Aircraft rudder limiting module, stall protection device and single-engine propeller aircraft

Abstract

The utility model discloses an aircraft rudder limiting module, a stall protection system and a single-engine propeller aircraft, and the aircraft rudder limiting module comprises a rudder limiter, a rudder control mechanism and a mounting support. The ignition control module activates the rudder limiting stopper by receiving aircraft engine power data and stall warning signals, a plunger of the rudder limiting stopper moves to a set position and is locked after the rudder limiting stopper is activated, a limiting column controls the rudder control mechanism, the rudder control mechanism controls a rudder to stop through a rocker arm connected with the rudder control mechanism, and the rudder control mechanism controls the rudder to stop. The rudder limiting function is achieved, tail rotation or deep stall during flight is avoided, and therefore the safety of the aircraft is remarkably improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft stall protection control, and in particular relates to an aircraft rudder limit module, a stall protection device and a single-engine propeller aircraft. Background Art

[0002] Stall means that when an aircraft is flying in the air, due to unstable airflow or too low flight speed, the wings lose lift and cannot maintain normal flight status. After a stall occurs, the aircraft's control performance will drop sharply and the aircraft will lose control. At this time, the pilot needs to take correct measures immediately to restore lift as soon as possible to avoid crashing. Usually, pilots will take measures such as accelerating and changing the nose attitude to recover. Pilots need to receive stall / spin recovery training.

[0003] For aircraft with mechanical control systems, the inherent stall characteristics of the aircraft may pose a risk of entering a stall and deviation state. There are three main methods of stall protection: text warning, voice warning and stick shaker warning. Due to weather conditions, pilot reaction time and misoperation, the above methods cannot completely prevent the aircraft from entering a stall state. Especially for single-engine propeller aircraft, the rudder is affected by the propeller slipstream to cause the aircraft to slide to one side. The rudder travel to the sideslip side must be limited, otherwise the stall of the aircraft will be aggravated. Summary of the invention

[0004] In order to prevent the aircraft from entering a stall state, limit the pilot's erroneous operation in an emergency state and control the aircraft away from the stall boundary, thereby improving the flight safety of the aircraft, the utility model provides an aircraft rudder limit module, including:

[0005] A rudder limiter, a rudder control mechanism, and a mounting support, wherein the rudder limiter is connected to the rudder control mechanism via the mounting support, the rudder limiter comprises a solenoid valve, a return spring, a plunger, a crank rocker arm, and a limit column, the solenoid valve is connected to one end of the return spring, the other end of the return spring is connected to the plunger, the crank rocker arm is connected to the limit column, the rudder control mechanism comprises a mounting rocker arm and a connecting rocker arm, the mounting rocker arm is connected to the mounting support, and the connecting rocker arm is connected to the rudder.

[0006] Optionally, when the coil inside the solenoid valve is energized, the electromagnetic force generated acts on the plunger, and the plunger moves to the set position and is locked, and the crank rocker arm connected to the plunger moves toward the rudder control mechanism, and the rudder control mechanism rotates normally to one side, but when the rudder control mechanism rotates to the other side, the mounting rocker arm contacts the limit column on the crank rocker arm, and the contact position is the stop position of the rudder control mechanism. After the rudder operating mechanism stops, the travel of one side of the rudder connected by the connecting rocker arm is restricted, thereby realizing the rudder limit function.

[0007] Optionally, the limit column on the crank rocker arm is located on the left or right side of the mounting rocker arm of the rudder control mechanism.

[0008] This patent also provides an aircraft stall protection device, including:

[0009] A stall warning module, an ignition control module and an aircraft rudder limit module, wherein one end of the ignition control module is connected to the stall warning module, and the other end is connected to the aircraft rudder limit module;

[0010] The aircraft rudder limit module comprises: a rudder limiter, a rudder control mechanism, and a mounting support, wherein the rudder limiter is connected to the rudder control mechanism via the mounting support, the rudder limiter comprises a solenoid valve, a return spring, a plunger, a crank rocker arm and a limit column, the solenoid valve is connected to one end of the return spring, the other end of the return spring is connected to the plunger, the crank rocker arm is connected to the limit column, the rudder control mechanism comprises a mounting rocker arm and a connecting rocker arm, the mounting rocker arm is connected to the mounting support, and the connecting rocker arm is connected to the rudder;

[0011] The stall warning module obtains a stall sensor signal and outputs a stall warning signal when the aircraft stalls;

[0012] The ignition control module receives engine power data and a stall warning signal, and outputs a rudder limit control signal;

[0013] The aircraft rudder limit module receives a rudder limit control signal and controls the rudder limiter to enable or disable the rudder limit function.

[0014] Optionally, the stall warning module includes a stall warning port, a stall warning sensor, a locking relay, a locking micro switch, an alarm module, and a stick shaker. The stall warning port is installed at the leading edge of the wing, the stall alarm is connected to the stall warning port, the locking relay is arranged between the stall warning sensor and the alarm module, the locking micro switch is connected to the locking relay, the alarm module is connected to the locking relay, and the stick shaker is installed on the control column.

[0015] Optionally, the ignition control module includes a single chip microcomputer.

[0016] This patent also provides a single-engine propeller aircraft with the aircraft stall protection device. When the propeller of the single-engine propeller aircraft rotates clockwise when viewed from the driver's direction, the limit column on the crank rocker arm is located at the installation rocker arm of the rudder control mechanism and is arranged relative to the left side of the driver, thereby realizing the left side limit of the rudder; when the propeller of the single-engine propeller aircraft rotates counterclockwise when viewed from the driver's direction, the limit column on the crank rocker arm is located at the installation rocker arm of the rudder control mechanism and is arranged relative to the right side of the driver, thereby realizing the right side limit of the rudder.

[0017] In summary, the aircraft rudder limit module and stall protection device described in this application have the following advantages:

[0018] 1. The aircraft rudder limiter module of the present invention can limit the pilot's erroneous operation in an emergency state and control the aircraft away from the stall boundary, thereby significantly improving the safety of the aircraft;

[0019] 2. The ignition control module of the aircraft stall protection system of the present invention receives engine power data and stall warning signals, outputs rudder limit control signals and issues text warnings, voice warnings, and stick shaker warnings, and the locking relay implements text, voice, tactile stall warnings and stall warning retention to prevent the aircraft from entering a stall / spin state;

[0020] 3. The aircraft stall protection system of the present invention is connected in parallel to the control system of a single-engine propeller aircraft. The system can be installed by only partially modifying the control system, which will not affect the normal operation of the flight control system and can be widely applied to mechanical control systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 This is a schematic diagram of the structure of the rudder limiter module of the utility model embodiment;

[0023] Figure 2 It is a structural diagram of each module of the aircraft stall protection system according to an embodiment of the utility model. DETAILED DESCRIPTION

[0024] In order to make the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0025] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0026] Embodiment 1:

[0027] Aircraft rudder limiter module structure and working mode

[0028] Aircraft rudder limiter module, such as Figure 1 As shown, including:

[0029] A rudder limiter 1, a rudder control mechanism 2, and a mounting support 3, wherein the rudder limiter 1 comprises a solenoid valve 101, a return spring 102, a plunger 103, a crank rocker arm 104, and a limit column 105; the rudder limiter 1 is connected to the rudder control mechanism 2 via the mounting support 3; the rudder control mechanism 2 comprises a mounting rocker arm 201 and a connecting rocker arm 202; the rudder control mechanism 2 is provided with a connecting rocker arm 202 connected to the rudder.

[0030] In order to avoid the aircraft from continuing to enter a spin or deep stall after a stall, especially to prevent flight trainees from making operational errors when recovering from a stall, a rudder travel limitation function is set in the system, and a rudder limiter 1 is connected in parallel to the rudder control system. When the rudder limiter 1 is activated, a new stop position is imposed on the moving parts of the rudder control system to limit the rudder travel.

[0031] During the aircraft operation phase, when the engine power exceeds a certain threshold and the stall alarm is continuously activated for more than a set time, the rudder limit function is turned on and remains in the limited state; when the engine power drops to a certain threshold or the stall alarm stops for a set time, the rudder limit function is released.

[0032] The rudder limit function is implemented as follows:

[0033] When the engine power exceeds a certain threshold and the stall alarm is continuously activated for more than a set time, the rudder limiter 1 receives an activation signal, the coil inside the solenoid valve 101 is energized, and the generated electromagnetic force acts on the plunger 103, the plunger 103 moves to the set position and locks, and the crank rocker arm 104 connected to the plunger 103 moves toward the rudder control mechanism 2, and the rudder control mechanism 2 rotates normally to one side, but when the rudder control mechanism 2 rotates to the other side, the mounting rocker arm 201 contacts the limit column 105 on the crank rocker arm 104, and the contact position is the stop position of the rudder control mechanism 2. After the rudder control mechanism 2 stops, the travel of the rudder side connected by the connecting rocker arm 202 is limited, thereby realizing the rudder limit function.

[0034] The method to release the rudder limit function is:

[0035] When the engine power drops to a certain threshold or the stall alarm stops for a set time, the rudder limiter 1 receives a release signal, the coil inside the solenoid valve 101 is de-energized, no electromagnetic force acts on the plunger 103, and the plunger 103 extends to the initial position under the spring force of the return spring 102. The crank rocker arm 104 is lifted in the opposite direction of the rudder control mechanism 2. The rudder control mechanism 2 can rotate freely without being restricted by the stop column 105, and the rudder limit function is released.

[0036] The rudder limiter module can realize the rudder limit function, limit the pilot's erroneous operation in an emergency and control the aircraft away from the stall boundary, thereby significantly improving the safety of the aircraft.

[0037] Embodiment 2:

[0038] An aircraft stall protection device, such as Figure 2 As shown, including:

[0039] A stall warning module 10, an ignition control module 20 and a rudder limit module 30, wherein one end of the ignition control module 20 is connected to the stall warning module 10, and the other end is connected to the rudder limit module 30;

[0040] The stall warning module 10 includes a stall warning port, a stall warning sensor, a locking relay, a locking micro switch, a warning module, and a stick shaker. The stall warning port is installed at the leading edge of the wing, the stall warning device is connected to the stall warning port, the locking relay is arranged between the stall warning sensor and the warning module, the locking micro switch is connected to the locking relay, the warning module is connected to the locking relay, and the stick shaker is installed on the control column. Its working method is: when the aircraft stalls, the pressure signal of the wing stall warning port is collected through the stall warning sensor. When the airflow at the leading edge of the wing reaches the stall warning design pressure difference, the stall warning sensor is triggered electrically to provide trigger information, namely, the stall warning signal, to the warning module of the aircraft avionics system, and a text warning and a voice warning are issued on the display. At the same time, the stick shaker control box collects the trigger signal of the stall warning sensor to control the operation of the stick shaker. When the stall warning sensor is triggered, the stick shaker control box detects the trigger signal and starts the stick shaker with an eccentric counterweight motor, and rotates the motor back and forth, thereby generating obvious vibration on the joystick, forming a tactile stall warning, which attracts the pilot's attention and prompts the pilot to take corresponding measures.

[0041] In order to maintain a continuous and effective stall warning signal, especially when the stall warning may work intermittently during a rough or erroneous stall recovery (the control stick is close to the maximum stroke of the push rod), a lockout relay and a lockout microswitch are set between the stall warning sensor and the warning module.

[0042] The locking micro switch is installed on the control stick. By operating the control stick to correct the stall, the change of the control stick position will cause the locking micro switch state to change, thereby causing the stall warning signal to be maintained or released. When the stall warning signal provided by the locking micro switch and the stall warning sensor are both activated, the locking relay detects the signal and provides a continuous stall warning signal to the stall warning module 10 to realize the stall warning holding function; when the control stick moves to the position where the locking micro switch is disconnected or the stall warning signal disappears, the stall warning holding function is released.

[0043] The ignition control module 20 includes a single chip microcomputer, and the ignition control module 20 receives engine power data and stall warning signals. When the aircraft is in the operation stage, the ignition control module 20 detects that the aircraft engine power exceeds a certain threshold and the stall warning continues to be activated for more than a certain set time, and will output a control signal to activate the rudder limiter 1, mechanically reduce the rudder travel, and once the rudder limiter 1 is turned on, the rudder limiter 1 will remain in the limit state; until the ignition control module 20 detects that the aircraft engine power drops below a certain threshold or the stall warning has stopped for a certain set time, the ignition control module 20 outputs a control signal, the rudder limiter 1 stops working, the rudder travel is restored, and the rudder limit state is released.

[0044] The aircraft rudder limiting module 30 is the aircraft rudder limiting module described in the first embodiment.

[0045] Example 3: Single-engine propeller aircraft

[0046] The present invention also provides a single-engine propeller aircraft with the aircraft stall protection system. When the propeller of the single-engine propeller aircraft rotates clockwise when viewed from the driver's direction, the limit post 105 on the crank rocker arm 104 is located at the mounting rocker arm 201 of the rudder control mechanism 2 and is arranged relative to the left side of the driver, thereby realizing left-side limiting of the rudder; when the propeller of the single-engine propeller aircraft rotates counterclockwise when viewed from the driver's direction, the limit post 105 on the crank rocker arm 104 is located at the mounting rocker arm 201 of the rudder control mechanism 2 and is arranged relative to the right side of the driver, thereby realizing right-side limiting of the rudder.

[0047] In summary, the utility model discloses an aircraft rudder limit module and a stall protection device. When the aircraft stalls, the ignition control module activates the rudder limiter by receiving the aircraft engine power data and the stall warning signal. After the rudder limiter is activated, its plunger moves to the set position and locks, and the limit column controls the rudder control mechanism. The rudder control mechanism controls the rudder stop through its connecting rocker arm to realize the rudder limit function, avoid the flight from entering a tailspin or a deep stall, and thus significantly improve the safety of the aircraft.

[0048] Finally, it should be noted that any modification or equivalent replacement of part or all of the technical features based on the device structure of this patent and the technical solution of the described embodiment, which does not deviate from the essence of the corresponding technical solution of this patent, belongs to the patent scope of the device structure of this patent and the described implementation scheme.

Claims

1. An aircraft rudder limit module, characterized in that: include: A rudder limiter, a rudder control mechanism, and a mounting support, wherein the rudder limiter is connected to the rudder control mechanism via the mounting support, the rudder limiter comprises a solenoid valve, a return spring, a plunger, a crank rocker arm, and a limit column, the solenoid valve is connected to one end of the return spring, the other end of the return spring is connected to the plunger, the crank rocker arm is connected to the limit column, the rudder control mechanism comprises a mounting rocker arm and a connecting rocker arm, the mounting rocker arm is connected to the mounting support, and the connecting rocker arm is connected to the rudder.

2. The aircraft rudder limit module according to claim 1, characterized in that: When the coil inside the solenoid valve is energized, the electromagnetic force generated acts on the plunger, and the plunger moves to the set position and is locked. The crank rocker arm connected to the plunger moves toward the rudder control mechanism, and the rudder control mechanism rotates normally to one side. However, when the rudder control mechanism rotates to the other side, the mounting rocker arm contacts the limit post on the crank rocker arm, and the contact position is the stop position of the rudder control mechanism. After the rudder control mechanism stops, the travel of one side of the rudder connected by the connecting rocker arm is restricted, thereby realizing the rudder limit function.

3. The aircraft rudder limit module according to claim 1, characterized in that: The limiting column on the crank rocker arm is located on the left side or right side of the mounting rocker arm of the rudder control mechanism.

4. An aircraft stall protection device, characterized in that: include: A stall warning module, an ignition control module and an aircraft rudder limit module, wherein one end of the ignition control module is connected to the stall warning module, and the other end is connected to the aircraft rudder limit module; The aircraft rudder limit module comprises: a rudder limiter, a rudder control mechanism, and a mounting support, wherein the rudder limiter is connected to the rudder control mechanism via the mounting support, the rudder limiter comprises a solenoid valve, a return spring, a plunger, a crank rocker arm and a limit column, the solenoid valve is connected to one end of the return spring, the other end of the return spring is connected to the plunger, the crank rocker arm is connected to the limit column, the rudder control mechanism comprises a mounting rocker arm and a connecting rocker arm, the mounting rocker arm is connected to the mounting support, and the connecting rocker arm is connected to the rudder; The stall warning module obtains a stall sensor signal and outputs a stall warning signal when the aircraft stalls; The ignition control module receives engine power data and a stall warning signal, and outputs a rudder limit control signal; The aircraft rudder limit module receives a rudder limit control signal and controls the rudder limiter to enable or disable the rudder limit function.

5. The aircraft stall protection device according to claim 4, characterized in that: The stall warning module includes a stall warning port, a stall warning sensor, a locking relay, a locking micro switch, a warning module, and a stick shaker. The stall warning port is installed at the leading edge of the wing, the stall warning device is connected to the stall warning port, the locking relay is arranged between the stall warning sensor and the warning module, the locking micro switch is connected to the locking relay, the warning module is connected to the locking relay, and the stick shaker is installed on the control column.

6. The aircraft stall protection device according to claim 4, characterized in that: The ignition control module includes a single chip microcomputer.

7. A single-engine propeller aircraft having an aircraft stall protection device as claimed in any one of claims 4 to 6, characterized in that: When the propeller of the single-engine propeller aircraft rotates clockwise when viewed from the pilot's direction, the limit post on the crank rocker arm is located at the installation rocker arm of the rudder control mechanism and is arranged relative to the pilot's left side, thereby realizing the left side limit of the rudder; when the propeller of the single-engine propeller aircraft rotates counterclockwise when viewed from the pilot's direction, the limit post on the crank rocker arm is located at the installation rocker arm of the rudder control mechanism and is arranged relative to the pilot's right side, thereby realizing the right side limit of the rudder.

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