CN209454981U - A kind of slide-type helicopter landing gear - Google Patents
A kind of slide-type helicopter landing gear Download PDFInfo
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- CN209454981U CN209454981U CN201920169767.5U CN201920169767U CN209454981U CN 209454981 U CN209454981 U CN 209454981U CN 201920169767 U CN201920169767 U CN 201920169767U CN 209454981 U CN209454981 U CN 209454981U
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- Prior art keywords
- slide
- helicopter
- landing gear
- hydraulic actuator
- helicopter landing
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Abstract
The utility model provides a kind of slide-type helicopter landing gear, it is related to Helicopter Technology field, it includes two skid plates for being set to helicopter fuselage two sides, every skid front edge of board and rear end are connected on helicopter fuselage by hydraulic actuator, each hydraulic actuator is correspondingly arranged on range sensor, hydraulic actuation bobbin is connected on oil pump, oil pump is located in helicopter fuselage, proportioning valve is provided on the oil feed line of hydraulic actuator, displacement sensor is provided in pressure pressurized strut, range sensor and displacement sensor are electrically connected to the input terminal of controller, oil pump, proportioning valve is electrically connected to the output end of controller.Solve the problems, such as that helicopter in the prior art can not the landing on the sloping floor of great slope.
Description
Technical field
The utility model relates to Helicopter Technology fields, more particularly to a kind of slide-type helicopter landing gear.
Background technique
Helicopter is widely used to patrol in investigation, Strike, medical aid, rescue and relief work, geological exploration, electric power over the ground
Line etc..Instantly the structure type of undercarriage is more, usually wheeled and ski type two major classes.
Skid landing gear is generally made of bow beam and ripping bar, and structure is simple, light-weight, easy to maintain, use cost
It is low.The flexible deformation of structure is relied primarily on to absorb landing energy.Air speed is slow, take-off weight is light, place is easy to protect
The weaker civil field of card, logistics has greater advantage.But its bearing capacity is lower, place bad adaptability, can not ground taxi,
It is difficult to absorb vibration and anti-pendant.The effect that cannot obtain certain protection and buffering is in emergency circumstances in aircraft.
Wheel undercarriage is divided into framework type, column support type etc..Advantage is that almost all of wheel undercarriage is equipped with oil-gas type
Damper.With certain absorption landing energy, reduce the effect of shock, and " ground is total by shock absorber spring and damping elimination
Vibration ".
Existing helicopter landing gear on the sloping floor of great slope due to that landing cannot cause emergency poor, nothing
Method meets the forced landing needs of helicopter in emergency situations, is easy rollover when forced landing in field and aircraft accident occurs, can not
Guarantee the personal safety of crew.
Utility model content
For the above problem in the prior art, the utility model provides a kind of slide-type helicopter landing gear, solves
Helicopter in the prior art can not be the landing on the sloping floor of great slope the problem of.
In order to achieve the above object of the invention, the technical solution adopted in the utility model is as follows:
There is provided a kind of slide-type helicopter landing gear comprising be set to two skid plates of helicopter fuselage two sides, often
Root skid front edge of board and rear end are connected on helicopter fuselage by hydraulic actuator, be provided on each hydraulic actuator away from
From sensor, hydraulic actuation bobbin is connected on oil pump, and oil pump is located in helicopter fuselage, on the oil feed line of hydraulic actuator
It is provided with proportioning valve, displacement sensor is provided on hydraulic actuator, range sensor and displacement sensor are electrically connected to control
The input terminal of device, oil pump, proportioning valve are electrically connected to the output end of controller.
Further, the piston rod of hydraulic actuator is connected on skid plate by three-way connection.
Further, the spacing between two skid plates is greater than the width of helicopter fuselage, forms skid plate with ground
One triangular support improves the stability of helicopter during landing under helicopter fuselage.
Further, range sensor is infrared distance measuring sensor.The infrared distance measuring sensor response time is short, can
The terrestrial information that helicopter will land is fed back into controller in time, controller is facilitated to adjust each hydraulic actuator in time
Stroke adapt to the irregularities on ground.
Further, the model GP2Y0A02YK0F of range sensor.
Further, proportioning valve is electro-hydraulic proportion reversing valve.Since electro-hydraulic proportion reversing valve is replaced with proportion electro-magnet
General electromagnet in solenoid directional control valve, so that spool can not only replace, but also the stroke to replace can continuously or in proportion
Ground variation.
Further, displacement sensor is magnetostriction position sensor.The stability of magnetostriction position sensor is high,
Degree of protection is high, can adapt to the natural environment of field complexity.
Further, controller is single-chip microcontroller STC12C5A60S2.
The utility model has the following beneficial effects: the helicopter landing gear in this programme can be according to the landform feelings on forced landing ground
Condition adjusts the stroke of hydraulic actuator, keeps skid plate parallel to the ground, so that either smooth ground or inclined
Ground, skid plate can stable landing, be conducive to helicopter in case of emergency carry out operation with emergency force-land and return safely
Boat.
It is by the airborne of helicopter that the entire height detection and control hydraulic actuator of undercarriage, which do corresponding movement,
Computer is automatically performed, good reliability, without additionally increasing the work load of driver, does not influence normally driving for driver
It sails.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of slide-type helicopter landing gear.
Fig. 2 is the schematic diagram for being equipped with the helicopter of slide-type helicopter landing gear and force-landing on face of slope.
Wherein, 1, skid plate；2, hydraulic actuator；21, piston rod；3, three-way connection.
Specific embodiment
Specific embodiment of the present utility model is described below, in order to facilitate understanding by those skilled in the art
The utility model, it should be apparent that the utility model is not limited to the range of specific embodiment, to the common skill of the art
For art personnel, if various change the attached claims limit and determine the utility model spirit and scope in,
These variations are it will be apparent that all utilize the innovation and creation of the utility model design in the column of protection.
As shown in Figure 1, the slide-type helicopter landing gear includes two skid plates 1 for being set to helicopter fuselage two sides,
Every 1 front-end and back-end of skid plate are connected on helicopter fuselage by hydraulic actuator 2, the piston rod 21 of hydraulic actuator 2
It is connected on skid plate 1 by three-way connection 3.Spacing between two skid plates 1 is greater than the width of helicopter fuselage.
Hydraulic actuator 2 be it is a kind of hydraulic energy pressure actuation is converted into the Hydraulic Elements of mechanical energy, basic composition substantially by
The components such as cylinder, piston, piston rod, end cap, sealing element, inlet and outlet piping composition, when cylinder is fixed, if cylinder left chamber input service
Liquid, fluid pressure is increased to when being enough to overcome extraneous load, and piston begins to move right.If continuously for oil supply
Liquid, then piston is continuously moved with certain speed.In the present solution, when needing hydraulic actuator 2 to change the length of piston rod, only
Need the i.e. controllable oil liquid entered in 2 inner cavity of hydraulic actuator of control oil pump and electro-hydraulic proportion reversing valve.
Each hydraulic actuator 2 is correspondingly arranged on range sensor, and range sensor is infrared distance measuring sensor,
Model GP2Y0A02YK0F.Range sensor is fixed on the cylinder of hydraulic actuator 2, is slided although range sensor is fixed to
The distance between skid plate and ground can be directly measured on skid plate, it is easier to which control calculates, but the self weight of range sensor is held
The balance for easily influencing skid plate, reduces stationarity when helicopter landing.Signal that controller detects range sensor with
The actual range on skid plate and ground can be obtained after the elongation combination processing for the piston rod 21 that displacement sensor detects.
Oil liquid in hydraulic actuator 2 is sent by oil pump, oil liquid storage in the fuel tank on helicopter fuselage, oil pump and straight
The power supply connection of the machine of liter, is in series with relay, relay model LL2C-BL on the power line, and controller passes through control relay
The on-off of device carrys out the power on/off of control oil pump.Oil pump is hydraulic planger pump, model A10FR01H-12.
Electro-hydraulic proportion reversing valve is connected on the oil inlet pipe and flowline of hydraulic actuator 2, electro-hydraulic proportion reversing valve is logical
Crossing proportion electro-magnet allows that its spool replaces and the stroke that replaces continuously or pari passu changes, by controller to electromagnetism
Iron issues electric signal to control the oil liquid flow to circulate in oil inlet pipe and flowline, to control the piston rod of hydraulic actuator 2
21 stroke.
Displacement sensor is provided on hydraulic actuator 2, displacement sensor is magnetostriction position sensor, magnetostriction
Position sensor includes built-in and external two kinds of mounting means, and built-in is magnet ring and piston inside insertion hydraulic actuator 2
Fixed, waveguide is inserted into hydraulic actuator 2, there is metric thread between electronics storehouse and waveguide, is screwed on hydraulic actuator 2
Opening；External is the outside for being placed in hydraulic actuator 2, has a guide rail slide block, sliding block on magnetostriction position sensor
On there is push-pull rod to connect with piston, the mobile band movable slider of piston is dynamic, and magnet ring is housed inside sliding block.Pass through detection magnet ring and waveguide
The distance between come detect hydraulic actuator 2 piston moving distance, to judge the elongation of piston rod 21.
Controller is single-chip microcontroller STC12C5A60S2, and the winged control that single-chip microcontroller STC12C5A60S2 is electrically connected to helicopter calculates
In machine.When helicopter needs to force-land, by flight control computer opening controller, controller command range sensor is detected at this time
The vertical range of skid plate and ground, after analog/digital conversion circuit conversion, and the altitude information and horizon instrument that will test
The aspect of display does corresponding comparison, and the data that comparison obtains are transferred in single-chip microcontroller STC12C5A60S2, the list is passed through
Piece machine controls the stroke of the piston rod 21 of four hydraulic actuators 2, makes four hydraulic actuators 2 that different extended lengths be presented
Cooperate the inclined degree on forced landing ground, so that helicopter stablizes forced landing on inclined ground, as shown in Figure 2.
Claims (8)
1. a kind of slide-type helicopter landing gear, which is characterized in that two skid plates including being set to helicopter fuselage two sides
(1), every skid plate (1) front-end and back-end are connected on helicopter fuselage by hydraulic actuator (2), each liquid
It is provided with range sensor in pressure pressurized strut (2), hydraulic actuator (2) pipe is connected on oil pump, and the oil pump is located at
In helicopter fuselage, it is provided with proportioning valve on the oil feed line of the hydraulic actuator (2), is arranged on the pressure pressurized strut (2)
There is displacement sensor, the range sensor and displacement sensor are electrically connected to the input terminal of controller, the oil pump, proportioning valve
It is electrically connected to the output end of controller.
2. slide-type helicopter landing gear according to claim 1, which is characterized in that the work of the hydraulic actuator (2)
Stopper rod (21) is connected on the skid plate (1) by three-way connection (3).
3. slide-type helicopter landing gear according to claim 1, which is characterized in that between two skid plates (1)
Spacing be greater than helicopter fuselage width.
4. slide-type helicopter landing gear according to claim 1, which is characterized in that the range sensor is infrared ray
Distance measuring sensor.
5. slide-type helicopter landing gear according to claim 4, which is characterized in that the model of the range sensor
GP2Y0A02YK0F。
6. slide-type helicopter landing gear according to claim 1, which is characterized in that the proportioning valve changes for electric-hydraulic proportion
To valve.
7. slide-type helicopter landing gear according to claim 1, which is characterized in that institute's displacement sensors are stretched for mangneto
Contracting position sensor.
8. slide-type helicopter landing gear according to claim 1, which is characterized in that the controller is single-chip microcontroller
STC12C5A60S2。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920169767.5U CN209454981U (en) | 2019-01-30 | 2019-01-30 | A kind of slide-type helicopter landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920169767.5U CN209454981U (en) | 2019-01-30 | 2019-01-30 | A kind of slide-type helicopter landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209454981U true CN209454981U (en) | 2019-10-01 |
Family
ID=68046345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920169767.5U Expired - Fee Related CN209454981U (en) | 2019-01-30 | 2019-01-30 | A kind of slide-type helicopter landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209454981U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12060148B2 (en) | 2022-08-16 | 2024-08-13 | Honeywell International Inc. | Ground resonance detection and warning system and method |
| CN118579256A (en) * | 2024-08-01 | 2024-09-03 | 北京中科光析科学技术研究所山东分所 | Safe low altitude aircraft |
-
2019
- 2019-01-30 CN CN201920169767.5U patent/CN209454981U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12060148B2 (en) | 2022-08-16 | 2024-08-13 | Honeywell International Inc. | Ground resonance detection and warning system and method |
| CN118579256A (en) * | 2024-08-01 | 2024-09-03 | 北京中科光析科学技术研究所山东分所 | Safe low altitude aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20191001 Termination date: 20220130 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |