CN1915744A

CN1915744A - Force landing chassis in failure of landing gear

Info

Publication number: CN1915744A
Application number: CN 200510019929
Authority: CN
Inventors: 周柏林; 李文良
Original assignee: Individual
Current assignee: Individual
Priority date: 2005-11-29
Filing date: 2005-11-29
Publication date: 2007-02-21
Anticipated expiration: 2025-11-29
Also published as: CN100387487C

Abstract

A supporting car used for the forced landing of airplane due to the failure of landing chassis is composed of a platform car, wheels, a fixed platform, airplane supporting frame, accelerating rocket, decelerating umbrella, intelligent high-speed camera, laser distance finder, servo motor, and control circuit consisting of programmable PLC controller, power supply, gravitational sensor, etc.

Description

Force landing chassis in failure of landing gear

Technical field

The present invention relates to a kind ofly be used for that aircraft takeoffs and landings breaks down and the holder car that can't open time forced landing usefulness belongs to airport airplane emergency forced landing technical field.

Background technology

Undercarriage is the device of taking off, must using when landing.When aircraft flight, in the alighting gear income abdomen, with the minimizing flight resistance, but necessary drop before the aircraft landing is faced the enormous impact power of aircraft to cushion ground, realizes the aircraft safety landing.When the alighting gear et out of order, aircraft landing can't drop, thereby causes airframe directly to contact with ground, when aircraft holds when can't stand ground to its enormous impact friction force that brings, fatal crass's serious accident can take place just.Up to the present, when undercarriage can't be opened and when force-landing, the airport can only be to establish block or spill lubricant on ground on runway, and does not have to make the emergency landing device of the normal safe landing of aircraft.

Summary of the invention

Purpose of the present invention is exactly to provide at above-mentioned weak point that a kind of aircraft can be at the force landing chassis in failure of landing gear of the normal safe landing in airport when undercarriage can't be opened.

Technical solution of the present invention is: a kind of force landing chassis in failure of landing gear is characterized in that: comprise flat frame and be located at wheel below this flat frame; Be provided with fixed platform at the flat frame middle part; This fixed platform is provided with and the corresponding identical aircraft carriage of aircraft lower surface shape; Be provided with acceleration rocket in flat frame tail end bilateral symmetry, be provided with rocket igniter in this acceleration rocket; Tail end bilateral symmetry in fixed platform is provided with the deceleration pack, and this deceleration parachute is wrapped and is provided with the electromagnetism parachute opening device; On the fixed platform of deceleration pack inboard, both sides, be respectively equipped with high-speed intelligent pick up camera and laser rangefinder; Be provided with intelligent camera in flat frame front end centre; The wheel of flat frame front end bottom connects with vehicle frame by steering hardware, and the deflecting bar of this steering hardware connects with the output shaft of servomotor on being fixed on vehicle frame; Be provided with braking mechanism on wheel, be provided with servomotor on flat frame, the control stalk of this braking mechanism connects with the output shaft of servomotor; Comprise that also the holder car that is made of high-speed intelligent pick up camera, laser rangefinder, PLC Programmable Logic Controller and rocket igniter quickens control circuit, wherein, the V of high-speed intelligent pick up camera, D, O end connect with one group of I/O end of PLC Programmable Logic Controller, the V of laser rangefinder, D, O end connect with another group I/O end of PLC Programmable Logic Controller, and rocket igniter connects with the mouth of PLC Programmable Logic Controller (13); Constitute line of centers observing and controlling steering controling circuit by intelligent camera, PLC Programmable Logic Controller, power supply amplification module and servomotor, wherein, the V of intelligent camera, D, O end connect with the I/O end of PLC Programmable Logic Controller, power supply amplification module input end connects with the mouth of PLC Programmable Logic Controller, and power supply amplification module mouth connects with the servo motor power supply control end; Constitute the slowing-down brake control circuit by weight sensor, PLC Programmable Logic Controller, power relay, electromagnetism parachute opening device, power supply amplification module, servomotor, wherein, the weight sensor mouth connects with PLC Programmable Logic Controller I/O end, one group of mouth of power relay input end and PLC Programmable Logic Controller connects, mouth connects with the electromagnetism parachute opening device, power supply amplification module input end connects with another mouth of PLC Programmable Logic Controller, and mouth connects with the servomotor input end.

The present invention is owing to adopt by vehicle frame, the holder car that wheel constitutes, and on vehicle frame, be fixed with and the corresponding identical aircraft carriage of aircraft lower surface shape, be respectively equipped with acceleration rocket in vehicle frame tail end both sides, the deceleration pack, be provided with intelligent camera at the vehicle frame front end, be provided with high-speed intelligent pick up camera and laser rangefinder at the vehicle frame rear portion, on vehicle frame front end wheel, be provided with steering hardware, on wheel, be provided with braking mechanism, employing is by the high-speed intelligent pick up camera, laser rangefinder, the holder car that PLC Programmable Logic Controller and rocket igniter constitute quickens control circuit, employing is by weight sensor, the PLC Programmable Logic Controller, power relay, the electromagnetism parachute opening device, the power supply amplification module, the slowing-down brake control circuit that servomotor constitutes, thereby, when undercarriage can't normally be opened for some reason, aviator airport earthward requires assistance, the airport places designated runway landing end with holder car of the present invention, and open operating switch, the position of holder vehicle automatic monitoring breakdown plane, speed, after the forced landing aircraft enters down the skating area setpoint distance, start electric firearm and make rocket firing, the holder car quickens rapidly and travels along runway centerline, reach the speed identical then with breakdown plane, identical position, at this moment, breakdown plane drops on the aircraft carriage, after weight sensor detects aircraft landing, control circuit is opened the deceleration pack, simultaneously, the action of control braking mechanism, holder car carrying breakdown plane slides, slow down, stop, making the breakdown plane safe landing.Because spot speed, the position of breakdown plane landing are all identical with speed, the position of holder car, and the breakdown plane low profile is identical with the carriage shape, thereby, after dropping on the holder car, just slided breakdown plane by the carrying of holder car, and there is not excessive friction between it, make the suffered impulsive force of breakdown plane reach minimum, in the scope of safety, avoided fatal crass in the forced landing process.The present invention is mainly used in the safety forced landing of the breakdown plane of alighting gear can't open the time on the airport.

Description of drawings

Fig. 1 is a main TV structure scheme drawing of the present invention; Fig. 2 is a plan structure scheme drawing of the present invention; Fig. 3 is a backsight structural representation of the present invention; Fig. 4 is that the present invention quickens control circuit figure; Fig. 5 is line of centers observing and controlling steering controling circuit figure of the present invention; Fig. 6 is slowing-down brake control circuit figure of the present invention.

The specific embodiment

Holder bassinet structure of the present invention such as Fig. 1, Fig. 2, shown in Figure 3.Vehicle frame 1 is a flat frame, trapezoidal for symmetry, and inswept, the rear end is wide.Wheel has three groups, and wheel 2 is in vehicle frame 1 front center, and wheel 3 symmetries are located at both sides, vehicle frame 1 rear end.Wheel 2 connects with vehicle frame 1 by steering hardware, and the deflecting bar of this steering hardware connects with the output shaft of servomotor 9 on being fixed on vehicle frame 1.Be equipped with braking mechanism on the

wheel

2,3, the control stalk of this braking mechanism connects with the output shaft of servomotor.Fixed platform 12 is arranged on vehicle frame 1 middle part, also is the trapezoidal of symmetry, and solid welding is on vehicle frame 1.Aircraft carriage 6 is fixed on the fixed platform 12.Aircraft carriage 6 surface configurations and aircraft lower surface shape match.Because of the aircraft type difference, surface configuration, the size of aircraft carriage 6 also have nothing in common with each other.Since the speed difference that aircraft descends, the distance of glide difference, thereby the explosive load of rocket does not wait because of various aircrafts yet.Two acceleration rocket 4 symmetry branches are located at vehicle frame 1 tail end both sides.Be provided with rocket igniter in the acceleration rocket 4.Rocket igniter is made up of circuit hot and discharging gap.Two deceleration packs were located at the tail end both sides of fixed platform 12 in 5 minutes, and this deceleration pack 5 is provided with the electromagnetism parachute opening device.The electromagnetism parachute opening device is made up of single or double acting door and electromagnet snib.On the fixed platform 12 of both sides deceleration pack 5 inboards, be respectively equipped with high-speed intelligent pick up camera 10 and laser rangefinder 11.High-speed intelligent pick up camera 10 is a YH5705 type high-speed intelligent pick up camera, enters down the aircraft of skating area in order to supervision.Laser rangefinder 11 is the laser rangefinder of YP1000 type, enters down the aircraft of skating area in order to supervision.Intelligent camera 8 is located at the middle part of vehicle frame 1 front end, is the ADTB12 intelligent camera, in order to monitor runway centerline in holder garage advances.Electrical control cubicles 7 is located at vehicle frame 1 front end, and electrical controller all is contained in the cabinet.

The present invention quickens control circuit figure as shown in Figure 4.The holder car quickens control circuit and is made of high-speed intelligent pick up camera 10, laser rangefinder 11, PLC Programmable Logic Controller 13 and rocket igniter 14.PLC Programmable Logic Controller 13 adopts the PLC Programmable Logic Controller of 6ES7216-2AD21-OXBOZ type, and this controller has 8 I/O input ports, and the present invention has only used 2.Rocket igniter 14 makes rocket firing in order to initial igniter.12OHA type battery pack 15 is in order to give PLC Programmable Logic Controller 13 and rocket igniter 14 power supplies.The V of high-speed intelligent pick up camera 10, D, O end connect with one group of I/O end of PLC Programmable Logic Controller 13, the V of laser rangefinder 11, D, O end connect with another group I/O end of PLC Programmable Logic Controller 13, and rocket igniter 14 connects with the mouth of PLC Programmable Logic Controller 13.In the time of after aircraft enters down the skating area, the alerting signal of high-speed intelligent pick up camera 10 output image signals and switching value is to the I/O mouth " 1 " of PLC Programmable Logic Controller 13.Enter down the setpoint distance (the aircraft setpoint distance difference of different model) of skating area when aircraft after, laser rangefinder 11 provides the alerting signal of switching value.PLC Programmable Logic Controller 13 is in order to the analog signal and the digital signal of identification and the input of computing I/O mouth, and export control signal by setup program, when the aircraft picture signal of skating area under the entering that high-speed intelligent pick up camera 10 and laser rangefinder 11 gathered and range signal reach setting apart from the time, the signal of i.e. output control rocket firing starts rocket igniter 14 and makes rocket firing.

Line of centers observing and controlling steering controling circuit of the present invention as shown in Figure 5.Line of centers observing and controlling steering controling circuit is made of intelligent camera 8, PLC Programmable Logic Controller 16, power supply amplification module 17 and servomotor 9.Intelligent camera 8 is the ADTB12 intelligent camera, PLC Programmable Logic Controller 16 is a 6ES7216-2AD21-OXBOZ type PLC Programmable Logic Controller, power supply amplification module 17 is a QCA150AA100IGBT power supply amplification module, servomotor 9 adopts SXMINAS type servomotor, and power supply 15 is in order to give circuit supply shown in Figure 5.The V of intelligent camera 8, D, O end connect with the I/O mouth of PLA Programmable Logic Controller 16, and power supply amplification module 17 input ends connect with the mouth of PLA Programmable Logic Controller 16, and power supply amplification module 17 mouths connect with servomotor 9 power control terminals.Intelligent camera 8 is in order to monitor runway centerline in holder garage advances, because of intelligent camera 8 is to be fixed on holder car front central, and therefore can output pulse signal when holding in the palm car drift off the runway line of centers.PLC Programmable Logic Controller 16 is in order to export control signal by setup program with the pulse digital signal of I/O mouth.Power supply amplification module 17 is finished mechanical action in order to weak impulse singla is amplified back promotion servomotor 9.Servomotor 9 is in order to drive steering box control holder car direction.

Slowing-down brake control circuit of the present invention as shown in Figure 6.The slowing-down brake control circuit is made of weight sensor 18, PLC Programmable Logic Controller 19, power relay 20, electromagnetism parachute opening device 21, power supply amplification module 22, servomotor 23.Weight sensor 18 is in order to the weight of monitoring holder car carrying, PLC Programmable Logic Controller 19 adopts 6ES7216-2AD21-OXBOZ type PLC Programmable Logic Controller, power relay 20 adopts the JRX power relay, electromagnetism parachute opening device 21 is made up of single or double acting door and electromagnet snib, power supply amplification module 22 adopts IGBT power supply amplification module, and servomotor 23 adopts SXMINAS type servomotor.Weight sensor 18 mouths connect with the I/O mouth of PLC Programmable Logic Controller 19, power relay 20 input ends connect with PLC Programmable Logic Controller 19 mouths, power relay 20 mouths connect with electromagnetism parachute opening device 21, power supply amplification module 22 input ends connect with PLC Programmable Logic Controller 19 another mouths, and power supply amplification module 22 mouths connect with servomotor 23 input ends.When aircraft dropped on the holder car, weight sensor 18 was promptly exported the signal of switching value.PLC Programmable Logic Controller 19 is in order to monitor the signal of weight sensor 18, when the signal of I/O mouth " 1 " reaches setting program, OUT " 1 " promptly exports the parachute-opening bag signal of switching value, and OUT " 2 " i.e. while output pulse string brakes to " B1X ", the startup of " B2X " control servomotor of servomotor 23.The parachute-opening bag signal that power relay 20 is exported in order to the OUT " I " with PLC Programmable Logic Controller 19 amplifies 21 actions of drive electromagnetism parachute opening device and finishes the action of opening pack.Finishing parachute-opening kinetic energy when electromagnetism parachute opening device 21 moves in order to power relay 20 suctions slows down the holder car.Power supply amplification module 22 amplifies in order to the pulse brake signal with the OUT " 2 " of PLC Programmable Logic Controller 19, drives servomotor 23 execution.

Claims

1, a kind of force landing chassis in failure of landing gear is characterized in that: comprise flat frame (1) and be located at the following wheel (2,3) of this flat frame (1); Be provided with fixed platform (12) at flat frame (1) middle part; This fixed platform (12) is provided with and the corresponding identical aircraft carriage (6) of aircraft lower surface shape; Be provided with acceleration rocket (4) in flat frame (1) tail end bilateral symmetry, this acceleration rocket is provided with rocket igniter in (4); Tail end bilateral symmetry in fixed platform (12) is provided with deceleration pack (5), and this deceleration pack (5) is provided with the electromagnetism parachute opening device; On the fixed platform (12) of both sides deceleration pack (5) inboard, be respectively equipped with high-speed intelligent pick up camera (10) and laser rangefinder (11); Be provided with intelligent camera (8) in flat frame (1) front end centre; The wheel (2) of flat frame (1) front end bottom connects with vehicle frame by steering hardware, and the deflecting bar of this steering hardware connects with the output shaft of servomotor (9) on being fixed on vehicle frame (1); Be provided with braking mechanism on wheel (2,3), be provided with servomotor on flat frame (1), the control stalk of this braking mechanism connects with the output shaft of servomotor; Comprise that also the holder car that is made of high-speed intelligent pick up camera (10), laser rangefinder (11), PLC Programmable Logic Controller (13) and rocket igniter (14) quickens control circuit, wherein, V, the D of high-speed intelligent pick up camera (10), O end connects with one group of I/O end of PLC Programmable Logic Controller (13), V, the D of laser rangefinder (11), O end connects with another group I/O end of PLC Programmable Logic Controller (13), and rocket igniter (14) connects with the mouth of PLC Programmable Logic Controller (13); Constitute line of centers observing and controlling steering controling circuit by intelligent camera (8), PLC Programmable Logic Controller (16), power supply amplification module (17) and servomotor (9), wherein, V, the D of intelligent camera (8), O end connects with the I/O end of PLC Programmable Logic Controller (16), power supply amplification module (17) input end connects with the mouth of PLC Programmable Logic Controller (16), and power supply amplification module (17) mouth connects with servomotor (9) power control terminal; By weight sensor (18), PLC Programmable Logic Controller (19), power relay (20), electromagnetism parachute opening device (21), power supply amplification module (22), servomotor (23) constitutes the slowing-down brake control circuit, wherein, weight sensor (18) mouth connects with PLC Programmable Logic Controller (19) I/O end, (19) one groups of mouths of power relay (20) input end and PLC Programmable Logic Controller connect, mouth connects with electromagnetism parachute opening device (21), power supply amplification module (22) input end connects with another mouth of PLC Programmable Logic Controller (19), and mouth connects with servomotor (23) input end.