CN113335491A

CN113335491A - Gravity center balancing device of airship and adjusting method thereof

Info

Publication number: CN113335491A
Application number: CN202110835208.5A
Authority: CN
Inventors: 曾如海; 李锦栋; 胡豆
Original assignee: Hubei Hangte Aircraft Co ltd
Current assignee: Hubei Hangte Aircraft Co ltd
Priority date: 2021-07-23
Filing date: 2021-07-23
Publication date: 2021-09-03

Abstract

The invention discloses a gravity center balancing device of an airship and an adjusting method thereof, relating to the technical field of gravity center balancing devices of airships; in order to balance the center of gravity of the airship; the gravity center balancing device comprises an air bag main body and a cockpit, wherein the air bag main body is connected with the cockpit through a vibration damping assembly, a driving system is arranged at the tail of the air bag main body, a cover plate is arranged on the inner wall of the cambered surface of the cockpit, a first hollow cylinder is arranged on the outer wall of the bottom of the cover plate, and an adjusting ball is movably connected to the inner wall of the first hollow cylinder; the adjusting method of the gravity center balancing device comprises the following steps: when the airship is in a standby state, the clamping disc is utilized to carry out limiting clamping on the chuck, so that the cross-shaped clamping seat is in a horizontal static state. The air bag driving device can be used for driving the air bag main body and adjusting the direction by arranging the driving system, and can effectively reduce the impact on a cab caused by wind power in high altitude by arranging the vibration reduction assembly.

Description

Gravity center balancing device of airship and adjusting method thereof

Technical Field

The invention relates to the technical field of airship gravity center balancing devices, in particular to a gravity center balancing device of an airship and an adjusting method thereof.

Background

The airship is a light aircraft, and the airship comprises huge streamlined hull, the nacelle that is located below the hull, the tail face and the advancing device that play the stable control effect, and fields such as present airship mainly used scientific experiment and shooting are at the in-process that uses, and the airship is because high altitude region wind speed is great, can produce great impact force to the airship surface to make the holistic focus of airship appear unstably, consequently need design a focus balancing unit can effectively improve the centrobaric balance of airship.

Through the retrieval, chinese patent application number is CN 201820214577.6's patent, discloses a model aeroplane and model ship gravity center balancing unit that takes off and land, including the frame, the frame mounting still includes steering wheel, power transmission device and balancing piece in model aeroplane and model ship gravity center position, steering wheel, power transmission device and balancing piece are installed in the frame, the steering wheel passes through power transmission device and is connected to the balancing piece, balancing piece and frame sliding connection.

The gravity center balancing device for model airplane take-off and landing in the patent has the following defects: in the lifting process of the model airplane, the steering engine needs to be controlled manually by using the remote control assembly, and the steering engine cannot be precisely matched and controlled according to the specific size of wind power, so that the gravity center balance has errors.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a gravity center balancing device of an airship and an adjusting method thereof.

In order to achieve the purpose, the invention adopts the following technical scheme:

the utility model provides a focus balancing unit of dirigible, includes gasbag main part and cockpit, connect through damping subassembly between gasbag main part and the cockpit, gasbag main part afterbody is provided with actuating system, cockpit cambered surface inner wall is provided with the apron, apron bottom outer wall is provided with hollow section of thick bamboo one, an inner wall swing joint of hollow section of thick bamboo has the adjusting ball, adjusting ball sphere outer wall has the spliced pole through threaded connection, spliced pole bottom outer wall is provided with cross screens seat, cross screens seat inner wall all around all has the electromagnetism suction disc through the screw fixation, electromagnetism suction disc surface adsorbs there is the balancing ball, and balancing ball sphere outer wall swing joint in cross screens seat inner wall, cross screens seat bottom inner wall is provided with the gag lever post.

Preferably: the outer wall of the cambered surface of the cockpit is provided with an air inlet net, and the outer wall of the cross-shaped clamping seat is provided with four air deflectors.

Preferably: the vibration reduction assembly comprises four guard plates and four sleeves; four the backplate all sets up in apron top outer wall, four the sleeve sets up respectively in four backplate one side inner walls.

Preferred for the present invention are: the inner wall swing joint of sleeve circumference has the telescopic link, telescopic link one side outer wall and sleeve one side inner wall joint have same spring.

As a preferable aspect of the present invention: four the outer wall of telescopic link one side is provided with same fixed plate, fixed plate top outer wall sets up in gasbag main part bottom outer wall.

As a preferable aspect of the present invention: the cockpit cambered surface inner wall is provided with the backup pad, backup pad top outer wall is provided with limiting plate and diplopore post, cockpit one side outer wall swing joint has hollow post, hollow post inner wall has the counter weight post through threaded connection, hollow post circumference outer wall is provided with the arc and dials the board more than two.

Further: the utility model discloses a hollow post, including hollow post, eccentric disc, inserted bar, adjusting bracket, push rod circumference outer wall swing joint in limiting plate inner wall, hollow post one side outer wall has the eccentric disc through the screw fixation, eccentric disc one side outer wall has the inserted bar through pivot swing joint, inserted bar one end swing joint has the adjusting bracket, adjusting bracket one side outer wall is provided with the push rod, and push rod circumference outer wall swing joint in limiting plate inner wall.

As a further scheme of the invention: double-bore post inner wall swing joint has second pass type seat, second pass type seat top outer wall is provided with first pass type seat, first pass type seat top outer wall is provided with the screens dish, gag lever post bottom outer wall is provided with the chuck, and chuck outer wall joint in screens dish inner wall.

As a still further scheme of the invention: the outer wall of the top of the cover plate is provided with a slide, the outer wall of the bottom of the fixing plate is provided with two hollow cylinders II, two universal balls are movably connected to the inner walls of the two hollow cylinders II, and the spherical outer walls of the universal balls are connected to the inner wall of the slide in a rolling mode.

A method for adjusting a center of gravity balance device of an airship comprises the following steps:

s1: when the airship is in a standby state, the clamping disc is used for limiting and clamping the chuck, so that the cross-shaped clamping seat is in a horizontal static state;

s2: the airship ascends by utilizing the airbag main body and the driving system, and after the cockpit ascends to a certain height, the hollow column rotates under the action of wind power, so that the push rod is separated from the through hole in the second hole-shaped seat, and the clamping disc is separated from the surface of the chuck;

s3: when wind power acts on the surface of the cockpit, and the cockpit tends to incline towards a certain direction, the two balance balls positioned in the cross-shaped clamping seat in the same straight line direction slide along the inner wall of the cross-shaped clamping seat in the same direction, so that the center of gravity of the whole cross-shaped clamping seat is changed, and the center of gravity of the whole cockpit is balanced;

s4: the air passes through the air inlet net and acts on the surface of the air guide plate, so that the adjusting ball rotates in the horizontal direction along the air inlet net, and the gravity center of the balancing ball is balanced according to the wind direction;

s5: and the vibration generated in the lifting process of the cab is relieved by utilizing the spring.

The invention has the beneficial effects that:

1. when the too big impact of producing of wind speed to cockpit surface, make the cockpit can produce the trend to a certain position slope, when this moment need balancing airship's focus, through the absorption of disconnection electromagnetism suction disc to the balancing ball, because inertial effect, thereby make cross screens seat swing towards the opposite direction with the direction that wind blows, at the wobbling in-process of cross screens seat, make two balancing balls that are located collinear to roll along cross screens seat inner wall, one of them balancing ball moves the gag lever post surface gradually at rolling in-process, another balancing ball moves electromagnetism suction disc surface, because balancing ball itself has weight, thereby can utilize two balancing balls that are located collinear to balance airship's focus.

2. Can make wind-force can enter into cockpit inside through being provided with the air inlet net to make wind-force can make the cross screens seat carry out the rotation of horizontal direction after acting on the air deflector surface, thereby make the ball of adjusting to carry out the rotation of horizontal direction along the air inlet net, thereby can adjust the rotation angle of cross screens seat at the horizontal direction, thereby can make the balancing ball in the cross screens seat can carry out centrobaric regulation according to the wind direction better, thereby can improve the effect that the focus was adjusted better.

3. Through being provided with the spring can make can reduce the vibration of horizontal direction when wind-force acts on the cockpit surface to can guarantee wherein two springs are tensile throughout, two other springs shrink, thereby can make the cockpit can be for being reciprocating motion in the production of horizontal direction between the fixed plate, thereby can effectively reduce the vibration that the cockpit received.

4. When the airship rises gradually in the use process, the wind speed increases gradually, so that the wind power produces and stirs the more than two arc-shaped stirring plate surfaces, thereby making the hollow column rotate, thereby making the eccentric disc can utilize the adjusting function of the inserted bar in the rotating process, making the push rod can carry out horizontal reciprocating motion along the limiting plate, the push rod breaks away from in the through-hole that sets up gradually in the second pass seat in the horizontal sideslip process, thereby making first pass seat and second pass seat wholly fall to the diplopore bottom of the column under the effect of gravity, thereby can realize that the screens dish breaks away from chuck surface automatically, thereby can make when the wind speed reaches certain amount, make the cross screens seat can realize automatically carrying out centrobaric balance to the cockpit.

5. Can make the fixed plate carry out lateral shifting's in-process at the horizontal direction and roll along the slide inner wall through being provided with universal ball to can improve the stability of fixed plate when the horizontal slip, thereby can realize more stable damping.

Drawings

Fig. 1 is a schematic view of the overall installation structure of a gravity center balancing device of an airship according to the present invention;

FIG. 2 is a schematic view of the overall structure of a cockpit of the gravity center balancing device of an airship according to the present invention;

FIG. 3 is a schematic side view of a cockpit of a gravity center balancing apparatus for an airship according to the present invention;

FIG. 4 is an exploded view of a shock absorber assembly of the center of gravity balancing apparatus of an airship according to the present invention;

fig. 5 is a schematic diagram of the overall explosion structure of the gravity center balancing assembly of the gravity center balancing device of the airship according to the invention;

fig. 6 is a schematic diagram of a partial explosion structure of a gravity center balancing assembly of the gravity center balancing device of the airship according to the present invention;

fig. 7 is an exploded view of a balancing ball assembly of a gravity center balancing device of an airship according to the present invention.

In the figure: 1-an airbag main body, 2-a driving system, 3-a cockpit, 4-an eccentric disc, 5-a first hollow cylinder, 6-an air inlet net, 7-a supporting plate, 8-a hollow column, 9-an arc-shaped stirring plate, 10-a counterweight column, 11-a cover plate, 12-a fixed plate, 13-a sleeve, 14-a second hollow cylinder, 15-a universal ball, 16-a telescopic rod, 17-a guard plate, 18-a spring, 19-a slideway, 20-a limiting plate, 21-a double-hole column, 22-an air deflector, 23-a cross clamping seat, 24-a rocker, 25-an adjusting frame, 26-a clamping disc, 27-a first hole type seat, 28-a second hole type seat, 29-a push rod, 30-an adjusting ball, 31-an electromagnetic suction plate, 32-a limiting rod, 33-chuck, 34-balance ball and 35-connecting column.

Detailed Description

The technical solution of the present patent will be described in further detail with reference to the following embodiments.

Reference will now be made in detail to embodiments of the present patent, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary only for the purpose of explaining the present patent and are not to be construed as limiting the present patent.

In the description of this patent, it is to be understood that the terms "center," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for the convenience of describing the patent and for the simplicity of description, and are not to be construed as limiting the device, structure, or element to which reference is made to have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner.

In the description of this patent, it is noted that unless otherwise specifically stated or limited, the terms "mounted," "connected," and "disposed" are to be construed broadly and can include, for example, fixedly connected, disposed, detachably connected, disposed, or integrally connected and disposed. The specific meaning of the above terms in this patent may be understood by those of ordinary skill in the art as appropriate.

Example 1:

a gravity center balancing device of an airship, as shown in figures 1-7, comprises an airbag main body 1 and a cockpit 3, the airbag main body 1 is connected with the cockpit 3 through a vibration damping component, the tail part of the airbag main body 1 is provided with a driving system 2, a cover plate 11 is fixed on the inner wall of the cambered surface of the cockpit 3 through screws, a hollow cylinder I5 is fixed on the outer wall of the bottom of the cover plate 11 through screws, the inner wall of the hollow cylinder I5 is rotatably connected with an adjusting ball 30, the outer wall of the spherical surface of the adjusting ball 30 is connected with a connecting column 35 through threads, the outer wall of the bottom of the connecting column 35 is fixed with a cross clamping seat 23 through a bolt, the inner walls of the periphery of the cross clamping seat 23 are all fixed with an electromagnetic suction plate 31 through screws, a balance ball 34 is adsorbed on the surface of the electromagnetic suction plate 31, the spherical outer wall of the balance ball 34 is connected with the inner wall of the cross-shaped clamping seat 23 in a sliding manner, and the inner wall of the bottom of the cross-shaped clamping seat 23 is fixed with a limiting rod 32 through a screw; the driving system 2 can be used for driving the air bag main body 1 and adjusting the direction, the shock to the cockpit 3 caused by wind power in high altitude can be effectively reduced by the vibration reduction assembly, so that the safety of the cockpit 3 in use can be improved, the wind speed is gradually increased along with the rise of the altitude along with the continuous rise of the height of the air bag main body 1, the air bag main body 1 and the cockpit 3 are impacted integrally, the cockpit 3 can shake, the center of gravity is deviated, the outer diameter of the connecting column 35 is smaller than the inner diameter of the air inlet net 6, the connecting column 35 can swing at any angle along the air inlet net 6 under the rolling action of the adjusting ball 30, the cross clamping seat 23 can tilt and shake in the horizontal direction according to the swing of the connecting column 35, and the balancing ball 34 can roll along the inner wall of the cross clamping seat 23 in the tilting process, the electromagnetic suction plate 31 can adsorb the balance ball 34 when the airship stops, so that the airship can be prevented from moving in a standby state; when the surface of the cockpit 3 is impacted by overlarge wind speed, the cockpit 3 tends to incline to a certain direction, and at the moment, the gravity center of the airship needs to be balanced, the adsorption of the electromagnetic suction plate 31 to the balance balls 34 is cut off, so that the cross-shaped clamping seat 23 swings towards the direction opposite to the wind blowing direction due to the inertia effect, in the swinging process of the cross-shaped clamping seat 23, two balance balls 34 positioned on the same straight line can roll along the inner wall of the cross-shaped clamping seat 23, one balance ball 34 gradually moves to the surface of the limiting rod 32 in the rolling process, the other balance ball 34 moves to the surface of the electromagnetic suction plate 31, and because the balance balls 34 have the weight, the gravity center of the airship can be balanced by the two balance balls 34 positioned on the same straight line, and the four balance balls 34 can be prevented from being contacted with each other by the limiting rod 32, thereby limiting the position of the balance ball 34.

In order to better balance the centre of gravity of the cockpit 3; as shown in fig. 5, an air inlet net 6 is arranged on the outer wall of the cambered surface of the cockpit 3, four air deflectors 22 are fixed on the outer wall of the cross-shaped clamping seat 23 through screws, and the four air deflectors 22 are distributed at equal intervals of 90 degrees; because the wind direction has uncertainty and arbitrariness, consequently can make wind-force can enter into cockpit 3 inside through being provided with air inlet net 6, thereby make wind-force can make cross screens seat 23 carry out the rotation of horizontal direction after acting on aviation baffle 22 surface, thereby make adjust ball 30 can carry out the rotation of horizontal direction along air inlet net 6, thereby can adjust the rotation angle of cross screens seat 23 in the horizontal direction, thereby can make balance ball 34 in the cross screens seat 23 can carry out the regulation of focus according to the wind direction better, thereby can improve the effect that the focus was adjusted better.

In order to reduce the vibration of the cockpit 3 during the lifting process; as shown in fig. 4, the damping assembly includes four guard plates 17 and four sleeves 13; the four guard plates 17 are all fixed on the outer wall of the top of the cover plate 11 through bolts, the four sleeves 13 are respectively fixed on the inner wall of one side of each of the four guard plates 17 through bolts, the inner wall of the circumference of each sleeve 13 is connected with a telescopic rod 16 in a sliding mode, the outer wall of one side of each telescopic rod 16 and the inner wall of one side of each sleeve 13 are connected with the same spring 18 in a clamping mode, the outer wall of one side of each telescopic rod 16 is fixed with the same fixing plate 12 through bolts, and the outer wall of the top of each fixing plate 12 is fixed on the outer wall of the bottom of the airbag main body 1 through bolts; in the advancing process of the airship, frictional resistance is generated between wind power and the cockpit 3, the horizontal vibration can be reduced when the wind power acts on the surface of the cockpit 3 by arranging the springs 18, so that the stretching of the two springs 18 can be ensured all the time, the other two springs 18 are contracted, the cockpit 3 can reciprocate in the horizontal direction relative to the fixed plate 12, and the vibration received by the cockpit 3 can be effectively reduced.

When the airship is used, the airbag main body 1 can drive the cockpit 3 to move up and down by adjusting the gas filled in the airbag main body 1, the airbag main body 1 can be driven and adjusted in direction by the driving system 2, when the airship is at a lower altitude, the airship can move stably because of relatively low wind speed, and as the airship gradually rises, the wind speed gradually increases to generate a shaking trend to the airbag main body 1 and the cockpit 3 integrally, so that the center of gravity of the cockpit 3 is unbalanced, the four balance balls 34 can freely roll along the inner wall of the cross-shaped clamping seat 23 by disconnecting the adsorption of the electromagnetic suction plate 31 to the balance balls 34, and when the cockpit 3 has a trend of inclining to one side, the connecting column 35 moves towards the direction opposite to the inclination direction of the cockpit 3 under the action of inertia and gravity, thereby make two balance balls 34 that are located collinear to carry out the syntropy along cross screens seat 23, thereby can make the holistic focus of cross screens seat 23 change, thereby can balance the focus of cockpit 3, simultaneously can guarantee through being provided with air inlet net 6 that wind-force can enter into cockpit 3 inside, thereby make wind-force can stir aviation baffle 22, thereby make cross screens seat 23 can rotate at the horizontal direction, thereby can make balance ball 34 can be better according to the change of wind direction, can adjust the focus of cockpit 3.

Example 2:

a gravity center balancing device for an airship, as shown in figures 5-7, for ensuring the stability of a cross-shaped clamping seat 23 when the airship is in a standby state; this example is supplemented by example 1 with the following: the cambered surface inner wall of the cockpit 3 is fixed with a supporting plate 7 through a bolt, the outer wall at the top of the supporting plate 7 is fixed with a limiting plate 20 and a double-hole column 21 through a bolt, the outer wall at one side of the cockpit 3 is connected with a hollow column 8 in a rotating way, the inner wall of the hollow column 8 is connected with a counterweight column 10 through a thread, the outer wall at the circumference of the hollow column 8 is fixed with more than two arc-shaped stirring plates 9 through a bolt, the outer wall at one side of the hollow column 8 is fixed with an eccentric disc 4 through a bolt, the outer wall at one side of the eccentric disc 4 is connected with an inserted link 24 through a rotating shaft in a rotating way, one end of the inserted link 24 is connected with an adjusting frame 25 in a rotating way, the outer wall at one side of the adjusting frame 25 is fixed with a push rod 29 through a bolt, the outer wall at the circumference of the push rod 29 is connected with the inner wall of the limiting plate 20 in a sliding way, the inner wall of the double-hole column 21 is connected with a second hole-shaped seat 28, the outer wall at the top of the second hole-shaped seat 28 is fixed with a first hole-shaped seat 27 through a bolt, a clamping disc 26 is fixed on the outer wall of the top of the first hole-shaped seat 27 through screws, a chuck 33 is fixed on the outer wall of the bottom of the limiting rod 32 through screws, and the outer wall of the chuck 33 is clamped on the inner wall of the clamping disc 26; when the airship is in a standby state, the push rod 29 is inserted into the through hole arranged in the second hole-shaped seat 28, so that the position of the second hole-shaped seat 28 relative to the double-hole column 21 can be limited, the chuck 33 can be limited and clamped at the top of the clamping disc 26, the connecting column 35 can be prevented from rotating relative to the air inlet net 6, when the airship is gradually lifted in the using process, the wind speed is gradually increased, the wind power can stir the surfaces of more than two arc-shaped stirring plates 9, so that the hollow column 8 can rotate, so that the eccentric disc 4 can utilize the adjusting function of the inserting rod 24 in the rotating process, the push rod 29 can horizontally reciprocate along the limiting plate 20, the push rod 29 gradually breaks away from the through hole arranged in the second hole-shaped seat 28 in the horizontal traversing process, so that the first hole-shaped seat 27 and the second hole-shaped seat 28 integrally fall to the bottom of the double-hole column 21 under the action of gravity, therefore, the clamping disc 26 can be automatically separated from the surface of the clamping disc 33, when the wind speed reaches a certain amount, the cross-shaped clamping seat 23 can automatically realize the gravity center balance of the cockpit 3, and the weight of the counterweight column 10 is adjusted, so that the gravity center balance of the cross-shaped clamping seat 23 can be adjusted in different wind speed intervals, and the use flexibility is improved; meanwhile, when different wind directions can be guaranteed to act on the surfaces of more than two arc-shaped poking plates 9 by arranging the eccentric disc 4 and the inserted rod 24, the push rod 29 can normally perform reciprocating motion, and simultaneously, the push rod 29 can horizontally slide along a through hole arranged in the first hole-shaped seat 27 in the reciprocating motion process along with the falling of the first hole-shaped seat 27 and the second hole-shaped seat 28, so that the situation that the hollow column 8 and the arc-shaped poking plates 9 are radially damaged under the action of wind power due to the fact that the push rod 29 is clamped can be avoided.

In order to improve the stability of the fixing plate 12 when moving horizontally; as shown in fig. 4, a slide way 19 is fixed on the outer wall of the top of the cover plate 11 through a bolt, two hollow cylinders 14 are fixed on the outer wall of the bottom of the fixing plate 12 through screws, universal balls 15 are rotatably connected to the inner walls of the two hollow cylinders 14, and the spherical outer walls of the two universal balls 15 are respectively connected to the inner walls of the slide way 19 in a rolling manner; can make fixed plate 12 carry out lateral shifting's in-process can roll along 19 inner walls of slide through being provided with universal ball 15 to can improve the stability of fixed plate 12 when the level slides, thereby can realize more stable damping.

In the embodiment, when the airship is in a standby state, the push rod 29 is manually slid into the through hole in the second hole-shaped seat 28, so that the clamping disc 26 clamps the limiting rod 32, and the cross-shaped clamping seat 23 is in a horizontal state, and meanwhile, due to the counterweight effect of the counterweight column 10, the overall stability of the push rod 29 when being clamped into the second hole-shaped seat 28 can be ensured, when the airship gradually moves upwards in the using process, the wind speed gradually increases, the hollow column 8 rotates under the wind guiding effect of the arc-shaped poking plate 9, so that the push rod 29 gradually separates from the second hole-shaped seat 28 by performing reciprocating sliding along the horizontal direction under the adjusting effect of the inserting rod 24, so that the clamping disc 26 falls along the double-hole column 21 under the gravity effect, and the clamping disc 26 separates from the surface of the chuck 33, at this time, because the wind speed is high, the cross-shaped clamping seat 23 can simultaneously realize the balance of the center of gravity, thereby ensuring synchronicity.

Example 3:

s1: when the airship is in a standby state, the chuck 33 is limited and clamped by using the clamping disk 26, so that the cross-shaped clamping seat 23 is in a horizontal static state;

s2: the airship is lifted by the airbag main body 1 and the driving system 2, and after the cockpit 3 is lifted to a certain height, the hollow column 8 is rotated by the action of wind power, so that the push rod 29 is separated from the through hole in the second hole-shaped seat 28, and the clamping disc 26 is separated from the surface of the clamping disc 33;

s3: when wind force acts on the surface of the cockpit 3, so that the cockpit 3 has a tendency of inclining towards a certain direction, the two balance balls 34 positioned in the cross-shaped clamping seat 23 and in the same straight line direction slide along the inner wall of the cross-shaped clamping seat 23 in the same direction, so that the gravity center of the whole cross-shaped clamping seat 23 is changed, and the gravity center of the whole cockpit 3 is balanced;

s4: the wind passes through the air inlet net 6 and acts on the surface of the air deflector 22, so that the adjusting ball 30 rotates along the air inlet net 6 in the horizontal direction, and the balance ball 34 balances the gravity center according to the wind direction;

s5: the springs 18 are used to dampen vibrations of the cabin 3 during lifting.

The above description is for the purpose of illustrating the preferred embodiments of the present invention and is not intended to be exhaustive or to limit the invention to the precise embodiments disclosed, and all modifications, equivalents, and improvements that may occur to those skilled in the art and that fall within the spirit and scope of the invention are intended to be embraced therein.

Claims

1. The utility model provides a focus balancing unit of dirigible, includes gasbag main part (1) and cockpit (3), characterized by, connect through damping subassembly between gasbag main part (1) and cockpit (3), gasbag main part (1) afterbody is provided with actuating system (2), cockpit (3) cambered surface inner wall is provided with apron (11), apron (11) bottom outer wall is provided with hollow section of thick bamboo one (5), hollow section of thick bamboo one (5) inner wall swing joint has adjusting ball (30), adjusting ball (30) sphere outer wall has spliced pole (35) through threaded connection, spliced pole (35) bottom outer wall is provided with cross screens seat (23), cross screens seat (23) inner wall all around is fixed with electromagnetism suction plate (31) through the screw, electromagnetism suction plate (31) surface adsorbs has balancing ball (34), and balancing ball (34) sphere outer wall swing joint in cross screens seat (23) inner wall, and a limiting rod (32) is arranged on the inner wall of the bottom of the cross clamping seat (23).

2. The gravity center balancing device of the airship as claimed in claim 1, wherein the outer wall of the cambered surface of the cockpit (3) is provided with an air inlet net (6), and the outer wall of the cross-shaped clamping seat (23) is provided with four air deflectors (22).

3. The apparatus as claimed in claim 2, wherein said damping means comprises four shields (17) and four sleeves (13); four backplate (17) all set up in apron (11) top outer wall, four sleeve (13) set up respectively in four backplate (17) one side inner walls.

4. The gravity center balancing device of the airship as claimed in claim 3, wherein the inner wall of the circumference of the sleeve (13) is movably connected with a telescopic rod (16), and the same spring (18) is clamped on the outer wall of one side of the telescopic rod (16) and the inner wall of one side of the sleeve (13).

5. The gravity center balancing device of the airship according to claim 4, wherein the four telescopic rods (16) are provided with the same fixing plate (12) on one side of the outer wall, and the top outer wall of the fixing plate (12) is arranged on the bottom outer wall of the airbag main body (1).

6. The gravity center balancing device of the airship according to claim 1, wherein the supporting plate (7) is arranged on the inner wall of the cambered surface of the cockpit (3), the limiting plate (20) and the double-hole column (21) are arranged on the outer wall of the top of the supporting plate (7), the hollow column (8) is movably connected to the outer wall of one side of the cockpit (3), the inner wall of the hollow column (8) is connected with the counterweight column (10) through threads, and the outer wall of the circumference of the hollow column (8) is provided with more than two arc-shaped shifting plates (9).

7. The gravity center balancing device of the airship according to claim 6, wherein the eccentric disc (4) is fixed on the outer wall of one side of the hollow column (8) through a screw, the insert rod (24) is movably connected on the outer wall of one side of the eccentric disc (4) through a rotating shaft, one end of the insert rod (24) is movably connected with the adjusting frame (25), the push rod (29) is arranged on the outer wall of one side of the adjusting frame (25), and the circumferential outer wall of the push rod (29) is movably connected to the inner wall of the limiting plate (20).

8. The gravity center balancing device of the airship as claimed in claim 7, wherein the inner wall of the double-hole column (21) is movably connected with a second hole-shaped seat (28), the outer wall of the top of the second hole-shaped seat (28) is provided with a first hole-shaped seat (27), the outer wall of the top of the first hole-shaped seat (27) is provided with a clamping disc (26), the outer wall of the bottom of the limiting rod (32) is provided with a clamping disc (33), and the outer wall of the clamping disc (33) is clamped on the inner wall of the clamping disc (26).

9. The gravity center balancing device of the airship according to claim 5, wherein the top outer wall of the cover plate (11) is provided with a slideway (19), the bottom outer wall of the fixing plate (12) is provided with two hollow cylinders II (14), the inner walls of the two hollow cylinders II (14) are movably connected with universal balls (15), and the spherical outer walls of the two universal balls (15) are respectively connected with the inner walls of the slideway (19) in a rolling manner.

10. A method of adjusting a center of gravity balance apparatus of an airship according to any one of claims 1 to 9, comprising the steps of:

s1: when the airship is in a standby state, the clamping disc (26) is used for limiting and clamping the clamping disc (33), so that the cross-shaped clamping seat (23) is in a horizontal static state;

s2: the airship is lifted by the airbag main body (1) and the driving system (2), and after the cockpit (3) is lifted to a certain height, the hollow column (8) is rotated by the action of wind power, so that the push rod (29) is separated from the through hole in the second hole-shaped seat (28), and the clamping disc (26) is separated from the surface of the clamping disc (33);

s3: when wind power acts on the surface of the cockpit (3) to cause the cockpit (3) to incline towards a certain direction, two balance balls (34) which are positioned in the cross-shaped clamping seat (23) and are in the same linear direction slide along the inner wall of the cross-shaped clamping seat (23) in the same direction, so that the center of gravity of the whole cross-shaped clamping seat (23) is changed, and the center of gravity of the whole cockpit (3) is balanced;

s4: wind passes through the air inlet net (6) and acts on the surface of the air deflector (22), so that the adjusting ball (30) rotates along the air inlet net (6) in the horizontal direction, and the gravity center of the balancing ball (34) is balanced according to the wind direction;

s5: the vibration generated by the cab (3) in the lifting process is relieved by the spring (18).