CN217198626U - Aircraft canopy door lock mechanism and light sport aircraft - Google Patents
Aircraft canopy door lock mechanism and light sport aircraft Download PDFInfo
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- CN217198626U CN217198626U CN202220468798.2U CN202220468798U CN217198626U CN 217198626 U CN217198626 U CN 217198626U CN 202220468798 U CN202220468798 U CN 202220468798U CN 217198626 U CN217198626 U CN 217198626U
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Abstract
The utility model discloses an aircraft canopy lock mechanism and motion aircraft, including installing the sticking department on aircraft canopy and installing the spacing portion on the aircraft body, including interior handle, outer handle, pivot, rotating crank, bolt connecting rod and bolt, the handle is connected with the pivot, and rotating crank is connected with the pivot and turns to along with the pivot, and bolt connecting rod one end is connected with rotating crank, and the other end and bolt connection, bolt pass through the guide block and fix at the edge of aircraft canopy, through the control of interior handle and outer handle to the bolt, have realized the function of the inside and outside homoenergetic control cockpit switching of small aircraft, have improved the safety and stability of locking, have avoided the problem that emergency down the cabin door can't in time be opened.
Description
Technical Field
The utility model relates to a light-duty aircraft locking technical field, more specifically relates to an aircraft canopy lock mechanism moves aircraft promptly.
Background
In the small airplane, the entrance and the exit of a cockpit are realized by opening a hatch cover, according to the regulations, an emergency exit of the airplane must be opened from the inner side and the outer side, and the hatch cover is used as the only entrance and the exit of the small airplane and needs to fully ensure the safety of opening and closing the hatch cover. Under emergency, the crew member not only can open the hatch cover from inside and leave the position, and when the crew member is injured or unconscious and can not actively open the hatch cover from the cabin, the crew member outside can open the hatch cover from the outside in time to rescue the crew member.
CN202110273679.1 discloses a hatch door locking device comprising an inner handle, an outer handle, a rotating shaft and a lock pin, wherein the inner handle is connected to one end of the rotating shaft, the outer handle is connected to the other end of the rotating shaft, the lock pin is connected to the rotating shaft, one end of the rotating shaft and the outer handle are located at the outer side of the hatch cover, and the other end of the rotating shaft, the inner handle and the lock pin are located at the inner side of the hatch cover. When the aircraft hatch is in a closed state, the hatch is opened through the inner handle under normal conditions, the inner handle is not linked with the outer handle, and the retraction state of the outer handle is kept; in an emergency, the hatch is opened by means of an external handle. However, the outer handle in the structure is placed in the box cover and cannot move when not used, the inner handle needs to rotate under the condition that the outer handle is affected to be immobile, the complexity of the linkage structure is caused, meanwhile, the spring is arranged on the lock pin, and the lock pin is easy to displace in the arc-shaped hole of the rotating joint due to the extrusion of the spring, so that the clamping stagnation property of the rotation of the handle is caused.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to aircraft cockpit lid locking mechanism's complicacy among the prior art, and structural design is unreasonable not enough, provides an aircraft canopy lock mechanism.
The utility model discloses another technical problem that solve provides the light aircraft who contains above-mentioned aircraft canopy lock mechanism.
The purpose of the utility model is realized through the following technical scheme:
an airplane canopy door lock mechanism comprises a locking part and a limiting part, wherein the locking part is installed on an airplane canopy, and the limiting part is installed on an airplane body.
The locking part comprises a handle, a rotating shaft, a rotating crank, a bolt connecting rod and a bolt, wherein 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, and the bolt is fixed on the edge of the aircraft canopy through a guide block.
The handle comprises an inner handle and an outer handle, the inner handle is installed at one end of the rotating shaft, and the outer handle penetrates through the canopy of the airplane and is fixed at the other end of the rotating shaft.
The limiting part is provided with a limiting hole for inserting the bolt, and the opening and closing of the aircraft canopy and the aircraft body are controlled through the matching of the bolt and the limiting hole.
Further, the handle comprises an inner handle and an outer handle, the inner handle is installed in the cabin, the outer handle is installed outside the cabin, and the opening and closing of the canopy of the airplane can be controlled through the inner handle and the outer handle simultaneously.
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, so that the flow of air outside the machine cannot be blocked, and the resistance is reduced.
Furthermore, the rotating shaft is fixed on the canopy of the airplane through a rotating shaft mounting seat, and the inner handle and the outer handle can both control the rotation of the rotating shaft.
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, a compression spring is arranged on the movable contact surface of the rotating shaft and the inner handle, 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 rotating shaft is connected with the rotating shaft mounting seat through a radial spherical plain bearing.
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.
Furthermore, a key lock is arranged on the canopy or the body of the airplane.
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 characterised by an aircraft canopy door lock mechanism as hereinbefore described.
Compared with the prior art, the beneficial effects are:
the utility model discloses an inside and outside handle is to the rotation of pivot to the control lockpin slides, has reached from the aircraft in and the aircraft outside homoenergetic opens the technological effect in cockpit. The utility model discloses an outer handle and interior handle are direct and the fixed connection of pivot, and the control action of outer handle and interior handle is synchronous to outer handle adopts the fin-shaped, and direct mount does not influence the streamlined of aircraft on the sky canopy. Simultaneously the utility model discloses directly utilize the activity of the rotatory drive round pin axle of pivot, the action does not have the hysteresis quality. The utility model discloses simplify the structure of unblanking, improved locking mechanism's safety and stability nature.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic view of the present invention;
FIG. 3 is a schematic structural view of the present invention;
fig. 4 is a sectional view of the structure of the present invention.
The novel bolt-locking mechanism comprises an outer handle 1, a 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 piece 11 and a bolt hole 12.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to 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 provided in the embodiments of the present invention, the directional indications are only used to explain the relative position relationship between the components, the motion situation, and the like in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indication is changed accordingly. If there is a description in an embodiment of the present invention referring to "first", "second", etc., 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, and for example, "connected" may be either fixedly connected or 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 meaning 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 an airplane canopy door lock mechanism which comprises a locking part and a limiting part, wherein the locking part is installed on an airplane canopy, and the limiting part is installed on an airplane body.
The locking part comprises an inner handle 5, an outer handle 1, a 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 aircraft canopy, the 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 rotating shaft 2, the outer handle 1 is arranged on the outer side of the aircraft canopy and penetrates through the aircraft canopy to be fixedly connected with the other end of the rotating shaft 2, and the inner handle 5 and the outer handle 1 can both control the rotation of the rotating shaft 2. The rotary crank 4 is provided with two shaft holes, one of which is sleeved on the outer wall of the rotating shaft 2 and the rotary crank 4 can rotate along with the rotating shaft 2. Another shaft hole on the rotating 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 bolt 10 is fixed on the edge of the canopy of the airplane 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 airplane body and the airplane canopy, 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 airplane canopy and the airplane 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 outside air, and reduces resistance.
When the cockpit is closed, a person in the aircraft can rotate the inner handle 5, the inner handle 5 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating shaft to drive the bolt 10 to slide in the guide block 9 and withdraw from the bolt hole 12, and the aircraft canopy is unlocked.
When the cockpit is closed, a person in the aircraft cannot rotate the inner handle 5, the person outside the aircraft can rotate the outer handle 1, the outer handle 1 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating shaft, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the aircraft ceiling is unlocked.
Example 2
The embodiment provides an aircraft canopy door lock mechanism, which comprises a locking part and a limiting part, wherein the locking part is installed on an aircraft canopy, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a 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 aircraft canopy, the 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 rotating shaft 2, the outer handle 1 is arranged on the outer side of the aircraft canopy and penetrates through the aircraft canopy to be fixedly connected with the other end of the rotating shaft 2, and the inner handle 5 and the outer handle 1 can both control the rotation of the rotating shaft 2. The rotating crank 4 is provided with two shaft holes, one of which is sleeved on the outer wall of the rotating shaft 2 and the rotating crank 4 can rotate along with the 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 canopy of the airplane 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 airplane body and the airplane canopy, 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 airplane canopy and the airplane body are assembled, 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 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 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 aircraft 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 rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating crank, so that the bolt 10 is driven to slide in the guide block 9, and retreats from the bolt hole 12, and the aircraft ceiling is unlocked.
When the cockpit is closed, a person in the aircraft cannot rotate the inner handle 5, the person outside the aircraft can rotate the outer handle 1, the outer handle 1 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating shaft, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the aircraft ceiling is unlocked.
Example 3
The embodiment provides an aircraft canopy door lock mechanism, which comprises a locking part and a limiting part, wherein the locking part is installed on an aircraft canopy, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a 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 aircraft canopy, the 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 rotating shaft 2, the outer handle 1 is arranged on the outer side of the aircraft canopy and penetrates through the aircraft canopy to be fixedly connected with the other end of the rotating shaft 2, and the inner handle 5 and the outer handle 1 can both control the rotation of the rotating shaft 2. The outer wall of the rotating shaft 2 is connected with a rotating crank 4, and the rotating crank 4 can rotate along with the rotating shaft 2. The rotary crank 4 is connected with one end of a bolt connecting rod 6, the other end of the bolt connecting rod 6 is connected with a 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 an airplane canopy through sliding holes in a guide block 9 respectively, and the bolts 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 airplane body and the airplane canopy, 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 airplane canopy and the airplane 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 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 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 aircraft rotates the T-shaped handle around the pin shaft to put down, then rotates the inner handle 5, the inner handle 5 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore 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, the aircraft canopy is unlocked, and the aircraft canopy is withdrawn from the aircraft canopy through the bolt hole 12.
When the cockpit is closed, a person in the aircraft cannot rotate the inner handle 5, the person outside the aircraft can rotate the outer handle 1, the outer handle 1 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating shaft, the bolt 10 is driven to slide in the guide block 9 and withdraw from the bolt hole 12, and the aircraft ceiling is unlocked.
Example 4
The embodiment provides an aircraft canopy door lock mechanism, which comprises a locking part and a limiting part, wherein the locking part is installed on an aircraft canopy, and the limiting part is installed on an aircraft body.
The locking part comprises an inner handle 5, an outer handle 1, a rotating shaft 2, a rotating crank 4, a bolt connecting rod 6 and a bolt 10, wherein a rotating shaft 2 mounting seat is fixed on the inner side of the aircraft canopy, the rotating shaft 2 is connected with the rotating shaft 2 mounting seat through a radial knuckle bearing, the inner handle 5 is fixedly connected with one end of the rotating shaft 2, the outer handle 1 is arranged on the outer side of the aircraft canopy and penetrates through the aircraft canopy to be fixedly connected with the other end of the rotating shaft 2, and the inner handle 5 and the outer handle 1 can both control the rotation of the rotating shaft 2. The outer wall of the rotating shaft 2 is connected with a rotating crank 4, and the rotating crank 4 can rotate along with the rotating shaft 2. The rotary crank 4 is connected with one end of a bolt connecting rod 6, the other end of the bolt connecting rod 6 is connected with a bolt connecting sheet 11, two parallel and level bolts 10 are arranged on the bolt connecting sheet 11, the two parallel and level bolts 10 are fixed on the edge of an airplane canopy through sliding holes in a 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 aircraft ceiling, a key opening is formed in the outer side of the aircraft ceiling, and the end part of the rotating tongue lock 8 in the aircraft ceiling is connected with the rotating tongue 7.
The limiting part is fixed at the joint of the airplane body and the airplane canopy, 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 airplane canopy is combined with the airplane 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 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 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 aircraft 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 rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating crank, so that the bolt 10 is driven to slide in the guide block, withdraw from the bolt hole 12, and the aircraft ceiling is unlocked.
When the cockpit is closed, a person in the aircraft cannot rotate the inner handle 5, the person outside the aircraft can rotate the outer handle 1, the outer handle 1 drives the rotating shaft 2 to rotate, the rotating crank 4 sleeved on the rotating shaft 2 rotates along with the rotating shaft, and therefore the bolt connecting rod 6 connected with the rotating crank 4 moves along with the rotating shaft, the bolt 10 is driven to slide in the guide block and withdraw from the bolt hole 12, and the aircraft ceiling is unlocked.
Example 5
A small sports aircraft comprising the canopy door lock mechanism of any of embodiments 1-4.
It is obvious that the above embodiments of the present invention are only examples for clearly illustrating the present invention, and are not limitations to 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 (9)
1. An aircraft canopy door lock mechanism is characterized by comprising a locking part and a limiting part, wherein the locking part is installed on an aircraft canopy;
the locking part comprises a handle, a rotating shaft, a rotating crank, a bolt connecting rod and a bolt, wherein 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, and the bolt is fixed on the edge of the aircraft canopy through a guide block;
the handle comprises an inner handle and an outer handle, the inner handle is arranged at one end of the rotating shaft through a pin shaft, and the outer handle is a fin-shaped handle and penetrates through the canopy of the airplane to be fixedly arranged at the other end of the rotating shaft;
the limiting part is provided with a limiting hole for inserting the bolt.
2. The canopy door lock mechanism of claim 1, wherein the shaft is secured to the canopy by a shaft mount.
3. The canopy door lock mechanism of claim 1, wherein the inner handle is a T-handle.
4. The canopy door lock mechanism of claim 1, wherein the movable interface of the shaft and the inner handle is provided with a compression spring.
5. The canopy door lock mechanism of claim 2, wherein the shaft is coupled to the shaft mount via a radial spherical bearing.
6. An aircraft canopy door lock mechanism as claimed in claim 1, wherein the number of bolts is not less than two, and a plurality of bolts are combined together by a bolt connecting piece.
7. The canopy door lock mechanism of claim 1, wherein the canopy or body of the aircraft is further provided with a key lock.
8. The aircraft canopy door lock mechanism of claim 7, wherein the key lock comprises a turn tongue lock, a turn tongue, and a turn tongue hole that is defined for the turn tongue.
9. A light sport aircraft comprising a canopy door lock mechanism according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220468798.2U CN217198626U (en) | 2022-03-04 | 2022-03-04 | Aircraft canopy door lock mechanism and light sport aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220468798.2U CN217198626U (en) | 2022-03-04 | 2022-03-04 | Aircraft canopy door lock mechanism and light sport aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217198626U true CN217198626U (en) | 2022-08-16 |
Family
ID=82753086
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220468798.2U Active CN217198626U (en) | 2022-03-04 | 2022-03-04 | Aircraft canopy door lock mechanism and light sport aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217198626U (en) |
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2022
- 2022-03-04 CN CN202220468798.2U patent/CN217198626U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 no.768 Zhixing street, Lusong District, Zhuzhou City, Hunan Province Patentee after: Shanhe Xinghang Industrial Co.,Ltd. Address before: 412002 no.768 Zhixing street, Lusong District, Zhuzhou City, Hunan Province Patentee before: HUNAN SUNWARD SCIENCE & TECHNOLOGY Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder |