CN208325607U - A kind of rudder suitable for trainer aircraft - Google Patents
A kind of rudder suitable for trainer aircraft Download PDFInfo
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- CN208325607U CN208325607U CN201820893465.8U CN201820893465U CN208325607U CN 208325607 U CN208325607 U CN 208325607U CN 201820893465 U CN201820893465 U CN 201820893465U CN 208325607 U CN208325607 U CN 208325607U
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- rudder
- rocker arm
- trainer aircraft
- brake
- cable wire
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Abstract
The utility model discloses a kind of rudders suitable for trainer aircraft, including three supports, two radome fairings, rudder face and rocker arm for adjusting rudder face angle, described two radome fairings are located at the both ends of rudder face, the rudder is connected by the vertical fin of three supports and afterbody, and the rocker arm is connect by rope gearing with the rudder control system that front fuselage is arranged.It pulls rocker arm to carry out adjustment direction rudder rudder face angle by using rope gearing, guarantees rudder rudder face angle stabilization, so that it is guaranteed that the stability in aircraft flight.
Description
Technical field:
The utility model belongs to rudder of aircraft technical field, in particular to a kind of rudder suitable for trainer aircraft.
Background technique:
- 700 aircraft of eaglet is a primary trainer, is applicable to aeroclub, flight parachute jumping, aviation by repacking
The General Aviations fields such as shooting.Rudder is used to control the yaw of aircraft, guarantee aircraft in flight course flight path it is steady
Fixed, general aircraft, in order to limit the power on empennage, needs to control the deflection angle of rudder, direction in flat winged or turning
The control of rudder is generally manipulated with foot, and with foot manipulation levels of precision it is low, rudder rudder face angle vulnerable to external environment influence and
Change, to influence the stability of aircraft flight.
Utility model content:
The purpose of this utility model is to provide a kind of rudder suitable for trainer aircraft, direction rudder can prevent direction
Rudder rudder face angle changes, and guarantees the stabilization of aircraft flight path.
To achieve the above object, the technical solution adopted in the utility model are as follows: a kind of rudder suitable for trainer aircraft, packet
It includes three supports, two radome fairings, rudder face and the rocker arm for adjusting rudder face angle, described two radome fairings and is located at rudder
The both ends in face, the rudder are connected by the vertical fin of three supports and afterbody, and the rocker arm passes through rope drive
Device is connect with the rudder control system that front fuselage is arranged, and the rudder of rocker arm adjustment direction rudder is pulled by rope gearing
Face angle degree.
The utility model has the beneficial effects that
The utility model pulls pull rod by using cable wire and then rocker arm is pulled to come adjustment direction rudder rudder face angle, guarantor
To rudder rudder face angle stabilization, so that it is guaranteed that the stability in aircraft flight.
Detailed description of the invention:
Fig. 1 is a kind of schematic diagram of the rudder suitable for trainer aircraft of the utility model.
Fig. 2 is the rope gearing schematic diagram of the utility model
Fig. 3 is the schematic diagram of the front wheel brake system of the utility model.
Description of symbols: 1- support, 2- radome fairing, 3- rudder face, 4- rocker arm, 5- pull rod, 6- cable wire.
Specific embodiment:
The utility model is described in further details combined with specific embodiments below.One kind as shown in Figure 1 is suitable for
The rudder of trainer aircraft, including three supports, 1, two radome fairing 2, rudder face 3 and Rocker arm 4 for adjusting 3 angle of rudder face, institute
The both ends that two radome fairings 2 are located at rudder face 3 are stated, the rudder passes through the vertical fin of three supports 1 and afterbody
Connection, the Rocker arm 4 are connect by rope gearing with the rudder control system that front fuselage is arranged, and rope drive is passed through
The rudder face angle of device pulling Rocker arm 4 adjustment direction rudder.
The rope gearing of the utility model includes cable wire 6 and pull rod 5, and one end of the cable wire 6 is by pull rod 5 and rocker arm
4 link together, and the other end is connect with rudder control system.
The rudder control system of the utility model includes manual operation device, foot manipulation device and retainer, is grasped by hand
Vertical device and foot manipulation device drive cable wire 6, so that cable wire 6 is successively pulled pull rod 5 and Rocker arm 4, so as to adjust the rudder face of rudder
Angle.
The foot manipulation device of the utility model and the front wheel brake system of the trainer aircraft are crosslinked, and pass through control foot manipulation dress
The front wheel brake system for setting starting trainer aircraft, makes aircraft be braked and be realized on the ground Nose Wheel Steering.
The front wheel brake system of the utility model by hydraulic system drive, including brake gear, for being switched on or switched off
The shutdown brake knob of hydraulic system, for controlling the braking action cylinder of output brake pressure, for reaching the pressure of output
The brake conduit of brake gear.
The utility model rudder can be -20 °~20 ° relative to the fixed fin left-right rotation of vertical fin, slewing area.
When aircraft is flat to fly or turn, the manual operation device for passing through rudder control system starts cable wire and pulls Rocker arm 4 adjustment direction
3 angle of rudder face of rudder, thus change of flight posture；When aircraft brake, stopped by the front-wheel that foot manipulation device starts trainer aircraft
Vehicle system, first opens shutdown brake knob and connects hydraulic system, and pressure required for being braked by the control of braking action cylinder passes through
Brake pressure is transferred to brake gear to realize aircraft brake by brake conduit.Since the intensity of cable wire is high, not vulnerable to the external world
The influence of environment and deform, therefore cooperated using cable wire and pull rod and rocker arm, pull Rocker arm 4 come adjustment direction rudder rudder by cable wire
Face angle degree guarantees rudder rudder face angle stabilization, so that it is guaranteed that the stability in aircraft flight.
Claims (6)
1. a kind of rudder suitable for trainer aircraft, it is characterised in that: including three supports (1), two radome fairings (2), rudder faces
(3) and the rocker arm (4) for adjusting rudder face (3) angle, described two radome fairings (2) are located at the both ends of rudder face (3), institute
State rudder and connect with the vertical fin of afterbody by three supports (1), the rocker arm (4) pass through rope gearing and
The rudder control system connection of front fuselage setting, the rudder face of rocker arm (4) adjustment direction rudder is pulled by rope gearing
Angle.
2. a kind of rudder suitable for trainer aircraft according to claim 1, it is characterised in that: the rope gearing
Including cable wire (6) and pull rod (5), one end of the cable wire (6) links together pull rod (5) and rocker arm (4), the other end and side
It is connected to rudder steerable system.
3. a kind of rudder suitable for trainer aircraft according to claim 2, it is characterised in that: the rudder control system
System includes that manual operation device, foot manipulation device and retainer are made by manual operation device and foot manipulation device driving cable wire (6)
Cable wire (6) successively pulls pull rod (5) and rocker arm (4), so as to adjust the rudder face angle of rudder.
4. a kind of rudder suitable for trainer aircraft according to claim 3, it is characterised in that: the foot manipulation device with
The front wheel brake system of the trainer aircraft is crosslinked, and is started the front wheel brake system of trainer aircraft by control foot manipulation device, is made to fly
Machine is braked and is realized on the ground Nose Wheel Steering.
5. a kind of rudder suitable for trainer aircraft according to claim 4, it is characterised in that: the front wheel brake system
It is driven by hydraulic system, it is defeated for controlling including brake gear, the shutdown brake knob for being switched on or switched off hydraulic system
The braking action cylinder of brake pressure out, for the pressure of output to be reached to the brake conduit of brake gear.
6. a kind of rudder suitable for trainer aircraft according to claim 1, it is characterised in that: the rudder can be opposite
In the fixed fin left-right rotation of vertical fin, slewing area is -20 °~20 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820893465.8U CN208325607U (en) | 2018-06-11 | 2018-06-11 | A kind of rudder suitable for trainer aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820893465.8U CN208325607U (en) | 2018-06-11 | 2018-06-11 | A kind of rudder suitable for trainer aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208325607U true CN208325607U (en) | 2019-01-04 |
Family
ID=64773654
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820893465.8U Active CN208325607U (en) | 2018-06-11 | 2018-06-11 | A kind of rudder suitable for trainer aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208325607U (en) |
-
2018
- 2018-06-11 CN CN201820893465.8U patent/CN208325607U/en active Active
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