JP2000079898A - Helicopter - Google Patents

Abstract

PROBLEM TO BE SOLVED: To realize the safety flight by operating a flight control system by a hydraulic fluid filled in an accumulator over the whole flight control range, and confirming the secure operation of the flight control system. SOLUTION: An accumulator 1 is used as a hydraulic source in the pre-flight check. The accumulator 1 as the hydraulic source for pre-flight check is connected to a switching device 013 through an accumulator line 2. When an ordinary flight control system is operated, the discharged oil from a hydraulic pump 08 driven by an engine is fed to a hydraulic equipment 011 as the hydraulic fluid through a hydraulic feed pipe 012, the switching device 013 and the hydraulic feed pipe 012 to operate most of flight control devices such as a main flight control device by the flight control operation over the whole flight control range.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a main rotor and a tail rotor (hereinafter referred to as both a main rotor and a tail rotor) provided with an accumulator as a preflight check hydraulic power source for confirming operation of a control system performed before a flight to confirm flight safety. (The rotor is simply referred to as the rotor at the same time.) The oil discharged from the hydraulic pump directly driven by the engine that drives the rotor is not directly used as the working oil, but is used not only for the main control system but also for the helicopter necessary for helicopter flight. Most of the control system mounted on the vehicle is operated over the entire control system range of the control system by the hydraulic oil filled in the accumulator without starting the engine and operating the hydraulic pump, and the control system operates reliably. The present invention relates to a helicopter that ensures a safe flight.

[0002]

2. Description of the Related Art In order to make a helicopter fly safely,
As a pre-flight confirmation (inspection) item, “Airworthiness Examination Guidelines” (revised on April 17, 1995) edited by the Aircraft Safety Division of the Civil Aviation Bureau of the Ministry of Transport, “Airworthiness Examination Guidelines 4-3-1-3”
A method must be provided that allows all main control systems to operate over the entire maneuvering range before the flight, or that allows the pilot to determine that he has sufficient maneuvering capability before the flight. And a corresponding operation check of the control system of the helicopter before flight has been performed.

[0003] Specifically, the operation of the control system is confirmed by, after the engine is started, a state in which the rotor is rotated by the driving of the engine, and is directly connected to these rotors to be operated. One method is to operate the main control system over the entire control range while the pump discharge oil is loaded as hydraulic oil, and only confirm that the rotor head of the main control system moves as controlled. Has been conventionally adopted.

[0004] That is, as shown in FIG. 3, a conventional helicopter 01 has a main rotor 03 which needs to be changed in accordance with an azimuth angle accompanying rotation of a main rotor 03 having a blade root connected to a rotor head 02. One end of a pitch link for changing the pitch angle is connected to change the pitch angle, or to generate a propulsive force by the lift generated in the main rotor 03, and to tilt the rotating surface of the main rotor 03 in the flight direction, and the entirety of the pitch link from the horizontal plane The main rotor servo 05 for changing the angle of the swash plate 04, the main rotor 03 is rotated around the flapping axis to control the feathering angle, or the main rotor 03 is connected to the lead lug so that the swash plate 04 can change the angle. A hydraulic device such as a servo, which is not shown in the drawing, is rotated around an axis to control the lead angle. It is provided to Taheddo 02.

Further, with the rotation of the main rotor 03,
A tail rotor 06 is provided at the rear end of the helicopter 01 in order to generate a thrust for preventing the helicopter 01 from rotating by a reaction force generated in a direction opposite to the rotation direction of the main rotor 03. To adjust the thrust of the tail rotor 0 according to the magnitude of the reaction force.
Tail rotor servo 0 for changing the pitch angle of No. 6
7 is provided so as to constitute a hydraulic device of a main control system together with the above-mentioned hydraulic device provided on the rotor head 02.

In order to make such a helicopter 01 fly safely, it is necessary to check the operation before flight, especially by operating the above-mentioned hydraulic device of the main control system.
It is necessary to operate the auxiliary control system that operates the hydraulic device for driving the auxiliary device mounted on the helicopter 01 to check the operation of all the control systems including the main control system.

[0007] For this purpose, an engine (not shown) for rotating the rotor 03,06 to generate high-pressure hydraulic oil of 3000 psi to operate these hydraulic devices on the ground before flight. Hydraulic pump 0
8, it is necessary to operate each hydraulic device and perform a preflight check to ensure flight safety. In the figure, reference numeral 09 denotes a reservoir described later.

However, as in the above-described conventional operation check of the control system, the hydraulic equipment of the main control system is
When high-pressure discharge oil generated by the engine-driven hydraulic pump 08 is operated as hydraulic oil, the hydraulic pump 0
As described above, the output shaft of the engine that drives the motor 8 and the rotating shaft of the rotors 03 and 06 are directly connected by gears or the like, and therefore, between the output shaft and the rotating shaft, that is, in the middle of the driving force transmission mechanism. Unless a clutch or the like is provided, since the rotors 03 and 06 also rotate when the engine is started, it is difficult to closely check whether or not the main control system is operating according to the control operation. There was a problem that only a preflight check could be performed to confirm whether the swash plate 04 of the head 02 was deflected according to the steering operation.

That is, when the engine is started, the operating oil generated by the hydraulic pump 08 operated by driving the engine while the rotors 03 and 06 are rotating is used.
If the preflight check is performed, the control system can be operated, but the rotation of the main rotor 03 may cause the helicopter 01 to float or fall, and may approach the helicopter 01 to operate the control system. It is very dangerous to check that the control system for controlling the operating unit is operating in accordance with the control operation because the rotors 03 and 06, whose operation needs to be checked, operate simultaneously with the start of the engine. It is impossible to check whether the operation
Whether or not the control system operates as controlled can only be confirmed remotely, as described above, and a preflight check to ensure that all control systems, including the main control system, are operating correctly as controlled. Was very difficult.

Further, a clutch is provided in the middle of the driving force transmission mechanism, and by disengaging this clutch, the connection between the engine and the rotors 03, 06 is cut off, and the rotors 03, 0
It is conceivable to operate the control system over the entire operation range by operating the control system with the hydraulic oil discharged from the engine-driven hydraulic pump 08 without rotating the motor 6, and confirm the operation. The above-mentioned safety issues, or
Although the problem that the preflight check to check whether the control system for controlling the operating part is operating according to the control operation cannot be accurately performed is resolved, in this case, the driving force transmission mechanism is disengaged and disconnected. However, there is a problem that the cost is increased and the weight is increased in accordance with the installation of the clutch that performs the operation. Also, with the installation of the clutch,
There is also a disadvantage that the driving force transmission mechanism is complicated.

[0011] Further, it is generated by a system capable of confirming whether or not the main control system operates according to a control operation without starting the engine, that is, a hydraulic pump 08 driven by an engine directly connected to the rotors 03 and 06. A preflight check, which checks the operation of the main control system over the entire range without using hydraulic oil, has been conventionally performed.

That is, as shown in FIG. 4, instead of the above-described hydraulic oil discharged from the hydraulic pump 08 driven by the engine, the hydraulic oil generated by the additional equipment 010 is used for steering. Conventionally, a preflight check for confirming whether the main control system or the like can be operated according to the maneuvering operation without operating the rotors 03 and 06 without rotating the rotors 03 and 06 has been conventionally performed.

In the control system operation confirmation by this method, hydraulic oil from a hydraulic pump 08 operated by driving an engine (not shown) is supplied to a hydraulic device 0 for operating the control system.
A switching device 013 provided in the middle of the pressure oil supply pipe 012 to be supplied to the oil supply 11, a battery 014 for generating hydraulic oil instead of oil discharged from the hydraulic pump 08, an electric motor 015, and a small pump 016. Additional equipment 0
10 is mounted on the helicopter 01, and a preflight check is performed using hydraulic oil generated by the additional equipment 010.

In the operation check of the control system using the hydraulic oil generated by the additional equipment 010, the connection between the hydraulic pump 08 and the hydraulic equipment 011 is cut off by the switching device 013, and the discharge of the hydraulic equipment 011 and the small pump 016 is performed. After connecting the outlet, the electric motor 015 is driven by the electricity stored in the battery 014, and the hydraulic oil from the small pump 016 operated by driving the electric motor 015 is supplied to the switching device 013.
By supplying to the hydraulic equipment 011 through the main control system, it is checked whether the main control system or the like operates according to the control operation. In the drawing, 09 stores hydraulic oil discharged from the hydraulic device 011 and flows in through the return pipe 017, and also stores hydraulic oil stored by the hydraulic pump 08 and / or the small pump 015 through the suction pipe 018. The reservoir as described above, which can be supplied to the reservoir.

As described above, in the case where the operation of the main control system or the like is performed by using the additional equipment 010 and the preflight check is performed, a clutch is provided in the middle of the driving force transmission mechanism described above. As in the case where the operation of the main control system or the like is confirmed without rotating the rotors 03 and 06 by disengaging the clutch, the safety problem described above or the main control system due to the operation being performed. There is an advantage that the problem that the preflight check of whether or not the air conditioner is operating in accordance with the steering operation cannot be accurately performed is solved.

However, a battery 014 for supplying hydraulic oil to the hydraulic equipment 011 instead of the hydraulic pump 08,
Since it is necessary to newly provide the electric motor 015 and the small pump 016, the cost increases, the weight of the additional equipment 010 becomes 35 kg, the payload of the helicopter 01 is reduced, and the operation efficiency of the helicopter 01 is improved. There is a defect that is bad.

[0017]

SUMMARY OF THE INVENTION As described above, the present invention does not use the working oil which can be generated by the operation of the engine in which various troubles occur, and also increases the cost and weight. Hydraulic oil can be supplied to hydraulic equipment that operates the control system without using clutches and additional equipment that cause malfunctions, and most of the control systems required for helicopter flight as well as the main control system by the control operation It is an object of the present invention to provide a helicopter in which a pre-flight check hydraulic power source is provided, which can be operated over the entire maneuvering range and in which the operation can be confirmed in a safe state and in detail before flight.

[0018]

Therefore, the helicopter of the present invention has the following means.

(1) A control system operated by hydraulic oil discharged from a hydraulic pump driven by an engine that rotates a rotor can be operated over the entire control range by a control operation before flight. The pre-flight check hydraulic power source required for the pre-flight check performed to check whether or not the pre-flight check is equipped with an accumulator that can be selectively used during the pre-flight check.

It is desirable that the accumulator be of a pressure and a capacity capable of operating the control system over the entire control range for preflight check, and be of a light weight. In addition, the accumulator is designed to fill the operating system with the pressure and capacity of operating oil that can operate the control system over the entire operation range before mounting, even if the accumulator discharges oil from the hydraulic pump driven by the engine that rotates the rotor. Alternatively, the hydraulic oil may be pre-filled during flight or the like.

(A) This eliminates not only the above-mentioned problem in performing the preflight check while operating with the hydraulic oil from the engine-driven hydraulic pump, but also the use of the engine-driven hydraulic pump. Instead of this, it is possible to eliminate the problem that has occurred when the preflight check is performed with hydraulic oil generated by separately installed additional equipment or the like.

That is, (i) whether or not the rotor head operates according to the steering operation, which has occurred when the preflight check is performed using the hydraulic oil discharged from the engine-driven hydraulic pump as it is, can be remotely determined. In the case where a clutch that can be fitted and disengaged from the engine and the main rotor is provided in order to resolve the problem that the operation of the main control system cannot be confirmed accurately, and the problems of (ii) and (i) cannot be confirmed. However, in order to eliminate the disadvantages of increasing the cost and weight and complicating the driving force transmission mechanism from the engine to the main rotor, and (iii) (i), replacing the engine-driven hydraulic pump with In order to separately provide a hydraulic source for generating hydraulic oil to operate the control system in addition to the engine-driven hydraulic pump, a battery, an electric motor, and a small pump are provided. Have occurred in the case of performing the preflight check mounted equipment in helicopters, failure of cost and weight increase due to the mounting of additional equipment,
Respectively, and hydraulic oil capable of operating most of the control system can be supplied to the hydraulic equipment.

Thus, the entire operation range of the control system can be operated by the control operation before the flight of the helicopter, and the operation of the control system can be accurately confirmed in a safe state. Furthermore, since the rotor operated by the steering operation is stationary at the time of the flight check, it is possible to accurately confirm whether or not these pitch angles and the like, which were conventionally difficult to confirm, are operated according to the steering operation, A preflight check can be performed to check the flight safety of the helicopter.

Further, the helicopter of the present invention has the above-mentioned (1)
In addition to the above means, the following means were adopted.

(2) The accumulator is filled with pressurized hydraulic oil before mounting, and is mounted on the helicopter. The pressurized hydraulic oil filled in the accumulator is operated at a pressure of about 3000 psi at which the control system can be operated over the entire control range and a preflight check can be performed, that is, the hydraulic oil supplied from the conventional hydraulic pump to the control system. It is desirable that the pressure be the same as that of the pressure and the capacity required for the preflight check.

(B) Thus, in addition to the above (a), the accumulator can be made completely independent of the engine-driven hydraulic pump, and a hydraulic oil supply pipe for filling the accumulator with hydraulic oil from the hydraulic pump. This eliminates the need for installation and the like, thereby further reducing the weight.

Further, the helicopter of the present invention provides the above-mentioned (1)
In addition to the above means, the following means were adopted.

(3) The accumulator is provided with a filling check valve that allows only the inflow of the discharge oil from the hydraulic pump operated by the drive of the engine that drives the rotor. A filling line, which is installed in parallel with the filling line, is connected to the hydraulic pump by a supply line interposed with a starter valve that allows only the outflow of the filled hydraulic oil supplied to the hydraulic device from the accumulator, Filling the discharge oil from the hydraulic pump driven by the engine during the flight from the filling line as hydraulic oil, and supplying the hydraulic oil filled in the accumulator to the hydraulic equipment from the supply line before starting the engine. did.

The supply line for supplying the hydraulic oil from the accumulator to each hydraulic device is connected to the pressure supply pipe for supplying the hydraulic oil from the hydraulic pump to each hydraulic device during flight. The hydraulic pump is connected to a filling line that fills the accumulator with hydraulic oil discharged from a hydraulic pump that is arranged in parallel, and is connected to the hydraulic pump. It is preferable to provide a discharge check valve on the discharge side of the hydraulic pump to prevent the hydraulic oil charged in the accumulator from being loaded on the hydraulic pump during the preflight check supplied to the device.

(C) Thus, in addition to the above (a), the accumulator is filled with hydraulic oil by a hydraulic pump driven by an engine driving the main rotor during the flight, so that the conventional preflight The same pressure as when checking, that is, hydraulic oil equivalent to the pressure that activates the control device during flight, and high pressure from a hydraulic pump or the like for filling the accumulator with hydraulic oil on the ground etc. The need for an oil generator is eliminated.

In addition, although the accumulator is filled with hydraulic oil by a hydraulic pump driven by the engine, it is not necessary to operate the hydraulic pump during the preflight check.
The main rotor that was rotating with the operation of the hydraulic pump,
Conventionally required to stop the tail rotor,
It is not necessary to install a clutch in the middle of the driving force transmission mechanism, so that the cost and weight can be avoided and the driving force transmission mechanism does not become complicated.

Further, the helicopter of the present invention provides the above-mentioned (3)
In addition to the above means, the following means were adopted.

(4) A check valve for protecting the starter valve, which prevents the discharge oil from the hydraulic pump from flowing into the starter valve, is interposed in the supply line.

(D) In addition to the above (c), when the accumulator is filled with hydraulic oil from the hydraulic pump, the discharge oil discharged from the hydraulic pump at 3000 psi, and the pulsating discharge oil The starter valve installed in the supply line is not directly loaded, and the starter valve can be protected.At the time of preflight check, the starter valve operates normally and the hydraulic oil filled in the accumulator Normal pressure and flow rate can be supplied to equipment smoothly.

[0035]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the helicopter according to the present invention will be described below with reference to the drawings. In the drawings, the same or similar members as those shown in FIGS. 3 and 4 are denoted by the same reference numerals, and description thereof will be omitted as much as possible. FIG. 1 is a block diagram showing a preflight check hydraulic power source used in the first embodiment of the helicopter of the present invention.

As shown in the figure, during helicopter 01 flight,
From the hydraulic pump 08 to the hydraulic equipment 011, the main rotor 0
3 and a switching device 0 in the middle of a pressure oil supply pipe 012 that supplies hydraulic oil when an engine (not shown) that drives the tail rotor 06 and drives them is operated.
13 are installed. The switching device 013 is connected to an accumulator line 2 for supplying hydraulic oil filled in the accumulator 1 to a pressure oil supply pipe 012 by a hydraulic pump installed on the ground.

That is, the switching device 013 has a structure similar to that of a three-way valve similarly to that shown in FIG. 4 and, when the engine is operating, discharges oil from a hydraulic pump 08 driven by the engine by operation. As described above, at the time of a preflight check performed by stopping the engine due to various problems as described above, the communication between the hydraulic pump 08 and the hydraulic device 011 is performed by operating the switching device 013. Is shut off, and the accumulator 1 and the hydraulic device 011 can communicate with each other.

The accumulator 1 supplies hydraulic oil to the hydraulic equipment 011 during a preflight check.
Has a cylindrical shape having a length of 28 inches and a diameter of about 3.7 inches, and is internally supplied to a hydraulic device 011 from a hydraulic pump 08 driven by an engine, and includes a flight system including a main control system. Most of the control systems required for
Pressure 30 capable of operating over the entire operating range
At the same pressure as 00 psi, hydraulic oil of the volume required for the preflight check is filled on the ground and used at the time of the preflight check.

The accumulator 1 used as the preflight check hydraulic power source used in the helicopter 01 of the present embodiment has the above-described configuration, and the accumulator line 2
In order to operate a normal control system, the oil discharged from the hydraulic pump 08 driven by an engine (not shown) is supplied to the pressure oil supply pipe 012 and the switching device Most of the control devices, including the main control device, which are supplied as hydraulic oil to the hydraulic equipment 011 through the hydraulic oil supply pipe 13 and the hydraulic oil supply pipe 012, can be operated over the entire control range by the control operation.

Before the flight of the helicopter 01, the control device, particularly the main control device specified in the airworthiness examination guidelines,
At the time of preflight check to confirm that operation can be performed over the entire control range, the hydraulic pump 0
The switching device 013 that has made the hydraulic device 011 communicate with the hydraulic device 011 is switched to cut off the communication between the hydraulic pump 08 and the hydraulic device 011, and also stores the accumulator 1 and the hydraulic device 01.
And the pressure oil supply pipe 0 on the right side of the accumulator line 2
The hydraulic oil in the accumulator 1 can be supplied to the hydraulic device 011 of the control device for confirming the operation by communicating with the control device 12 via the control unit 12.

Thus, the pre-pressurized and filled hydraulic oil in the accumulator 1 can be supplied to the hydraulic equipment 02 for operating the main control system and the like required at the time of preflight check.

That is, the aforementioned “Airworthiness examination procedure”
In order to operate the main control system specified in the preflight check clause of the present invention over the entire operation range, it is necessary to send hydraulic oil to a hydraulic device 011 for operating the main control system. It is possible to perform preflight checks that meet the regulations by using the hydraulic oil that has been set.

As described above, in view of the demand for improvement in the preflight check conventionally performed, the helicopter according to the present embodiment uses the accumulator 1 as a hydraulic power source during the preflight check. I did it. Moreover, this accumulator 1 has
The hydraulic equipment 011 can be easily pressurized by previously filling the hydraulic oil with the hydraulic pump installed on the ground. In addition, the number of accessories to be added to the accumulator 1 can be reduced, the cost can be reduced, and the preflight check is performed using the hydraulic pump generated by the above-described additional accessories 10 of the electric pump type. It can be made as light as 9 kg or less, which is 1/3 or less, as compared with the above-mentioned structure.

Next, FIG. 2 is a block diagram showing a preflight check hydraulic power source used in a second embodiment of the helicopter of the present invention, and FIG. 2 (a) shows a hydraulic fluid supplied to an accumulator during flight. FIG. 2 shows a state in which
(B) is a diagram showing a state in which the hydraulic oil filled in the accumulator is being supplied to the hydraulic equipment during a preflight check on the ground.

As shown in the figure, during the flight of the helicopter 01, the hydraulic pump 08 is directly connected to the hydraulic equipment 011 to the main rotor 03 and the tail rotor 06, and supplies hydraulic oil at the time of operation of an engine (not shown) for driving these. In the middle of the pressure oil supply pipe 012 as described above, only the discharge oil from the hydraulic pump 08 operated by driving the engine operating the rotors 03 and 06 is allowed to flow into the accumulator 1, The other end of the filling line 3 in which the filling check valve 4 for filling the working oil into the accumulator 1 to which one end is connected is connected.

A starter valve 6 is installed in parallel with the filling line 3 and allows only the outflow of the filled hydraulic oil supplied to the servomotor of the hydraulic device 011 from the accumulator 1 having one end connected thereto. The other end of the supply line 5 is also connected in the middle of the pressure oil supply pipe 012.

That is, one end is connected to the accumulator 1 and the juxtaposed filling line 3 and supply line 5 are connected to the hydraulic oil supply pipe 012 at the other end, respectively. It is connected to the discharge port.

In the starter valve 6, a check valve 7 (with a built-in starter valve) that allows only the flow of hydraulic oil from the accumulator 1 to the pressure oil supply pipe 012 is installed. In the supply line 5 between the provided starter valve 6 and the pressure oil supply pipe 012, in other words, the hydraulic pump 08, a starter valve protection that allows only the flow of hydraulic oil from the accumulator 1 to the pressure oil supply pipe 012. A check valve 8 is provided.

Further, at the discharge side of the hydraulic pump 08, the accumulator 1 is stopped during the preflight check in which the hydraulic pump 08 is stopped to supply hydraulic oil to the hydraulic oil supply pipe 012.
There is provided a discharge check valve 9 for preventing the hydraulic oil filled in the hydraulic pump 08 from being loaded on the hydraulic pump 08. In addition, the accumulator 1 is provided with a pressure gauge 10 for displaying the pressure of the working oil filled therein.

The preflight check hydraulic pressure source of the present embodiment is configured as described above. During the flight of the helicopter 01, the starter valve 6 installed on the supply line 5 is closed, and the main rotor 03, Discharge oil from a hydraulic pump 08 driven by an engine for operating the tail rotor 06 is used as hydraulic oil from the charging line 3 to the accumulator 1.
When the preflight check is performed before the engine is started, the hydraulic oil filled in the accumulator 1 is opened by opening the starter valve 6 which has been closed, so that each hydraulic pressure for operating the control system from the supply line 5 is increased. It can be supplied to the pressure oil supply pipe 012 that supplies the servo motor of the device.

Thus, the hydraulic source for preflight check according to the present embodiment is a hydraulic pump 08 driven by the engine driving the rotors 03 and 06 during flight, and the conventional pre-flight check is supplied to the accumulator 1 during flight. Hydraulic oil of the same pressure as the flight check is performed, that is, the same pressure as the one operated by the pilot during the flight, fills the capacity required for the preflight check in about one minute of flight. At the same time, it is not necessary to install a high-pressure oil generator such as a hydraulic pump provided on the ground or the like, which is required in the first embodiment for filling the hydraulic oil.

The hydraulic oil charged in the accumulator 1 stops the engine after the landing of the helicopter 01, and when the operation of the hydraulic pump 08 stops, the check valve 4 for charging and the charging valve as described above are charged. Due to the closed starter valve 6, the pressure and capacity required for the preflight check are maintained without backflow to the pressure oil supply pipe 012 side.

In addition, although the accumulator 1 is filled with hydraulic oil by the hydraulic pump 08 which is driven by the engine and supplies the hydraulic oil for operating the control system during flight, the hydraulic pump 08 is used during the preflight check. When the hydraulic pump 08 is operated, the main rotor and the tail roller, which have been rotating together with the operation of the hydraulic pump, are conventionally required to stop for the preflight check. It is not necessary to install a clutch in the mechanism, thereby avoiding an increase in cost and an increase in weight, and without complicating the driving force transmission mechanism.

Also, since the starter valve protection valve 8 is provided in the supply line, when the accumulator 1 is filled with the hydraulic oil from the hydraulic pump 08, three times
The discharge oil discharged from the hydraulic pump 08 which also has a pressure of 00 psi, and the pulsating discharge oil is not directly loaded on the closed starter valve 6 installed in the supply line 5, and the starter valve 6 performs the preflight check. Occasionally, the operation oil normally operates, and the hydraulic oil filled in the accumulator 1 can be smoothly supplied to each hydraulic device 011 at a normal pressure and flow rate.

As described above, since the main control system of the helicopter 01 in flight has conventionally used the operating oil discharged from the hydraulic pump 08 which is operated by the rotation of the engine, Even in the preflight check, if the oil discharged from the hydraulic pump 08 is to be used, no design has been made such as providing a clutch in a drive system in which the rotors 03 and 06 are directly driven by the engine. As long as the rotor 03, 06 is rotated by the start of the engine, if the preflight check is performed in this state, the helicopter for performing the preflight check may rise or fall, which is very dangerous. In order to avoid such a danger, it was necessary to provide a clutch in the power transmission system. By providing the hydraulic source for preflight check, the preflight check can be performed without considering such danger and without increasing the cost, weight, or complicating the transmission system due to the installation of the clutch. In order to solve the above-mentioned problems, the hydraulic pump 08 driven by the engine is used.
A system in which a hydraulic pump is provided separately, and a small pump 016 driven by an electric motor 015 is provided by a switching device 013 as a hydraulic source of a system used only during a preflight check.
4. The number of the electric motor 015, the small pump 016, and the additional equipment 010 increases, and the preflight check can be performed while avoiding the increase in weight and cost.

[0056]

As described above, the helicopter according to the present invention completely controls the control system operated by the oil discharged from the hydraulic pump driven by the engine for rotating the main rotor by the pre-flight control operation. An accumulator that can be selectively used during the preflight check is installed as a preflight check hydraulic power source required for the preflight check performed to confirm the operation over the control range.

As a result, not only safety problems, weight increase and price increase in the case of performing a preflight check with oil discharged from an engine-driven hydraulic pump are solved, but also an engine-driven hydraulic pump is used. Without the need for a preflight check, the problem of increased weight and higher price that had occurred when the preflight check was performed can be eliminated, hydraulic oil can be supplied to the hydraulic equipment that operates the control system, and the piloting operation can be performed before the helicopter flies. As a result, the entire flight range of the flight control system can be operated and a preflight check that can be confirmed can be performed.

The helicopter of the present invention is filled with hydraulic oil pressurized by an accumulator before mounting, and mounted on the helicopter.

Thus, the accumulator can be made completely independent of the engine-driven hydraulic pump, and there is no need to install a supply pipe for filling the accumulator with discharge oil from the hydraulic pump, thereby reducing the weight. become.

Further, in the helicopter of the present invention, the accumulator is provided with a check valve for filling that allows only the inflow of the discharge oil from the hydraulic pump operated by driving the engine, and the discharge oil is used as the hydraulic oil. It is connected to the hydraulic pump by a filling line to be filled and a supply line interposed with a starter valve that is installed in parallel with the filling line and allows only the outflow of hydraulic oil supplied from the accumulator to the hydraulic equipment. The hydraulic oil discharged from the hydraulic pump driven by is supplied from the filling line as hydraulic oil, and the hydraulic oil filled before the start of the engine is supplied to the hydraulic equipment from the supply line.

Thus, the accumulator is filled with hydraulic oil by a hydraulic pump driven by an engine during flight, and a high-pressure oil generating device such as a hydraulic pump for filling the accumulator with hydraulic oil on the ground or the like is used. It becomes unnecessary.

Further, in the helicopter of the present invention, a check valve for protecting the starter valve for preventing the discharge oil from the hydraulic pump from flowing into the starter valve is interposed in the supply line.

Thus, when the accumulator is filled with hydraulic oil from the hydraulic pump, the hydraulic oil is discharged from the hydraulic pump,
The pulsating discharge oil is no longer directly added to the starter valve installed in the supply line, and the starter valve can be protected.
By operating the starter valve normally, hydraulic oil can be smoothly supplied to each hydraulic device at a normal pressure and flow rate.

[Brief description of the drawings]

FIG. 1 is a block diagram showing a preflight check hydraulic power source used in a first embodiment of a helicopter according to the present invention;

FIG. 2 is a block diagram showing a preflight check hydraulic power source used in a second embodiment of the helicopter according to the present invention. FIG. 2A shows an accumulator filled with hydraulic oil during flight. FIG. 2B is a diagram showing a state, and FIG. 2B is a diagram showing a state in which hydraulic oil is supplied to a hydraulic device during a preflight check;

FIG. 3 is an overall view of a helicopter showing a part of hydraulic equipment for performing a preflight check of the helicopter;
3A is a plan view, FIG. 3B is a side view, FIG. 3C is a front view,

FIG. 4 is a block diagram showing a conventional hydraulic power source for preflight check of a helicopter.

[Explanation of symbols]

 Reference Signs List 1 accumulator 2 accumulator line 3 filling line 4 filling check valve 5 supply line 6 starter valve 7 (built-in starter valve) check valve 8 check valve for starter valve protection 9 discharge check valve 10 pressure gauge 01 helicopter 02 rotor Head 03 Main rotor 04 Swash plate 05 Main rotor servo 06 Tail rotor 07 Tail rotor servo 08 Hydraulic pump 09 Reservoir 010 Additional accessories 01 Hydraulic equipment 012 Pressure oil supply pipe 013 Switching device 014 Battery 015 Electric motor 016 Small pump 017 Return pipe 018 Suction tube

Claims (4)

[Claims] 1. A hydraulic oil for operating a hydraulic device in a helicopter provided with a hydraulic pump driven by an engine for rotating a rotor and a control system operated by a hydraulic device driven by oil discharged from the hydraulic pump. A helicopter which is equipped with an accumulator which is selectively filled as a hydraulic source for preflight check of the control system. 2. The helicopter according to claim 1, wherein the accumulator is filled with the hydraulic oil before mounting, and is mounted on an airframe. 3. The accumulator is provided in parallel with the filling line, interposed with a filling check valve allowing only the inflow of the discharge oil, and filling the discharge oil as the working oil. The hydraulic pump is connected to the hydraulic pump by a supply line interposed with a starter valve that allows only the outflow of the hydraulic oil supplied from the accumulator to the hydraulic device, and is driven by the engine during flight. Wherein the discharge oil is filled as the hydraulic oil from the charging line, and the hydraulic oil filled before the start of the engine is supplied from the supply line to the hydraulic device. 1 helicopter. 4. The helicopter according to claim 3, wherein a check valve for protecting a starter valve for preventing the discharge oil from the hydraulic pump from flowing into the starter valve is interposed in the supply line.