RU2333866C2 - Method of helicopter control in failure of power plant with propeller mechanical drive (versions) - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to helicopters. Method of helicopter control in failure of power plant with propeller mechanical drive consists in mounting on the helicopter of an air-operated power unit (11) running in the air-operated engine conditions, the air-operated unit air intake (14) being connected, via an air-control apparatus (17), with gas cylinder (18) filled, before the flight, with high-pressure compressed air. Power plat (4) failed and the propeller windmilling, the air-operated power unit is cut in, while its shaft (12) being connected, via transmission (6), to the propeller shaft (8). In compliance with the second version, the helicopter incorporates an additional air-operated power unit to be switched over, by remote means, into the air-operated engine or the compressor mode.

EFFECT: higher flight safety.

8 cl, 2 dwg

Description

Technical field

The invention relates to airborne aircraft, and in particular to helicopters with power plants with mechanical propeller drive.

State of the art

A known method of flight of a helicopter in the event of a power plant failure with a mechanical screw drive [1], which consists in the fact that the power plant shaft is automatically switched off with the help of a freewheel so as not to expend the main rotor’s power to rotate the engine, and the helicopter will switch to emergency mode autorotation descent, consisting of four stages: the first is planning at a constant angle and constant speed, the second is braking (reducing the planning angle and vertical speed) and reducing due to the use of the kinetic energy of the helicopter and the main rotor, the third - landing and the fourth - the run and the pitch of the main rotor, with manual pilot control.

There is also a method of increasing the safety of helicopter flight by providing gas fire protection for the helicopter power plant [1], which consists in the fact that when a fire occurs in any of the protected compartments of the power plant from the fire alarm sensors, an electrical signal is supplied to the actuator, the corresponding display is lit in the pilot’s cockpit, and as a result of automatic or manual activation of the fire extinguishing system, the ignition circuit of the squibs in the head of the fire extinguishers closes, Electromagnetic distribution valves and extinguishing agent enters the appropriate compartment through pipelines and distribution manifolds, while exiting the collector, the extinguishing agent evaporates and fills the compartment with inert gas, as a result of which atmospheric oxygen flow to the fire is limited, and the temperature in the compartment decreases sharply, which contributes to stopping the fire.

The disadvantage of this widely used method of emergency descent of a helicopter is the difficulty of controlling autorotation of the helicopter, and therefore, the great dependence of the latter's successful landing on the pilot's experience, as well as on weather conditions and terrain, which often leads to serious injuries or even death of the crew and passengers, and also to damage or complete destruction of the helicopter.

The above method of fire protection of the power plant requires the installation of special fire extinguishers.

SUMMARY OF THE INVENTION

The basis of the invention is the task of proposing variants of a method that can significantly improve the safety of a helicopter flight in case of failure of its power plant.

The solution to this problem is achieved by the fact that in the known method of flight of a helicopter in case of failure of the power plant with a mechanical drive of the screws, which consists in automatically disconnecting using the freewheel of the shaft of the power plant from the rotor shaft or rotor shafts of the coaxial circuit when controlling the pilot using equipment control and flight, the planning speed and the angle of descent of the helicopter, according to the invention, an additional pneumatic power device is installed on the helicopter, which operates in air engine mode, while its air inlet is connected via a controlled pneumatic control device to a gas cylinder into which compressed gas is pumped to high pressure before flight, and in flight if the power plant fails at the stage of autorotation planning descent or immediately after the power plant is automatically disconnected from the screw or coaxial propellers, which depends on the altitude and flight conditions, include a pneumatic power device and connect its shaft through a transmission containing a mechanical gp clutch shaft pneumatic pulling device and the shafts of the rotors, with a screw shaft or shafts of screws coaxial through gearboxes, the pneumatic power unit, feeding compressed high-pressure air from the gas cylinder through a controllable pnevmoreguliruyuschy apparatus Command pilot provides a smooth controlled landing of the helicopter.

In addition, the exhaust gas from the pneumatic power device is directed in the area of the chassis towards the ground.

At the same time, the task was further set to further increase helicopter flight safety in the event of a power plant failure with a mechanical propeller drive, as well as to increase the fire protection of the helicopter power plant.

The solution to this problem is achieved by the fact that in the known method of flight of a helicopter in case of failure of the power plant with a mechanical drive of the screws, which consists in automatically disconnecting with the help of the freewheel of the shaft of the power plant from the rotor shaft or rotor shaft of the coaxial circuit when controlling the pilot using equipment control and flight, planning speed and angle of descent of the helicopter, according to the invention, an additional pneumatic power device is installed on the helicopter, which can remotely switch to either the pneumatic engine operation mode or the compressor operation mode, while the gas motor input of the pneumatic power device and its compressor output are connected through a controlled pneumatic control device with a gas cylinder, while before the helicopter flying, the power plant shaft is disconnected using the freewheel clutch from the rotor shaft or the rotor shafts of the coaxial circuit and connecting it to the shaft of the pneumatic power device, which is switched to the compressor operation mode, including a power plant is installed, with the help of which the pneumatic power device, working in compressor mode, pumps gas, for example air, into a gas cylinder through a controlled pneumatic control device to a certain high pressure, after which the above equipment is returned to its original state, and the pneumatic power device is switched to operate in the mode of a pneumatic engine in flight in case of failure of the power plant on the autorotation gliding descent or immediately after the automatic disconnection of forces the installation from a screw or screws of a coaxial circuit, which depends on the altitude and flight conditions, include a transmission clutch mechanism that connects the shaft of the pneumatic power device to the screw shaft or shaft of the coaxial circuit screws through gearboxes, and the pneumatic power device, operating in the air motor mode, feeding on compressed gas (air) from a gas cylinder through a controlled pneumatic control device on the pilot’s commands provides an optimal smooth controlled landing of the helicopter.

In addition, options for improving this method are proposed, namely:

- the exhaust air discharge from the pneumatic power device is directed in the chassis area towards the ground;

- after the emergency descent of the helicopter, automatically or manually by the pilot, the above pneumatic system switches to the mode of filling the gas cylinder with high-pressure compressed air;

- before the flight of the helicopter, the gas cylinder is filled with fire extinguishing gas compressed to high pressure and connected through a controlled pneumatic control device to the helicopter’s fire extinguishing system that extinguishes the fire of the power plant with the above fire extinguishing gas, and if the fire occurred during an emergency descent of the helicopter, then the fire extinguishing gas is used as working fluid for rotation of the pneumatic engine, and the gas exhausted therein is used to extinguish a fire;

- after liquidation of the fire and landing of the helicopter or during emergency landing of the helicopter outside its service area and bringing the helicopter into working condition, the crew will fill the gas cylinder with compressed air to continue the flight, with the possibility of a repeated controlled smooth emergency landing of the helicopter if necessary;

- in single-rotor helicopters in case of failure of the tail rotor or its mechanical drive during emergency descent, compressed air is supplied through a controlled pneumatic control device through a pipe to the nozzle, which is installed at the end of the tail boom of the helicopter from a gas cylinder, providing compensation for the reactive moment created by the main rotor, and, respectively , or a controlled emergency soft landing, or the continuation of a helicopter flight.

Brief Description of the Drawings

Figure 1 presents an example of a functional diagram of a single-rotor helicopter, and figure 2 - a helicopter with two coaxial screws for implementing these variants of the method, where the positions indicated:

1 - fuselage;

2 - tail boom;

3 - chassis;

4 - power plant;

5 - shaft of the power plant;

6 is a transmission comprising a mechanism for coupling the shaft of a pneumatic power device with a screw shaft or shafts of screws of a coaxial circuit through gearboxes;

7 - rotor or shafts of the rotors of the coaxial circuit;

8 - rotor shaft or shafts of the rotors of the coaxial circuit;

9 - tail rotor;

10 - control and flight equipment;

11 - pneumatic power device operating in the air motor mode or in compressor mode;

12 - shaft of a pneumatic power device;

13 - remote control mode of operation of a pneumatic power device;

14 - gas motor inlet of a pneumatic power device;

15 - gas compressor inlet of a pneumatic power device;

16 - exhaust gas output of a pneumatic engine;

17 - controlled pneumatic control device;

18 - gas cylinder;

19 - gas fire system with fire sensors;

20 - nozzle;

21 - stabilizer;

22 - vertical plumage.

The best option for implementation

A variant of the method according to claim 1 of the formula is as follows.

Before the flight of the helicopter, compressed air is pumped into a gas cylinder 18 from an external source to a high pressure, for example, up to 20 ... 31.4 MPa, and when flying in the event of a power plant 4 failure using the transmission free-wheel clutch 6, its shaft is automatically disconnected from the shaft rotor or rotor shafts of the coaxial circuit so that the rotor or rotor of the coaxial circuit does not expend power on the rotation of the power plant 4, after which, using the flight control equipment, the pilot either starts an emergency autorotation plan helicopter flying at a constant angle and constant speed until a certain reduction height is reached to save compressed air energy in a gas cylinder, and then includes a transmission clutch 6, which connects the shaft of the pneumatic power device 11 operating in the engine mode through the transmission 6 to the rotor shaft or shafts of rotors of the coaxial circuit 8, which begins to be fed through controlled pneumatic control apparatus 17 with high-pressure compressed air and rotate the rotor or rotor s of the coaxial scheme, providing, according to the pilot’s commands, an optimal smooth, controlled landing of the helicopter, or if the height of the helicopter at which the power unit 4 failed, then the pneumatic power device 11 is automatically activated immediately after the transmission clutch 6 is activated, and the pilot makes a smooth controlled landing of the helicopter.

The addition according to claim 2 to the method variant according to claim 1 of the formula is as follows.

To improve the smooth landing of the helicopter, the exhaust air from the pneumatic power device 11 is carried out in the area of the chassis 3 in the direction of the earth.

A variant of the method according to claim 3 of the formula is as follows.

Before the flight of the helicopter, the pilot, having disconnected the shaft 5 of the power unit 4 from the rotor or rotors of the coaxial circuit with the help of the freewheel of the transmission 6 and connecting it to the shaft 12 of the pneumatic power device 11, which he switches to the compressor operation mode, turns on the power unit 4 and the compressor, through a controlled pneumatic control apparatus 17, pumps compressed gas, for example air, into a gas cylinder 18, to a certain pressure, for example up to 20 ... 31.4 MPa, after which it returns the above equipment to its original state and the pneumatic power device 11 switches using the remote switch 13 to the pneumatic engine mode, and during flight and in case of failure of the power plant 4 using the transmission freewheel 6, its shaft 5 is automatically disconnected from the rotor 7 so that the rotor 7 does not waste rotational power of the power plant 4, after which, using the control and flight equipment 10, the pilot either first starts the emergency autorotating planning flight of the helicopter at a constant angle and constant speed to reach reducing a certain reduction height to save energy of compressed gas in the gas cylinder 18, and then includes a clutch mechanism for the transmission 6, which connects the shaft of the pneumatic power device 11 through the transmission 6 to the rotor shaft or rotor shafts of the coaxial circuit 7, which begins to be fed through a controlled pneumatic control the apparatus 17 with high-pressure compressed gas from the gas cylinder 18 and rotate the rotor or rotors of the coaxial circuit 7, providing the pilot with optimal control of the landing helicopter Then, or if the height of the helicopter at which the power unit 4 failed, the pneumatic power device 11 is turned on in the air motor mode immediately after the freewheel of the transmission 6 is activated and the pilot makes a controlled landing of the helicopter.

Supplement according to claim 4 of the formula to a variant of the method according to claim 3 of the formula is as follows.

To improve the smooth landing of the helicopter, the exhaust gas from the pneumatic power device 11 operating in the air motor mode is carried out in the area of the chassis 3 in the direction of the earth.

Addition according to claim 5 of the formula to a variant of the method according to claim 3 of the formula is as follows.

After the emergency descent of the helicopter to the ground to accelerate the cessation of rotation of the screw or screws of the coaxial circuit 7, the pneumatic equipment automatically or manually by the pilot switches to filling the gas cylinder 18 with compressed gas, which creates a load on the rotor shaft 8 or rotors of the coaxial circuit 7, while part the consumed energy of compressed air is returned to the gas cylinder 18.

Addition according to claim 6 of the formula to a variant of the method according to claim 3 of the formula is as follows.

Before a helicopter flies at a service base, its gas cylinder is filled with fire-extinguishing gas, for example nitrogen, and connected through a controlled pneumatic control device 17 to the helicopter’s fire fighting system 19, which extinguishes the fire of the power plant 4 with the above fire-fighting gas, and if a fire occurred during an emergency descent of the helicopter, for example, due to a fire of the power plant 4, the extinguishing gas is simultaneously used to rotate the pneumatic power device 11, and the gas exhausted in it is used to extinguish the source fire.

The addition according to claim 7 to the variant of the method according to claim 3 is as follows.

After the elimination of the fire and emergency landing of the helicopter or simply emergency landing of the helicopter outside its service area and bringing it into operational condition by the crew, the gas cylinder 18 is filled with compressed air before resuming the flight to continue the flight with the possibility of reliable re-controlled emergency emergency landing of the helicopter.

Supplement according to claim 8 of the formula to a variant of the method according to claim 3 of the formula is as follows.

In single-rotor helicopters, in case of failure of the tail rotor 9 or its drive, compressed gas is supplied through a controlled pneumatic control device 17 through a pipeline to the nozzle 20, which is installed at the end of the tail boom 2 of the helicopter, in case of emergency descent from the gas cylinder 18, and in case of a good power plant 4 from the pneumatic power device 11, operating in compressor mode, providing compensation for the reactive moment created by the rotor 7, and, accordingly, or controlled emergency landing, or continued flight of the helicopter but.

From the above it can be seen that the introduction of sets of distinctive features allows, in comparison with the prototype, to significantly increase the safety of helicopter flights and their reliability.

Industrial applicability

The implementation of the proposed variants of the method and the creation on its basis of the design of helicopters does not present great technical difficulties for the aviation industry, because For this purpose, widely used equipment is offered, characterized by increased reliability due to the simplicity of its design. It is possible to use, in particular, pneumatic engines and cylinders for high-pressure compressed air up to 31.6 MPa, used on naval combat torpedoes.

The source of information

1. Volodko A.M. "Helicopter Flight Safety." Moscow: Transport, 1981, pp. 195 ... 200, p. 131 (Prototype).

Claims (8)

1. The method of flight of a helicopter in case of failure of the power plant with a mechanical drive of the screws, which consists in automatically disconnecting using the freewheel of the shaft of the power plant from the main rotor shaft or the rotor shaft of the coaxial circuit when the pilot is controlled using control and flight equipment, planning speed and angle the descent of the helicopter, characterized in that the helicopter additionally install a pneumatic power device that operates in the air motor mode, while its air input they are connected through a controlled pneumatic control device with a gas cylinder into which compressed gas is pumped to high pressure before the flight, and in flight if the power plant fails at the stage of autorotation planning descent or immediately after the power plant is automatically disconnected from the screw or screws of the coaxial circuit, which depends on the height and flight conditions, include a pneumatic power device and connect its shaft through a transmission containing a clutch mechanism of the shafts of the pneumatic power device and s rotor, with the screw shaft or the screw shaft coaxial through gearboxes, the pneumatic power unit, feeding compressed air from a high pressure gas cylinder through a controllable pnevmoreguliruyuschy apparatus according to pilot commands provides optimum controlled smooth landing of the helicopter. 2. The method according to claim 1, characterized in that the exhaust gas from the pneumatic power device is sent to the chassis area towards the ground. 3. The method of flight of a helicopter in the event of a power plant failure with a mechanical drive of the screws, which consists in automatically disconnecting, using the freewheel of the power plant shaft, from the rotor shaft or rotor shaft of the coaxial circuit when the pilot is controlled using control and flight equipment, planning speed and angle the descent of the helicopter, characterized in that the helicopter additionally install a pneumatic power device that can remotely switch either to the pneumatic mode the needle, or in the compressor operation mode, while the gas motor input of the pneumatic power device and its compressor output are connected through a controlled pneumatic control device to a gas cylinder, while before flying the helicopter, disconnecting the power unit shaft from the rotor shaft or shafts using the freewheel rotors of the coaxial circuit and connecting it to the shaft of the pneumatic power device, which is switched to the compressor operation mode, turn on the power unit, with which Some power device, working in compressor mode, pumps gas, for example air, into a gas cylinder through a controlled pneumatic control device to a certain high pressure, after which the above equipment is returned to its original state, and the pneumatic power device is switched to operate in air motor mode, in flight in case of failure of the power plant on the autorotation gliding descent or immediately after automatic disconnection of the power plant from the screw or screws of the coaxial circuit, which depends on the altitude and flight conditions, they include a transmission clutch mechanism, which connects the shaft of the pneumatic power device with the screw shaft or the shaft of the screws of the coaxial circuit through the gearboxes, and the pneumatic power device, working in the air motor mode, is fed by compressed gas (air) from the gas cylinder through controlled pneumatic control device, on the instructions of the pilot provides an optimal smooth controlled landing of the helicopter. 4. The method according to claim 3, characterized in that the exhaust air from the pneumatic power device is sent to the chassis area in the direction of the earth. 5. The method according to claim 3, characterized in that after the emergency descent of the helicopter, automatically or manually by the pilot, the above pneumatic system switches to the mode of filling a gas cylinder with high-pressure compressed air. 6. The method according to claim 3, characterized in that before the start of the helicopter’s flight, the gas cylinder is filled with extinguishing gas compressed to high pressure and connected through a controlled pneumatic control device to the helicopter’s fire extinguishing system that extinguishes the power plant fire with the above extinguishing gas, and if the fire occurred during the emergency descent of the helicopter, the extinguishing gas is used as a working fluid to rotate the pneumatic engine, and the exhaust gas used in it is used to extinguish a fire. 7. The method according to claim 3, characterized in that after the elimination of the fire and landing of the helicopter or during emergency landing of the helicopter, outside its service area and bringing the helicopter into working condition by the crew, the gas cylinder is filled with compressed air to continue the flight with the possibility of re-controlled if necessary smooth emergency helicopter landing. 8. The method according to claim 3, characterized in that in single-rotor helicopters when the tail rotor or its mechanical drive breaks down, during emergency descent, compressed air through a controlled pneumatic control device is piped into the nozzle, which is installed at the end of the tail boom of the helicopter, from the gas cylinder , providing compensation for the reactive moment created by the rotor, and, accordingly, or controlled emergency smooth landing, or the continuation of the flight of the helicopter.

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