CN109436301A - The trimming system of aircraft - Google Patents
The trimming system of aircraft Download PDFInfo
- Publication number
- CN109436301A CN109436301A CN201811617637.XA CN201811617637A CN109436301A CN 109436301 A CN109436301 A CN 109436301A CN 201811617637 A CN201811617637 A CN 201811617637A CN 109436301 A CN109436301 A CN 109436301A
- Authority
- CN
- China
- Prior art keywords
- elevator
- rod
- control
- worm gear
- push rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
-
- 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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- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to airplane trim systems.Airplane trim system, for finely tuning aerial statue of the tilt angle of simultaneously positioning stablity elevator with steady aircraft normal flight when, including matching flat seat, being set to the leveling wheel with flat seat, worm gear structure and outflow structure；Rotation of the leveling wheel by one end of force transfer element connecting worm to control the worm screw, worm screw unidirectionally turn worm gear, and the axis of worm gear and the transfer piece for spreading out of structure are connected.Trimming system of the invention effectively can generate fine tuning to elevator, be different from the control system of elevator, this fine tuning will not generate rebound；Trimming system of the invention can effectively form buffer function, to reduce the strength demand to driver, can also reduce fatigue strength of the driver in long drives；Also damage of the excessive strength of driver to elevator control system can be effectively buffered, service life is effectively improved.
Description
Technical field
The present invention relates to control systems when a kind of baby plane state of flight, especially airplane trim system.Belong to winged
Machine flight Machinery Control System technical field.
Background technique
Flight 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
Primary control circuit and secondary control system can be divided into, primary control circuit 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.Secondary control system
Including trimmer, wing flap, flap, adjustable stabilizer and wing sweep control mechanism etc., for controlling the movement of aircraft
State.
Primary control circuit includes elevator-control system, Aileron control system and rudder control system, controls aircraft liter
It drops rudder, aileron and rudder kick and generates the torque around three spatial axes of aircraft, aircraft is made to carry out phase by the intention of driver
Pitching, inclination and the yawing rotation answered.Secondary control system is flap control system and elevator trimming system；Flap control system
System control wing flap deflection, increases lift；Elevator trimming system is used to finely tune neutral position of the elevator in flat fly, to adjust
It is flat winged to save constant speed of the aircraft under different conditions and environment (including air flow condition and speed state).Control stick control is secondary
The wing, lifting rudder kick, two pedal pedal controls rudder kick, and electric motor control wing flap deflects.
The control of aircraft evelvator is mainly realized by control stick.Aircraft is in normal flight, the minor adjustments of elevator
The flight attitude that aircraft can more be significantly affected, since the precision of manual control control stick is inadequate and cannot keep continual and steady
Pull rod operation can make the generation of aircraft normal flight jolt, so need to carry out further finely positioning adjusting to elevator,
Fly so that (including air flow condition and speed state) stabilization is flat under different conditions and environment.
Summary of the invention
The invention solves the above problems, to propose a kind of airplane trim system.
Technical proposal that the invention solves the above-mentioned problems is as follows:
Airplane trim system, it is aerial when for finely tuning the tilt angle of simultaneously positioning stablity elevator with steady aircraft normal flight
Posture, including matching flat seat, being set to the leveling wheel with flat seat, worm gear structure and outflow structure；The leveling wheel is logical
Rotation of the one end of force transfer element connecting worm to control the worm screw is crossed, worm screw unidirectionally turns worm gear, the axis of worm gear and institute
The transfer piece for stating outflow structure is connected；On the basis of vertical line, the adjustable range of transfer piece setting is in ± 30 °.
As above-mentioned technical proposal further preferred, the adjustable range of transfer piece setting is in ± 15 °.
As a preferred embodiment of the above technical solution, the sliding block that the outflow structure further includes guide rod, is set on the guide rod
And it is set in the guide rod and is located at the first spring and second spring of the sliding block two sides；One end of the transfer piece
It is connected on the axis of worm gear, the other end is connected with one end of the guide rod；The sliding block and aircraft evelvator control system
Linkage.
It as a preferred embodiment of the above technical solution, further include the restriction mechanism of leveling wheel.The restriction mechanism is a micro- resistance machine
Structure can avoid leveling wheel in nobody control and issue the control that life is freely rotated, but not driver is interfered to take turns leveling.
As a preferred embodiment of the above technical solution, the force transfer element is transmission belt.
As a preferred embodiment of the above technical solution, the aircraft evelvator control system is pushed away including driving bar assembly, elevator
Bar, transmission bridgeware and elevator skeleton；Driving bar assembly includes control crank, control stick, horizontal brace rod, vertical adjusting rod
And installation pedestal；Vertical adjusting rod lower end is hinged in installation pedestal, and upper end is mutually fixed with horizontal brace rod, horizontal brace rod
Both ends are connect with one end of two control cranks respectively, the other end setting of the control crank control crank；Elevator pushes away
The lower part of the vertical adjusting rod is arranged in one end of bar, and the other end of elevator push rod passes through transmission bridgeware and the lifting
The connection of rudder skeleton；So that making elevator generate angular deflection when pushing or pulling on the control crank.
As a preferred embodiment of the above technical solution, on the basis of vertical line, the angular deflection range of elevator is in 30 °.
As a preferred embodiment of the above technical solution, the elevator push rod includes preceding push rod and rear push-rod, preceding push rod and pusher
Pass through a conversion component connection between bar；The conversion component includes that fixing seat and one end are hinged on the fixing seat other end point
Not She You forward and backward interconnecting piece driver blade, the preceding interconnecting piece and the preceding push rod are hinged, it is described after interconnecting piece and the pusher
Bar is hinged.
As a preferred embodiment of the above technical solution, the linkage portion that the sliding block is set to aircraft evelvator control system is mounted on institute
On the driver blade or rear push-rod stated.
For aircraft in normal flight, air drag generates wind pressure, and wind pressure can generate some reactions to the control of elevator
Power resists the reaction force and needs driver by holding control stick to balance.I.e. under state of flight, when being adjusted to elevator,
Elevator can be replied voluntarily, to maintain the deflection adjusted to elevator to adjust, needed to hold control stick and driven with balancing to be transmitted to
Sail the wind pressure resistance of bar.
The characteristic of trimming system of the invention be it is unidirectionally controlled, i.e., trimming system can to elevator control system realize it is micro-
It adjusts, but the adjusting of elevator control system will not feed back trimming system rigidly.Due to trimming system access elevator control
System is that one kind is flexible coupling, this, which is flexible coupling, is realized by way of spring, sliding block and guide rod.When wind pressure resistance or manipulation
Power, when being transmitted on sliding block, sliding block moves back and forth on guide rod, rather than is transmitted to guide rod by spring, then anti-by guide rod
Act on worm gear.Worm screw be for the control of worm gear it is unidirectional, made by the rotation of worm gear worm screw rotation be difficult to realize.And
It is conventional control mode that worm gear rotation is driven by worm screw rotation, at this point, the power of rotation leveling wheel is transmitted to by transfer piece
When guide rod, by the transmitting of spring, power is switched into soft power, which is transmitted to sliding block, sliding block act on driver blade or
Rear push-rod, as long as threshold value needed for the soft power is greater than effect elevator can be realized；In other words, as long as spring as long as being too soft
It is able to achieve above-mentioned function.Certainly, if spring is very hard, although being also able to achieve above-mentioned function, thus there is bigger power that can make
Worm gear structure is used, it, for a long time can be right although the power can be by digestion inside the one-way function of worm gear structure
Worm gear mechanism generates damage.The buffer system of spring, guide rod and sliding block composition, effectively alleviates and controls from elevator
The reaction force of system has obvious action to protection worm gear mechanism.
In addition, elevator is acted on whether through control lever or elevator reacts on control lever, one therein
The buffer system that component amount can be formed by spring, guide rod and sliding block is digested and assimilated.And this digestion and absorption, it is clear that also have significant
Effect, the reaction force of especially wind pressure resistance can be effectively reduced, and significantly reduce the strength demand to driver.Just
Xiang Di also can effectively buffer the damage that the excessive strength of driver understands elevator system.
The invention has the following advantages:
1, trimming system of the invention effectively can generate fine tuning to elevator, be different from the control system of elevator, this
Fine tuning will not generate rebound；
2, trimming system of the invention can effectively form buffer function, to reduce the strength demand to driver, can also drop
Fatigue strength of the low driver in long drives；
3, trimming system of the invention can effectively form buffer function, also can effectively buffer the excessive strength pair of driver
The damage of elevator control system, effectively improves service life；
4, trimming system of the invention can act on the control system of elevator, but the control system of elevator can not be hard
Trimming system is reacted to property, when wind pressure resistance or manipulation force, when anti-pass is delivered to trimming system, effectively by of the invention
It is digested and assimilated by the buffer system that spring, guide rod and sliding block form.
Detailed description of the invention
Fig. 1 is the structure chart of trimming system of the present invention；
Fig. 2 is the overall structure diagram of elevator control system；
Fig. 3 is the manipulation part of elevator control system；
Fig. 4 is the intermediate conversion structure of elevator control system；
Fig. 5 is the terminal transformational structure of elevator control system；
In figure, 1- matches flat seat, 2- leveling wheel, 3- worm gear structure, and 4- spreads out of structure, and 41- transfers piece, 42- guide rod, 43- the
One spring, 44- sliding block, 45- second spring, a- drive bar assembly, b- elevator push rod, and c- is driven bridgeware, d- elevator bone
Frame, a1- control crank, a2- control stick, a3- horizontal brace rod, the vertical adjusting rod of a4-, a5- installation pedestal, push rod before b1-,
B2- rear push-rod, d1- fixing seat, d2- driver blade, interconnecting piece before d2a-, interconnecting piece after d2b-.
Specific embodiment
The present invention is further detailed below in conjunction with attached drawing.
Present embodiment is only explanation of the invention, is not limitation of the present invention.Those skilled in the art
Member is after having read the present invention, made any change, as long as within the scope of the claims, all by the guarantor by Patent Law
Shield.
As shown in Figure 1, airplane trim system, is normally flown for finely tuning and stablizing the tilt angle of elevator with steady aircraft
Aerial statue when row, including matching flat seat 1, being set to the leveling wheel 2 with flat seat, worm gear structure 3 and outflow structure
4。
The outflow structure 4 includes the transfer 41 guide rod 42 of piece, the sliding block 44 being set on the guide rod and is set in institute
The first spring 43 and second spring 45 stated guide rod and be located at the sliding block two sides；One end of the transfer piece 41 is connected to
On the axis of worm gear, the other end is connected with one end of the guide rod 42；The sliding block 44 joins with aircraft evelvator control system
It is dynamic.
Rotation of the leveling wheel 2 by one end of transmission belt connecting worm to control the worm screw, worm screw unidirectionally turn snail
The transfer piece 41 of wheel, the axis of worm gear and the outflow structure 4 is connected；On the basis of vertical line, the adjustable range of transfer piece setting
In ± 30 °.
Above-mentioned sliding block 44 links with aircraft evelvator control system.As shown in Figure 2-5, aircraft evelvator control system includes
Drive bar assembly a, elevator push rod b, transmission bridgeware c and elevator skeleton d；Driving bar assembly a includes control crank a1, behaviour
Vertical pole a2, horizontal brace rod a3, vertical adjusting rod a4 and installation pedestal a5；The vertical lower end adjusting rod a4 is hinged on installation pedestal a5
On, upper end is fixed with horizontal brace rod a3 phase, and the both ends of horizontal brace rod a3 are connect with one end of two control crank a1 respectively,
The other end setting of the control crank a1 control crank a1；One end of elevator push rod b is arranged in the vertical adjusting rod
The lower part of a4, the other end of elevator push rod b are connect by being driven bridgeware c with the elevator skeleton d；So that push away or
When drawing the control crank a1, elevator is made to generate angular deflection.On the basis of vertical line, the angular deflection range of elevator exists
In 30 °.The elevator push rod b includes preceding push rod b1 and rear push-rod b2, passes through a conversion between preceding push rod b1 and rear push-rod b2
Component d connection；The conversion component d includes fixing seat d1 and one end be hinged on the fixing seat d1 other end be respectively equipped with before,
The driver blade d2, the preceding interconnecting piece d2a and the preceding push rod b1 of interconnecting piece d2a, d2b are hinged afterwards, it is described after interconnecting piece d2b with
The rear push-rod b2 is hinged.The linkage portion that the sliding block 44 is set to aircraft evelvator control system is mounted on the driver blade d2
Or on rear push-rod b2.
When aircraft flight, air drag generates wind pressure, and wind pressure generates reaction force to control stick, and resisting the reaction force needs
Driver is wanted by holding control stick to balance.In other words, under state of flight, when adjusting to elevator, elevator can be voluntarily
It replys, to maintain the deflection adjusted to elevator to adjust, needs to hold control stick to balance the wind pressure resistance for being transmitted to control stick
Power.
The characteristic of trimming system of the invention be it is unidirectionally controlled, i.e., trimming system can to elevator control system realize it is micro-
It adjusts, but the adjusting of elevator control system will not feed back trimming system rigidly.Due to trimming system access elevator control
System is that one kind is flexible coupling, this, which is flexible coupling, is realized by way of spring, sliding block and guide rod.When wind pressure resistance or manipulation
Power when being transmitted on sliding block, due to the single-direction transmission characteristic of worm and gear, so that sliding block moves back and forth on guide rod, is realized slow
Rush effect.
Claims (7)
1. airplane trim system, for finely tuning and stablizing aerial appearance of the tilt angle of elevator with steady aircraft normal flight when
State, including matching flat seat (1), being set to the leveling wheel (2) with flat seat, worm gear structure (3) and outflow structure (4)；Its
Be characterized in that: rotation of the leveling wheel (2) by one end of force transfer element connecting worm to control the worm screw, worm screw are single
To worm gear is turned, the axis of worm gear and the transfer piece (41) for spreading out of structure (4) are connected；On the basis of vertical line, transfer piece is set
The adjustable range set is in ± 30 °.
2. airplane trim system according to claim 1, it is characterised in that: the outflow structure (4) further includes guide rod
(42), it the sliding block (44) that is set on the guide rod and is set in the guide rod and is located at the first of the sliding block two sides
Spring (43) and second spring (45)；One end of transfer piece (41) is connected on the axis of worm gear, and the other end is led with described
One end of bar (42) is connected；The sliding block (44) and aircraft evelvator control system link.
3. airplane trim system according to claim 1, it is characterised in that: the force transfer element is transmission belt.
4. airplane trim system according to claim 2, it is characterised in that: the aircraft evelvator control system includes driving
Sail bar assembly (a), elevator push rod (b), transmission bridgeware (c) and elevator skeleton (d)；Driving bar assembly (a) includes manipulation
Handle (a1), control stick (a2), horizontal brace rod (a3), vertical adjusting rod (a4) and installation pedestal (a5)；Vertical adjusting rod
(a4) lower end is hinged on installation pedestal (a5), and upper end is mutually fixed with horizontal brace rod (a3), the both ends of horizontal brace rod (a3)
It is connect respectively with one end of two control cranks (a1), the other end setting of control crank (a1) control crank (a1)；
One end of elevator push rod (b) is arranged in the lower part of the vertical adjusting rod (a4), and the other end of elevator push rod (b) passes through biography
Dynamic bridgeware (c) is connect with the elevator skeleton (d)；So that making elevator when pushing or pulling on the control crank (a1)
Generate angular deflection.
5. airplane trim system according to claim 4, it is characterised in that: on the basis of vertical line, the angle of elevator
Range of deflection is in 30 °.
6. airplane trim system according to claim 4, it is characterised in that: the elevator push rod (b) includes preceding push rod
(b1) and rear push-rod (b2), pass through conversion component (d) connection between preceding push rod (b1) and rear push-rod (b2)；The conversion component
It (d) include that fixing seat (d1) and one end are hinged on the fixing seat (d1) other end and are respectively equipped with forward and backward interconnecting piece (d2a, d2b)
Driver blade (d2), the preceding interconnecting piece (d2a) and the preceding push rod (b1) hingedly, it is described after interconnecting piece (d2b) and it is described after
Push rod (b2) is hinged.
7. airplane trim system according to claim 6, it is characterised in that: the sliding block (44) is set to aircraft evelvator control
The linkage portion of system processed is mounted on the driver blade (d2) or rear push-rod (b2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811617637.XA CN109436301A (en) | 2018-12-28 | 2018-12-28 | The trimming system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811617637.XA CN109436301A (en) | 2018-12-28 | 2018-12-28 | The trimming system of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109436301A true CN109436301A (en) | 2019-03-08 |
Family
ID=65538592
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811617637.XA Withdrawn CN109436301A (en) | 2018-12-28 | 2018-12-28 | The trimming system of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109436301A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148115A (en) * | 2021-03-25 | 2021-07-23 | 中国商用飞机有限责任公司 | Rudder balancing system for aircraft and control method thereof |
-
2018
- 2018-12-28 CN CN201811617637.XA patent/CN109436301A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113148115A (en) * | 2021-03-25 | 2021-07-23 | 中国商用飞机有限责任公司 | Rudder balancing system for aircraft and control method thereof |
| CN113148115B (en) * | 2021-03-25 | 2024-03-22 | 中国商用飞机有限责任公司 | Rudder trimming system for aircraft and control method thereof |
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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 | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190308 |