CN201647127U - Safety landing-assistant rescuing system for faulted airplane - Google Patents
Safety landing-assistant rescuing system for faulted airplane Download PDFInfo
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- CN201647127U CN201647127U CN2010201814697U CN201020181469U CN201647127U CN 201647127 U CN201647127 U CN 201647127U CN 2010201814697 U CN2010201814697 U CN 2010201814697U CN 201020181469 U CN201020181469 U CN 201020181469U CN 201647127 U CN201647127 U CN 201647127U
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- landing
- assistant
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- aircraft
- guide rail
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Abstract
The utility model relates to a safety landing-assistant system, in particular to a safety landing-assistant rescuing system for a faulted airplane. The safety landing-assistant rescuing system is used when an airplane is out of function in the air and particularly when the air plane is in landing and an undercarriage cannot be normally opened, and comprises an airplane landing-assistant vehicle (1), a guide rail (8), an electric force acceleration and speed regulating system (11) and a braking device. A control room (7) is arranged at the front end of the airplane landing-assistant vehicle (1). The safety landing-assistant rescuing system is characterized in that: the airplane landing-assistant vehicle (1) is arranged on the guide rail (8) by groups of wheels (9) matched with the guide rail (8), an airplane tray (12) is arranged above the airplane landing-assistant vehicle (1), the electric force acceleration and speed regulating system (11) and the braking device are arranged below the airplane landing-assistant vehicle (1), hydraulic mechanical fixed arms (4) are arranged at the left and right sides of the airplane tray (12), the electric force acceleration and speed regulating system (11) is connected with a conductive circuit (10) arranged along the inner side of the guide rail (8), and a folding anti-impact net (5) is arranged above a vehicle head of the airplane landing-assistant vehicle (1). With quick starting and acceleration, simple as well as convenient operation and safe as well as stable power, the safety landing-assistant rescuing system which adopts the electric force acceleration and speed regulating system does not cause open fire, and cannot easily cause other accidents such as fire hazards and the like; moreover, the airplane can be quickly fixed after butt joint, so as to prevent forward rushing or lateral turnover.
Description
Technical field
The utility model relates to the aircraft safety landing system, specially refers to be the aerial et out of order of aircraft, a kind of safe assistance landing system that alighting gear provides in the time of can not normally opening.
Background technology
When the aircraft et out of order, when alighting gear can't be opened, generally can only lean on the aircraft ventral to slide at present, force-land, for preventing to realize on the runway on fire that carrying out fire-fighting foams handles by friction taking place with ground along the runway friction in the airport.But problems such as the directivity rollover during aircraft taxi can't solve, in normal conditions, can't open and emergency landing owing to alighting gear, the directivity rollover fatal crass's that causes tragedy is startling during aircraft taxi, and each serious accident all causes great personal casualty and property damage.China's utility model patent 200510019929 discloses a kind of force landing chassis in failure of landing gear, this forced landing holder car adopts PLC Programmable Logic Controller and acceleration rocket and rocket igniter as acceleration device, adopt intelligent camera, PLC Programmable Logic Controller, power supply amplification module and servomotor as line of centers observing and controlling steering hardware, adopt weight sensor, PLC Programmable Logic Controller, power relay, electromagnetism parachute opening device, power supply amplification module and servomotor to constitute the slowing-down brake system.Because this utility model adopts acceleration rocket as power system, the high-temperature high-pressure air flow that rocket is produced when spraying can produce very big landing hidden danger to the landing aircraft, and produced simultaneously naked light can bring inflammable and explosive danger when forced landing; Simultaneously, on the forced landing holder car any anchor fitting is not set, the aircraft preshoot easily takes place, locate insecure; Adopt the common wheel high-speed cruising in addition, problems such as directivity rollover take place in wayward rectilinearity of advancing easily during aircraft landing.
Summary of the invention
The technical problems to be solved in the utility model is: overcome the deficiencies in the prior art, provide that a kind of power safety is stable, linear running is steady, the security landing-assistant rescuing system for breakdown plane of aircraft butt joint back firm position.
The technical scheme that its technical matters that solves the utility model adopts is: this security landing-assistant rescuing system for breakdown plane, comprise aircraft landing aid vehicle, guide rail, Electronmotive Force acceleration and velocity-controlled system and brake equipment, aircraft landing aid vehicle front end is provided with control cabin, it is characterized in that: described aircraft landing aid vehicle is installed on the guide rail by the many groups of wheels that match with guide rail, the top is provided with the aircraft pallet, the below is provided with Electronmotive Force acceleration and velocity-controlled system and brake equipment, the described aircraft pallet left and right sides is provided with the hydraulic machinery fixed arm, described Electronmotive Force acceleration and velocity-controlled system are connected with the electrical lead road that is provided with along the guide rail inboard, and aircraft landing aid vehicle headstock top is provided with collapsible erosion control net.
Described aircraft tray upper surface is equipped with fire blanket and inflatable packer.
Described inflatable packer is the erosion control inflatable packer that matches with the breakdown plane type.
Described aircraft landing aid vehicle is provided with a plurality of applicators around the top, and a plurality of applicators are connected with the interior fire-fighting fluid circulation of car.
Described aircraft landing aid vehicle vehicle frame is provided with a plurality of apomecometers, and apomecometer is connected with hydraulic machinery fixed arm control system and butt joint velocity indicator.
During aircraft landing, with the security landing-assistant rescuing system maintenance in-line in the airport, the Electronmotive Force that starts aircraft landing aid vehicle is quickened and velocity-controlled system, when aircraft landing aid vehicle is identical with breakdown plane speed, carry out equidirectionally with speed butt joint, realizes staticly relatively, frictionless lands.Breakdown plane drops on the aircraft pallet that is provided with fire blanket and inflatable packer, and in time by the hydraulic machinery fixed arm aircraft is fixed, and collapsible erosion control net is opened, and covers the head position, prevents the aircraft preshoot.Closing fault aero-engine, and the emergent fire-fighting system of starting start the sliding brake equipment that runs of security landing-assistant rescuing system and finish safe falling.
Compared with prior art, the beneficial effect that security landing-assistant rescuing system for breakdown plane of the present utility model had is: 1, adopt Electronmotive Force to quicken and velocity-controlled system, startup and speed-raising are fast, easy and simple to handle, power safety is stable, does not produce naked light, not other accidents such as fire hazardous; 2, adopt the design of guide rail and track adjusting wheel, guarantee that aircraft landing aid vehicle linear running is steady, the roll-over accident that deflection produces when avoiding aircraft to fall; 3, aircraft landing aid vehicle front end is provided with the erosion control net, and both sides are provided with the hydraulic machinery fixed arm, can rapidly aircraft be fixed after the aircraft butt joint, prevents the aircraft preshoot or turns on one's side.
Description of drawings
Fig. 1 is the utility model security landing-assistant rescuing system for breakdown plane structural representation.
Fig. 2 is the utility model security landing-assistant rescuing system for breakdown plane structure birds-eye view.
Wherein: 1, aircraft landing aid vehicle 2, fire blanket 3, inflatable packer 4, hydraulic machinery fixed arm 5, erosion control net 6, applicator 7, control cabin 8, guide rail 9, wheel 10, electrical lead road 11, Electronmotive Force acceleration and velocity-controlled system 12, aircraft pallet 13, apomecometer 14, breakdown plane.
Fig. 1～2nd, the most preferred embodiment of the utility model security landing-assistant rescuing system for breakdown plane is described further below in conjunction with 1～2 pair of the utility model of accompanying drawing:
The specific embodiment
With reference to accompanying drawing 1:
Security landing-assistant rescuing system for breakdown plane, comprise aircraft landing aid vehicle 1, be arranged on aircraft landing aid vehicle 1 end face aircraft pallet 12, be arranged on that fire blanket 2 and the inflatable packer 3 on the aircraft pallet 12, the hydraulic machinery fixed arm 4 that is arranged on aircraft pallet 12 both sides, Electronmotive Force quicken and velocity-controlled system 11, guide rail 8, the electrical lead road 10 along guide rail 8 is set up, apomecometer 13, brake equipment and be arranged on Air Ground Communication System, butt joint velocity indicator, fire-fighting liquid cyclic control system, hydraulic machinery fixed arm control system and braking control system service platform in the control cabin 7.
Aircraft landing aid vehicle 1 is installed on the guide rail 8 by the many groups of wheels 9 that match with guide rail 8, the top is provided with aircraft pallet 12, the below is provided with Electronmotive Force and quickens and velocity-controlled system 11 and brake equipment, Electronmotive Force is quickened and velocity-controlled system 11 adopts present motor train unit Electronmotive Force to quicken and velocity-controlled system, directly with along the guide rail 8 inboard electrical lead roads 10 that are provided be connected by electric wire, aircraft pallet 12 left and right sides are provided with hydraulic machinery fixed arm 4, aircraft landing aid vehicle 1 front end is provided with control cabin 7, is provided with Air Ground Communication System in the control cabin 7, the butt joint velocity indicator, fire-fighting, hydraulic pressure and braking control system service platform.The headstock top is provided with collapsible erosion control net 5.Aircraft pallet 12 upper surfaces are equipped with fire blanket 2 and inflatable packer 3.Inflatable packer 3 is the erosion control inflatable packer 3 that matches with breakdown plane 14 types.Be provided with a plurality of applicators 6 around aircraft landing aid vehicle 1 top, a plurality of applicators 6 are connected with fire-fighting fluid circulation in the car.Aircraft landing aid vehicle 1 vehicle frame is provided with a plurality of apomecometers 13, and apomecometer 13 is connected with hydraulic machinery fixed arm 4, control system and butt joint velocity indicator.Set Air Ground Communication System, butt joint velocity indicator, fire-fighting liquid cyclic control system etc. are present airport conventional techniques in the control cabin 7, are not giving unnecessary details.
Principle of work and working process are as follows:
When the aerial et out of order alighting gear of aircraft can not normally be opened, this system will be enabled in the aircraft airport.Electronmotive Force is quickened and velocity-controlled system 11 energized, drives aircraft landing aid vehicle 1 and quickens.Needed speed when the airdrome control personnel enter this system overhead maintenance certain height and landing by instruction directs breakdown plane 14 is done equidirectional rectilinear flight with the aircraft landing aid vehicle 1 on this system track.When aircraft landing aid vehicle 1 equates with breakdown plane 14 speed, when zero distance was parallel up and down, breakdown plane 14 entered the decline landing procedure.After breakdown plane 14 follow procedures drop on the aircraft pallet 12 that is provided with fire blanket 2 and type inflatable packer 3, the hydraulic machinery fixed arm 4 of aircraft pallet 12 both sides closes up, breakdown plane 14 is fixed, collapsible erosion control net 5 is opened, cover the head position, to slide before and after rollover of prevention aircraft and the aircraft.Close aero-engine, the track Electronmotive Force is quickened and velocity-controlled system 11 slows down, and the circulation fluid fire-fighting system carries out preventative fire-fighting to aircraft, avoids on fire.In fact owing to there is not friction when this landing system and aircraft landing, aircraft probability on fire is very low.Start brake system, aircraft landing aid vehicle 1 enters the sliding retrosequence that runs, and reaches the purpose of safe falling.
The above, it only is the preferred embodiment of utility model, be not to be the restriction of the utility model being made other form, any those skilled in the art may utilize the technology contents of above-mentioned announcement to be changed or be modified as the equivalent embodiment of equivalent variations.But every technical solutions of the utility model content that do not break away to any simple modification, equivalent variations and remodeling that above embodiment did, still belongs to the protection domain of technical solutions of the utility model according to technical spirit of the present utility model.
Claims (5)
1. security landing-assistant rescuing system for breakdown plane, comprise aircraft landing aid vehicle (1), guide rail (8), Electronmotive Force is quickened and velocity-controlled system (11) and brake equipment, aircraft landing aid vehicle (1) front end is provided with control cabin (7), it is characterized in that: described aircraft landing aid vehicle (1) is installed on the guide rail (8) by the wheel (9) that many groups match with guide rail (8), the top is provided with aircraft pallet (12), the below is provided with Electronmotive Force and quickens and velocity-controlled system (11) and brake equipment, described aircraft pallet (12) left and right sides is provided with hydraulic machinery fixed arm (4), described Electronmotive Force is quickened and velocity-controlled system (11) is connected with the electrical lead road (10) that is provided with along guide rail (8) inboard, and aircraft landing aid vehicle (1) headstock top is provided with collapsible erosion control net (5).
2. security landing-assistant rescuing system for breakdown plane according to claim 1 is characterized in that: described aircraft pallet (12) upper surface is equipped with fire blanket (2) and inflatable packer (3).
3. security landing-assistant rescuing system for breakdown plane according to claim 2 is characterized in that: described inflatable packer (3) is the erosion control inflatable packer (3) that matches with breakdown plane (14) type.
4. security landing-assistant rescuing system for breakdown plane according to claim 1 is characterized in that: described aircraft landing aid vehicle (1) is provided with a plurality of applicators (6) around the top, and a plurality of applicators (6) are connected with fire-fighting fluid circulation in the car.
5. security landing-assistant rescuing system for breakdown plane according to claim 1 is characterized in that: described aircraft landing aid vehicle (1) vehicle frame is provided with a plurality of apomecometers (13), and apomecometer (13) is connected with hydraulic machinery fixed arm control system and butt joint velocity indicator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201814697U CN201647127U (en) | 2010-05-07 | 2010-05-07 | Safety landing-assistant rescuing system for faulted airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201814697U CN201647127U (en) | 2010-05-07 | 2010-05-07 | Safety landing-assistant rescuing system for faulted airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201647127U true CN201647127U (en) | 2010-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201814697U Expired - Lifetime CN201647127U (en) | 2010-05-07 | 2010-05-07 | Safety landing-assistant rescuing system for faulted airplane |
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| CN (1) | CN201647127U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837838A (en) * | 2010-05-07 | 2010-09-22 | 霍方华 | Security landing-assistant rescuing system for breakdown plane |
| CN107628264A (en) * | 2017-09-04 | 2018-01-26 | 山东鲁交智能设备股份有限公司 | A kind of undercarriage failure forced landing base apparatus |
| CN111498132A (en) * | 2020-04-27 | 2020-08-07 | 南京工程学院 | Servo tracking robot for intelligent safe landing of aircraft landing gear fault |
| CN116573152A (en) * | 2023-07-13 | 2023-08-11 | 中国人民解放军空军工程大学 | Omnidirectional driving aircraft rescue carrier with dynamic self-adjusting platform |
-
2010
- 2010-05-07 CN CN2010201814697U patent/CN201647127U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101837838A (en) * | 2010-05-07 | 2010-09-22 | 霍方华 | Security landing-assistant rescuing system for breakdown plane |
| CN101837838B (en) * | 2010-05-07 | 2013-04-03 | 霍方华 | Security landing-assistant rescuing system for breakdown plane |
| CN107628264A (en) * | 2017-09-04 | 2018-01-26 | 山东鲁交智能设备股份有限公司 | A kind of undercarriage failure forced landing base apparatus |
| CN111498132A (en) * | 2020-04-27 | 2020-08-07 | 南京工程学院 | Servo tracking robot for intelligent safe landing of aircraft landing gear fault |
| CN116573152A (en) * | 2023-07-13 | 2023-08-11 | 中国人民解放军空军工程大学 | Omnidirectional driving aircraft rescue carrier with dynamic self-adjusting platform |
| CN116573152B (en) * | 2023-07-13 | 2023-09-19 | 中国人民解放军空军工程大学 | Omnidirectional driving aircraft rescue carrier with dynamic self-adjusting platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20101124 Effective date of abandoning: 20130410 |
|
| RGAV | Abandon patent right to avoid regrant |