CN112623234B - Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft - Google Patents
Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft Download PDFInfo
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- CN112623234B CN112623234B CN202011611101.4A CN202011611101A CN112623234B CN 112623234 B CN112623234 B CN 112623234B CN 202011611101 A CN202011611101 A CN 202011611101A CN 112623234 B CN112623234 B CN 112623234B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
- B64D31/02—Initiating means
- B64D31/04—Initiating means actuated personally
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
- B64D31/14—Transmitting means between initiating means and power plants
Abstract
The application provides a mechanical interlocking protection device of turboprop aircraft double-rod shape throttle platform, the device is including positive pull rod (1), anti-oar pole (2), cam conversion equipment (3), first pull rod mechanism (4), second pull rod mechanism (5), throttle platform body (6), stop device (7), anti-oar pole rotary part (8), roll bayonet lock (9), throttle angle sensor (10), wherein: the positive tension rod (1) is of a hollow rod-shaped structure, and a cam conversion device (3) is arranged in the positive tension rod (1); the lower end of the cam conversion device (3) is connected with the accelerator angle sensor (10) through a first pull rod mechanism (4), the lower end of the cam conversion device (3) is connected with a rolling bayonet (9) through a second pull rod mechanism (5), one end of the reverse paddle rod (2) is connected with the side face of the cam conversion device (3), the reverse paddle rod (2) is connected with the first pull rod mechanism (4) through the cam conversion device (3), and the second pull rod mechanism (5) is connected.
Description
Technical Field
The invention belongs to the technical field of aviation, and relates to a mechanical interlocking protection device for a double-rod type accelerator stage of a turboprop aircraft.
Background
For a turboprop airplane, in order to prevent an air throttle lever from being lower than a flight slow vehicle by mistake and enable a propeller to generate large negative pulling force, the airworthiness clause FAR25.1155 reverse thrust and pitch setting lower than a flight state are shown: "for reverse thrust and for pitch setting below the flight condition, measures must be taken to prevent unwanted actuation. This measure necessitates the presence of a positive lock or stop in the slow-flight position and requires an additional significant action by the unit in order to move the manoeuvring member away from the position of flight (positive thrust for the turbojet) condition. "
In order to meet the requirement, a mechanical lock and an electromagnetic lock are generally arranged at a slow-flight position of the throttle platform, and the mechanical lock can be unlocked only by manually operating a mechanical trigger (see figure 1) or a similar device after the electromagnetic lock meets a certain condition and is automatically unlocked.
The throttle platform (see figure 1) of the turboprop single-rod type is designed with the maximum reverse propeller behind a ground slow vehicle, a clamping groove is generally designed at the ground slow vehicle position, the machine set senses the position by increasing the operating force of the throttle rod, but the throttle platform clamping groove is abraded or the operating force is too large, the throttle platform clamping groove often crosses the ground slow vehicle position and directly enters the maximum reverse propeller, the power of an engine is increased, the propeller reverses, the engine surges or sucks foreign matters, even the aircraft backs up, and unsafe factors are formed.
In order to prevent the unit misoperation accelerator lever from crossing the ground slow parking position to enter the maximum reverse paddle state, if the design of a similar slow flying mechanical lock is added at the reverse slow parking position, the unit operation is difficult to distinguish whether the slow flying parking position is unlocked or the slow ground parking position is unlocked due to space limitation, and if the design is realized, the unit operation is easy to cause the unit confusion and the misoperation is caused.
Disclosure of Invention
In order to solve the technical problem, the application provides a mechanical interlocking protection device of two pole-shaped throttle platforms of turboprop, can prevent the unit maloperation.
The application provides a mechanical interlocking protection device of turboprop aircraft double-rod shape throttle platform, mechanical interlocking protection device includes positive pull rod (1), anti-oar pole (2), cam conversion equipment (3), first pull rod mechanism (4), second pull rod mechanism (5), throttle platform body (6), stop device (7), anti-oar pole rotary part (8), roll bayonet lock (9), throttle angle sensor (10), wherein:
the positive tension rod (1) is of a hollow rod-shaped structure, a cam conversion device (3) is arranged in the positive tension rod (1), and the cam conversion device (3) comprises a cam conversion mechanism A and a cam conversion mechanism B;
the lower end of the cam conversion device (3) is connected with the reverse paddle lever rotating part (8) through a first pull rod mechanism (4), the lower end of the cam conversion device (3) is connected with the rolling bayonet (9) through a second pull rod mechanism (5), one end of the reverse paddle lever (2) is connected with the side face of the cam conversion device (3), the reverse paddle lever (2) is connected with the first pull rod mechanism (4) through the cam conversion device (3), and the second pull rod mechanism (5) is connected;
a limiting device (7) is arranged in the accelerator platform body (6), the limiting device (7) comprises an AB section through groove, a CD section through groove and a DE section through groove, the radius of the AB section through groove is larger than that of the CD section through groove, and the BC section through groove and the DE section through groove are both in radial hollow clamping groove structures; the rolling bayonet lock (9) moves in the track of the limiting device (7); the lower end of the second pull rod mechanism (5) is connected with one end of a spring, a rolling clamping pin (9) is connected with the other end of the spring, and the elastic force of the spring enables the rolling clamping pin (9) to move outwards along the radial direction of the positive pull rod (1);
the fixed end of the accelerator angle sensor (10) is arranged on the accelerator table body (6), and the reverse paddle lever rotating component (8) drives the rotating shaft of the accelerator angle sensor (10) through gear engagement.
Specifically, when the rolling bayonet lock (9) moves in the AB section through groove of the limiting device (7), the rolling bayonet lock is used for controlling the power of the engine for taking off to flying slowly in an aerial operation area by the positive tension rod (1);
when the rolling clamping pin (9) moves in the CD section through groove of the limiting device (7), the rolling clamping pin is used for controlling the power of the engine from flying slow-speed to ground slow-speed by the positive tension rod (1) in a ground operation area;
when the rolling bayonet lock (9) moves in the BC section through groove of the limiting device (7), the positive tension rod (1) is positioned at the slow flying position and used for unlocking the positive tension rod (1) by the reverse propeller rod (2), so that the positive tension rod (1) can enter a ground operation area from an aerial operation area;
when the rolling bayonet lock (9) moves in the through groove of the DE section of the limiting device (7), the positive tension rod (1) is positioned at the slow vehicle position on the ground and is used for controlling the reverse propeller of the engine by the reverse propeller rod (2) in the ground area.
Specifically, the AB section through groove and the CD section through groove are both of circular arc hollow structures with the rotating shaft of the tension rod (1) as the center.
Specifically, the cam changing mechanism a functions as follows: when the positive tension rod (1) moves between a take-off slow vehicle and a slow flying vehicle and a ground slow vehicle, the cam conversion mechanism A transfers the force of the positive tension rod (1) through a mechanical shaft → the first tension rod mechanism (4) → the reverse paddle rotating component (8) → the accelerator angle sensor (10); when the reverse paddle lever (2) is from the retracted position → the slow flight vehicle unlocking position, the rotation motion of the reverse paddle lever (2) is not transmitted to the reverse paddle lever rotating part (8); when the reverse paddle lever (2) is in the unlocking position of the slow flying vehicle → the maximum reverse paddle, the rotary motion of the reverse paddle lever (2) is transmitted to the reverse paddle lever rotating component (8) to drive the accelerator angle sensor (10).
Specifically, the cam changing mechanism B functions as follows: when the positive tension rod (1) moves between the take-off slow-flying vehicle and the ground slow-flying vehicle, the cam conversion mechanism B transfers the force of the positive tension rod (1) through a mechanical shaft → the second tension rod mechanism (5) → the rolling bayonet lock (9) and drives the rolling bayonet lock (9) to move in the through grooves of the AB and CD sections; and when the reverse paddle lever (2) moves from the reverse paddle lever retracting position → the slow flying vehicle unlocking position → the maximum reverse paddle, the rolling bayonet (9) is driven to move in the BC and DE section through grooves.
Specifically, the accelerator angle sensor (10) is used for measuring the rotation angle of the forward tension rod (1) and the rotation angle of the reverse paddle rod (2).
Specifically, a rotating shaft of the throttle angle sensor (10) is meshed with a gear transmission device of the reverse paddle rotating component (8) through a gear.
Specifically, when the positive tension rod (1) is in the ground slow motion position and the flight slow motion position, one end of the reverse paddle rod (2) is connected with the cam conversion device (3), and the other end of the reverse paddle rod (2) rotates by taking the cam conversion device (3) as a circle center.
The invention provides a set of engine propeller which is controlled by two rods in a combined mode and has definite division of labor. The positive tension rod controls positive tension, and the reverse propeller rod controls reverse propeller of the propeller, so that a man-machine operation interface is improved, and man-machine efficiency is improved; the two rods are mechanically interlocked, so that misoperation is effectively prevented. The reverse paddle rod realizes two functions through one set of interlocking mechanism, function one: for the mechanical lock in the slow car position of flight, function two: and controlling the reverse propeller of the engine propeller. The throttle lever design of single pole form, throttle lever subregion is too much, and every district's working stroke is less, increases the manipulation degree of difficulty of unit, and the working stroke increase of positive pull rod and anti oar pole of this design has solved this problem well.
Drawings
FIG. 1 is a schematic diagram of a single-rod type throttle stand according to the prior art;
fig. 2 is a schematic structural diagram of a mechanical interlocking protection device of a double-rod type throttle platform of a turboprop aircraft according to the present application;
FIG. 3 is the interlocking intention of the positive tension rod and the negative paddle rod in the slow-vehicle flying-takeoff provided by the application;
FIG. 4 provides a schematic illustration of the present application with the anti-pitch drive shaft unlocked in a slow flight position;
fig. 5 is a schematic diagram of the interlocking of the forward tension rod and the reverse paddle rod during reverse paddle provided by the application.
Detailed Description
The set of engine propellers is controlled by the combination of two rods and is clearly divided into work, the forward tension rod controls the forward tension, and the reverse propeller rod controls the reverse propeller of the propeller, so that a man-machine control interface is improved, and the man-machine effect is improved; the two rods are mechanically interlocked, so that misoperation is effectively prevented. The two rods are respectively called: a positive tension rod (called the main rod for short) and a reverse paddle rod (called the main rod for short). Specifically, the method comprises the following steps:
in the range from slow flying to take-off (without slow flying position), the reverse paddle rod is kept at the reverse paddle rod retracting position, the reverse paddle rod is mechanically interlocked with the forward tension rod and moves along with the forward tension rod, and the forward tension rod drives the angle sensor to output an instruction to control the engine propeller.
In the range from the ground slow vehicle to the flight slow vehicle (without the ground slow vehicle position), the reverse paddle lever is kept at the flight slow vehicle unlocking position, and the reverse paddle lever is mechanically interlocked with the positive tension lever and moves along with the positive tension lever. The positive tension rod drives the angle sensor to output an instruction to control the engine propeller.
When the vehicle is in the ground slow vehicle position, the reverse paddle rod is pulled, the reverse paddle rod drives the angle sensor to output an instruction to control the engine propeller, and the positive tension rod is locked at the ground slow vehicle position and cannot move.
The forward tension rod and the reverse paddle rod are definite in labor division, a man-machine operation interface is improved, and man-machine efficiency is improved. The operating range of the positive tension rod is as follows: the ground slow-taking-off is used in the whole flight phase. The anti-oar bar is only used for ground landing or stopping take-off and the maximum anti-oar state is needed.
The mechanical lock for the slow-flying vehicle operates the positive tension rod in two areas: the air area, the control range is: the power flight slow vehicle-take-off is mainly used for flight stages such as take-off, climbing, cruising and landing; the ground area, the range of manipulation is: the ground slow vehicle-flying slow vehicle is mainly used in the gliding and landing flight stages.
The reverse paddle rod realizes two functions through one set of mechanism, function one: the mechanical lock is used for locking the position of the slow flying vehicle, prevents an air throttle lever from being lower than the slow flying vehicle by mistake, and enables the propeller to generate larger negative tension so as to meet the requirement of airworthiness regulation FAR 25.1155. And a second function: and controlling the reverse propeller of the engine propeller. The throttle lever is lowered to the ground by mistake and slowly enters the maximum reverse-oar state on the ground, so that the engine surges or foreign matters are sucked into the engine.
The working stroke of the positive tension rod and the reverse paddle rod is increased. In the single rod version throttle lever design, the throttle lever is divided into at least 3 regions: in the design scheme, the positive tension rod is divided into 2 areas: slow flying vehicle-take-off and slow flying vehicle-ground vehicle. Assuming that the total throttle strokes are the same, the angle range allocated to the corresponding area of the design is increased, and the problem that the operation difficulty of the unit is increased due to too many subareas and small working stroke of each area in the single-rod type throttle rod design is solved.
The mechanical interlock and mechanical lock in the flight shuttle position are implemented as follows (see fig. 2): the reverse paddle rod is connected with the pull rod mechanism 1 and the pull rod mechanism 2 through the cam conversion device, the pull rod mechanism 1 is finally connected with the angle sensor, the pull rod mechanism 2 drives the rolling bayonet lock, the bayonet lock moves in the track of the limiting device, the bayonet lock is mechanically connected with the forward tension rod, the bayonet lock is connected with a spring, and the spring elasticity enables the bayonet lock to move outwards along the radial direction of the forward tension rod.
In the range from slow flying to take-off (without slow flying position), the reverse paddle lever is kept at the reverse paddle lever retracting position and can not move, and the reverse paddle lever is mechanically interlocked with the positive tension lever and moves along with the positive tension lever. The positive tension rod drives an angle sensor to output instructions to control the engine propeller. When the positive tension rod moves in the range from slow flying to take-off (see fig. 3, the driving angle sensor sends an instruction to the engine propeller and drives the bayonet lock to move between the tracks A and B, the bayonet lock is limited in the front and back directions at the point A (take-off position) and the point B (slow flying position) of the track of the limiting device, so that the positive tension rod is limited to move only in the range from slow flying to take-off, if the reverse Jiang Gan is lifted, the bayonet lock can move up and down, but the track between the A and B limits the bayonet lock to move up and down, so that the reverse propeller rod is limited to the retraction position of the reverse propeller rod, and the mechanical interlocking of the positive tension rod and the reverse propeller rod is realized.
After the electromagnetic lock is unlocked, the reverse propeller shaft is pulled to the unlocking position of the slow flying vehicle, the bayonet lock is moved from B → C, and after the electromagnetic lock is unlocked, the positive propeller shaft can continuously move to the slow flying vehicle after C, so that the mechanical lock of the slow flying vehicle is unlocked by pulling the reverse propeller shaft, and the requirements of FAR 8978 zft 8978 are met.
When the slow vehicle moves from the flying slow vehicle to the takeoff direction and passes through the slow vehicle position, the spring generates an elastic force to enable the bayonet lock to automatically move from C → B to the point B and then enter the track between A and B.
In the range from slow flying vehicle to slow ground vehicle (see figure 5), the reverse paddle lever is kept at the unlocking position of the slow flying vehicle and cannot move, the reverse paddle lever and the positive tension lever are mechanically interlocked, and the principle is the same as the movement and limitation of the range from slow flying vehicle to takeoff.
In the ground slow position (see fig. 5), the positive tension rod is limited in the ground slow position through the rail and the bayonet lock and cannot move; the reverse paddle rod is pulled to the maximum reverse paddle position, the bayonet is driven from D → E, and the angle sensor is driven by the pull rod 2 to output a command to control the engine propeller.
The engine propeller provided by the application is controlled by the combination of the two rods, the labor division is clear, the forward tension rod controls the forward tension, the reverse propeller rod controls the reverse propeller of the propeller, a man-machine control interface is improved, and the man-machine effect is improved; and the two rods are mechanically interlocked, so that misoperation is effectively prevented. The working strokes of the positive tension rod and the negative paddle rod are increased, and the problem that the operation difficulty of the unit is increased due to too many subareas and small working stroke of each subarea in the single-rod throttle rod design is solved. Wherein, anti-oar pole realizes two functions, function one through one set of mechanism: as the mechanical lock of slow parking stall of flight, function two: and controlling the reverse propeller of the engine propeller.
Claims (8)
1. The utility model provides a mechanical interlocking protection device of turboprop two pole type throttle platform, its characterized in that, mechanical interlocking protection device includes positive pull rod (1), anti-oar pole (2), cam conversion equipment (3), first pull rod mechanism (4), second pull rod mechanism (5), throttle platform body (6), stop device (7), anti-oar pole rotary part (8), roll bayonet lock (9), throttle angle sensor (10), wherein:
the positive tension rod (1) is of a hollow rod-shaped structure, a cam conversion device (3) is arranged in the positive tension rod (1), and the cam conversion device (3) comprises a cam conversion mechanism A and a cam conversion mechanism B;
the lower end of the cam conversion device (3) is connected with a reverse paddle rod rotating component (8) through a first pull rod mechanism (4), the lower end of the cam conversion device (3) is connected with a rolling bayonet lock (9) through a second pull rod mechanism (5), one end of a reverse paddle rod (2) is connected with the side face of the cam conversion device (3), the reverse paddle rod (2) is connected with the first pull rod mechanism (4) through the cam conversion device (3), and the second pull rod mechanism (5) is connected;
a limiting device (7) is arranged inside the accelerator platform body (6), the limiting device (7) comprises an AB section through groove, a CD section through groove and a DE section through groove, the radius of the AB section through groove is larger than that of the CD section through groove, and the BC section through groove and the DE section through groove are both radial hollow clamping groove structures; the rolling bayonet lock (9) moves in the track of the limiting device (7); the lower end of the second pull rod mechanism (5) is connected with one end of a spring, a rolling clamping pin (9) is connected with the other end of the spring, and the elastic force of the spring enables the rolling clamping pin (9) to move outwards along the radial direction of the positive pull rod (1);
the fixed end of the accelerator angle sensor (10) is arranged on the accelerator table body (6), and the reverse paddle lever rotating component (8) drives the rotating shaft of the accelerator angle sensor (10) through gear engagement.
2. The mechanical interlock protection device of claim 1,
when the rolling bayonet lock (9) moves in the AB section through groove of the limiting device (7), the rolling bayonet lock is used for controlling the power of the engine for taking off to flying slow vehicles in an aerial operation area by the positive tension rod (1);
when the rolling clamping pin (9) moves in the CD section through groove of the limiting device (7), the rolling clamping pin is used for controlling the power of the engine from the flying slow vehicle to the ground slow vehicle by the positive tension rod (1) in a ground operation area;
when the rolling bayonet lock (9) moves in the BC section through groove of the limiting device (7), the positive tension rod (1) is positioned at the slow flying position and used for unlocking the positive tension rod (1) by the reverse propeller rod (2), so that the positive tension rod (1) enters the ground operation area from the air operation area;
when the rolling bayonet lock (9) moves in the through groove of the DE section of the limiting device (7), the positive tension rod (1) is positioned at the slow vehicle position on the ground and is used for controlling the reverse propeller of the engine by the reverse propeller rod (2) in the ground area.
3. The mechanical interlock protection device of claim 1, wherein the AB section through groove and the CD section through groove are both circular arc hollow structures centered on the rotation axis of the positive tension rod (1).
4. The mechanical interlock protection device of claim 1, wherein the cam conversion mechanism A functions to: when the positive tension rod (1) moves between a take-off slow vehicle and a slow flying vehicle and a ground slow vehicle, the cam conversion mechanism A transfers the force of the positive tension rod (1) through a mechanical shaft → the first tension rod mechanism (4) → the reverse paddle rotating component (8) → the accelerator angle sensor (10); when the reverse paddle lever (2) is from the retracted position → the slow flight vehicle unlocking position, the rotation motion of the reverse paddle lever (2) is not transmitted to the reverse paddle lever rotating part (8); when the reverse paddle lever (2) is in the unlocking position of the slow flight vehicle → the maximum reverse paddle, the rotary motion of the reverse paddle lever (2) is transmitted to the reverse paddle lever rotating component (8) to drive the accelerator angle sensor (10).
5. The mechanical interlock protection device of claim 1, wherein the cam conversion mechanism B functions to: when the positive tension rod (1) moves between the take-off slow-flying vehicle and the ground slow-flying vehicle, the cam conversion mechanism B transfers the force of the positive tension rod (1) through a mechanical shaft → the second tension rod mechanism (5) → the rolling bayonet lock (9) and drives the rolling bayonet lock (9) to move in the through grooves of the AB and CD sections; and when the reverse paddle lever (2) moves from the reverse paddle lever retracting position → the slow flying vehicle unlocking position → the maximum reverse paddle, the rolling bayonet (9) is driven to move in the BC and DE section through grooves.
6. Mechanical interlock protection device according to claim 1, characterized in that a throttle angle sensor (10) is used to measure the rotation angle of the positive tension bar (1) and the rotation angle of the negative pitch bar (2).
7. A mechanical interlock protection device according to claim 6, characterized in that the rotational axis of the throttle angle sensor (10) is driven by a gear in engagement with a gear transmission of the counter-blade rotating member (8).
8. The mechanical interlock protection device according to claim 3, wherein when the positive tension rod (1) is in the ground slow motion position and the flight slow motion position, one end of the reverse paddle rod (2) is connected with the cam conversion device (3), and the other end of the reverse paddle rod (2) rotates around the cam conversion device (3).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011611101.4A CN112623234B (en) | 2020-12-29 | 2020-12-29 | Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011611101.4A CN112623234B (en) | 2020-12-29 | 2020-12-29 | Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft |
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| CN112623234A CN112623234A (en) | 2021-04-09 |
| CN112623234B true CN112623234B (en) | 2022-10-28 |
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| CN202011611101.4A Active CN112623234B (en) | 2020-12-29 | 2020-12-29 | Mechanical interlocking protection device of double-rod-shaped throttle platform of turboprop aircraft |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4276018A1 (en) * | 2022-05-11 | 2023-11-15 | Ratier-Figeac SAS | Throttle control levers |
| CN117104510B (en) * | 2023-10-25 | 2023-12-22 | 北京蓝天航空科技股份有限公司 | Control lever assembly and flight control device |
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| CN112623234A (en) | 2021-04-09 |
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