CN114476017A - Locking mechanism for light aircraft cockpit cover and using method - Google Patents

Locking mechanism for light aircraft cockpit cover and using method Download PDF

Info

Publication number
CN114476017A
CN114476017A CN202210211785.1A CN202210211785A CN114476017A CN 114476017 A CN114476017 A CN 114476017A CN 202210211785 A CN202210211785 A CN 202210211785A CN 114476017 A CN114476017 A CN 114476017A
Authority
CN
China
Prior art keywords
handle
cockpit
bolt
rotating shaft
cover
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.)
Withdrawn
Application number
CN202210211785.1A
Other languages
Chinese (zh)
Inventor
李孚右
周志东
赵轶
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hunan Sunward Science & Technology Co ltd
Original Assignee
Hunan Sunward Science & Technology Co ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hunan Sunward Science & Technology Co ltd filed Critical Hunan Sunward Science & Technology Co ltd
Priority to CN202210211785.1A priority Critical patent/CN114476017A/en
Publication of CN114476017A publication Critical patent/CN114476017A/en
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1423—Passenger doors

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Lock And Its Accessories (AREA)

Abstract

The invention discloses a locking mechanism and a locking method for a light aircraft cockpit cover, which comprises a locking part arranged on the cockpit cover and a limiting part arranged on an aircraft body, wherein the locking part comprises an inner handle, an outer handle, a rotating shaft, a rotating crank, a bolt connecting rod and a bolt, the handle is connected with the rotating shaft, the rotating crank is connected with the rotating shaft and turns along with the rotating shaft, one end of the bolt connecting rod is connected with the rotating crank, the other end of the bolt connecting rod is connected with the bolt, the bolt is fixed at the edge of the cockpit cover through a guide block, and the bolt is controlled by the inner handle and the outer handle, so that the function of controlling the opening and closing of the cockpit inside and the outside of a small aircraft is realized, the safety and the stability of locking are improved, and the problem that a cockpit door cannot be opened in time in an emergency state is avoided.

Description

Locking mechanism for light aircraft cockpit cover and using method
Technical Field
The invention relates to the technical field of light aircraft locking structures, in particular to a light aircraft cockpit lid locking mechanism and a using method thereof.
Background
The entrance and exit of a cockpit in a small airplane realize the entrance and exit of personnel through the opening of a hatch cover, according to the regulation, an emergency exit of the airplane must be capable of being opened from both the inner side and the outer side, and the hatch cover is used as the only entrance and exit of the small airplane and needs to fully ensure the safety of opening and closing the hatch cover.
CN202110982316.5 an opening and closing mechanism of an airplane cabin cover, an airplane cabin mechanism and an opening and closing method thereof are disclosed to comprise a bolt system, a push rod system and a tightening device; the bolt system comprises an elastic element and a bolt, the elastic element is sleeved on the bolt, the bolt comprises a first end and a second end, and one end of the elastic element is fixedly connected with the first end; the tightening device comprises a tightening rope; one end of the push rod system is connected with the first end, and the other end of the push rod system is connected with the tightening rope; the push rod system is used for pushing the bolt when the tightening rope is tightened. According to the structure, the opening and closing method of the opening and closing mechanism comprises the following steps:
when the hatch cover is in an open state in the initial state, the hatch cover is closed, the tightening rope is tightened, the pressure lever moves and drives the bolt to be sequentially inserted into the second bolt hole and the first bolt hole, and the closing of the hatch cover is completed;
when the hatch cover is in a closed state in the initial state, the acting force of the tightening rope on the pressing rod is relieved, and the pressing rod drives the bolt to sequentially withdraw from the first bolt hole and the second bolt hole under the action of the elastic element, so that the hatch cover is separated from the cabin body.
However, the opening and closing mechanism is built under the condition that the members in the aircraft can normally operate the opening and closing mechanism, and in an emergency state, the crew members not only can open the hatch cover from the inside to get away, but also can open the hatch cover from the outside in time to rescue the crew members when the crew members are injured or in a coma and can not actively open the hatch cover from the cabin. Obviously, the opening and closing mechanism cannot be timely and effectively opened from the outside.
Meanwhile, the sealing performance of the cockpit and the transmission stability of the locking mechanism are guaranteed under the high pressure of the cockpit cover in the flying process, the complexity of a transmission structure is reduced, and jamming is avoided. CN202110273679.1 discloses an inside and outside opening handle of a hatch cover and an opening method thereof, wherein the hatch cover is opened by an outside handle in an emergency. However, the outer handle in this structure is placed in the lid, can't remove when not using, the inner handle need rotate under the condition that influences outer handle motionless, lead to linkage's complexity, for example the link of pivot and outer handle need set up the arc boss, the end of outer handle is equipped with the arc cavity that corresponds with the arc boss, the arc length of this arc cavity is the twice of arc boss, the arc boss of pivot is pegged graft in the arc cavity at outer handle end, be equipped with the spring on the lockpin simultaneously, the lockpin shifts in the arc hole of swivelling joint because of the extrusion of spring easily, lead to handle pivoted card stagnation nature, thereby be difficult to guarantee emergency's safety and stability.
Disclosure of Invention
The invention aims to solve the technical problems of complexity and unreasonable structural design of a locking mechanism of an aircraft cockpit cover in the prior art, and provides a light locking mechanism of the aircraft cockpit cover.
The invention also provides a use method of the locking mechanism of the light aircraft cockpit cover.
The purpose of the invention is realized by the following technical scheme:
a method for opening a cockpit cover of a light sports aircraft comprises the following steps:
opening from the inside of the cockpit under normal conditions: when the cockpit is closed, personnel in the cockpit firstly unfold the inner handle, rotate the inner handle, the inner handle drives the rotating shaft to rotate, the rotating crank sleeved on the rotating shaft rotates along with the rotating shaft, and therefore the bolt connecting rod connected with the rotating crank moves along with the rotating crank to drive the bolt to slide in the guide block and withdraw from the bolt hole, the cockpit cover is unlocked, after the crew comes out, the cockpit cover is pressed down, and the outer handle is rotated to enable the bolt to be inserted into the bolt hole, so that the cockpit is closed.
Mode of opening from outside the cockpit in normal state: the key lock is unlocked by a key, the outer handle is rotated to drive the rotating shaft to rotate, the rotating crank sleeved on the rotating shaft rotates along with the rotating shaft, so that the bolt connecting rod connected with the rotating crank moves along with the rotating crank to drive the bolt to slide in the guide block and withdraw from the bolt hole, the cockpit cover is unlocked, after a crew enters, the cockpit cover is pulled to be closed, and the inner handle is rotated to enable the bolt to be inserted into the bolt hole to close the cockpit.
Opening from the outside of the cockpit in an emergency: when the cockpit is closed, a person in the cockpit cannot rotate the inner handle, the person outside the cockpit directly rotates the outer handle, the outer handle drives the handle rotating shaft to rotate, the rotating crank sleeved on the handle rotating shaft rotates along with the outer handle, and therefore the bolt connecting rod connected with the rotating crank moves along with the rotating crank to drive the bolt to slide in the guide block and withdraw from the bolt hole, and the cockpit cover is unlocked.
According to the invention, the handle linked inside and outside is arranged on the cockpit cover, so that the cockpit cover can be controlled to be opened and closed at the same time, the cockpit can be opened quickly and timely from the outside by personnel outside the cockpit under the condition that the cockpit cannot be opened actively by the cockpit under the normal state of the cockpit by the pilot, the problem that the cockpit can be rescued by destroying the cockpit cover is avoided, and the safety guarantee of the cockpit is improved.
A locking mechanism of a light-weight aircraft cockpit cover for realizing an opening method of the light-weight moving aircraft cockpit cover comprises a locking part arranged on the cockpit cover and a limiting part arranged on an aircraft body;
the locking part comprises an inner handle, an outer handle, a handle rotating shaft, a rotating crank, a bolt connecting rod and a bolt, wherein the inner handle is connected with one end of the handle rotating shaft, the handle rotating shaft is arranged on the inner side of the cockpit cover, the outer handle is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover to be connected with the other end of the handle rotating shaft, and the cockpit cover can be controlled to be opened and closed simultaneously through the inner handle and the outer handle. The rotary crank is connected with the handle rotating shaft and can rotate along with the handle rotating shaft, one end of the bolt connecting rod is connected with the rotary crank, the other end of the bolt connecting rod is connected with the bolt, and the bolt is fixed on the edge of the cockpit cover through the guide block;
the outer handle is a fin-shaped handle. The inner handle and the handle rotating shaft are connected with the handle rotating shaft through a pin shaft, and the inner handle can be folded around the rotating shaft;
the limiting part is provided with a limiting hole for inserting the bolt, and the cockpit cover and the airplane body are controlled to be opened and closed through the matching of the bolt and the limiting hole.
Furthermore, the handle rotating shaft is fixed on the cabin cover through a rotating shaft mounting seat, and the handle rotating shaft is connected with the rotating shaft mounting seat through a radial spherical plain bearing.
Furthermore, the inner handle is a T-shaped handle, so that the inner handle can be rotated conveniently and can be used as a handle for closing the awning cover. The outer handle is a fin-shaped handle, the locking state is consistent with the running direction of the airplane, and the effect of reducing the resistance of the streamline of the airplane cannot be influenced.
Furthermore, the inner handle is connected with the rotating shaft through a pin shaft, and the inner handle can rotate, fold and fold around the pin shaft, so that the collision between personnel and the end part of the handle is avoided.
Furthermore, one end of the handle rotating shaft is provided with a concave connecting hole, two lug positions of the connecting hole are provided with a first pin hole, one end of the inner handle is provided with a convex connecting piece correspondingly matched with the concave connecting hole, and the convex connecting piece is provided with a second pin hole.
Furthermore, a blocking piece for folding the inner handle is arranged in the concave connecting hole of the handle rotating shaft. The blocking piece is a compression spring, the state of the inner handle is stabilized by the extrusion of the spring, and the rotation control of the handle is not obstructed.
Furthermore, the number of the bolts is not less than two, a plurality of bolts are combined together through the bolt connecting pieces, and the bolt connecting rods are connected with the bolt connecting pieces to control the movement of the bolts in a unified mode.
Further, a key lock is arranged on the cockpit cover or the airplane body.
Furthermore, the key lock comprises a rotating tongue lock, a rotating tongue and a rotating tongue hole for limiting the rotating tongue, the rotating tongue lock is connected with the rotating tongue, and the insertion between the rotating tongue and the rotating tongue hole can be controlled through a key.
A lightweight sports aircraft comprising a lightweight aircraft cockpit lid locking mechanism as described above.
Compared with the prior art, the beneficial effects are:
according to the invention, the inner and outer linked handles are arranged on the cockpit cover, the outer handle and the inner handle are directly and fixedly connected with the rotating shaft, the control actions of the outer handle and the inner handle are synchronous, and the sliding of the lock pin is controlled through the rotation of the inner handle and the outer handle to the rotating shaft, so that the cockpit cover can be controlled to be opened and closed from the inside and the outside of the airplane, the opening and closing of a cockpit cover can be ensured under the normal state of a pilot, and the problem that the pilot can be rescued only by damaging the cockpit cover can be avoided under the condition that the pilot can not actively open the cockpit under the emergency state.
The outer handle of the invention adopts fin shape and is directly arranged on the cockpit cover without influencing the streamline of the airplane. The inner handle can be folded, and can be used as a handle to facilitate the closing of the cockpit when avoiding the collision of people. The invention simplifies the unlocking structure, directly utilizes the rotation of the rotating shaft to drive the movement of the pin shaft, has no hysteresis in action, and improves the safety and stability of the locking mechanism.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of the present invention;
FIG. 3 is a schematic structural view of the present invention;
fig. 4 is a cross-sectional view of the inventive structure.
The novel bolt-free lock comprises an outer handle 1, a handle rotating shaft 2, a rotating shaft mounting seat 3, a rotating crank 4, an inner handle 5, a bolt connecting rod 6, a rotating bolt 7, a rotating bolt lock 8, a guide block 9, a bolt 10, a bolt connecting sheet 11 and a bolt hole 12.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. 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.
It should be noted that, if directional indications (such as up, down, left, right, front, and back) are involved in the embodiment of the present invention, the directional indications are only used to explain the relative positional relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indications are changed accordingly. If there is a description of "first", "second", etc. in an embodiment of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, such as "connected," which may 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.
Example 1
The embodiment provides a light aircraft cockpit cover locking mechanism which comprises a locking part and a limiting part, wherein the locking part is installed on a cockpit cover, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a handle rotating shaft 2, a rotating crank 4, a bolt connecting rod 6 and a bolt 10, wherein a rotating shaft mounting seat 3 is fixed on the inner side of the cockpit cover, the handle rotating shaft 2 is connected with the rotating shaft mounting seat 3 through a radial knuckle bearing, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover and the other end of the handle rotating shaft 2 to be fixedly connected, and the inner handle 5 and the outer handle 1 can both control the rotation of the handle rotating shaft 2. The rotary crank 4 is provided with two shaft holes, one of which is sleeved on the outer wall of the handle rotating shaft 2, and the rotary crank 4 can rotate along with the handle rotating shaft 2. Another shaft hole on the rotary crank 4 is connected with one end of the bolt connecting rod 6 through a movable shaft, the other end of the bolt connecting rod 6 is connected with the bolt 10, the bolt 10 is fixed on the edge of the cockpit cover through the guide block 9, and the bolt 10 can slide in the guide block 9 under the pulling of the bolt connecting rod 6.
The limiting part is fixed at the joint of the aircraft body and the cockpit cover, a bolt hole 12 is formed in the position corresponding to the bolt 10, after the bolt 10 is inserted into the bolt hole 12, the cockpit cover and the aircraft body are integrated, and the cockpit is closed.
The inner handle 5 is a T-shaped handle, so that the crew member can hold the inner handle to rotate conveniently. The outer handle 1 is a fin-shaped handle, is attached to the streamline of an airplane, cannot block the flow of air outside the airplane, and reduces resistance.
When the cockpit is closed, a person in the cockpit can rotate the inner handle 5, the inner handle 5 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating handle, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating handle to drive the bolt 10 to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
When the cockpit is closed, a person in the cockpit cannot rotate the inner handle 5, the person outside the cockpit can rotate the outer handle 1, the outer handle 1 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating handle, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating handle, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
Example 2
The embodiment provides a light aircraft cockpit cover locking mechanism which comprises a locking part and a limiting part, wherein the locking part is installed on a cockpit cover, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a handle rotating shaft 2, a rotating crank 4, a bolt connecting rod 6 and a bolt 10, wherein a rotating shaft mounting seat 3 is fixed on the inner side of the cockpit cover, the handle rotating shaft 2 is connected with the rotating shaft mounting seat 3 through a radial knuckle bearing, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover and the other end of the handle rotating shaft 2 to be fixedly connected, and the inner handle 5 and the outer handle 1 can both control the rotation of the handle rotating shaft 2. The rotary crank 4 is provided with two shaft holes, one of which is sleeved on the outer wall of the handle rotating shaft 2, and the rotary crank 4 can rotate along with the handle rotating shaft 2. Another shaft hole on the rotary crank 4 is connected with one end of a bolt connecting rod 6 through a movable shaft, the other end of the bolt connecting rod 6 is connected with a bolt 10, the other end of the bolt connecting rod 6 is connected with the bolt 10, the bolt 10 is fixed on the edge of the cockpit cover through a guide block 9, and the bolt 10 can slide in the guide block 9 under the pulling of the bolt connecting rod 6.
The limiting part is fixed at the joint of the aircraft body and the cockpit cover, a bolt hole 12 is formed in the position corresponding to the bolt 10, after the bolt 10 is inserted into the bolt hole 12, the cockpit cover and the aircraft body are integrated, and the cockpit is closed.
The inner handle 5 is a T-shaped handle, so that a crew member can conveniently hold and rotate, the end part of the T-shaped handle is connected with the handle rotating shaft 2 through a bolt 10, the T-shaped handle can rotate around a pin shaft, a spring is further arranged at the end part of the handle rotating shaft 2 and extrudes the T-shaped handle, and the T-shaped handle can be kept in a bent and folded state under acting force.
The outer handle 1 is a fin-shaped handle, is attached to the streamline of an airplane, cannot block the flow of air outside the airplane, and reduces resistance.
When the cockpit is closed, a person in the cockpit firstly puts down the T-shaped handle by rotating around the pin shaft, then rotates the inner handle 5, the inner handle 5 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating crank, so that the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating crank, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
When the cockpit is closed, a person in the cockpit cannot rotate the inner handle 5, the person outside the cockpit can rotate the outer handle 1, the outer handle 1 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating handle, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating handle, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
Example 3
The embodiment provides a light aircraft cockpit cover locking mechanism which comprises a locking part and a limiting part, wherein the locking part is installed on a cockpit cover, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a handle rotating shaft 2, a rotating crank 4, a bolt connecting rod 6 and a bolt 10, wherein a rotating shaft mounting seat 3 is fixed on the inner side of the cockpit cover, the handle rotating shaft 2 is connected with the rotating shaft mounting seat 3 through a radial knuckle bearing, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover and the other end of the handle rotating shaft 2 to be fixedly connected, and the inner handle 5 and the outer handle 1 can both control the rotation of the handle rotating shaft 2. The outer wall of the handle rotating shaft 2 is connected with a rotating crank 4, and the rotating crank 4 can rotate along with the handle rotating shaft 2. The rotary crank 4 is connected with one end of the bolt connecting rod 6, the other end of the bolt connecting rod 6 is connected with the bolt connecting piece 11, two parallel and level bolts 10 are arranged on the bolt connecting piece 11, the two parallel and level bolts 10 are fixed on the edge of the cab cover through sliding holes in the guide blocks 9 respectively, and the bolts 10 can slide in the guide blocks 9 under the pulling of the bolt connecting rod 6.
The limiting part is fixed at the joint of the aircraft body and the cockpit cover, a bolt hole 12 is formed in the position corresponding to the bolt 10, after the bolt 10 is inserted into the bolt hole 12, the cockpit cover and the aircraft body are integrated, and the cockpit is closed.
The inner handle 5 is a T-shaped handle, so that a crew member can conveniently hold and rotate, the end part of the T-shaped handle is connected with the handle rotating shaft 2 through a bolt 10, the T-shaped handle can rotate around a pin shaft, a spring is further arranged at the end part of the handle rotating shaft 2 and extrudes the T-shaped handle, and the T-shaped handle can be kept in a bent and folded state under acting force.
The outer handle 1 is a fin-shaped handle, is attached to the streamline of an airplane, cannot block the flow of air outside the airplane, and reduces resistance.
When the cockpit is closed, a person in the cockpit firstly puts down the T-shaped handle by rotating around the pin shaft, then rotates the inner handle 5, the inner handle 5 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating crank, so that the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating crank, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
When the cockpit is closed, a person in the cockpit cannot rotate the inner handle 5, the person outside the cockpit can rotate the outer handle 1, the outer handle 1 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating handle, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating handle, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
Example 4
The embodiment provides a light aircraft cockpit cover locking mechanism which comprises a locking part and a limiting part, wherein the locking part is installed on a cockpit cover, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a handle rotating shaft 2, a rotating crank 4, a bolt connecting rod 6 and a bolt 10, wherein a handle rotating shaft 2 mounting seat is fixed on the inner side of the cockpit cover, the handle rotating shaft 2 and the handle rotating shaft 2 mounting seat are connected through a radial knuckle bearing, the inner handle 5 is fixedly connected with one end of the handle rotating shaft 2, the outer handle 1 is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover and the other end of the handle rotating shaft 2 to be fixedly connected, and the inner handle 5 and the outer handle 1 can both control the rotation of the handle rotating shaft 2. The outer wall of the handle rotating shaft 2 is connected with a rotating crank 4, and the rotating crank 4 can rotate along with the handle rotating shaft 2. The rotary crank 4 is connected with one end of the bolt connecting rod 6, the other end of the bolt connecting rod 6 is connected with the bolt connecting piece 11, two parallel and level bolts 10 are arranged on the bolt connecting piece 11, the two parallel and level bolts 10 are fixed on the edge of the cab cover through sliding holes in the guide block respectively, and the bolts 10 can slide in the guide block under the pulling of the bolt connecting rod 6.
The locking part further comprises a key lock, the key lock comprises a rotating tongue lock 8, a rotating tongue 7 and a rotating tongue hole for limiting the rotating tongue 7, the rotating tongue lock 8 is fixed on the edge of the cockpit cover, a key opening is formed in the outer side of the cockpit cover, and the end part of the rotating tongue lock 8 in the cockpit cover is connected with the rotating tongue 7.
The limiting part is fixed at the joint of the aircraft body and the cockpit cover, a bolt hole 12 is formed in the position corresponding to the bolt 10, a rotating tongue hole is formed in the position corresponding to the rotating tongue 7, the bolt 10 is inserted into the bolt hole 12, the rotating tongue 7 is inserted into the rotating tongue hole, the cockpit cover is combined with the aircraft body, and the cockpit is closed.
The inner handle 5 is a T-shaped handle, so that a crew member can conveniently hold and rotate, the end part of the T-shaped handle is connected with the handle rotating shaft 2 through a bolt 10, the T-shaped handle can rotate around a pin shaft, a spring is further arranged at the end part of the handle rotating shaft 2 and extrudes the T-shaped handle, and the T-shaped handle can be kept in a bent and folded state under acting force.
The outer handle 1 is a fin-shaped handle, is attached to the streamline of an airplane, cannot block the flow of air outside the airplane, and reduces resistance.
When the cockpit is closed, a person in the cockpit firstly puts down the T-shaped handle by rotating around the pin shaft, then rotates the inner handle 5, the inner handle 5 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating crank, so that the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating crank, the bolt 10 is driven to slide in the guide block and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
When the cockpit is closed, a person in the cockpit cannot rotate the inner handle 5, the person outside the cockpit can rotate the outer handle 1, the outer handle 1 drives the handle rotating shaft 2 to rotate, the rotating crank 4 sleeved on the handle rotating shaft 2 rotates along with the rotating handle, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating handle, the bolt 10 is driven to slide in the guide block and withdraw from the bolt hole 12, and the cockpit cover is unlocked.
Example 5
A small-sized sports airplane comprises the light airplane cockpit cover locking mechanism in any one of embodiments 1 to 4.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims (10)

1. A method for opening a cockpit cover of a light sports aircraft, comprising:
opening from the inside of the cockpit under normal conditions: when the cockpit is closed, personnel in the cockpit firstly unfold the inner handle, rotate the inner handle, the inner handle drives the rotating shaft to rotate, the rotating crank sleeved on the rotating shaft rotates along with the rotating shaft, so that the bolt connecting rod connected with the rotating crank moves along with the rotating crank, the bolt is driven to slide in the guide block and withdraw from the bolt hole, the cockpit cover is unlocked, after the crew comes out, the cockpit cover is pressed down, the outer handle is rotated to enable the bolt to be inserted into the bolt hole, and then the key lock is locked by a key;
opening from the outside of the cockpit in an emergency: when the cockpit is closed, a person in the cockpit cannot rotate the inner handle, the person outside the cockpit rotates the outer handle, the outer handle drives the handle rotating shaft to rotate, the rotating crank sleeved on the handle rotating shaft rotates along with the outer handle, and therefore the bolt connecting rod connected with the rotating crank moves along with the rotating crank to drive the bolt to slide in the guide block and withdraw from the bolt hole, and the cockpit cover is unlocked.
2. A locking mechanism of a light-weight aircraft cockpit cover for realizing an opening method of the light-weight moving aircraft cockpit cover is characterized by comprising a locking part arranged on the cockpit cover and a limiting part arranged on an aircraft body;
the locking part comprises an inner handle, an outer handle, a handle rotating shaft, a rotating crank, a bolt connecting rod and a bolt, wherein the inner handle is connected with one end of the handle rotating shaft, the handle rotating shaft is arranged on the inner side of the cockpit cover, the outer handle is arranged on the outer side of the cockpit cover and penetrates through the cockpit cover to be connected with the other end of the handle rotating shaft, the rotating crank is connected with the handle rotating shaft and can rotate along with the handle rotating shaft, one end of the bolt connecting rod is connected with the rotating crank, the other end of the bolt connecting rod is connected with the bolt, and the bolt is fixed on the edge of the cockpit cover through a guide block;
the outer handle is a fin-shaped handle; the inner handle and the handle rotating shaft are connected with the handle rotating shaft through a pin shaft, and the inner handle can be folded around the rotating shaft;
the limiting part is provided with a limiting hole for inserting the bolt.
3. The light aircraft cockpit cover locking mechanism of claim 2 wherein the handle shaft is secured to the canopy by a shaft mount and the handle shaft is coupled to the shaft mount by a radial spherical bearing.
4. The light aircraft cockpit cover locking mechanism of claim 2 wherein said inner handle is a T-handle.
5. The light aircraft cockpit lid locking mechanism of claim 2 wherein said handle shaft has a female connection hole at one end, a first pin hole is formed at each of two ears of said connection hole, a male connection member correspondingly matching said female connection hole is formed at one end of said inner handle, and a second pin hole is formed in said male connection member.
6. The light aircraft cockpit lid locking mechanism of claim 2 wherein the female coupling hole of the handle pivot shaft has a check for internal handle folding.
7. The light aircraft cockpit cover locking mechanism of claim 6 wherein said check member is a compression spring.
8. The light aircraft cockpit cover locking mechanism of claim 2 wherein the number of latches is no less than two and a plurality of latches are combined together by a latch connecting plate.
9. The light aircraft cockpit cover locking mechanism of claim 2 wherein a key lock is further provided on the cockpit cover or the aircraft body, the key lock comprising a lock tongue, and a lock tongue hole for limiting the lock tongue.
10. A light sports aircraft comprising a light aircraft cockpit lid locking mechanism according to any one of claims 2 to 9.
CN202210211785.1A 2022-03-04 2022-03-04 Locking mechanism for light aircraft cockpit cover and using method Withdrawn CN114476017A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210211785.1A CN114476017A (en) 2022-03-04 2022-03-04 Locking mechanism for light aircraft cockpit cover and using method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210211785.1A CN114476017A (en) 2022-03-04 2022-03-04 Locking mechanism for light aircraft cockpit cover and using method

Publications (1)

Publication Number Publication Date
CN114476017A true CN114476017A (en) 2022-05-13

Family

ID=81485459

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210211785.1A Withdrawn CN114476017A (en) 2022-03-04 2022-03-04 Locking mechanism for light aircraft cockpit cover and using method

Country Status (1)

Country Link
CN (1) CN114476017A (en)

Similar Documents

Publication Publication Date Title
US10647403B2 (en) Actuatable emergency exit door and an aircraft or space craft with a pressurized cabin having such an actuatable emergency exit door
EP0743240B1 (en) Latch-lock mechanism for load carrying airplane cargo doors
JP3060139U (en) Door latch device
US6945497B2 (en) Cockpit door of aircraft
EP2781451B1 (en) Aircraft with integrated jettison mechanism
AU2018282478B2 (en) Aircraft privacy door and door frame assembly
EP1988239B1 (en) Dual action structural latch
CN111287583A (en) System for latching and locking an aircraft door
US20200199920A1 (en) Aircraft door handle assembly
US10871013B2 (en) Load transfer interface for a vehicle door, in particular for an aircraft cabin door
CN114476017A (en) Locking mechanism for light aircraft cockpit cover and using method
US6997414B2 (en) Cargo door modification to ease emergency egress
CN217198626U (en) Aircraft canopy door lock mechanism and light sport aircraft
US10472041B2 (en) System and method for flag door operation
CN112550661B (en) Civil aircraft semi-plugging type wing upper emergency cabin door
CA2451832C (en) Cargo door modification to ease emergency egress
EP3524510B1 (en) Aircraft privacy door and door frame assembly
US20240018802A1 (en) Handle Assembly for Escape Hatch
EP4201808A1 (en) Emergency device actuation assemblies and aircraft including same
EP3524512A1 (en) Aircraft privacy door and door frame assembly
CN115556918A (en) Aircraft cabin door pressurization preventing device
JPH05286495A (en) Door lock device for aircraft

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
CB02 Change of applicant information

Address after: 412002 no.768 Zhixing street, Lusong District, Zhuzhou City, Hunan Province

Applicant after: Shanhe Xinghang Industrial Co.,Ltd.

Address before: 412002 no.768 Zhixing street, Lusong District, Zhuzhou City, Hunan Province

Applicant before: HUNAN SUNWARD SCIENCE & TECHNOLOGY Co.,Ltd.

CB02 Change of applicant information
WW01 Invention patent application withdrawn after publication

Application publication date: 20220513

WW01 Invention patent application withdrawn after publication