CN101607601A - Rail mounted forced landing platform and control process - Google Patents
Rail mounted forced landing platform and control process Download PDFInfo
- Publication number
- CN101607601A CN101607601A CNA2008101109307A CN200810110930A CN101607601A CN 101607601 A CN101607601 A CN 101607601A CN A2008101109307 A CNA2008101109307 A CN A2008101109307A CN 200810110930 A CN200810110930 A CN 200810110930A CN 101607601 A CN101607601 A CN 101607601A
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- aircraft
- forced landing
- landing platform
- rail mounted
- implantation
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Abstract
Rail mounted forced landing platform comprises following formation: aircraft implantation, forced landing platform stand and rectilinear orbit, owing to adopted the rectilinear orbit mode, therefore can satisfy the straight line high speed gliding motility of forced landing aircraft, utilize the buffer action of aircraft implantation to reduce the impulsive contact force that the forced landing aircraft produces when landing, improved the probability of aircraft safety forced landing.
Description
Technical field
Occur aircraft fault or the airport standby quick track platform when suffering that accident makes that the airport can not provide the landing and sliding runway of aircraft that can not land when the present invention relates to a kind of aircraft landing, specifically relate to military airfield airplane emergency forced landing technology.
Background technology
At present, when force-landing, mostly adopt by aircraft runway to establish block or lubricant is spread on ground, have this problem has been proposed various inventions, as patent " undercarriage fault forced landing trailer " number of patent application 200510019929X, this invention adopts the automobile pattern of dragging to carry out forced landing, make it reach the purpose of safe landing, but this invention is to be based upon on the perfect basis of airfield runway, in case the airport is destroyed, when the runway landing can not be provided, this patented technology then exists if runway is when having scarce road or unfairness, or small-sized obstacle is arranged, can make " trailer " can not straight-line travelling, or turn over before and after causing trailer, problems such as rollover, when high-speed motion, " trailer " must someone be driven, and adopts driver's operation can have height accident potential, and aircraft lands speed per hour usually about hundred kilometers when landing, and the self-propelled vehicle of up to a hundred kilometers of speed per hours almost nobody can drive, the driverless operation technology also is in conceptual phase under the situation of running at high speed at present.
The invention benefit
The research of forced landing support system flat-bed is of great significance.Fighter plane tends to cause grave accidents such as fatal crass when landing after alighting gear is ineffective.This platform technology is exactly the damaged aircraft ineffective to alighting gear, plays the safety control effect when coming back to the base land.Particularly under war condition, guarantee the normal land of damaged aircraft, just guaranteed my army's fighter plane effective strength, for effectively shortening the time of battlefield damage repairing, the work efficiency that improves repairing provides strong guarantee.
Summary of the invention
Existing problem during at above original forced landing, the technical problem to be solved in the present invention provides rail mounted forced landing platform and control process, comprise following formation: the aircraft implantation, on described aircraft implantation, possessed the buffering gauze pad, linked network is protected groove, aircraft implantation chassis, head spillway and the external power plant Connection Block that has at least more than four, when aircraft adopts the aircraft implantation as accepting object when force-landing, owing to have described buffering gauze pad on this implantation, can reduce the destructive force that produces because of colliding, linked network on described implantation is protected groove, can protect because of aircraft deviations side and rush the aircraft implantation, make this buffering gauze pad break away from described forced landing platform, described head spillway can make the head of the aircraft of forced landing exceed outside this buffering gauze pad when forced landing, more help getting in touch and safe escape of aviator and ground staff, described external power plant Connection Block can be installed the power plant of no more than power plant Connection Block number, with the demand of the aircraft that satisfies different model necessary requirement different motion speed when the forced landing; Forced landing platform stand, the stand that has more than at least two on described forced landing platform stand is striden beam, has the electric controlled brake device that contains automatic detection in described forced landing platform stand bottom, both sides in described forced landing platform stand bottom have damping spring, described stand is striden beam across on described rectilinear orbit, guarantee that described forced landing platform can be along rail running, this stand is striden the bar number of beam on the forced landing platform can be according to bearing gravity adjustment in the centre of guaranteeing this platform maximum speed in the cards and described platform stand, described damping spring can reduce this forced landing platform because of slide the degree of jolting that produces at a high speed on described rectilinear orbit, the electric controlled brake device of described automatic detection has adopted the mature technology of railway locomotive electric braking, guarantees can reach the purpose that safety stops by slow deceleration of classification at described forced landing platform on the system trajectory; Rectilinear orbit, at described rectilinear orbit, the bottom surface is provided with fixed track railway spike hole, the two ends of track are provided with the track joint face, adopted described rectilinear orbit, except condition, can also realize the purpose that described platform slides at a high speed in orbit fast with the linear ramp that can satisfy the forced landing aircraft, comparatively wide to described rectilinear orbit in the environmental requirement of laying, can realize setting up fast requirement; Described linked network is protected the inboard of groove and is adopted fire-resistant soft material to constitute, can avoid aircraft to produce secondary on described platform ignites, its frame adopts metallic material and is connected with described aircraft implantation chassis, the metal fiber rope that the nettle that described buffering gauze pad is adopted has intensity and pulling force constitutes, make the buffering gauze pad made from this kind material have better elastic and pulling force, the buffering gauze pad protects embedded slot with described linked network and is connected, the inside of buffering gauze pad has the mesh space that waits of placing soft weighting material, and the soft weighting material of filling in this space can be changed the impulsive contact force that subtracts aircraft once more.Described external power plant Connection Block is positioned at the rear end on aircraft implantation chassis, this Connection Block can connect engine installation, in complete horizontal fixed power plant, owing to have certain space in the rear end on implantation chassis, can realize the adjustment at the interval of described Connection Block, the electric controlled brake device that contains automatic detection is installed in the both sides of load-carrying moving wheel below the aircraft implantation chassis.Described stand is striden beam and is had one and stride the beam axis, load-carrying moving wheel with at least more than one is installed striding beam axis both sides, moving wheel contacts with described rectilinear orbit is vertical, this load-carrying wheel has adopted existing railway locomotive wheel technology can realize the flat-bed high speed gliding motility of force-landing fully, the both sides that described stand is striden beam have the beam of striding extension axle, extend and balance auxiliary motion wheel to be installed on the axle striding beam, the balance auxiliary wheel can be so that the probability of aircraft rollover greatly reduces.Described rectilinear orbit is the channel-section steel type, narrow slightly above, the bottom surface is wide slightly, it is through hole that the bottom surface is provided with fixed track railway spike hole, be used for rectilinear orbit fixing on sleeper, it is plumb cut that the two ends of track are provided with the track joint face, and the connection of whole piece rail mounted forced landing runway is finished in the butt joint that can finish many tracks.
Process to described rail mounted forced landing platform is controlled may further comprise the steps:
In the 1st step,, make parked rail mounted forced landing platform controlled motion in orbit by the power plant on the remote control equipment (RCE) startup rail mounted forced landing platform;
In the 2nd step, make rail mounted forced landing flat-bed kinematic velocity descending speed with aircraft when aircraft contacts this platform identical by remote control equipment (RCE);
The 3rd step fell within this platform when the electric controlled brake device of automatic detection detects aircraft, or after receiving the cutoff command that wireless device sends, and closed engine installation and started electric controlled brake device simultaneously and implement brake;
Description of drawings
Fig. 1 is rail mounted forced landing platform scheme drawing of the present invention;
Fig. 2 protects the pit nation scheme drawing of groove for rail mounted forced landing platform linked network of the present invention;
Fig. 3 strides the beam scheme drawing for rail mounted forced landing platform stand of the present invention;
Fig. 4 contacts scheme drawing for rail mounted forced landing platform of the present invention with the forced landing aircraft;
Wherein, 10-aircraft implantation, 11-cushions gauze pad, 12-head spillway, the 13-linked network is protected groove, the external power plant Connection Block of 14-, the 15-net protects the pit nation of groove, and the 20-stand is striden beam, and 21-strides the beam axis, 22-load-carrying moving wheel, 23-balance auxiliary motion wheel, 24-are striden beam extension axle, 30-rectilinear orbit, 31-track joint face, 32-fixed track railway spike hole.
The specific embodiment
Practice below in conjunction with accompanying drawing and typical case and to explain the present invention in more detail.
See also Fig. 1, the technical problem to be solved in the present invention provides rail mounted forced landing platform and control process, comprise following formation: aircraft implantation 10, on described aircraft implantation 10, possessed buffering gauze pad 11, linked network is protected groove 13, aircraft implantation chassis, head spillway 12 and the external power plant Connection Block 14 that has at least more than four, when aircraft adopts aircraft implantation 10 as accepting object when force-landing, owing to have described buffering gauze pad 11 on this implantation 10, can reduce the destructive force that produces because of colliding, linked network on described implantation 10 is protected groove 13, can protect because of aircraft deviations side and rush aircraft implantation 10, make this buffering gauze pad 11 can not break away from described forced landing platform, described head spillway 12, the head that can make the forced landing aircraft time exceeds outside this buffering gauze pad 11 in forced landing, more help getting in touch and safe escape of aviator and ground staff, described external power plant Connection Block 14, the power plant of no more than power plant Connection Block 14 numbers can be installed, demand with the aircraft that satisfies different model necessary requirement different motion speed when the forced landing, aircraft implantation 10 is to adopt array mode to realize bonded assembly with described forced landing platform stand, therefore can select multi-form aircraft implantation 10 to combine with forced landing platform stand according to the kind of aircraft;
See also Fig. 2,3, forced landing platform stand, the stand that has more than at least two on described forced landing platform stand is striden beam 20, the width that this stand is striden beam depends on the cabin width requirement, has the electric controlled brake device that contains automatic detection in described forced landing platform stand bottom, can in braking procedure, realize autobrake, both sides in described forced landing platform stand bottom have damping spring, described stand is striden beam 20 across on described rectilinear orbit 30, guarantee that described forced landing platform can travel along rectilinear orbit 30, this stand is striden the bar number of beam 20 on the forced landing platform, can be according to bearing gravity adjustment in the centre of guaranteeing this platform maximum speed in the cards and described platform stand, described damping spring can reduce this forced landing platform because of slide the degree of jolting that produces at a high speed on described rectilinear orbit 30, the electric controlled brake device of described automatic detection has adopted the mature technology of railway locomotive electric braking, guarantee on system trajectory 30, can classification slowly to slow down, reach the purpose that safety stops at described forced landing platform; Rectilinear orbit 30, on described rectilinear orbit 30 bottom surfaces, be provided with fixed track railway spike hole 32, the two ends of track are provided with track joint face 31, adopted described rectilinear orbit 30, except condition with the linear ramp that can satisfy the forced landing aircraft, can also realize the purpose that described platform slides at a high speed in orbit fast, comparatively wide to described rectilinear orbit 30 in the environmental requirement of laying, can realize setting up fast and repairing requirement;
Described linked network is protected the inboard of groove 13 and is adopted fire-resistant soft material to constitute, can avoid aircraft to produce secondary on described platform ignites, its frame adopts metallic material, the height of this frame can be lower than the thickness of described buffering gauze pad 11, and be connected with described aircraft implantation chassis, the metal fiber rope that the nettle that described buffering gauze pad 11 is adopted has intensity and pulling force constitutes, make the buffering gauze pad made from this kind material 11 have better elastic and pulling force, buffering gauze pad 11 protects 15 embedded connections of groove with described linked network, the inside of buffering gauze pad 11 has the mesh space that waits of placing soft weighting material, and the soft weighting material of filling in this space can be changed the impulsive contact force that subtracts aircraft once more.Described external power plant Connection Block 14 is positioned at the rear end on aircraft implantation chassis, this Connection Block 14 can connect engine installation, the engine installation that adopts can be an aero-engine, it also can be rocket booster, in complete horizontal fixed power plant,, can realize the adjustment at the interval of described Connection Block owing to, have certain space in the rear end on implantation chassis, the electric controlled brake device that contains automatic detection is installed in the both sides of load-carrying moving wheel 22 below the aircraft implantation chassis.Described stand is striden beam 20 and is had one and stride beam axis 21, load-carrying moving wheel 22 with at least more than one is installed striding beam axis 21 both sides, plant heavy moving wheel 22 and described rectilinear orbit 30 vertical contacts, this load-carrying wheel 22 has adopted existing railway locomotive wheel technology, can realize the flat-bed high speed gliding motility of force-landing fully, described stand is striden the both sides of beam 21, has the beam of striding extension axle 24, extend and balance auxiliary motion wheel 23 to be installed on the axle 24 striding beam, balance auxiliary wheel 23 can be so that the probability of aircraft rollover greatly reduces.Described rectilinear orbit 30 is the channel-section steel type, and narrow slightly above, the bottom surface is wide slightly, the bottom surface is provided with fixed track railway spike hole 31, be used for rectilinear orbit 30 fixing on sleeper, the two ends of track are provided with track joint face 32, and the connection of whole piece rail mounted forced landing runway is finished in the butt joint that can finish many tracks.
Process to described rail mounted forced landing platform is controlled may further comprise the steps:
The 1st step, by the power plant on the remote control equipment (RCE) startup rail mounted forced landing platform, as the aircraft driving engine, make parked rail mounted forced landing platform controlled motion in orbit, the engine installation of controlled starting is many table apparatus, can realize adjusting the order of igniting by remote control equipment (RCE), to reach the motion from slow to fast of forced landing platform;
The 2nd step, make rail mounted forced landing flat-bed kinematic velocity descending speed with aircraft when aircraft contacts this platform identical by remote control equipment (RCE), touch the forced landing flat-bed at the forced landing aircraft and have only both kinematic velocity basically identicals just can make stable the falling within on the forced landing platform of forced landing aircraft constantly;
The 3rd step, when detecting aircraft, the electric controlled brake device of automatic detection falls within this platform, or after receiving the cutoff command that wireless device sends, close engine installation and start electric controlled brake device enforcement brake simultaneously, because electric control braking can progressively pressurize, so braking procedure can be realized progressively adjusting rate of braking and stops gliding motility until the forced landing platform.
Only be one embodiment of the present invention below, be not limited to the present invention, for a person skilled in the art, the present invention can have various changes, variation and omission.For example, change the form of aircraft implantation, the implantation periphery is installed indicator lamp; the single track rail of rectilinear orbit is become two pass rail etc.; within the spirit and principles in the present invention all, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (6)
1, rail mounted forced landing platform is characterized in that, comprises following formation: the aircraft implantation has possessed the buffering gauze pad, linked network is protected groove, aircraft implantation chassis, head spillway and have external power plant Connection Block more than four at least on described aircraft implantation; Forced landing platform stand, the stand that has more than at least two on described forced landing platform stand is striden beam, has the electric controlled brake device that contains automatic detection in described forced landing platform stand bottom, has damping spring in the both sides of described forced landing platform stand bottom; Rectilinear orbit, at described rectilinear orbit, the bottom surface is provided with fixed track railway spike hole, and the two ends of track are provided with the track joint face.
2, rail mounted forced landing platform according to claim 1, it is characterized in that: described linked network is protected the inboard of groove and is adopted fire-resistant soft material to constitute, its frame adopts metallic material and is connected with described aircraft implantation chassis, the metal fiber rope that the nettle that described buffering gauze pad is adopted has intensity and pulling force constitutes, the buffering gauze pad protects embedded slot with described linked network and is connected, and the inside of buffering gauze pad has the mesh space that waits of placing soft weighting material.
3, rail mounted forced landing platform according to claim 1, it is characterized in that: described external power plant Connection Block is positioned at the rear end on aircraft implantation chassis, this Connection Block can connect engine installation, and the electric controlled brake device that contains automatic detection is installed in the both sides of load-carrying moving wheel below the aircraft implantation chassis.
4, rail mounted forced landing platform according to claim 1, it is characterized in that: described stand is striden beam and is had one and stride the beam axis, load-carrying moving wheel with at least more than one is installed striding beam axis both sides, moving wheel contacts with described rectilinear orbit is vertical, the both sides that described stand is striden beam have the beam of the striding axle that extends, and extend and balance auxiliary motion wheel are installed on the axle striding beam.
5, rail mounted forced landing platform according to claim 1, it is characterized in that: described rectilinear orbit is the channel-section steel type, and narrow slightly above, the bottom surface is wide slightly, and the bottom surface is provided with fixed track railway spike hole, and the two ends of track are provided with the track joint face.
6, a kind of process that the forced landing of rail mounted described in claim 1 platform is controlled is characterized in that, may further comprise the steps:
In the 1st step,, make parked rail mounted forced landing platform controlled motion in orbit by power plant such as the aircraft driving engine on the remote control equipment (RCE) startup rail mounted forced landing platform;
In the 2nd step, make rail mounted forced landing flat-bed kinematic velocity descending speed with aircraft when aircraft contacts this platform identical by remote control equipment (RCE);
The 3rd step fell within this platform when the electric controlled brake device of automatic detection detects aircraft, or after receiving the cutoff command that wireless device sends, and closed engine installation and started electric controlled brake device simultaneously and implement brake.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008101109307A CN101607601A (en) | 2008-06-17 | 2008-06-17 | Rail mounted forced landing platform and control process |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008101109307A CN101607601A (en) | 2008-06-17 | 2008-06-17 | Rail mounted forced landing platform and control process |
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| Publication Number | Publication Date |
|---|---|
| CN101607601A true CN101607601A (en) | 2009-12-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008101109307A Pending CN101607601A (en) | 2008-06-17 | 2008-06-17 | Rail mounted forced landing platform and control process |
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| Country | Link |
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| CN (1) | CN101607601A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103373473A (en) * | 2012-04-11 | 2013-10-30 | 周庆才 | Aircraft pathway running takeoff and landing assisting device |
| CN105151312A (en) * | 2015-09-30 | 2015-12-16 | 罗元建 | Buried type automatic aircraft traction system and traction method |
| 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 |
| CN114212257A (en) * | 2022-01-10 | 2022-03-22 | 中国民用航空飞行学院 | Safety auxiliary device for forced landing of airplane |
-
2008
- 2008-06-17 CN CNA2008101109307A patent/CN101607601A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103373473A (en) * | 2012-04-11 | 2013-10-30 | 周庆才 | Aircraft pathway running takeoff and landing assisting device |
| CN105151312A (en) * | 2015-09-30 | 2015-12-16 | 罗元建 | Buried type automatic aircraft traction system and traction method |
| 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 |
| CN114212257A (en) * | 2022-01-10 | 2022-03-22 | 中国民用航空飞行学院 | Safety auxiliary device for forced landing of airplane |
| CN114212257B (en) * | 2022-01-10 | 2023-04-11 | 中国民用航空飞行学院 | Safety auxiliary device for forced landing of airplane |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Open date: 20091223 |