CN113955127A - Whole escape survival capsule of aircraft - Google Patents
Whole escape survival capsule of aircraft Download PDFInfo
- Publication number
- CN113955127A CN113955127A CN202111218487.7A CN202111218487A CN113955127A CN 113955127 A CN113955127 A CN 113955127A CN 202111218487 A CN202111218487 A CN 202111218487A CN 113955127 A CN113955127 A CN 113955127A
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- Prior art keywords
- capsule
- escape
- lifesaving
- rocket
- parachute
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- 230000004083 survival effect Effects 0.000 title description 4
- 239000000725 suspension Substances 0.000 claims description 11
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 4
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- 230000003139 buffering effect Effects 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
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- 238000000034 method Methods 0.000 description 13
- 230000008569 process Effects 0.000 description 6
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- 230000009286 beneficial effect Effects 0.000 description 2
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- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 206010013647 Drowning Diseases 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
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- 238000013467 fragmentation Methods 0.000 description 1
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Images
Classifications
-
- 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
- B64D17/00—Parachutes
- B64D17/22—Load suspension
- B64D17/38—Releasable fastening devices between parachute and load or pack
-
- 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
- B64D17/00—Parachutes
- B64D17/62—Deployment
-
- 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
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Business, Economics & Management (AREA)
- Emergency Management (AREA)
- Emergency Lowering Means (AREA)
- Toys (AREA)
Abstract
The invention discloses an integral escape rescue capsule of an airplane, which is characterized in that: comprises a lifesaving capsule body, a capsule cover, an ejection posture-adjusting rocket, an umbrella-shooting rocket and a parachute kit, wherein the capsule cover is arranged on the lifesaving capsule body; the lifesaving capsule body is a cavity polyhedron, a pair of side surfaces are respectively provided with an ejection posture-adjusting rocket, and the other pair of side surfaces are respectively provided with an escape releasing device connected with the airplane; a pair of accommodating cavities are arranged in the accommodating cavity, and an umbrella shooting rocket and a parachute kit are arranged in the accommodating cavities; when the parachute is ejected, the parachute-shooting rocket and the parachute kit in the accommodating cavity are exposed outwards. The invention can ensure that the pilot of the airplane in accident can not leave the flight cabin body for protection, and the safety escape and landing lifesaving can be realized along with the whole cabin. The problem that the life safety of a pilot is endangered by irregular fragments generated by lifting or bursting or penetrating the cover of the existing cockpit cover when the existing cockpit cover escapes is fundamentally avoided. Meanwhile, other threats caused by abrupt changes of key physiological indexes such as air temperature difference, air pressure and the like are avoided.
Description
Technical Field
The invention belongs to the technical field of aviation lifesaving, and particularly relates to an integral escape rescue capsule of an airplane.
Background
At present, especially in the escape lifesaving mode of a high-speed fighter, a pilot is thrown out of a cabin of an airplane by using an ejection seat, and the pilot also needs to go through the escape process of lifting and separating a cabin cover, or controlled and active blasting and fragmentation of the cabin cover, or the escape process of directly endangering the life safety of the pilot by passively puncturing and breaking the cover, penetrating the cover and the like by using an ejection seat tip cone.
Disclosure of Invention
In view of at least one of the above defects or improvement requirements of the prior art, the invention provides an aircraft integral escape rescue capsule to significantly improve the survival probability of the pilots in distress and protect flight data and key equipment to the maximum extent.
To achieve the above object, according to one aspect of the present invention, there is provided an aircraft integral escape capsule, wherein: comprises a lifesaving capsule body, a capsule cover, an ejection posture-adjusting rocket, an umbrella-shooting rocket and a parachute kit, wherein the capsule cover is arranged on the lifesaving capsule body;
the lifesaving capsule body is a cavity polyhedron;
the ejection posture-adjusting rockets are respectively arranged on a pair of side surfaces of the rescue capsule body
The other pair of side surfaces of the lifesaving capsule body are respectively provided with escape releasing devices connected with the airplane;
a pair of accommodating cavities are arranged in the lifesaving cabin body, the parachute launching rocket and the parachute kit are installed in the accommodating cavities, and the parachute kit is connected to the tail end of the parachute launching rocket;
when the escape releasing device releases the connection between the lifesaving cabin body and the airplane, the parachute rocket and the parachute kit in the accommodating cavity are exposed outwards.
Further preferably, the rescue capsule body is provided with a rotating shaft of the ejection posture-adjusting rocket which is perpendicular to the tangent plane at the position corresponding to the horizontal shaft of the two symmetrical tangent planes of the rescue capsule body, and the ejection posture-adjusting rocket is arranged on the rotating shaft.
Further preferably, the accommodating cavity of the rescue capsule body is respectively provided with an umbrella-shooting rocket chute parallel to the tangent plane at the corresponding position of the longitudinal axes of the two symmetrical tangent planes of the accommodating cavity, and the umbrella-shooting rocket chute is provided with an umbrella-shooting rocket.
Preferably, the life-saving capsule body is provided with two symmetrical parachute fixing suspension loops with a falling control mechanism on the upper part of the tangent plane of the parachute-launching rocket chute, and the fixed suspension loops are provided with movable suspension loops of parachute kits.
Further preferably, the bottom of the rescue capsule body correspondingly extends at two sides of the tangent plane of the chute of the rocket with the parachute to form a bearing platform of the parachute kit, and the parachute kit is configured on the bearing platform.
Further preferably, the rescue capsule body is provided with an ejection chute, the ejection chute is provided with the escape releasing device, and the ejection chute and the escape releasing device are respectively matched with a guide rail and a limiting part of the aircraft body.
Further preferably, the rescue capsule body is provided with a detection device and a wireless communication device.
Further preferably, a wired connection socket or plug is arranged on the rescue capsule body and is matched with a wired connection plug or socket of the airplane body.
Further preferably, the life-saving capsule body is internally provided with a flight control system device, a communication system device, a pilot life support system device, a data equipment self-destruction system device and the like.
Further preferably, the lifesaving capsule body is provided with an explosion buffer air bag at the bottom thereof.
The above-described preferred features may be combined with each other as long as they do not conflict with each other.
Generally, compared with the prior art, the above technical solution conceived by the present invention has the following beneficial effects:
the invention can ensure that the pilot of the airplane in accident can not leave the flight cabin body for protection, and the safety escape and landing lifesaving can be realized along with the whole cabin. The problem that the life safety of a pilot is endangered by irregular fragments generated by lifting or bursting or penetrating the cover of the existing cockpit cover when the existing cockpit cover escapes is fundamentally avoided. Meanwhile, other threats caused by abrupt changes of key physiological indexes such as air temperature difference, air pressure and the like are avoided.
Drawings
FIG. 1 is a side view of an overall escape capsule structure of an aircraft according to an embodiment of the invention;
FIG. 2 is a front bottom view of an overall escape capsule structure of an aircraft according to an embodiment of the invention;
FIG. 3 is an enlarged schematic view of a catapult attitude-adjusting rocket for the aircraft to integrally escape from the rescue capsule in the embodiment of the invention;
FIG. 4 is a schematic diagram of the instant the aircraft integral escape capsule is ejected and departed from the aircraft according to an embodiment of the invention;
FIG. 5 is a schematic view of an aircraft integral escape capsule shooting instant of the embodiment of the invention;
fig. 6 is a schematic diagram of the parachute opening and landing of the aircraft integral escape capsule of the embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other. The present invention will be described in further detail with reference to specific embodiments.
As a preferred embodiment of the present invention, as shown in fig. 1 to 6, the present invention provides an aircraft escape capsule, which includes: the lifesaving capsule comprises a lifesaving capsule body 1, a capsule cover 2 arranged on the lifesaving capsule body 1, an ejection posture-adjusting rocket 3, a parachute launching rocket 4, a parachute kit 5 and the like.
As shown in fig. 1-4, the rescue capsule body 1 is a cavity polyhedron, and each surface has a certain matching tangent plane angle according to the functional requirement. The lifesaving capsule body 1 is a cavity polyhedron, and each surface has a certain matching tangent plane angle according to the functional requirement. Therefore, the lifesaving capsule body 1 can be designed and manufactured firmly and lightly, and further, the lifesaving capsule body 1 can be made of high-strength composite materials such as aluminum alloy, titanium alloy and carbon fiber, so that the capsule body strength is further improved while the weight is reduced.
As shown in fig. 1-2, preferably, the rescue capsule body 1 has a rotating shaft 31 of the ejection posture-adjusting rocket 3 perpendicular to the tangent plane at the position corresponding to the horizontal axis of the two symmetrical tangent planes, and the ejection posture-adjusting rocket 3 is mounted on the rotating shaft 31. Thus, when the airplane 10 is in danger and wants to fall, the ejection posture-adjusting rocket 3 is controlled to be ignited and started, firstly, the integral escape rescue capsule of the airplane is instantly ejected and separated from the airplane body, and then the posture-adjusting program is automatically started immediately, and the ejection posture-adjusting rocket 3 enables the escape rescue capsule to generate beneficial integral rolling or swinging through corresponding adjustment and change of vector ejection angle and force according to the inclination degree of the escape rescue capsule, so that the integral posture of the escape rescue capsule is quickly corrected to the correct orientation.
As shown in fig. 3, the ejection posture-adjusting rocket 3 is composed of a posture-adjusting actuator 32, a vector-jetting rocket 33, and the like, and further, the posture-adjusting actuator 32 is controlled by a regulation instruction of a built-in flight control system device (not shown in the drawing) of the aircraft overall escape capsule. Further, vector jet rocket 33 may be operated with one or more ignitions using solid or liquid fuels.
As shown in fig. 1-2, the rescue capsule body 1 preferably has two parachute-launching rocket chutes 41 parallel to the longitudinal plane at the positions corresponding to the longitudinal axes of the two symmetrical tangent planes, and parachute-launching rockets 4 are mounted on the chutes.
As shown in fig. 1-2, preferably, the rescue capsule body 1 is provided with two symmetrical parachute fixing suspension loops 51 having a drop control mechanism at the upper portion of the tangent plane of the parachute rocket chute 41, a movable suspension loop 52 of the parachute kit 5 is mounted on the fixed suspension loop 51, and a parachute rope 58 at the tail end of the parachute is fixed to the movable suspension loop 52.
As shown in fig. 1 to 2, preferably, the bottom of the capsule body 1 extends on both sides of the tangent plane of the rocket chute 41 to form a platform 53 of the parachute kit 5, and the parachute kit 5 is disposed on the platform 53.
As shown in fig. 1-2 and 4, as a preferable scheme, ejection chutes 11 are longitudinally arranged at two sides or 4 corners of the rescue capsule body 1, fixed clamping cavities 12 are arranged on the ejection chutes 11, and the ejection chutes 11 and the fixed clamping cavities 12 are matched with guide rails and limit clamps (not shown in the drawings) of an airplane body.
As shown in fig. 1-2, the rescue capsule body 1 is preferably provided with a detection device 6 and a wireless communication device 7 on the top surface or a certain tangent plane thereof, and is provided with a wired socket or plug 8 on the bottom surface or a certain tangent plane thereof, and the wired socket or plug 8 is matched with a wired plug or socket (not shown in the drawing) of the airplane body.
As a preferred scheme, the life-saving capsule body 1 is internally provided with a flight control system device, a communication system device, a pilot life support system device, a data equipment self-destruction system device and the like (all shown).
As shown in fig. 1-2 and 6, the rescue capsule body 1 is preferably provided with an explosion-filled buffer air bag 9 at the bottom thereof.
The embodiment of the invention provides an integral escape rescue capsule of an airplane, and an escape method of the integral escape rescue capsule comprises the following steps:
as shown in fig. 4, when an aircraft 10 encounters an irreversible dangerous situation and begins to crash, a pilot or a command tower starts an escape lifesaving program, firstly, a limit chuck (not shown in the drawing) of an aircraft body is controlled to loosen a fixed clamping hole 12 of an escape lifesaving cabin, two ejection posture-adjusting rockets 3 are linked, ignited and started to generate huge thrust to eject and separate the whole escape lifesaving cabin of the aircraft from the aircraft body instantly, and meanwhile, a wired connection socket or plug 8 between the two is forcibly disengaged, so that interconnected liquid, electricity and gas circuits are thoroughly separated. When the escape capsule is ejected to a safe distance, the ejection posture-adjusting rocket 3 automatically enters a posture-adjusting program immediately according to the inclination degree of the escape capsule, and the overall posture of the escape capsule is quickly corrected to the correct direction of the canopy 2, as shown in fig. 5. Then the two side-shooting rocket 4 is started to extend and straighten the folded parachute kit 5 in sequence to the air until the canopy 54 is pulled off and the canopy 56 of the parachute 55 is released, as shown in fig. 5. The canopy 56 is windy immediately, the canopy rope 57 generates enough air lifting tension, as shown in fig. 6, the aircraft escapes the rescue capsule as a whole and the pilot taking care of the aircraft inside the rescue capsule slowly and safely lands, when the aircraft is about to land or on the water, the catapulting posture-adjusting rocket 3 which is ignited for a plurality of times is adopted to ignite again to generate the reverse thrust to reduce and relieve the landing impact force of the escape rescue capsule. And if the posture-adjusting rocket 3 is ejected once, the explosion-inflation buffering air bag 9 needs to be started to reduce and relieve the landing buffering force of the escape capsule, as shown in fig. 6. When the escape capsule is successfully landed or on the water, the parachute fixing suspension loop 51 with the falling control mechanism is timely separated from the escape capsule body 1, so that the parachute 55 is prevented from continuously dragging the escape capsule in the ground wind.
Because the body of the pilot is not separated from the direct effective protection of the escape capsule system in the whole escape process, the danger of cover or body fragment when the pilot leaves the capsule and the threat of huge temperature difference, air pressure and air current abrupt change are avoided in the air. When the escape capsule lands or lands on water, a pilot depends on the firm shell of the integral escape capsule of the airplane, so that the escape capsule can avoid hurting or drowning, and can resist the invasion of wind, sand, rain and snow in the field or the attack of beasts or enemies. The life support system device in the escape rescue capsule can better and longer maintain the survival of the pilot to be rescued, and the communication system device can provide timely rescue communication and positioning coordinates.
It will be appreciated that the embodiments of the system described above are merely illustrative, in that elements illustrated as separate components may or may not be physically separate, may be located in one place, or may be distributed over different network elements. Some or all of the modules can be selected according to actual needs to achieve the purpose of the scheme of the embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
In addition, it should be understood by those skilled in the art that in the specification of the embodiments of the present invention, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
In the description of the embodiments of the invention, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description. Similarly, it should be appreciated that in the foregoing description of exemplary embodiments of the invention, various features of the embodiments of the invention are sometimes grouped together in a single embodiment, figure, or description thereof for the purpose of streamlining the disclosure and aiding in the understanding of one or more of the various inventive aspects.
However, the disclosed method should not be interpreted as reflecting an intention that: that is, the claimed embodiments of the invention require more features than are expressly recited in each claim. Rather, as the following claims reflect, inventive aspects lie in less than all features of a single foregoing disclosed embodiment. Thus, the claims following the detailed description are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate embodiment of an embodiment of this invention.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the embodiments of the present invention, and not to limit the same; although embodiments of the present invention have been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. An aircraft integral escape rescue capsule is characterized in that: comprises a lifesaving capsule body, a capsule cover, an ejection posture-adjusting rocket, an umbrella-shooting rocket and a parachute kit, wherein the capsule cover is arranged on the lifesaving capsule body;
the lifesaving capsule body is a cavity polyhedron;
the ejection posture-adjusting rockets are respectively arranged on a pair of side surfaces of the rescue capsule body
The other pair of side surfaces of the lifesaving capsule body are respectively provided with escape releasing devices connected with the airplane;
a pair of accommodating cavities are arranged in the lifesaving cabin body, the parachute launching rocket and the parachute kit are installed in the accommodating cavities, and the parachute kit is connected to the tail end of the parachute launching rocket;
when the escape releasing device releases the connection between the lifesaving cabin body and the airplane, the parachute rocket and the parachute kit in the accommodating cavity are exposed outwards.
2. An aircraft integral escape capsule as defined in claim 1, wherein:
the lifesaving capsule body is provided with a rotary shaft of the ejection posture-adjusting rocket which is vertical to the tangent plane at the corresponding position of the transverse shaft of the two symmetrical tangent planes of the lifesaving capsule body, and the ejection posture-adjusting rocket is arranged on the rotary shaft.
3. An aircraft integral escape capsule as defined in claim 1, wherein:
the accommodation cavity of the lifesaving capsule body is internally provided with two umbrella-shooting rocket sliding grooves parallel to the tangent plane at the corresponding positions of the longitudinal axes of the two symmetrical tangent planes of the accommodation cavity, and the umbrella-shooting rockets are arranged on the umbrella-shooting rocket sliding grooves.
4. An aircraft integral escape capsule as defined in claim 3, wherein:
the life-saving capsule body is provided with two symmetrical parachute fixing suspension loops with a falling control mechanism on the upper part of a tangent plane of the life-saving capsule body, and the fixed suspension loops are provided with movable suspension loops of parachute kits.
5. An aircraft integral escape capsule as defined in claim 3, wherein:
the bottom of the lifesaving capsule body correspondingly extends from two sides of the tangent plane of the chute of the parachute-launching rocket to form a bearing platform of a parachute kit, and the parachute kit is arranged on the bearing platform.
6. An aircraft integral escape capsule as defined in claim 1, wherein:
the life-saving capsule body is provided with the ejection chute, be provided with on the ejection chute escape release device, just ejection chute and escape release device cooperate with the guide rail and the locating part of aircraft organism respectively.
7. An aircraft integral escape capsule as defined in claim 1, wherein:
the lifesaving capsule body is provided with a detection device and a wireless communication device.
8. An aircraft integral escape capsule as defined in claim 1, wherein:
the lifesaving capsule body is provided with a wired connection socket or plug, and the wired connection socket or plug is matched with a wired connection plug or socket of the airplane body.
9. An aircraft integral escape capsule as defined in claim 1, wherein:
the life-saving capsule body is internally provided with a flight control system device, a communication system device, a pilot life support system device, a data equipment self-destruction system device and the like.
10. An aircraft integral escape capsule as defined in claim 1, wherein:
the bottom of the lifesaving capsule body is provided with an explosion-inflation buffering air bag.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111218487.7A CN113955127B (en) | 2021-10-20 | 2021-10-20 | Whole escape capsule of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111218487.7A CN113955127B (en) | 2021-10-20 | 2021-10-20 | Whole escape capsule of aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113955127A true CN113955127A (en) | 2022-01-21 |
| CN113955127B CN113955127B (en) | 2023-06-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111218487.7A Active CN113955127B (en) | 2021-10-20 | 2021-10-20 | Whole escape capsule of aircraft |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1709767A (en) * | 2005-05-31 | 2005-12-21 | 徐丽岗 | Split passenger plane and its escaping device |
| CN101927829A (en) * | 2010-04-26 | 2010-12-29 | 高恒伟 | Passenger cabin-separable aircraft |
| CN104029819A (en) * | 2014-06-15 | 2014-09-10 | 李家涛 | Escape seat of aircraft |
-
2021
- 2021-10-20 CN CN202111218487.7A patent/CN113955127B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1709767A (en) * | 2005-05-31 | 2005-12-21 | 徐丽岗 | Split passenger plane and its escaping device |
| CN101927829A (en) * | 2010-04-26 | 2010-12-29 | 高恒伟 | Passenger cabin-separable aircraft |
| CN104029819A (en) * | 2014-06-15 | 2014-09-10 | 李家涛 | Escape seat of aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113955127B (en) | 2023-06-30 |
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