the electrical consumption of the device is zero except during the progression of the controlled sequences: therefore, the door  3  can be held in the open position when the aircraft is on the ground without the device consuming power. 
     The control board  17  comprises an electrical input  34  for connecting an external power source to the control means, for example an external battery. External power source supply is used particularly when means of electrical supply coming from the aircraft are not available. The control means also comprise a “GDO STATUS” state indicator  35  which indicates:
         either that the device is in use if the door is open or in the process of being opened or closed or if the control means are not electrically isolated (“IN USE” message)   or that the device is in a state corresponding to a configuration consistent with take-off for the control means, i.e. at the end of the so-called isolation sequence (“FLIGHT” message).       

     Preferably, the “GDO STATUS” indicator  35  is an indicator having two stable states, which only consumes power during the transition from one state to the other. 
     According to a particular aspect of the invention, the “GDO STATUS” indicator  35  is linked with a marker  45  (which can be seen in  FIG. 1 ) which can be moved between a retracted position wherein it enables the panel  15  for accessing the control board  17  to be closed and which corresponds to the “FLIGHT” position of the “GDO STATUS” indicator  35 , and a projecting position (shown here) wherein it prevents the panel  15  for accessing the control board  17  from being closed, which corresponds to the “IN USE” position of the “GDO STATUS” indicator  35 . Therefore, the pilot can check, during the pre-flight inspection, which state the device of the invention is in, and be warned by the panel  15  remaining open that the device of the invention has not been returned to the “FLIGHT” status. 
     According to another particular aspect of the invention, the control board  17  comprises a second push-to-test button  41 , for checking, via a pressing action, that additional equipment operates correctly. In particular, it is especially advantageous to be able to check on the ground the sound operation of a landing gear uplock box emergency electromechanical actuator unhooking a hook used to lock the landing gear in the retracted position, since aircraft do not generally comprise means for testing this emergency electromechanical actuator in flight. Therefore, pressing on the push-to-test button  41  enables the landing gear uplock box emergency electromechanical actuator to be actuated, wherein the unhooking of the hook can be checked visually from the ground by an operator who will have previously manually put the hook in the hooked position. 
     The invention is not limited to the particular embodiment which has just been described, but, indeed on the contrary, covers any alternative falling within the scope of the invention as defined by the claims. 
     Although control means have been described which require successive pressing on two different push-buttons, it is possible of course to apply to this device any type of control action on any type of control member in any type of control sequence which comprises at least two separate actions, such as to prevent an untimely actuation of one of the control members from causing unwanted opening or closing of the controlled door(s). 
     Furthermore, it is possible to not use a control box  18  between the control means  17  and the linked actuators, the control means  17  then directly controlling the electromechanical actuators. 
     Furthermore, although an actuator has been described for controlling a valve for feeding a hydromechanical actuator for activating the door, it is possible to directly control an electromechanical actuator in order to directly activate the door.

Technology Classification (CPC): 1