CN112744359A - Aircraft anti-load seat - Google Patents
Aircraft anti-load seat Download PDFInfo
- Publication number
- CN112744359A CN112744359A CN202110233307.6A CN202110233307A CN112744359A CN 112744359 A CN112744359 A CN 112744359A CN 202110233307 A CN202110233307 A CN 202110233307A CN 112744359 A CN112744359 A CN 112744359A
- Authority
- CN
- China
- Prior art keywords
- seat
- hydraulic cylinder
- rotary
- aircraft load
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- QSHDDOUJBYECFT-UHFFFAOYSA-N mercury Chemical compound [Hg] QSHDDOUJBYECFT-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052753 mercury Inorganic materials 0.000 claims abstract description 10
- 238000006073 displacement reaction Methods 0.000 claims description 9
- 239000013536 elastomeric material Substances 0.000 claims 1
- 230000001133 acceleration Effects 0.000 abstract description 46
- 239000007788 liquid Substances 0.000 description 9
- 230000008602 contraction Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000013013 elastic material Substances 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 238000013519 translation Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 206010042772 syncope Diseases 0.000 description 1
- 238000012549 training Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
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
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0689—Arrangements of seats, or adaptations or details specially adapted for aircraft seats specially adapted for pilots
-
- 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
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0639—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with features for adjustment or converting of seats
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Seats For Vehicles (AREA)
Abstract
The invention provides an aircraft load-resisting seat, comprising: the device comprises a base, a rotary turntable assembly, a hydraulic cylinder assembly and a hollow seat; mercury is encapsulated inside the base; the rotary turntable assembly is arranged on the base and performs horizontal rotary motion; the bottom of the hydraulic cylinder assembly is fixedly connected with the rotary turntable assembly, and the top of the hydraulic cylinder assembly is fixedly connected with the hollowed-out seat. The aircraft load-resisting seat provided by the invention well solves the problem that the existing aircraft seat cannot weaken acceleration load.
Description
Technical Field
The invention relates to the technical field of aircraft seats, in particular to an aircraft load-resisting seat.
Background
With the continuous development of hypersonic aircraft and aerospace craft, the acceleration of the aircraft exceeds the limit load of human body syncope.
The aircraft seat in the prior art does not have the effect of weakening the acceleration load, and ordinary people cannot randomly drive the hypersonic aircraft and the aerospace plane spacecraft unless special training is carried out, and a trained driver also faces the hypersonic aircraft and the aerospace plane spacecraft which cannot adapt to faster acceleration.
Disclosure of Invention
The invention provides an aircraft load-resisting seat, and aims to solve the problem that an existing aircraft seat cannot weaken acceleration load.
The invention provides an aircraft load-resisting seat, comprising: the device comprises a base, a rotary turntable assembly, a hydraulic cylinder assembly and a hollow seat; mercury is encapsulated inside the base; the rotary turntable assembly is arranged on the base and performs horizontal rotary motion; the bottom of the hydraulic cylinder assembly is fixedly connected with the rotary turntable assembly, and the top of the hydraulic cylinder assembly is fixedly connected with the hollowed-out seat.
Further, the rotary turret assembly comprises: an electric control rotary support and a rotary table; the electric control rotary support is connected with the rotary table and used for driving the rotary table to do rotary motion.
The electric control rotary support plays a role in supporting on one hand and is used for driving the rotary table to do rotary motion on the other hand; when a pilot sits on the seat and is subjected to the action of acceleration load, the electric control rotary support drives the rotary table to rotate clockwise or anticlockwise, the rotating direction is opposite to the acceleration direction, and the rotation inertia acceleration of a horizontal plane is weakened.
Further, the electric control slewing support comprises a motor, an angular displacement sensor and a rotating shaft; the angular displacement sensor is electrically connected with the motor; one end of the rotating shaft is connected with the output end of the motor, and the other end of the rotating shaft is connected with the rotary table.
The angular displacement sensor captures a rotation inertia acceleration signal, the signal is transmitted to the motor, the output end of the motor drives the rotating shaft to rotate, the rotating table is further driven to rotate, the rotating direction is opposite to the inertia acceleration direction, and the rotation inertia acceleration of the horizontal plane is weakened.
Further, the hydraulic cylinder assembly comprises a hydraulic cylinder and a central control; the number of the hydraulic cylinders is not less than three, and the central control is electrically connected with the hydraulic cylinders respectively; the bottom of the hydraulic cylinder is fixedly connected with the rotary turntable assembly, and the top of the hydraulic cylinder is fixedly connected with the hollow seat.
The central control is used for receiving the information of the aircraft, processing the information and controlling the hydraulic contraction motion of the hydraulic cylinder to enable the hydraulic cylinder to perform reverse motion in the inertial acceleration direction, so that the inertial acceleration of six degrees of freedom is weakened; two points determine a plane, three points determine a space, and three hydraulic cylinders can drive the seat to do three-dimensional motion.
Further, the number of the hydraulic cylinders is six. The six hydraulic cylinders can weaken the inertia acceleration of six degrees of freedom more stably.
Further, the top of the hydraulic cylinder is a screw, and the hydraulic cylinder is connected with the hollowed-out seat through bolts.
Further, the hollow seat is made of elastic materials.
The hollow seat made of the elastic material further strengthens the damping effect and weakens the inertial acceleration.
Further, the shape of the hollow-out seat is semicircular.
Further, the turntable is horizontally disposed on the rotation shaft. The horizontally arranged turntable can weaken the inertia acceleration in the horizontal direction.
Furthermore, both sides of the hollow-out seat also comprise armrests.
The invention provides an aircraft anti-load seat, which can weaken inertial acceleration in three aspects: firstly, mercury is packaged in the base, and the seat has the characteristics of liquid self-stability and inertia acceleration resistance on a horizontal plane by utilizing the normal-temperature liquid state and ultrahigh density of the mercury; secondly, the rotating turntable assembly moves in the direction opposite to the acceleration direction to weaken the rotation inertia acceleration of the horizontal plane; thirdly, the hydraulic cylinder assembly makes hydraulic contraction movement, so that the hydraulic cylinder assembly moves in a direction opposite to the direction of inertial acceleration, and the inertial acceleration of six degrees of freedom is weakened; the problem that the existing aircraft seat does not weaken acceleration load is well solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a front view of an aircraft load resisting seat provided by an embodiment of the present invention;
fig. 2 is a side view of an aircraft anti-load seat provided by an embodiment of the invention.
Description of reference numerals:
1 is a base; 2, a rotary turntable assembly, 21, an electric control rotary support and 22, a turntable; 3 is a hydraulic cylinder, and 31 is a screw rod; 4, a hollow chair, 41, an armrest.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1-2, the present invention provides an aircraft anti-load seat, the anti-load principle is to increase damping effect, which includes: the device comprises a base 1, a rotary turntable assembly 2, a hydraulic cylinder assembly and a hollow seat 4; the base 1 internally encapsulates mercury; the rotary turntable component 2 is arranged on the base 1, and the rotary turntable component 2 rotates horizontally; the bottom of the hydraulic cylinder component is fixedly connected with the rotary turntable component 2, and the top of the hydraulic cylinder component is fixedly connected with the hollow seat 4.
Specifically, the rotary turntable assembly 2 is installed above the base 1, and the base 1 is filled with a normal-temperature liquid and a high-density liquid for resisting inertial acceleration.
Furthermore, the liquid is mercury, and the seat has the characteristics of liquid self-stability and inertia acceleration resistance on a horizontal plane by utilizing the normal-temperature liquid state and ultrahigh density of the mercury.
Specifically, the rotary turntable assembly 2 is mounted on a base, and the rotary turntable assembly 2 performs horizontal rotary motion to weaken the rotational inertia acceleration of a horizontal plane; the rotary turntable assembly 2 comprises an electric control rotary support 21 and a turntable 22; the electrically controlled rotary support 21 is connected with the rotary table 22 and is used for driving the rotary table 22 to make rotary motion. The electric control rotary support 21 plays a role of supporting on one hand and is used for driving the rotary table 22 to do rotary motion on the other hand; when a pilot sits on the seat and is subjected to acceleration load, the electrically controlled slewing support 21 drives the rotary table 22 to rotate clockwise or anticlockwise, the rotation direction is opposite to the acceleration direction, and the rotation inertia acceleration of the horizontal plane is weakened.
Further, the electrically controlled slewing support 21 includes a motor, an angular displacement sensor, and a rotating shaft (none of the motor, the angular displacement sensor, and the rotating shaft are shown in the figure); the angular displacement sensor is electrically connected with the motor; one end of the rotating shaft is connected with the output end of the motor, and the other end of the rotating shaft is connected with the rotary table.
The angular displacement sensor captures a rotation inertia acceleration signal and transmits the signal to the motor, the output end of the motor drives the rotating shaft to rotate, the rotating direction is opposite to the inertia acceleration direction, and the rotation inertia acceleration of the horizontal plane is weakened.
Further, the turntable 22 is horizontally disposed on the rotation shaft. The horizontally arranged turntable 22 can attenuate the inertial acceleration in the horizontal direction.
Specifically, the bottom of the hydraulic cylinder assembly is fixedly connected with the rotary table, and the top of the hydraulic cylinder assembly is fixedly connected with the hollow seat 4; the hydraulic cylinder component makes hydraulic contraction movement, so that the hydraulic cylinder component moves in the direction opposite to the inertial acceleration direction, and the inertial acceleration of six degrees of freedom is weakened. Wherein, six degrees of freedom include translation along the x-axis, translation along the y-axis, translation along the z-axis, rotation around the x-axis, rotation around the y-axis, rotation around the z-axis.
Further, the hydraulic cylinder assembly includes a hydraulic cylinder 31, a pivot control (not shown in the pivot control diagram); the central control is electrically connected with the hydraulic cylinders 31 respectively; the bottom of the hydraulic cylinder 31 is fixedly connected with the rotary turntable assembly 2, and the top of the hydraulic cylinder 31 is fixedly connected with the hollow seat 4.
The central control is used for receiving information of the aircraft, processing the information and controlling hydraulic contraction movement of the hydraulic cylinder 31, so that the hydraulic cylinder 31 makes reverse movement in the inertial acceleration direction, and inertial acceleration of six degrees of freedom is weakened.
Furthermore, the number of the hydraulic cylinders 31 is not less than three, two points determine a plane, and three points determine a space, so that the three hydraulic cylinders 31 can drive the seat to do three-dimensional motion.
Further, the number of the hydraulic cylinders 31 is six. The six hydraulic cylinders 31 can more stably attenuate the inertial acceleration of six degrees of freedom.
Further, the top of the hydraulic cylinder 31 is a screw, and the hydraulic cylinder 31 is connected with the hollow seat 4 through a bolt.
Specifically, the bottom of the hollow seat 4 is connected with the hydraulic cylinder 31, and the hollow seat 4 is arranged in a suspended manner; the hollow seat 4 is made of elastic materials. The hollow seat 4 made of elastic material further strengthens the damping effect and weakens the inertia acceleration.
Furthermore, the hollowed-out seat 4 is semicircular, so that the pilot can conveniently take the seat and can also protect the pilot.
Further, the two sides of the hollow seat 4 further include armrests 41.
Therefore, the invention provides an aircraft anti-load seat, which attenuates inertial acceleration in three aspects: firstly, mercury is packaged in the base, and the seat has the characteristics of liquid self-stability and inertia acceleration resistance on a horizontal plane by utilizing the normal-temperature liquid state and ultrahigh density of the mercury; secondly, the rotating turntable assembly moves in the direction opposite to the acceleration direction to weaken the rotation inertia acceleration of the horizontal plane; thirdly, the hydraulic cylinder assembly makes hydraulic contraction movement, so that the hydraulic cylinder assembly moves in a direction opposite to the direction of inertial acceleration, and the inertial acceleration of six degrees of freedom is weakened; the problem that the existing aircraft seat does not weaken acceleration load is well solved.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the 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 scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. An aircraft load-resisting seat, comprising: the device comprises a base, a rotary turntable assembly, a hydraulic cylinder assembly and a hollow seat;
mercury is encapsulated inside the base;
the rotary turntable assembly is arranged on the base and performs horizontal rotary motion;
the bottom of the hydraulic cylinder assembly is fixedly connected with the rotary turntable assembly, and the top of the hydraulic cylinder assembly is fixedly connected with the hollowed-out seat.
2. The aircraft load resisting seat of claim 1, wherein the rotary turret assembly comprises: an electric control rotary support and a rotary table;
the electric control rotary support is connected with the rotary table and used for driving the rotary table to do rotary motion.
3. The aircraft load resisting seat of claim 2, wherein the electrically controlled slewing support includes a motor, an angular displacement sensor, and a rotating shaft;
the angular displacement sensor is electrically connected with the motor;
one end of the rotating shaft is connected with the output end of the motor, and the other end of the rotating shaft is connected with the rotary table.
4. The aircraft load resisting seat of claim 1, wherein the hydraulic cylinder assembly comprises a hydraulic cylinder, a pivot control;
the number of the hydraulic cylinders is not less than three, and the central control is electrically connected with the hydraulic cylinders respectively;
the bottom of the hydraulic cylinder is fixedly connected with the rotary turntable assembly, and the top of the hydraulic cylinder is fixedly connected with the hollow seat.
5. Aircraft load-resisting seat according to claim 4, characterised in that the number of hydraulic cylinders is six.
6. The aircraft load resisting seat of claim 4, wherein the top of the hydraulic cylinder is a threaded rod, and the hydraulic cylinder is bolted to the hollowed seat.
7. The aircraft load resisting seat of claim 1, wherein the hollowed out seat is made of an elastomeric material.
8. The aircraft load resisting seat of claim 7, wherein the hollowed out seat is semi-circular in shape.
9. The aircraft load resisting seat of claim 3, wherein said turntable is disposed horizontally on said rotating shaft.
10. The aircraft load resisting seat of claim 1, wherein both sides of the hollowed out seat further comprise armrests.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110233307.6A CN112744359A (en) | 2021-03-03 | 2021-03-03 | Aircraft anti-load seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110233307.6A CN112744359A (en) | 2021-03-03 | 2021-03-03 | Aircraft anti-load seat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112744359A true CN112744359A (en) | 2021-05-04 |
Family
ID=75651614
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110233307.6A Pending CN112744359A (en) | 2021-03-03 | 2021-03-03 | Aircraft anti-load seat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112744359A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2196941Y (en) * | 1994-03-15 | 1995-05-17 | 北京华宇机器人技术开发公司 | Moveable chair installation for theater |
| FR2916184A1 (en) * | 2007-05-15 | 2008-11-21 | Astrium Sas Soc Par Actions Si | VEHICLE SEAT AND SPACE VEHICLE EQUIPPED WITH THIS SEAT. |
| CN109050937A (en) * | 2018-07-18 | 2018-12-21 | 苏州频聿精密机械有限公司 | A kind of adjustable lightweight aero seat |
| CN109406049A (en) * | 2018-11-16 | 2019-03-01 | 中国科学院西安光学精密机械研究所 | Centroid measuring system and centroid measuring method |
| CN109677620A (en) * | 2019-02-02 | 2019-04-26 | 河北工业大学 | A kind of active pour angle compensation aircraft seat |
| CN109849741A (en) * | 2019-03-07 | 2019-06-07 | 江苏理工学院 | It is a kind of to turn to adjustable automobile seat in real time |
| CN109876462A (en) * | 2018-12-17 | 2019-06-14 | 黎凯俊 | A kind of virtual reality high-altitude flight experience apparatus with governor weight system |
| CN109911213A (en) * | 2017-12-12 | 2019-06-21 | 镇江雅奕智能科技有限公司 | It is a kind of to reply seat certainly for aviation |
| CN110803076A (en) * | 2018-08-06 | 2020-02-18 | 现代自动车株式会社 | Seat rotating device for automatic driving vehicle |
| CN211296867U (en) * | 2019-09-10 | 2020-08-18 | 武汉集客科技有限公司 | Special supporting seat for router |
-
2021
- 2021-03-03 CN CN202110233307.6A patent/CN112744359A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2196941Y (en) * | 1994-03-15 | 1995-05-17 | 北京华宇机器人技术开发公司 | Moveable chair installation for theater |
| FR2916184A1 (en) * | 2007-05-15 | 2008-11-21 | Astrium Sas Soc Par Actions Si | VEHICLE SEAT AND SPACE VEHICLE EQUIPPED WITH THIS SEAT. |
| CN109911213A (en) * | 2017-12-12 | 2019-06-21 | 镇江雅奕智能科技有限公司 | It is a kind of to reply seat certainly for aviation |
| CN109050937A (en) * | 2018-07-18 | 2018-12-21 | 苏州频聿精密机械有限公司 | A kind of adjustable lightweight aero seat |
| CN110803076A (en) * | 2018-08-06 | 2020-02-18 | 现代自动车株式会社 | Seat rotating device for automatic driving vehicle |
| CN109406049A (en) * | 2018-11-16 | 2019-03-01 | 中国科学院西安光学精密机械研究所 | Centroid measuring system and centroid measuring method |
| CN109876462A (en) * | 2018-12-17 | 2019-06-14 | 黎凯俊 | A kind of virtual reality high-altitude flight experience apparatus with governor weight system |
| CN109677620A (en) * | 2019-02-02 | 2019-04-26 | 河北工业大学 | A kind of active pour angle compensation aircraft seat |
| CN109849741A (en) * | 2019-03-07 | 2019-06-07 | 江苏理工学院 | It is a kind of to turn to adjustable automobile seat in real time |
| CN211296867U (en) * | 2019-09-10 | 2020-08-18 | 武汉集客科技有限公司 | Special supporting seat for router |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210504 |
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| RJ01 | Rejection of invention patent application after publication |