CN101544279A - Airplane fault forced landing vehicles - Google Patents
Airplane fault forced landing vehicles Download PDFInfo
- Publication number
- CN101544279A CN101544279A CN200810070793A CN200810070793A CN101544279A CN 101544279 A CN101544279 A CN 101544279A CN 200810070793 A CN200810070793 A CN 200810070793A CN 200810070793 A CN200810070793 A CN 200810070793A CN 101544279 A CN101544279 A CN 101544279A
- Authority
- CN
- China
- Prior art keywords
- forced landing
- car
- airplane fault
- landing vehicles
- airplane
- 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.)
- Pending
Links
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention aims to provide airplane fault forced landing vehicles which can be quickly combined and arranged on an airfield runway to achieve the safe landing of the airplane which cannot lay down landing gears in time according to airplane size and fault conditions. The vehicles respectively comprise a guiding segment vehicle, a middle segment vehicle and a buffer segment vehicle. The middle part of the front end of a vehicle frame in each segment is provided with a drawer type nest for mounting a rocket engine and a rocket engine set. The upper part of the vehicle frame in each segment is provided with different soft body guiding transfer devices, soft body middle transfer slide-in devices and buffer devices of an airplane safe slide-in forced landing vehicle according to different requirements on each segment vehicle.
Description
(1) technical field:
The present invention relates to a kind of airplane fault forced landing vehicles.
(2) background technology:
If the aircraft alighting gear has had problem at present, drop timely when aircraft landing, unique best bet is exactly to spray foam on the runway of forced landing, play the fire retardation of reasons such as forced landing bump when on fire, the result is that the lighter's aircraft is scrapped, but is the fatal crass mostly.
(3) summary of the invention:
The objective of the invention is to provide a kind of can be according to the aircraft size, failure condition require Rapid Combination to be arranged into airfield runway to realize that aircraft is at the timely fault of drop of when landing, equipment-airplane fault forced landing vehicles that aircraft safety is force-landed.
The present invention includes and be provided with the introduction segment car, interlude car and breeze way car.Mainly also be provided with drawer type nest and the rocket engine group that is used for installing rocket engine every section vehicle frame front center.Require differently on vehicle frame top according to the effect of every section car, be provided with software that different aircraft safeties slips into forced landing car and import to carry in the middle of feedway and the software and slip into device and shock absorber.
(4) description of drawings:
Fig. 1 is an introduction segment car lateral plan of the present invention.
Fig. 2 is an interlude car lateral plan of the present invention.
Fig. 3 is a breeze way car lateral plan of the present invention.
Fig. 4 uses arrangement plan for the present invention.
Fig. 5 arranges for rocket engine of the present invention and the igniting packet diagram.
Fig. 6 is A of the present invention, B, C, D4 kind combination layout birds-eye view.
(5) specific embodiment:
The present invention is described in detail below in conjunction with accompanying drawing:
As Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, shown in Figure 6, the present invention mainly is made up of introduction segment car 1, interlude car 2, breeze way car 3, pipe link 4, rocket motor ignition flip flop equipment 5,6,7.The front middle part of every section car is provided with the rocket engine drawer type nest 15 that is used to install rocket engine 20, rocket motor ignition control plug board 44, the forward and backward below of every section car is provided with wheel 16 and is provided with recoil spring 43 separately, vehicle frame 21 tops are provided with frame beam 55, left and right, the place ahead of introduction segment car frame beam, the front, rear, left and right of interlude car frame beam, left and right, the rear of breeze way car frame beam all are provided with the bamboo shoot mouth 39 that is used to be connected.
Interlude car 2, frame beam 55 is provided with cylinder stay bearing plate 45, and the cylinder stay bearing plate is fixed on the frame beam 55 with screw.Software load-transfer device 11 is divided into three layers of 53,52,51 different densities, between cylinder 54 and the drum shaft 56 unilateral bearing is housed, and is used for aircraft and can only slides into and can not skid off.
Breeze way car 3, carriage frame beam 55 is provided with track 41, and front end is provided with support 36, and software hold-down arm 32 and software hold-down arm spring bumper 31 are housed on the support, and preceding half section of buffering software 58 is passed through button 35 and last button 33 down, and button is pricked on software hold-down arm 32.58 second half sections of software are attached on the liner plate 34, and the software head anchors with L template 12.The bottom of L template 12 is connected with movable support frame 37 with bearing pin, the movable support frame below is provided with the wheel 38 of being convenient to make the slip of movable support frame 37 front and back, movable support frame 37 and the support 36 middle spring horizontal shock absorbers 30 that are provided with, frame beam 55, the middle part, back is provided with and speed group 19 rocket engines, ignition trigger device 7, backguy 40.
Embodiment of the invention job description is as follows:
Arrange airplane fault forced landing vehicles according to breakdown plane size and failure condition, shown in A, the B of Fig. 6, C, D.Breakdown plane sets the runway of forced landing car and signal and commander in when forced landing by normal landing sequence alignment and force-lands.Aircraft is to first group of 17 rocket firing flip flop equipment of forced landing car high-speed flight bump forced landing car in the forced landing process.Rocket starts work, and aircraft forced landing car when entering the introduction segment car of forced landing car of forced landing is just started to walk to overtake.Slip into the forced landing car introduction segment car of an existing directed speed at aircraft, trigger second group of 18 accelerating rocket engine of igniting simultaneously.At this moment forced landing car improves the speed of forced landing car under the service condition at two groups of rockets simultaneously greatly, makes the aircraft of forced landing can slide into interlude car and breeze way car safely slowly.When slipping into the breeze way car, trigger the 3rd group 19 of igniting again, and fast rocket engine makes the speed of forced landing car slip into the speed of forced landing car substantially near aircraft, last aircraft is under the effect of shock absorber, and aircraft and forced landing car are with speed forward.At this moment one, two, three group of rocket engine is flame-out in order, and aircraft and forced landing car glide to walking in action of inertia and stop.
The present invention is novel, and is reasonable in design, is likely the another device of airport security grade requirement up to standard from now on.Its market outlook are considerable.
Claims (10)
1, a kind of airplane fault forced landing vehicles comprises introduction segment car 1, interlude car 2, and breeze way car 3, pipe link 4, rocket motor ignition flip flop equipment 5,6,7 is formed.It is characterized in that: the front middle part of every section car is provided with the rocket engine drawer type nest 15 that is used to install rocket engine 20.
2, airplane fault forced landing vehicles according to claim 1 is characterized in that: the forward and backward below of every section car is provided with wheel 16 and is provided with recoil spring 43 separately.
3, airplane fault forced landing vehicles according to claim 1 and 2 is characterized in that: vehicle frame 21 tops are provided with frame beam 55.
4, according to claim 1 or 3 described airplane fault forced landing vehicles, it is characterized in that: left and right, the place ahead of introduction segment car frame beam, the front, rear, left and right side of interlude car frame beam, left and right, the rear of breeze way car frame beam all are provided with the bamboo shoot mouth 39 that is used to be connected.
5, according to claim 1 or 3 or 4 described airplane fault forced landing vehicles, it is characterized in that: introduction segment car 1, frame beam 55, the rear portion is made as the inclined-plane.
6, airplane fault forced landing vehicles according to claim 1 is characterized in that: software load-transfer device 11 is divided into three layers of 53,52,51 different densities.
7, according to claim 1 or 6 described airplane fault forced landing vehicles, it is characterized in that: between cylinder 54 and the drum shaft 56 unilateral bearing is housed.
8, airplane fault forced landing vehicles according to claim 1 is characterized in that: front end is provided with support 36, and software hold-down arm 32 and software hold-down arm spring bumper 31 are housed on the support.
9, airplane fault forced landing vehicles according to claim 1 is characterized in that: the movable support frame below is provided with the wheel 38 of being convenient to make the slip of movable support frame 37 front and back.
10, airplane fault forced landing vehicles according to claim 1 is characterized in that: movable support frame 37 and the support 36 middle spring horizontal shock absorbers 30 that are provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810070793A CN101544279A (en) | 2008-03-24 | 2008-03-24 | Airplane fault forced landing vehicles |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810070793A CN101544279A (en) | 2008-03-24 | 2008-03-24 | Airplane fault forced landing vehicles |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101544279A true CN101544279A (en) | 2009-09-30 |
Family
ID=41191719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810070793A Pending CN101544279A (en) | 2008-03-24 | 2008-03-24 | Airplane fault forced landing vehicles |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101544279A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104724297A (en) * | 2015-03-02 | 2015-06-24 | 南通大学 | Anti-toppling system used during carrier rocket vertical descending recovery |
| CN107512388A (en) * | 2017-08-14 | 2017-12-26 | 交控科技股份有限公司 | A kind of the aircraft takeoffs and landings control system and method for the separation of Flight main body and undercarriage |
-
2008
- 2008-03-24 CN CN200810070793A patent/CN101544279A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104724297A (en) * | 2015-03-02 | 2015-06-24 | 南通大学 | Anti-toppling system used during carrier rocket vertical descending recovery |
| CN104724297B (en) * | 2015-03-02 | 2016-08-24 | 南通大学 | A kind of carrier rocket is vertically lowered back to the overturning-preventing system in time receiving |
| CN107512388A (en) * | 2017-08-14 | 2017-12-26 | 交控科技股份有限公司 | A kind of the aircraft takeoffs and landings control system and method for the separation of Flight main body and undercarriage |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205574298U (en) | Unmanned aerial vehicle rocket assist launcher | |
| CN102358430B (en) | Ship-borne aircraft capturing and arresting device | |
| CN103043220A (en) | Taking-off and landing system of shipboard aircraft of aircraft carrier and taking-off and landing method thereof | |
| CN104089547A (en) | Unfolding and locking device for foldable rudder face | |
| CN110116806B (en) | Device for butt joint of fixed-wing unmanned aerial vehicle and rotor wing launching platform | |
| US3000593A (en) | Carrier aircraft having an annular wing | |
| CN104786971A (en) | Separated anti-collision saloon car | |
| CN103482067A (en) | Pneumatic type built-in load releasing device | |
| CN101544279A (en) | Airplane fault forced landing vehicles | |
| CN103112591B (en) | Multipurpose pneumatic type launch airborne landing flight training device | |
| CN206841708U (en) | A kind of vapour-pressure type multi-rotor unmanned aerial vehicle undercarriage | |
| CN201176261Y (en) | Aeroplane fault forced landing vehicle | |
| CN105222646A (en) | A kind of high speed carrier loader and method realizing the horizontal transmitting of carrier rocket | |
| CN110615114A (en) | Method and device for assisting landing and landing of airplane | |
| CN109808873A (en) | A kind of straight line self-locking tail portion folding and unfolding buffer unit | |
| CN105292512A (en) | Airplane lander and landing system thereof | |
| CN102582836A (en) | Airplane with emergency landing device in fault | |
| RU2547208C1 (en) | Airborne vehicle | |
| CN110758748B (en) | Helicopter and ejection escape buffering device | |
| CN102431645A (en) | Anti-crash one-man helicopter | |
| CN100395160C (en) | Movable runway for plane landing | |
| CN102774506A (en) | Airplane forced landing trolley | |
| CN204056288U (en) | A kind of middle and short distance passenger transportation equipment | |
| CN103646602A (en) | Simulated ship-bone aircraft take-off and landing training platform | |
| US2996272A (en) | Controlled thrust ejection capsule rocket |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| DD01 | Delivery of document by public notice |
Addressee: Shen Jinzhong Document name: Notification that Application Deemed to be Withdrawn |
|
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20090930 |