CN109502012A - A kind of control system of light-duty sport plane - Google Patents
A kind of control system of light-duty sport plane Download PDFInfo
- Publication number
- CN109502012A CN109502012A CN201811638430.0A CN201811638430A CN109502012A CN 109502012 A CN109502012 A CN 109502012A CN 201811638430 A CN201811638430 A CN 201811638430A CN 109502012 A CN109502012 A CN 109502012A
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- China
- Prior art keywords
- control
- elevator
- control mechanism
- pedal
- aileron
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/042—Initiating means actuated personally operated by hand
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/02—Initiating means
- B64C13/04—Initiating means actuated personally
- B64C13/044—Initiating means actuated personally operated by feet, e.g. pedals
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
A kind of control system of light-duty sport plane, it include: elevator control mechanism, the elevator control mechanism includes elevator control control mechanism and elevator trimming control mechanism, the elevator control control mechanism is used to control elevator rapid sensitive, elevator trimming control mechanism is used to stablize elevator fine tuning control, the lifting action of two groups of control mechanism mating reaction control aircrafts；Aileron control mechanism, the aileron control mechanism control aileron movement, and aircraft is made to generate the athletic posture of inclination rolling；Wing flap control mechanism, the wing flap control mechanism control wing flap deflection increase lift to increase the area of aircraft wing；Turn to brake control mechanism, the steerings brake control mechanism includes rudder control mechanism, landing gear steering mechanism and undercarriage braking mechanism, be respectively used to the steering controlled aircraft in flight course, aircraft ground steering and aircraft ground brake.
Description
Technical field
The present invention relates to baby plane control system field, more specifically to a kind of control system of light-duty sport plane
System.
Background technique
Aircraft control system refers to the control command of transmitting driver or automatic pilot, driving rudder face and other mechanisms
With the system for controlling aircraft flight attitude.According to control command source, artificial manipulation can be divided into and automatically controlled.Artificial manipulation is again
Master control system and supplementary controlled system can be divided into, master control system is by control stick and pedal, i.e. central control mechanism comes
The operating mechanism of the elevator of aircraft, aileron and rudder is controlled to control aircraft flight path and posture.Supplementary controlled system
Including trimmer, wing flap, flap, adjustable stabilizer and wing sweep control mechanism etc., for controlling the movement of aircraft
State.
Master control system includes control system, aileron control system and rudder control system, controls aircraft evelvator, pair
The wing and rudder kick and generate the torque around three spatial axes of aircraft, so that aircraft is bowed accordingly by the intention of driver
It faces upward, tilt and yawing rotation.Supplementary controlled system is control system, and control wing flap deflection increases lift.And in addition to main control system
Except system and supplementary controlled system, steering and brake of the aircraft on ground are also required to be controlled by undercarriage.
Existing aircraft control system is much controlled by the way of automatically controlled since control content is more, although
Configuration aspects are simplified, but the automatically controlled control mode service life is shorter, and failure rate is higher, once breaking down will serious shadow
Ring the safety of aircraft.
Summary of the invention
The present invention provides a kind of control system of light-duty sport plane in view of the deficiencies of the prior art, and of the invention is light
The control system of type sport plane controls elevator control control mechanism and aileron control mechanism using bar assembly is driven, and uses
Pedal component controls rudder control mechanism, landing gear steering mechanism and undercarriage braking mechanism, is controlled using trim component
Elevator trimming control processed mechanism, entire control system are made of mechanical structure completely, guarantee the safety of aircraft control；And two
Driving bar assembly and the linkage of pedal component in a cockpit, it is ensured that two drivers can control aircraft, into one
Step guarantees safety.
The specific technical solution of the present invention is as follows, a kind of control system of light-duty sport plane, comprising:
Elevator control mechanism, the elevator control mechanism include elevator control control mechanism and elevator trimming control machine
Structure, the elevator control control mechanism are used to control elevator rapid sensitive, and elevator trimming control mechanism is used for
Fine tuning control, the lifting action of two groups of control mechanism mating reaction control aircrafts are stablized to elevator；
Aileron control mechanism, the aileron control mechanism control aileron movement, and aircraft is made to generate the athletic posture of inclination rolling；
Wing flap control mechanism, the wing flap control mechanism control wing flap deflection increase and rise to increase the area of aircraft wing
Power；
Turn to brake control mechanism, the steering brake control mechanism include rudder control mechanism, landing gear steering mechanism and
Undercarriage braking mechanism is respectively used to the steering controlled aircraft in flight course, aircraft in the steering on ground and aircraft on ground
The brake in face.
The control system of the light-duty sport plane includes for elevator, aileron, wing flap, aerial steering, ground as a result,
It turns to, the control of ground brake, all controls are all integrated in cockpit, and integrated level is high.
As a preference of the present invention, the elevator control control mechanism and the aileron control mechanism are by driving bar assembly
Control；The rudder control mechanism, the landing gear steering mechanism and the undercarriage braking mechanism are controlled by pedal component；
Elevator trimming control mechanism is controlled by trim component；The wing flap control mechanism is controlled by linear motor.
As a result, other than the wing flap control mechanism is automatically controlled, remaining described elevator control control mechanism, the liter
Jiang Duo trimming control mechanism, the aileron control mechanism, the rudder control mechanism, the landing gear steering mechanism and described
Undercarriage braking mechanism is controlled by mechanical structure, and securely and reliably, and wing flap is minimum for the safety effects of aircraft, therefore whole
Control system can ensure safety and stability.
As a preference of the present invention, the bar assembly that drives includes two groups of control sticks arranged side by side, manipulated described in two groups
Bar front end is connect by transition block with horizontal brace rod, and rear end is connected separately with control crank；It is solid below the horizontal brace rod
It is connected to vertical adjusting rod, the vertical adjusting rod is hinged with pedestal, pushes and pulls the control crank and is able to drive the vertical adjusting
Bar rotation before and after the pedestal；The control stick can be rotated relative to the transition block around axle center, below the control stick
It is connected with oscillating rod, the driving bar assembly is hinged with swinging disc, the oscillating rod and the swing between the oscillating rod
It is connected between disk by synchronising (connecting) rod, the swinging disc two sides are respectively equipped with cable wire connecting hole, and the swinging disc can follow institute
It states the rotation of control stick and swings.
The driving bar assembly is for the elevator control control mechanism and the aileron control mechanism at two as a result,
In cockpit can synchronously control, guarantee reliability.
As a preference of the present invention, the elevator control control mechanism passes through elevator driving member and the control stick group
Part is connected, and front and back pushes and pulls the downward shift that the control crank realizes elevator；The elevator driving member includes that elevator pushes away
Bar and transmission bridgeware, elevator push rod front end, which is connected on the vertical adjusting rod, to be located above the pedestal, rear end
It is connected by the transmission bridgeware with elevator skeleton.
As a preference of the present invention, the aileron control mechanism is connected by aileron driving member with the driving bar assembly,
The offset of the realization aileron of control crank described in left-right rotation；The aileron driving member includes aileron transmission rope and transmission conversion group
Part, the transmission transition components include drive plate and drive rod, the aileron transmission rope be connected to the cable wire connecting hole and
Between the drive plate, and between two drive plates in left and right, the oscillating rod swings by the aileron transmission steel
Strap moves the transmission disc spins, and the drive rod is connected between the drive plate and aileron skeleton, the rotation of the drive plate
Turn that the aileron skeleton is driven to deflect up and down.
As a preference of the present invention, the pedal component includes two groups of left pedal groups being articulated in rack and right pedal
Group, the left pedal group is connected the first left pedal of two operator seats in left and right with the second left pedal by left articulated shaft, described
Right pedal group is connected the first right pedal of the operator seat of left and right two and the second right pedal by right articulated shaft；The left articulated shaft
On be connected with left swing lever, be connected with right oscillating rod on the right articulated shaft.
The pedal component for the rudder control mechanism, the landing gear steering mechanism and described rises and falls as a result,
Frame braking mechanism in two cockpits can synchronously control, guarantee reliability.
As a preference of the present invention, the rudder control mechanism by left and right two transmission ropes respectively with the left swing
Lever is connected with the right oscillating rod, is connected at left and right sides of the other end and rudder skeleton of the transmission rope, steps on described
First left pedal and/or second left pedal, which are realized, deflects the pulling on the left of the rudder skeleton, steps on described first
Right pedal and/or second right pedal, which are realized, deflects the pulling on the right side of the rudder skeleton.
As a preference of the present invention, the left-hand rotation movement of the landing gear steering mechanism is pushed by left steering push rod, it is described
Left steering push rod both ends are articulated on the right side of nose-gear between first left pedal or second left pedal front side；It is described
Landing gear steering mechanism right-hand rotation movement pushed by right turn push rod, right turn push rod both ends be articulated with it is described before rise and fall
Between on the left of frame and on front side of first right pedal or second right pedal.
As a preference of the present invention, the undercarriage braking mechanism is mounted on main landing gear by brake fluid holding vessel
Checking cylinder by leather hose supply brake fluid, thus squeeze brake block realize brake；The brake fluid holding vessel supplies brake fluid
By the rotation for pedaling plate face of first left pedal, second left pedal, first right pedal or second right pedal
Power is provided.
As a preference of the present invention, the trim component includes the leveling wheel being set in cockpit, turbine and worm transmission
Mechanism and guide rod slide block mechanism, the leveling rotation kinetic energy enough pass through belt and drive worm screw in the turbine and worm transmission mechanism
It rotates, the turbine in the turbine and worm transmission mechanism passes through the guide rod in connected swing arm and the guide rod slide block mechanism
It is connected, is slidably matched between the sliding block and the guide rod in the guide rod slide block mechanism, and the sliding block is in the guide rod length
Reset spring is equipped between the both ends in direction and the guide rod；The sliding block and the elevator push rod are affixed.
Elevator can be finely adjusted by the trim component as a result, and keep the state of elevator, so that driving
The person of sailing is more stable for the adjusting of elevator, further increases safety.
In conclusion the invention has the following advantages:
The control system of light-duty sport plane of the invention controls elevator control control mechanism and pair using bar assembly is driven
Wing control mechanism is controlled rudder control mechanism, landing gear steering mechanism and undercarriage braking mechanism using pedal component, adopted
Elevator trimming control mechanism is controlled with trim component, entire control system is made of mechanical structure completely, guarantees aircraft control
The safety of system；And driving bar assembly and the linkage of pedal component in two cockpits, it is ensured that two drivers can be to winged
Machine is controlled, and is further ensured that safety.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the control system elevator control mechanism of the light-duty sport plane of the present invention；
Fig. 2 is that the control system of the light-duty sport plane of the present invention drives the structural schematic diagram of bar assembly；
Fig. 3 is structural representation of the control system elevator control mechanism of the light-duty sport plane of the present invention at transmission bridgeware
Figure；
Fig. 4 is the structural schematic diagram of the control system aileron control mechanism of the light-duty sport plane of the present invention；
Fig. 5 is structural representation of the control system aileron control mechanism of the light-duty sport plane of the present invention at transmission transition components
Figure；
Fig. 6 is that the control system of the light-duty sport plane of the present invention turns to the structural schematic diagram of brake control mechanism；
Fig. 7 is the structural schematic diagram of the control system pedal component of the light-duty sport plane of the present invention；
Fig. 8 is the control system pedal component of the light-duty sport plane of the present invention and the structural schematic diagram of transmission rope junction；
Fig. 9 is the control system rudder skeleton of the light-duty sport plane of the present invention and the structural schematic diagram of transmission rope junction；
Figure 10 is the structural schematic diagram of the control system trim component of the light-duty sport plane of the present invention；
Figure 11 is the structural schematic diagram of the control system landing gear steering mechanism of the light-duty sport plane of the present invention；
Figure 12 is the structural schematic diagram of the control system undercarriage braking mechanism of the light-duty sport plane of the present invention；
Figure 13 is the structural schematic diagram of the control system wing flap control mechanism of the light-duty sport plane of the present invention；
In figure, 1- elevator control mechanism, 11- elevator control control mechanism, 111- elevator driving member, 1111- elevator
Push rod, 1112- are driven bridgeware, 112- elevator skeleton, 12- elevator trimming control mechanism, 2- aileron control mechanism, 21-
Aileron driving member, 211- aileron transmission rope, 212- are driven transition components, 2121- drive plate, 2122- drive rod, 22- aileron
Skeleton, 3- wing flap control mechanism, 31- linear motor, 4- turn to brake control mechanism, 41- rudder control mechanism, 411- transmission
Cable wire, 412- rudder skeleton, 42- landing gear steering mechanism, 421- nose-gear, 422- left steering push rod, 423- right turn
Push rod, 43- undercarriage braking mechanism, 431- main landing gear, 432- brake fluid holding vessel, 433- leather hose, a- drive bar assembly,
A1- control stick, a11- oscillating rod, a2- horizontal brace rod, a3- control crank, the vertical adjusting rod of a4-, a5- pedestal, a6- transition
Block, a7- swinging disc, a71- cable wire connecting hole, a8- synchronising (connecting) rod, b- pedal component, b1- left pedal group, the left articulated shaft of b11-,
The first left pedal of b12-, the second left pedal of b13-, b14- left swing lever, b2- right pedal group, the right articulated shaft of b21-, b22- first
Right pedal, the second right pedal of b23-, the right oscillating rod of b24-, c- trim component, c1- leveling wheel, c2- turbine and worm transmission mechanism,
C3- guide rod slide block mechanism, c31- guide rod, c32- sliding block, c33- reset spring.
Specific embodiment
Below in conjunction with attached drawing, by specific embodiment, the invention will be further described.
Such as Fig. 1, Fig. 4, Fig. 6, Figure 13, a kind of control system of light-duty sport plane, comprising:
Elevator control mechanism 1, elevator control mechanism 1 include elevator control control mechanism 11 and elevator trimming control machine
Structure 12, elevator control control mechanism 11 be used for elevator rapid sensitive control, elevator trimming control mechanism 12 for pair
Elevator stablizes fine tuning control, the lifting action of two groups of control mechanism mating reaction control aircrafts；
Aileron control mechanism 2, aileron control mechanism 2 control aileron movement, and aircraft is made to generate the athletic posture of inclination rolling；
Wing flap control mechanism 3, wing flap control mechanism 3 controls wing flap deflection, to increase the area of aircraft wing, increases lift；
Brake control mechanism 4 is turned to, turning to brake control mechanism 4 includes rudder control mechanism 41, landing gear steering mechanism 42
With undercarriage braking mechanism 43, it is respectively used to steering, aircraft steering and aircraft on ground of the control aircraft in flight course
Brake on ground.
The control system of light-duty sport plane includes that elevator, aileron, wing flap, aerial steering, ground are turned as a result,
The control braked to, ground, all controls are all integrated in cockpit, integrated level height.
As shown in Figure 1, Figure 2, Fig. 4, Fig. 6, Fig. 7, Figure 10, Figure 11, Figure 12, elevator control control mechanism 11 and aileron control machine
Structure 2 is controlled by driving bar assembly a；Rudder control mechanism 41, landing gear steering mechanism 42 and undercarriage braking mechanism 43 are by foot
Pedal component b control；Elevator trimming control mechanism 12 is controlled by trim component c；Wing flap control mechanism 3 is controlled by linear motor 31
System.
As a result, other than wing flap control mechanism 3 is automatically controlled, remaining elevator control control mechanism 11, elevator trim
Control mechanism 12, aileron control mechanism 2, rudder control mechanism 41, landing gear steering mechanism 42 and undercarriage braking mechanism 43
It is controlled by mechanical structure, securely and reliably, and wing flap is minimum for the safety effects of aircraft, therefore whole control system can
Ensure safety and stability.
Such as Fig. 2, driving bar assembly a includes two groups of control stick a1 arranged side by side, and two groups of front ends control stick a1 pass through transition
Block a6 is connect with horizontal brace rod a2, and rear end is connected separately with control crank a3；Vertical tune is connected with below horizontal brace rod a2
Pole a4, vertical adjusting rod a4 and pedestal a5 are hinged, and push-and-pull control crank a3 is able to drive vertical adjusting rod a4 opposite base a5
Front and back rotation；Control stick a1 can be rotated relative to transition block a6 around axle center, be connected with oscillating rod a11 below control stick a1, be driven
Bar assembly a is hinged with swinging disc a7 between oscillating rod a11, is connected between oscillating rod a11 and swinging disc a7 by synchronising (connecting) rod a8
It connects, the two sides swinging disc a7 are respectively equipped with cable wire connecting hole a71, and swinging disc a7 can follow the rotation of control stick a1 and swing.
Driving bar assembly a is for elevator control control mechanism 11 and aileron control mechanism 2 in two cockpits as a result,
Can synchronously control, guarantee reliability.
As shown in Figure 1, Figure 2, Fig. 3, elevator control control mechanism 11 pass through elevator driving member 111 and driving bar assembly a phase
Even, front and back pushes and pulls the downward shift that control crank a3 realizes elevator；Elevator driving member 111 includes 1111 He of elevator push rod
It is driven bridgeware 1112,1111 front end of elevator push rod, which is connected on vertical adjusting rod a4, to be located above pedestal a5, and rear end passes through
Transmission bridgeware 1112 is connected with elevator skeleton 112.
Such as Fig. 4, Fig. 5, aileron control mechanism 2 is connected by aileron driving member 21 with bar assembly a is driven, left-right rotation manipulation
The offset of handle a3 realization aileron；Aileron driving member 21 includes aileron transmission rope 211 and transmission transition components 212, and transmission turns
Changing component 212 includes drive plate 2121 and drive rod 2122, and aileron transmission rope 211 is connected to cable wire connecting hole a71 and transmission
Between disk 2121, and between two drive plates 2121 in left and right, oscillating rod a11's swings by the drive of aileron transmission rope 211
Drive plate 2121 rotates, and drive rod 2122 is connected between drive plate 2121 and aileron skeleton 22, the rotation band of drive plate 2121
Dynamic about 22 aileron skeleton deflects.
If Fig. 7, pedal component b include two groups of left pedal group b1 being articulated in rack and right pedal group b2, left pedal group
B1 will control the first left pedal b12 and the second left pedal b13 connection of two operator seats, right pedal group by left articulated shaft b11
B2 passes through right articulated shaft b21 for the first right pedal b22 of the operator seat of left and right two and the second right pedal b23 connection；Left articulated shaft
It is connected with left swing lever b14 on b11, right oscillating rod b24 is connected on right articulated shaft b21.
Pedal component b is for rudder control mechanism 41, landing gear steering mechanism 42 and undercarriage braking mechanism 43 as a result,
In two cockpits can synchronously control, guarantee reliability.
Such as Fig. 6, Fig. 8, Fig. 9, rudder control mechanism 41 by two transmission ropes 411 in left and right respectively with left swing lever
B14 is connected with right oscillating rod b24, is connected at left and right sides of the other end and rudder skeleton 412 of transmission rope 411, steps on first
Left pedal b12 and/or the second left pedal b13 realizes that the pulling to 412 left side of rudder skeleton deflects, and steps on the first right pedal
B22 and/or the second right pedal b23 realizes that the pulling to 412 right side of rudder skeleton deflects.
If the left-hand rotation movement of Figure 11, landing gear steering mechanism 42 are pushed by left steering push rod 422, left steering push rod 422
Between both ends are articulated on front side of 421 right side of nose-gear and the first left pedal b12 or the second left pedal b13；Undercarriage turning machine
The right-hand rotation movement of structure 42 is pushed by right turn push rod 423,423 both ends of right turn push rod be articulated with the left side of nose-gear 421 and
Between on front side of first right pedal b22 or the second right pedal b23.
Such as Figure 12, undercarriage braking mechanism 43 gives the braking being mounted on main landing gear 431 by brake fluid holding vessel 432
Cylinder supplies brake fluid by leather hose 433, so that squeezing brake block realizes brake；Brake fluid holding vessel 432 supplies brake fluid by the
The powered rotation for pedaling plate face of one left pedal b12, the second left pedal b13, the first right pedal b22 or the second right pedal b23.
If Figure 10, trim component c include leveling wheel c1, turbine and worm transmission mechanism c2 and the guide rod being set in cockpit
Slide block mechanism c3, leveling wheel c1 rotation can drive the worm screw in turbine and worm transmission mechanism c2 to rotate by belt, turbine snail
Turbine in bar transmission mechanism c2 is connected by connected swing arm with one end guide rod c31 in guide rod slide block mechanism c3, and guide rod is sliding
Be slidably matched between sliding block c32 and guide rod c31 in block mechanism c3, and sliding block c32 guide rod c31 length direction both ends with lead
Reset spring c33 is equipped between bar c31；Sliding block c32 and elevator push rod 1111 are affixed.
Elevator can be finely adjusted by trim component c as a result, and keep the state of elevator, so that driving
Member is more stable for the adjusting of elevator, further increases safety.
Embodiment described above is only that preferred embodiments of the present invention will be described, not to design of the invention
It is defined with range.Without departing from the design concept of the invention, ordinary people in the field is to technical side of the invention
The all variations and modifications that case is made, should all drop into protection scope of the present invention, the claimed technology contents of the present invention,
Through being all described in the claims.
Claims (10)
1. a kind of control system of light-duty sport plane characterized by comprising
Elevator control mechanism (1), the elevator control mechanism (1) include elevator control control mechanism (11) and elevator
Trimming control mechanism (12), the elevator control control mechanism (11) are used to control elevator rapid sensitive, the lifting
Rudder trimming control mechanism (12) is used to stablize elevator fine tuning control, the lifting of two groups of control mechanism mating reaction control aircrafts
Movement；
Aileron control mechanism (2), the aileron control mechanism (2) control aileron movement, and aircraft is made to generate the movement of inclination rolling
Posture；
Wing flap control mechanism (3), wing flap control mechanism (3) the control wing flap deflection increase to increase the area of aircraft wing
Add lift；
It turns to brake control mechanism (4), the steering brake control mechanism (4) includes rudder control mechanism (41), undercarriage
Steering mechanism (42) and undercarriage braking mechanism (43) are respectively used to the steering controlled aircraft in flight course, aircraft on ground
The brake of the steering in face and aircraft on ground.
2. a kind of control system of light-duty sport plane according to claim 1, it is characterised in that: the elevator control
Control mechanism (11) and the aileron control mechanism (2) are controlled by driving bar assembly (a)；The rudder control mechanism (41),
The landing gear steering mechanism (42) and the undercarriage braking mechanism (43) are controlled by pedal component (b)；The elevator is matched
Flat control mechanism (12) is controlled by trim component (c)；The wing flap control mechanism (3) is controlled by linear motor (31).
3. a kind of control system of light-duty sport plane according to claim 2, it is characterised in that: the driving bar assembly
It (a) include two groups of control sticks (a1) arranged side by side, the front end (a1) of control stick described in two groups is connected by transition block (a6) and level
Extension bar (a2) connection, rear end is connected separately with control crank (a3)；Vertical adjusting is connected with below the horizontal brace rod (a2)
Bar (a4), the vertical adjusting rod (a4) and pedestal (a5) hingedly, push and pull the control crank (a3) be able to drive it is described vertical
Adjusting rod (a4) rotates before and after the pedestal (a5)；The relatively described transition block (a6) of the control stick (a1) can be around axle center
Rotation is connected with oscillating rod (a11) below the control stick (a1), the driving bar assembly (a) the oscillating rod (a11) it
Between be hinged with swinging disc (a7), connect between the oscillating rod (a11) and the swinging disc (a7) by synchronising (connecting) rod (a8), institute
It states the two sides swinging disc (a7) to be respectively equipped with cable wire connecting hole (a71), the swinging disc (a7) can follow the control stick (a1)
Rotation and swing.
4. a kind of control system of light-duty sport plane according to claim 3, it is characterised in that: the elevator control
Control mechanism (11) is connected by elevator driving member (111) with the driving bar assembly (a), and front and back pushes and pulls the control crank
(a3) downward shift of elevator is realized；The elevator driving member (111) includes elevator push rod (1111) and transmission conversion
Part (1112), elevator push rod (1111) front end, which is connected on the vertical adjusting rod (a4), to be located on the pedestal (a5)
Side, rear end are connected by the transmission bridgeware (1112) with elevator skeleton (112).
5. a kind of control system of light-duty sport plane according to claim 3, it is characterised in that: the aileron controls machine
Structure (2) is connected by aileron driving member (21) with the driving bar assembly (a), and control crank described in left-right rotation (a3) is realized secondary
The offset of the wing；The aileron driving member (21) includes aileron transmission rope (211) and transmission transition components (212), the transmission
Transition components (212) include drive plate (2121) and drive rod (2122), and the aileron transmission rope (211) is connected to the steel
Between rope connecting hole (a71) and the drive plate (2121), and between two drive plates (2121) in left and right, the swing
The aileron transmission rope (211) that swings by of bar (a11) drives drive plate (2121) rotation, the drive rod
(2122) it is connected between the drive plate (2121) and aileron skeleton (22), described in the rotation drive of the drive plate (2121)
Aileron skeleton (22) deflects up and down.
6. a kind of control system of light-duty sport plane according to claim 2, it is characterised in that: the pedal component
It (b) include two groups of left pedal groups (b1) and right pedal group (b2) being articulated in rack, the left pedal group (b1) passes through left hinge
Spindle (b11) connects the first left pedal (b12) of the operator seat of left and right two and the second left pedal (b13), the right pedal group
(b2) the first right pedal (b22) of the operator seat of left and right two and the second right pedal (b23) are connected by right articulated shaft (b21)；
It is connected with left swing lever (b14) on the left articulated shaft (b11), is connected with right oscillating rod on the right articulated shaft (b21)
(b24).
7. a kind of control system of light-duty sport plane according to claim 6, it is characterised in that: the rudder control
Mechanism (41) by left and right two transmission ropes (411) respectively with the left swing lever (b14) and the right oscillating rod (b24) phase
Even, it is connected at left and right sides of the other end with rudder skeleton (412) of the transmission rope (411), steps on first left pedal
(b12) and/or second left pedal (b13) is realized and is deflected to the pulling on the left of the rudder skeleton (412), is stepped on described
First right pedal (b22) and/or second right pedal (b23) are realized inclined to the pulling on the right side of the rudder skeleton (412)
Turn.
8. a kind of control system of light-duty sport plane according to claim 6, it is characterised in that: the undercarriage turns to
The left-hand rotation movement of mechanism (42) is pushed by left steering push rod (422), and left steering push rod (422) both ends are risen and fallen before being articulated with
Between on the right side of frame (421) and on front side of first left pedal (b12) or second left pedal (b13)；The undercarriage turns to
Mechanism (42) right-hand rotation movement by right turn push rod (423) push, right turn push rod (423) both ends be articulated with it is described before
Between on the left of undercarriage (421) and on front side of first right pedal (b22) or second right pedal (b23).
9. a kind of control system of light-duty sport plane according to claim 6, it is characterised in that: the undercarriage brake
Mechanism (43) gives the checking cylinder being mounted on main landing gear (431) to supply by leather hose (433) by brake fluid holding vessel (432)
Brake fluid, so that squeezing brake block realizes brake；Brake fluid holding vessel (432) the supply brake fluid is by first left pedal
(b12), second left pedal (b13), first right pedal (b22) or second right pedal (b23) pedal plate face
Powered rotation.
10. a kind of control system of light-duty sport plane according to claim 4, it is characterised in that: the trim component
It (c) include the leveling wheel (c1), turbine and worm transmission mechanism (c2) and guide rod slide block mechanism (c3) being set in cockpit, it is described
Leveling wheel (c1) rotation can drive the worm screw in the turbine and worm transmission mechanism (c2) to rotate by belt, the turbine snail
Turbine in bar transmission mechanism (c2) passes through connected swing arm and the one end guide rod (c31) phase in the guide rod slide block mechanism (c3)
Even, it is slidably matched between the sliding block (c32) and the guide rod (c31) in the guide rod slide block mechanism (c3), and the sliding block
(c32) reset spring (c33) is equipped between the both ends and the guide rod (c31) of the guide rod (c31) length direction；The cunning
Block (c32) and the elevator push rod (1111) are affixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811638430.0A CN109502012A (en) | 2018-12-29 | 2018-12-29 | A kind of control system of light-duty sport plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811638430.0A CN109502012A (en) | 2018-12-29 | 2018-12-29 | A kind of control system of light-duty sport plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109502012A true CN109502012A (en) | 2019-03-22 |
Family
ID=65757045
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811638430.0A Withdrawn CN109502012A (en) | 2018-12-29 | 2018-12-29 | A kind of control system of light-duty sport plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109502012A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654531A (en) * | 2019-09-19 | 2020-01-07 | 中国商用飞机有限责任公司 | Pedal system for controlling rudder of airplane and control method thereof |
| CN113022844A (en) * | 2019-12-25 | 2021-06-25 | 海鹰航空通用装备有限责任公司 | Linkage mechanism for tail wheel steering and rudder |
| CN113184168A (en) * | 2021-05-14 | 2021-07-30 | 陕西飞机工业有限责任公司 | Elevator adjustment sheet control system |
-
2018
- 2018-12-29 CN CN201811638430.0A patent/CN109502012A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110654531A (en) * | 2019-09-19 | 2020-01-07 | 中国商用飞机有限责任公司 | Pedal system for controlling rudder of airplane and control method thereof |
| CN110654531B (en) * | 2019-09-19 | 2022-05-03 | 中国商用飞机有限责任公司 | Pedal system for controlling rudder of airplane and control method thereof |
| CN113022844A (en) * | 2019-12-25 | 2021-06-25 | 海鹰航空通用装备有限责任公司 | Linkage mechanism for tail wheel steering and rudder |
| CN113184168A (en) * | 2021-05-14 | 2021-07-30 | 陕西飞机工业有限责任公司 | Elevator adjustment sheet control system |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190322 |
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| WW01 | Invention patent application withdrawn after publication |