CN205499344U - Liftable formula light aircraft undercarriage - Google Patents
Liftable formula light aircraft undercarriage Download PDFInfo
- Publication number
- CN205499344U CN205499344U CN201620196381.XU CN201620196381U CN205499344U CN 205499344 U CN205499344 U CN 205499344U CN 201620196381 U CN201620196381 U CN 201620196381U CN 205499344 U CN205499344 U CN 205499344U
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- CN
- China
- Prior art keywords
- undercarriage
- aircraft
- connecting rod
- auricle
- tire
- 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.)
- Expired - Fee Related
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Abstract
The utility model relates to a liftable formula light aircraft undercarriage, at the upper end swing joint undercarriage connecting rod of the tire support of tire, the outer circumference of undercarriage connecting rod is equipped with two auricles from top to bottom, and the one end of attenuator, the other end and the tire support swing joint of attenuator are connected to the lower extreme auricle, upper end auricle swing joint hydraulic pressure branch, the top of hydraulic pressure branch and the top of undercarriage connecting rod are connected with the aircraft fuselage through the attach fitting respectively. This undercarriage passes through the motion change undercarriage bearing structure's of hydraulic actuator angle to change the height of undercarriage, improved the performance of taking off and land of aircraft effectively, can shorten and take off and distance of landing run, increased the adaptability of aircraft to the runway.
Description
Technical field
This utility model relates to a kind of lifting type light aerocraft undercarriage, the auxiliary device during taking off sliding race.
Background technology
The landing airdrome length of aircraft is the key factor limiting takeoff and landing.Often due to the landing airdrome length of aircraft is inadequate, limit rising and falling of a lot of aircraft.When additionally some accident needs forced landing, often can not find suitable place and miss optimal lowerator meeting, cause the tragedy of fatal crass.How on the basis of not affecting aeroplane performance, the takeoff distance and the distance of landing run that shorten aircraft always are the difficult problem that aircraft industry is actively studied and inquired into.
Summary of the invention
The technical problems to be solved in the utility model is to provide a kind of lifting type light aerocraft undercarriage, this undercarriage changes the angle of landing gear support structure by the motion of hydraulic actuator, thus change the height of undercarriage, effectively improve the take-off and landing performance of aircraft, take-off and landing ground run distance can be shortened, add the aircraft adaptability to runway.
For solving problem above, concrete technical scheme of the present utility model is as follows: a kind of lifting type light aerocraft undercarriage, it is flexibly connected undercarriage connecting rod in the upper end of the tire support of tire, two auricles are had on the excircle of undercarriage connecting rod, one end of lower end auricle connection damper, the other end of antivibrator is flexibly connected with tire support；Upper end auricle is flexibly connected hydraulic strut, and the top of hydraulic strut and the top of undercarriage connecting rod are connected with airframe by jointing respectively.
Described landing gear structure is applied on aircraft nose wheel.
This lifting type light aerocraft undercarriage is connected with airframe structure by a hydraulic strut, and being changed by the stroke of hydraulic stem increases and reduce the height of nose-gear, increases the angle of attack of aircraft, increase airplane ascensional force during taking off sliding race；Reduce aircraft angle of attack during alightinging run, increase aircraft drag such that it is able to shorten take-off and landing ground run distance, add the aircraft adaptability to runway.Wherein hydraulic strut reliability is high, easily manipulates, and Landing Gear Design is simple, has the good suitability for light aerocraft.
Undercarriage is applied on front-wheel, and aircraft angle of attack change is fast, easy to control.
Accompanying drawing explanation
Fig. 1 is normal starting heats state and the angle of attack α of aircraft.
Fig. 2 is the normal condition schematic diagram of nose-gear.
Fig. 3 is that hydraulic strut stretches out, and makes nose-gear reach extreme higher position.
Fig. 4 is that hydraulic strut shrinks, and makes nose-gear reach extreme lower position.
Fig. 5 is under nose-gear diverse location, aircraft angle of attack change schematic diagram.
Detailed description of the invention
As shown in Figure 2, a kind of lifting type light aerocraft undercarriage, is flexibly connected undercarriage connecting rod 2 in the upper end of the tire support 6 of tire 4, the excircle of undercarriage connecting rod 2 has two auricles, one end of lower end auricle connection damper 3, the other end of antivibrator 3 is flexibly connected with tire support 6；Upper end auricle is flexibly connected hydraulic strut 1, and the top of hydraulic strut 1 and the top of undercarriage connecting rod are connected with airframe by jointing respectively.
As it is shown in figure 1, described landing gear structure is applied on aircraft nose wheel.
The work process of lifting type light aerocraft undercarriage: under normal condition, liftable undercarriage is as shown in Fig. 2, during taking off sliding race, when speed reaches certain fixing speed, hydraulic strut 1 stretches out, change the angle of undercarriage connecting rod 2, make nose-gear height maximum, as shown in Figure 3.Compared with normal sliding race state, aircraft angle of attack
α increases, and the angle of increase is as shown in Fig. 5, and lift increases, and aircraft can be lifted front-wheel under less than normal takeoff speed and take off, and reduces takeoff distance.
Before aircraft landing, shrink hydraulic strut 1, change the angle of undercarriage connecting rod 2, make nose-gear height minimum, as shown in Fig. 4.Compared with normal sliding race state, aircraft angle of attack
α reduces, and the angle of reduction is as shown in Fig. 5, and front face area increases, lift reduces, and causes frontal resistance increase, ground friction resistance to increase, thus shorten distance of landing run.
Claims (2)
1. a lifting type light aerocraft undercarriage, it is characterized in that: the upper end of the tire support (6) in tire (4) is flexibly connected undercarriage connecting rod (2), two auricles are had on the excircle of undercarriage connecting rod (2), one end of lower end auricle connection damper (3), the other end of antivibrator (3) is flexibly connected with tire support (6)；Upper end auricle is flexibly connected hydraulic strut (1), and the top of hydraulic strut (1) and the top of undercarriage connecting rod are connected with airframe by jointing respectively.
2. lifting type light aerocraft undercarriage as claimed in claim 1, it is characterised in that: described landing gear structure is applied on aircraft nose wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620196381.XU CN205499344U (en) | 2016-03-15 | 2016-03-15 | Liftable formula light aircraft undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620196381.XU CN205499344U (en) | 2016-03-15 | 2016-03-15 | Liftable formula light aircraft undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205499344U true CN205499344U (en) | 2016-08-24 |
Family
ID=56728657
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620196381.XU Expired - Fee Related CN205499344U (en) | 2016-03-15 | 2016-03-15 | Liftable formula light aircraft undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205499344U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019137078A1 (en) * | 2018-01-15 | 2019-07-18 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
-
2016
- 2016-03-15 CN CN201620196381.XU patent/CN205499344U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019137078A1 (en) * | 2018-01-15 | 2019-07-18 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20190315 |