CN106043710A - Aerial pilotless manned escaping device - Google Patents
Aerial pilotless manned escaping device Download PDFInfo
- Publication number
- CN106043710A CN106043710A CN201610406572.9A CN201610406572A CN106043710A CN 106043710 A CN106043710 A CN 106043710A CN 201610406572 A CN201610406572 A CN 201610406572A CN 106043710 A CN106043710 A CN 106043710A
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- sealed compartment
- compartment
- parachute
- escape
- control system
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 17
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 18
- 238000010276 construction Methods 0.000 claims description 15
- 230000007423 decrease Effects 0.000 claims description 11
- 239000000110 cooling liquid Substances 0.000 claims description 9
- 229910052757 nitrogen Inorganic materials 0.000 claims description 9
- 230000005484 gravity Effects 0.000 claims description 6
- 239000002994 raw material Substances 0.000 claims description 6
- 239000000203 mixture Substances 0.000 claims description 5
- 239000000956 alloy Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 230000004888 barrier function Effects 0.000 claims description 3
- 230000003247 decreasing effect Effects 0.000 claims description 3
- DMBHHRLKUKUOEG-UHFFFAOYSA-N diphenylamine Chemical compound C=1C=CC=CC=1NC1=CC=CC=C1 DMBHHRLKUKUOEG-UHFFFAOYSA-N 0.000 claims description 3
- 230000009429 distress Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000006698 induction Effects 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- 238000012544 monitoring process Methods 0.000 claims description 3
- 230000035939 shock Effects 0.000 claims description 3
- 238000009432 framing Methods 0.000 claims description 2
- 239000000295 fuel oil Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 238000007789 sealing Methods 0.000 abstract description 3
- 235000007237 Aegopodium podagraria Nutrition 0.000 abstract 1
- 241001138392 Euphorbia marginata Species 0.000 abstract 1
- 230000009194 climbing Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 230000033228 biological regulation Effects 0.000 description 2
- 108010066114 cabin-2 Proteins 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 230000008450 motivation Effects 0.000 description 2
- 238000006424 Flood reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000011982 device technology Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A62—LIFE-SAVING; FIRE-FIGHTING
- A62B—DEVICES, APPARATUS OR METHODS FOR LIFE-SAVING
- A62B1/00—Devices for lowering persons from buildings or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/12—Ejectable capsules
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/18—Flotation gear
Landscapes
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toys (AREA)
Abstract
The invention relates to an aerial pilotless manned escaping device capable of being independently ejected and separated. The aerial pilotless manned escaping device is arranged on an air vehicle including an airplane or a helicopter, so that in aloft working environment including high-rise buildings, mountain climbing, and the like, during appearance of urgent dangerous conditions including that the airplane is out of control, the airplane explodes, a fire generates in a high-rise building, a high tower and the like, or the high-rise building, the high tower and the like are collapsed during an earthquake, and snow on the mountain is avalanched , the aerial pilotless manned escaping device disclosed by the invention is rapidly ejected and separated from an air vehicle body or the high-rise building, and the purpose that a user safely lands to the ground or a water surface is achieved. The aerial pilotless manned escaping device consists of two parts: A. a parachute structure configuration which consists of a sealing cabin, a parachute, a driving unit, an automatic control system and an external ejecting system; and B. a non-parachute structure configuration which consists of an escaping cabin, a turbine driving unit, a control system and an ejecting system.
Description
Technical field
The present invention relates to unmanned manned under the aerial precarious position such as aircraft, skyscraper, high mountain of a kind of use
Escape device technology, is briefly a kind of unmanned manned aircraft.
Background technology
Aircarrier aircraft is not have launch escape system in high-altitude flight at present, only military aircraft particularly fighter flight
Escape device is launched in member's just configuration.And the high-altitudes such as the mountain-climbing of skyscraper, high mountain, overpass, overhead power transmission tower or other high towers are made
Industry seldom configures manned escape device.
Summary of the invention
The present invention, by a kind of aerial unmanned manned escape device that can independently launch separation, is arranged on aircraft
Including on aircraft, helicopter, in work high above the ground such as skyscraper, high mountain mountain-climbings environmentally, when emergency risks state occurs, including
Aircraft is out of control, blast, and the breaking out of fire such as skyscraper, high tower, earthquake are decayed, and when high landslide snow, quickly launch disengaging
Aircraft body or high vacant building, reach personal safety landing ground or the water surface.
In order to solve above-mentioned technical problem, present invention employs techniques below scheme:
A kind of aerial unmanned manned escape device, is made up of two parts:
A. parachute construction configuration 1, by sealed compartment 2, parachute 3, driver 4, automatic control system 5 and external ejection system 6
Composition；The most non-parachute construction 11 configures, and is made up of escape compartment 21, turbine drives 41, control system 51 and ejection system 61；
A. parachute construction configuration 1, is mostly installed on aircraft 7, and its described sealed compartment 2 is alloy shell explosion-proof, waterproof, joins
Putting hatch door, built-in inversion-prevention, shock proof seat, pressure-adjustable, homoiothermic, weightless balance in cabin, bottom external drive 4, top is external
Parachute 3；In the secure state, sealed compartment 2 is fixedly installed on aircraft 7；When there is state of necessity, escape personnel enters rapidly
After entering sealed compartment 2, promote sealed compartment by the automatic control system 5 external ejection system of automatic or manual startup within 6,20 seconds
2 orientations eject, and depart from aircraft 7 main body, and after sealed compartment 2 ejects, automatic control system 5 starts driver 4 simultaneously, and according to
Overhead or the safe distance of the water surface is highly automated opens parachute 3, due to force of gravity and air effect, parachute 3 is slowly
While decline, it is automatically adjusted the safe decrease speed of sealed compartment 2 safe landing or safe falling at the water surface by driver 4
On；
Described parachute 3 shrinks when safety is not opened and is folded in sealed compartment 2 top；
Described driver 4 is arranged on bottom sealed compartment 2, fixes with sealed compartment 2 all the time and is connected, and the configuration of described driver 4 includes sending out
The equipment such as motivation, turbine, electromotor, compressor, accumulator or Bunker；
Described automatic control system 5 is arranged on sealed compartment 2 inner bottom part, under precarious position, and automatic by automatic control system 5
Induction apparatus, sends distress signal, and after escape personnel enters sealed compartment 2, automatic or manual startup sealed compartment 2 orientation ejects,
Basis and ground, water surface elevation distance simultaneously, the most automatically opens parachute 3, and constantly regulation driver 4, makes sealed compartment 2 begin
It is maintained at safe uniform descent eventually, and avoids the barrier run into when declining；Described automatic control system 5, auto-control simultaneously
The stall of sealed compartment 2, pressure, temperature, gravity balance and landing etc., and keep the wireless communication with ground to contact；
Described external ejection system 6 is arranged on aircraft 7, using cooling liquid state nitrogen as ejection power raw material, heats during startup
Release cooling liquid state nitrogen, forms the allowance for expansion moment impulsive force more than more than 600 times, by many group jets around facing to close
Batten down 2 base injcction, produces counteracting force and is ejected by sealed compartment 2, separate with aircraft 7 main body；
The most non-parachute construction configuration 11, the escape compartment 21 be configured without parachute 3, arranging may be selected to be sealed compartment 2 or non-close
Envelope formula configures, and described escape compartment 21 shell may select metal material or inflated rubber formula, and turbine drives 51 by organizing turbine more
Composition, is mostly installed on the buildings such as the skyscraper 7 within 80 meters-5000m, high tower 8 and high mountain, escape compartment during danger and disaster
21 are ejected and decline, are automatically adjusted by turbine and reach safe decline safe landing or safe falling on the water surface；
Described turbine drives 41 is arranged on bottom escape compartment 21, fixes with escape compartment 21 all the time and is connected, described turbine drives
41 configuration many groups turbine ensures escape compartment 21 smooth decreasing and the safety of landing；Described turbine drives 41 other configuration with
The configuration of driver 4 is identical；
Described ejection system 61 is arranged on skyscraper 8, high tower 9 or high mountain, described ejection system 61 and control system 51, its
Structure, arrange with act on identical with automatic ejection system 6 and automatic control system 5 respectively.
As the further improvement of technique scheme, the shell shape of described sealed compartment 2 or escape compartment 21 can be according to need
Various shape to be designed, including spheroidal, cone or oval spherical, its volume can designed size, described sealing as required
Loading one people or the seat of many people can be set in cabin 2 and escape compartment 21 respectively.
As the further improvement of technique scheme, described driver 5, turbine drives 51 can use accumulator to supply
Electricity, fuel oil or cooling liquid nitrogen etc. are as power raw material.
As the further improvement of technique scheme, described automatic control system 6, control system 61 are provided with location letter
Number instrument, can be carried out conduct monitoring at all levels by GPS, the Big Dipper, Galileo or GLONASS satellite system, be followed the tracks of, regulate and control.
As the further improvement of technique scheme, the aerial unmanned escape device of described one, can pass through artificial
Under the most complete unmanned controlled state of remote control, automatic safe declines, lands or on the water surface, and can be at aircraft 7, skyscraper
8, many groups are arranged on high tower 9 or high mountain, and recyclable repeatedly Reusability, its device described can be as unmanned manned aircraft
It is used alone.
The invention has the beneficial effects as follows: before aircraft air crash, skyscraper decay before, collapse the dangerous situation such as mountain, floods when occurring,
Use this device implementation section personnel even all people's safe escapes.
Accompanying drawing explanation
Fig. 1 is this device schematic diagram.
Fig. 2 is that this device is arranged on carry-on schematic diagram.
Fig. 3 is that this device is arranged on and carry-on launches schematic diagram.
Fig. 4 is the schematic diagram that this device is arranged on that high-altitude is architectural.
Fig. 5 is the schematic diagram that this device is arranged on high tower.
Detailed description of the invention
Refering to Fig. 1-Fig. 5, a kind of aerial unmanned manned escape device, it is made up of two parts:
A. parachute construction configuration 1, by sealed compartment 2, parachute 3, driver 4, automatic control system 5 and external ejection system 6
Composition；The most non-parachute construction 11 configures, and is made up of escape compartment 21, turbine drives 41, control system 51 and ejection system 61；
A. parachute construction configuration 1, is mostly installed on aircraft 7, and its described sealed compartment 2 is alloy shell explosion-proof, waterproof, joins
Putting hatch door, built-in inversion-prevention, shock proof seat, pressure-adjustable, homoiothermic, weightless balance in cabin, bottom external drive 4, top is external
Parachute 3；In the secure state, sealed compartment 2 is fixedly installed on aircraft 7；When there is state of necessity, escape personnel enters rapidly
After entering sealed compartment 2, promote sealed compartment by the automatic control system 5 external ejection system of automatic or manual startup within 6,20 seconds
2 orientations eject, and depart from aircraft 7 main body, and after sealed compartment 2 ejects, automatic control system 5 starts driver 4 simultaneously, and according to
Overhead or the safe distance of the water surface is highly automated opens parachute 3, due to force of gravity and air effect, parachute 3 is slowly
While decline, it is automatically adjusted the safe decrease speed of sealed compartment 2 safe landing or safe falling at the water surface by driver 4
On；
Described parachute 3 shrinks when safety is not opened and is folded in sealed compartment 2 top；
Described driver 4 is arranged on bottom sealed compartment 2, fixes with sealed compartment 2 all the time and is connected, and the configuration of described driver 4 includes sending out
The equipment such as motivation, turbine, electromotor, compressor, accumulator or Bunker；
Described automatic control system 5 is arranged on sealed compartment 2 inner bottom part, under precarious position, and automatic by automatic control system 5
Induction apparatus, sends distress signal, and after escape personnel enters sealed compartment 2, automatic or manual startup sealed compartment 2 orientation ejects,
Basis and ground, water surface elevation distance simultaneously, the most automatically opens parachute 3, and constantly regulation driver 4, makes sealed compartment 2 begin
It is maintained at safe uniform descent eventually, and avoids the barrier run into when declining；Described automatic control system 5, auto-control simultaneously
The stall of sealed compartment 2, pressure, temperature, gravity balance and landing etc., and keep the wireless communication with ground to contact；
Described external ejection system 6 is arranged on aircraft 7, using cooling liquid state nitrogen as ejection power raw material, heats during startup
Release cooling liquid state nitrogen, forms the allowance for expansion moment impulsive force more than more than 600 times, by many group jets around facing to close
Batten down 2 base injcction, produces counteracting force and is ejected by sealed compartment 2, separate with aircraft 7 main body；
The most non-parachute construction configuration 11, the escape compartment 21 be configured without parachute 3, arranging may be selected to be sealed compartment 2 or non-close
Envelope formula configures, and described escape compartment 21 shell may select metal material or inflated rubber formula, and turbine drives 51 by organizing turbine more
Composition, is mostly installed on the buildings such as the skyscraper 7 within 80 meters-5000m, high tower 8 and high mountain, escape compartment during danger and disaster
21 are ejected and decline, are automatically adjusted by turbine and reach safe decline safe landing or safe falling on the water surface；
Described turbine drives 41 is arranged on bottom escape compartment 21, fixes with escape compartment 21 all the time and is connected, described turbine drives
41 configuration many groups turbine ensures escape compartment 21 smooth decreasing and the safety of landing；Described turbine drives 41 other configuration with
The configuration of driver 4 is identical；
Described ejection system 61 is arranged on skyscraper 8, high tower 9 or high mountain, described ejection system 61 and control system 51, its
Structure, arrange with act on identical with automatic ejection system 6 and automatic control system 5 respectively.
As the further improvement of technique scheme, the shell shape of described sealed compartment 2 or escape compartment 21 can be according to need
Various shape to be designed, including spheroidal, cone or oval spherical, its volume can designed size, described sealing as required
Loading one people or the seat of many people can be set in cabin 2 and escape compartment 21 respectively.
Being further used as preferred embodiment, described driver 5, turbine drives 51 can use storage battery power supply, combustion
Material oil or cooling liquid nitrogen etc. are as power raw material.
Being further used as preferred embodiment, described automatic control system 6, control system 61 are provided with framing signal
Instrument, can be carried out conduct monitoring at all levels by GPS, the Big Dipper, Galileo or GLONASS satellite system, be followed the tracks of, regulate and control.
As the further improvement of technique scheme, the aerial unmanned escape device of described one, can pass through artificial
Under the most complete unmanned controlled state of remote control, automatic safe declines, lands or on the water surface, and can be at aircraft 7, skyscraper
8, many groups are arranged on high tower 9 or high mountain, and recyclable repeatedly Reusability, its device described can be as unmanned manned
Device is used alone.
Embodiment one: refering to Fig. 1-Fig. 3, uses many group parachute construction configurations 1 on large-scale aircarrier aircraft, apply away from
Overhead 200 meters-10,000 meter of high-altitude, sealed compartment 1 built-in many people seat, for have purchased unmanned escape device insurance ticket
Use during flight attendant danger and disaster.
Embodiment two: refering to Fig. 1-Fig. 3, uses one group of parachute construction configuration 1, application on baby plane or helicopter
In distance-10,000 meters of high-altitudes, 200 meters of ground.The built-in people of sealed compartment 1 or many people seat, for part or all of air-service during danger and disaster
Librarian use.
Embodiment three: refering to Fig. 1, Fig. 4, Fig. 5, skyscraper more than 30th floors or more than 80 meters high empties, the highest
Using on tower, high mountain, use one or more groups non-parachute construction configuration 11, the built-in people of sealed compartment 1 or many people seat, in danger
For possessor time difficult.
Embodiment four: refering to Fig. 1, uses a kind of aerial unmanned escape device, need not configure automatic ejection system 6 or
Ejection system 61, is equivalent to the independent unmanned manned aircraft of a frame, may participate in 3, speedily carry out rescue work with the various flights of inner height for 000 meter
Rescue people's operation.
Although being described in conjunction with the accompanying embodiments of the present invention, but it should be noted that those skilled in the art can be
Within appended interest field, various changes and modifications can be made, as long as the protection model described by the claim of the present invention is crossed in not excess of export
Enclose, all should be within protection scope of the present invention.
Claims (5)
1. an aerial unmanned manned escape device, is made up of two parts: A. parachute construction configuration (1), by sealed compartment
(2), parachute (3), driver (4), automatic control system (5) and external ejection system (6) composition；The most non-parachute construction is joined
Put (11), be made up of escape compartment (21), turbine drives (41), control system (51) and ejection system (61)；
A. parachute construction configuration (1), is mostly installed on aircraft (7), and its described sealed compartment (2) is alloy explosion-proof, waterproof
Shell, configures hatch door, built-in inversion-prevention, shock proof seat, and in cabin, pressure-adjustable, homoiothermic, weightlessness balance, bottom external drive (4),
The external parachute in top (3)；In the secure state, sealed compartment (2) is fixedly installed on aircraft (7)；When state of necessity occurs,
After escape personnel quickly enters sealed compartment (2), by the external ejection system of automatic control system (5) automatic or manual startup
(6), promote sealed compartment (2) orientation to eject within 20 seconds, depart from aircraft (7) main body, after sealed compartment (2) ejects, automatically control
System processed (5) starts driver (4) simultaneously, and according to overhead or the safe distance of the water surface is highly automated opens parachute (3),
Due to force of gravity and air effect, while parachute (3) declines slowly, it is automatically adjusted sealed compartment (2) by driver (4)
Safe decrease speed safe landing or safe falling are on the water surface；
Described parachute (3) shrinks when safety is not opened and is folded in sealed compartment (2) top；
Described driver (4) is arranged on sealed compartment (2) bottom, fixes with sealed compartment (2) all the time and is connected, and described driver (4) is joined
Put equipment such as including electromotor, turbine, electromotor, compressor, accumulator or Bunker；
Described automatic control system (5) is arranged on sealed compartment (2) inner bottom part, under precarious position, by automatic control system (5)
Automatic induction apparatus, send distress signal, after escape personnel enters sealed compartment (2), automatic or manual startup sealed compartment (2)
Orientation ejects, and basis and ground, water surface elevation distance, the most automatically open parachute (3), and constantly regulate driver simultaneously
(4), make sealed compartment (2) remain at safe uniform descent, and avoid the barrier run into when declining；Described automatically controlling is
System (5), simultaneously stall, pressure, temperature, gravity balance and the landing etc. of auto-control sealed compartment (2), and keep the nothing with ground
Line call contact；
Described external ejection system (6) is arranged on aircraft (7), using cooling liquid state nitrogen as ejection power raw material, during startup
Heat and discharge cooling liquid state nitrogen, form the allowance for expansion moment impulsive force more than more than 600 times, by many group jets around right
Sealed compartment (2) base injcction, produce counteracting force and sealed compartment (2) is ejected, separate with aircraft (7) main body；
The most non-parachute construction configuration (11), escape compartment (21) shell be configured without parachute (3), arranging may select metal material
Material or inflated rubber formula, turbine drives (41) forms by organizing turbine more, be mostly installed at more than 80 meters skyscrapers (7),
On the buildings such as high tower (8) and high mountain, during danger and disaster escape compartment (21) eject decline, be automatically adjusted by turbine reach safety under
Fall safe landing or safe falling are on the water surface；
Described turbine drives (41) is arranged on escape compartment (21) bottom, fixes with escape compartment (21) all the time and is connected, described turbine
Driver (41) configuration many groups turbine ensures escape compartment (21) smooth decreasing and the safety of landing；Described turbine drives (41)
Other configuration identical with the configuration of driver (4)；
Described ejection system (61) is arranged on skyscraper (8), high tower (9) or high mountain, described ejection system (61) and control
System (51), its structure, arrange with act on identical with automatic ejection system (6) and automatic control system (5) respectively.
A kind of aerial unmanned manned escape device, it is characterised in that: described sealed compartment (2),
Or the shell shape of escape compartment (21) can design various shape as required, including spheroidal, cone or oval spherical, its body
Long-pending can setting respectively in designed size, described sealed compartment (2) and escape compartment (21) as required loads a people or the seat of many people
Chair.
A kind of aerial unmanned manned escape device, it is characterised in that automatically control described in: and be
System (6), control system (61) are provided with framing signal instrument, can be entered by GPS, the Big Dipper, Galileo or GLONASS satellite system
Row conduct monitoring at all levels, follow the tracks of, regulate and control.
A kind of aerial unmanned manned escape device, it is characterised in that: described driver (5),
Turbine drives (51) can use storage battery power supply, fuel oil or cooling liquid nitrogen etc. as power raw material.
A kind of aerial unmanned manned escape device, it is characterised in that: its device described can lead to
Cross under the most complete unmanned controlled state of manual remote control automatic safe to decline, land or on the water surface, and can aircraft (7),
Many groups are arranged on skyscraper (8), high tower (9) or high mountain, and recyclable repeatedly Reusability, its device described can be as unmanned
Driving manned vehicle is used alone.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610406572.9A CN106043710A (en) | 2016-06-12 | 2016-06-12 | Aerial pilotless manned escaping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610406572.9A CN106043710A (en) | 2016-06-12 | 2016-06-12 | Aerial pilotless manned escaping device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106043710A true CN106043710A (en) | 2016-10-26 |
Family
ID=57170750
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610406572.9A Pending CN106043710A (en) | 2016-06-12 | 2016-06-12 | Aerial pilotless manned escaping device |
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| Country | Link |
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| CN (1) | CN106043710A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163197A (en) * | 2017-12-22 | 2018-06-15 | 南京俊全科技有限公司 | A kind of unmanned aerial vehicle ejecting formula protection of instrumentation device and method |
| CN110935113A (en) * | 2019-11-21 | 2020-03-31 | 康定市和宏房地产开发有限公司 | Auto-induction parachute-opening escape device in weightless state |
| CN113997896A (en) * | 2021-10-09 | 2022-02-01 | 易显智能科技有限责任公司 | Automobile for guaranteeing safety of passengers |
-
2016
- 2016-06-12 CN CN201610406572.9A patent/CN106043710A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163197A (en) * | 2017-12-22 | 2018-06-15 | 南京俊全科技有限公司 | A kind of unmanned aerial vehicle ejecting formula protection of instrumentation device and method |
| CN110935113A (en) * | 2019-11-21 | 2020-03-31 | 康定市和宏房地产开发有限公司 | Auto-induction parachute-opening escape device in weightless state |
| CN113997896A (en) * | 2021-10-09 | 2022-02-01 | 易显智能科技有限责任公司 | Automobile for guaranteeing safety of passengers |
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Application publication date: 20161026 |