CN116928050B - Jolt middle energy extraction mechanism and aircraft - Google Patents
Jolt middle energy extraction mechanism and aircraft Download PDFInfo
- Publication number
- CN116928050B CN116928050B CN202310986762.2A CN202310986762A CN116928050B CN 116928050 B CN116928050 B CN 116928050B CN 202310986762 A CN202310986762 A CN 202310986762A CN 116928050 B CN116928050 B CN 116928050B
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- flexible bag
- flexible
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- 230000007246 mechanism Effects 0.000 title claims abstract description 37
- 238000000605 extraction Methods 0.000 title claims abstract description 25
- 239000007788 liquid Substances 0.000 claims abstract description 34
- 239000012530 fluid Substances 0.000 claims abstract description 27
- 230000005540 biological transmission Effects 0.000 claims description 44
- 238000005452 bending Methods 0.000 claims description 17
- 238000005265 energy consumption Methods 0.000 claims description 5
- 238000005192 partition Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 2
- 230000008569 process Effects 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 239000007789 gas Substances 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000011261 inert gas Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000004816 latex Substances 0.000 description 1
- 229920000126 latex Polymers 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000003534 oscillatory effect Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000000741 silica gel Substances 0.000 description 1
- 229910002027 silica gel Inorganic materials 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03G—SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR
- F03G7/00—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for
- F03G7/08—Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for recovering energy derived from swinging, rolling, pitching or like movements, e.g. from the vibrations of a machine
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
The invention relates to the technical field of aircrafts, in particular to a jolt energy extraction mechanism and an aircrafts, wherein the jolt energy extraction mechanism is suitable for being arranged at the bottom of the aircrafts and comprises a rigid chamber, a swinging plate and a flexible bag; when the rigid chamber swings, the liquid seal part flows along the inner wall of the rigid chamber, so that fluid on one side of the liquid seal part flows into the flexible bag arranged on one side of the swinging plate, and fluid on the other side of the liquid seal part flows out of the flexible bag arranged on the other side of the swinging plate, so that the flexible bag arranged on one side of the swinging plate is gradually expanded, and the flexible bag arranged on the other side of the swinging plate is gradually contracted; the flexible bags arranged on the two opposite sides of the swinging plate respectively push and pull the swinging plate to swing.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a jolt middle energy extraction mechanism and an aircraft.
Background
For aircraft, jolts can occur during travel, subject to an unstable airflow. Depending on the structural characteristics of the aircraft itself, the left-right swing amplitude tends to be large.
Therefore, how to effectively extract and utilize the bumping energy when the aircraft bumps is a technical problem to be solved by those skilled in the art.
Disclosure of Invention
The invention provides a jolt energy extraction mechanism and an aircraft, which are used for solving the problem that jolt energy cannot be effectively extracted and utilized when the aircraft jolts.
The invention provides a jolt energy extraction mechanism, which is suitable for being arranged at the bottom of an aircraft, and comprises:
a rigid chamber provided with a bending section; the top of the bending section is provided with more than two through holes, and a liquid sealing part is stored in the top of the bending section;
the swinging plate is arranged above the bending section in a swinging way, and the plane of the swinging plate is vertically arranged;
the flexible bag is more than two; the inside of the more than two flexible bags are correspondingly communicated with the more than two through holes one by one; the outer wall of at least one flexible bag is fixedly connected with one side surface of the swinging plate, and the outer wall of at least one flexible bag is fixedly connected with the other side surface of the swinging plate; the interior of each flexible bladder and the interior of the rigid chamber store fluid;
when the rigid chamber swings, the liquid seal part flows along the inner wall of the rigid chamber, so that fluid on one side of the liquid seal part flows into the flexible bag arranged on one side of the swinging plate, and fluid on the other side of the liquid seal part flows out of the flexible bag arranged on the other side of the swinging plate, so that the flexible bag arranged on one side of the swinging plate is gradually expanded, and the flexible bag arranged on the other side of the swinging plate is gradually contracted; the flexible bags arranged on the two opposite sides of the swinging plate respectively push and pull the swinging plate to swing.
In some embodiments, the fluid on both sides of the liquid seal is a predetermined volume of gas or liquid.
In some embodiments, a partition is provided within the rigid chamber to divide the interior of the rigid chamber into two upper flow channels and one lower flow channel;
the liquid seal part is stored in the lower runner;
one of the upper flow passages is communicated with the inside of the flexible bag arranged on one side of the swinging plate through the through hole, and the other upper flow passage is communicated with the inside of the flexible bag arranged on the other side of the swinging plate through the through hole;
the fluid is stored in the lower flow channel, the upper flow channel and the flexible bag.
In some embodiments, the cross section of each flexible bag is in a structure of two straight lines and one arc-shaped side, wherein one straight line side is fixedly connected with the top of the bending section, and the other straight line side is fixedly connected with the swinging plate;
the bottom of the swinging plate is rotationally connected with the top of the bending section.
In some embodiments, the arcuate side of each flexible bladder is provided with a plurality of folds.
An aircraft based on the same conception, wherein the bottom of the aircraft is provided with a jolt middle energy extraction mechanism and a boosting mechanism provided by any of the specific embodiments;
the bottom of the swinging plate is provided with a rotating shaft;
the boosting mechanism is arranged at one end of the rotating shaft and is in transmission connection with the rotating shaft.
In some embodiments, the boosting mechanism comprises:
the first gear is sleeved at one end of the rotating shaft;
the two second gears are arranged below the first gear, and the side walls of the two second gears are respectively connected with the side walls of the first gear in a meshed manner;
the two transmission blocks are connected with the two second gears in a one-to-one correspondence manner;
the first transmission arms are two; one end of one first transmission arm is connected with one transmission block, and the other end of the first transmission arm is connected with one end of one second transmission arm; one end of the other first transmission arm is connected with the other transmission block, and the other end of the other first transmission arm is connected with one end of the other second transmission arm;
the two swing webs are arranged, and the planes of the two swing webs are respectively parallel to the axis of the first gear; one end of one swing web is fixedly connected with the side wall of one second transmission arm, and one end of the other swing web is fixedly connected with the side wall of the other second transmission arm;
when the first gears rotate clockwise along with the rotating shaft, the two second gears are driven to rotate anticlockwise, so that one of the swing webs is driven to swing upwards, and one of the swing webs is driven to swing downwards; when the first gears rotate anticlockwise along with the rotating shaft, the two second gears are driven to rotate clockwise, and then one of the swing webs is driven to swing upwards and one of the swing webs is driven to swing downwards.
In some embodiments, the first gear has a larger diameter than the second gear.
In some of these embodiments, a bulkhead is provided in the middle of the aircraft and above the flexible bladder and the swing plate.
The invention has the beneficial effects that: according to the jolt energy extraction mechanism, the rigid chamber is arranged, when the rigid chamber swings due to water surface fluctuation, the liquid seal part flows along the inner wall of the rigid chamber, so that fluid on one side of the liquid seal part flows into the flexible bag arranged on one side of the swing plate, and fluid on the other side of the liquid seal part flows out of the flexible bag arranged on the other side of the swing plate, and further the flexible bag arranged on one side of the swing plate is gradually expanded, and the flexible bag arranged on the other side of the swing plate is gradually contracted. The flexible bags arranged on the two opposite sides of the swinging plate respectively push and pull the swinging plate to swing, so that the bottom of the swinging plate rotates. In this way, when the rigid chamber swings left and right, swing energy can be effectively extracted and utilized, and the swing energy can be converted into mechanical energy which can be output, and the mechanical energy can be used for generating electricity or providing thrust assistance for the forward movement of the rigid chamber (aircraft).
Drawings
FIG. 1 is a side view of some embodiments of a jounce energy extraction mechanism according to the present invention;
FIG. 2 is a cross-sectional view of the jounce energy extraction mechanism shown in FIG. 1 taken along line B-B;
FIG. 3 is a cross-sectional view of the jounce energy extraction mechanism shown in FIG. 1 taken along line A-A;
FIG. 4 is a schematic illustration of the combined configuration of the pitch energy extraction mechanism and the boost mechanism of the present invention in an aircraft.
110, rigid chamber; 111. partition; 120. a liquid seal part; 130. a swinging plate; 131. a rotating shaft; 140. a flexible bladder; 150. a fluid; 210. a first gear; 220. a second gear; 230. a transmission block; 240. a first transmission arm; 250. a second transmission arm; 260. and (5) swinging the web.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
Examples of the embodiments are illustrated in the accompanying drawings, wherein like or similar symbols indicate like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
In the description of the present invention, it should be understood that the terms "top," "bottom," "inner," "outer," "axis," "circumferential," "upper," "lower," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate describing the present invention or simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," "hinged," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
As described in the background, for an aircraft, jolting occurs under the influence of an unstable airflow during traveling. Depending on the structural characteristics of the aircraft itself, the left-right swing amplitude tends to be large. Therefore, how to effectively extract and utilize the bumping energy when the aircraft bumps is a technical problem to be solved by those skilled in the art.
To ameliorate the above problems, referring to fig. 1, 2 and 3, in one aspect of the present application, a jounce energy extraction mechanism is provided, adapted to be disposed at the bottom of an aircraft, comprising a rigid chamber 110, a wobble plate 130 and a flexible bladder 140. Wherein, the middle part of the rigid chamber 110 is provided with a bending section, the top of the bending section is provided with more than two through holes, and the liquid seal part 120 is stored inside. The swinging plate 130 is swingably arranged above the bending section, and is arranged vertically on a plane. The number of flexible bags 140 is two or more. The insides of the two or more flexible bags 140 are in one-to-one correspondence with the two or more through holes. At least one flexible bladder 140 is disposed on one side of the swing plate 130, and the outer wall is fixedly connected to one side of the swing plate 130. At least one flexible bag 140 is disposed on the other side of the swing plate 130, and the outer wall is fixedly connected with the other side of the swing plate 130. The interior of each flexible bladder 140 and the interior of rigid chamber 110 store fluid 150. The liquid seal 120 is used to isolate 111 the fluid 150 in the flexible bladder 140 located at the opposite sides of the swing plate 130, and the fluid 150 in the flexible bladder 140 at the opposite sides is flowed in and out by the movement of the liquid seal 120. Specifically, when the rigid chamber 110 swings, the liquid seal 120 flows along the inner wall of the rigid chamber 110, so that the fluid 150 on one side of the liquid seal 120 flows into the flexible bladder 140 provided on one side of the swing plate 130, and the fluid 150 on the other side of the liquid seal 120 flows out of the flexible bladder 140 provided on the other side of the swing plate 130, thereby gradually expanding the flexible bladder 140 provided on one side of the swing plate 130 and gradually contracting the flexible bladder 140 provided on the other side of the swing plate 130. The flexible bags 140 provided at opposite sides of the swing plate 130 push and pull the swing plate 130 to swing, respectively, so that the bottom of the swing plate 130 rotates. In this way, when the rigid chamber 110 swings left and right, swing energy can be effectively extracted and utilized, and converted into mechanical energy which can be output, and the mechanical energy can be used for generating electricity or providing boosting force for the forward movement of the rigid chamber 110 (aircraft).
It should be noted that the pitch energy extraction mechanism may be integrally provided in the lower part of the cabin of the aircraft, with the rigid chamber 110 being mounted on the belly of the cabin. Of course, the rigid chamber 110 can also be built into the cabin by means of the belly of the cabin of the aircraft. In addition, when the present application is applied to a ship or a vehicle, the entire pitch energy extraction mechanism may be provided at a lower portion in the cabin of the ship or a lower portion in the cabin of the vehicle.
Preferably, in the illustrated example, the rigid chamber 110 is made of metal or rigid plastic. The swing plate 130 is made of metal or hard plastic. The flexible bag 140 is made of latex, silica gel or the like, and can be deformed. The liquid seal 120 is water or a liquid medium having a density greater than water.
In some of these embodiments, the rigid chambers 110 are 4, 6, 8, or more, evenly distributed along the length of the aircraft. Accordingly, flexible bladder 140 is 4, 6, 8, or more, evenly distributed along the length of the body of the aircraft. The number of swing plates 130 is 1.
In some of these embodiments, the fluid 150 on both sides of the liquid seal 120 is a predetermined volume of gas. Such as nitrogen, is a poorly water-soluble inert gas. The lower viscosity of the fluid with respect to the inner wall of the rigid chamber 110 during flow, relative to the use of a liquid as the fluid 150, is more conducive to movement of the fluid 150 and improves the oscillatory response. In other embodiments, the fluid 150 on both sides of the seal 120 is a predetermined volume of liquid, such as oil or a liquid medium having a density less than that of water, and is poorly soluble in water. The amount is less susceptible to damage when squeezed relative to the use of gas as the fluid 150, meeting long-term use requirements.
Specifically, in the illustrated example, a partition 111 is provided in the rigid chamber 110 to divide the interior of the rigid chamber 110 into two upper flow channels and one lower flow channel. The liquid seal 120 is stored in the lower flow channel. One of the upper flow passages communicates with the inside of the flexible bladder 140 provided at one side of the swing plate 130 through the through-hole, and the other upper flow passage communicates with the inside of the flexible bladder 140 provided at the other side of the swing plate 130 through the through-hole. Fluid 150 is stored in the lower flow channel, the upper flow channel, and flexible bladder 140. In this manner, flexible bladders 140 on both sides are conveniently positioned proximate opposite sides of swing plate 130. The whole layout is reasonable and compact, and the volume is smaller.
Specifically, in the illustrated example, the cross section of each flexible bag 140 has a structure of two straight sides and one arc side, wherein one straight side is fixedly connected with the top of the bending section, and the other straight side is fixedly connected with the swing plate 130. The bottom of the swing plate 130 is rotatably connected with the mounting plate at the top of the bending section through a rotating shaft 131. The flexible bag 140 is supported and clamped by the rigid chamber 110 and the swinging plate 130, so that the position of the flexible bag 140 is not easy to deviate, and the energy extraction stability is ensured. The overall layout is compact, and is favorable for integrally realizing miniaturization and lightweight design. A plurality of folds are provided on the arc-shaped side of each flexible bladder 140 to facilitate deformation and recovery of the flexible bladder 140.
Referring to fig. 1, 2, 3 and 4, in another aspect of the present application, an aircraft is provided with a pitch energy extraction mechanism and a boost mechanism provided by any of the embodiments described above at the bottom of the aircraft. The swing plate 130 has a rotation shaft 131 at the bottom thereof. The boosting mechanism is arranged at one end of the rotating shaft 131 and is in transmission connection with the rotating shaft 131.
The boosting mechanism is integrally arranged at the tail part of the aircraft. The energy extraction mechanism can effectively extract the swing energy, and the swing energy is converted into mechanical energy which can be output through the rotating shaft 131. The energy extraction mechanism is matched with the boosting mechanism, so that swing energy can be converted into boosting force of the aircraft, and the advancing energy consumption of the aircraft is reduced. The boosting force can greatly reduce the energy consumption required for starting or advancing particularly when the aircraft is just started or in the advancing process.
Specifically, in the illustrated example, the boost mechanism includes a first gear 210, a second gear 220, a transmission block 230, a first transmission arm 240, a second transmission arm 250, and a swing web 260. The first gear 210 is sleeved at one end of the rotating shaft 131. The two second gears 220 are disposed below the first gear 210, and the side walls are respectively engaged with and connected to the side walls of the first gear 210. The transmission energy loss can be effectively reduced by adopting a gear rotation mode. The two transmission blocks 230 are fixedly connected with the two second gears 220 in a one-to-one correspondence manner, and can swing respectively. The first transmission arms 240 are two. One end of one of the first transmission arms 240 is connected to one of the transmission blocks 230, and the other end is connected to one end of one of the second transmission arms 250. One end of the other first transmission arm 240 is connected to the other transmission block 230, and the other end is connected to one end of the other second transmission arm 250. The swinging webs 260 are two in number, and the planes of the swinging webs are respectively parallel to the axis of the first gear 210. One end of one of the swing webs 260 is fixedly connected with the side wall of one of the second transmission arms 250, and one end of the other swing web 260 is fixedly connected with the side wall of the other second transmission arm 250. When the first gear 210 rotates clockwise along with the rotating shaft 131, the two second gears 220 are driven to rotate counterclockwise, so as to drive one of the swing webs 260 to swing upwards and drive one of the swing webs 260 to swing downwards. When the first gear 210 rotates counterclockwise along with the rotating shaft 131, the two second gears 220 are driven to rotate clockwise, so as to drive one of the swing webs 260 to swing upwards, and drive one of the swing webs 260 to swing downwards. The two rocking webs 260, which are alternately rocked up and down, can provide a boost to reduce the energy consumption required for the forward and take off of the aircraft.
Preferably, in the exemplary embodiment, first gear 210 has a larger diameter than second gear 220. In this way, the oscillation frequency of the oscillation web 260 can be effectively increased, and the thrust assist force can be further increased.
Preferably, in the exemplary embodiment, each second gear 220 is rotatably mounted to the aft portion of the aircraft.
Preferably, in the illustrated example, a bulkhead is provided in the middle of the aircraft, and above flexible bladder 140 and swing plate 130. Above the top surface of the partition is a passenger compartment, which can be isolated from the jolt energy extraction mechanism.
In the description of the present specification, reference to the terms "one embodiment," "some embodiments," "examples," "particular examples," "one particular embodiment," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The present invention is not limited to the above preferred embodiments, and any person skilled in the art, within the scope of the present invention, may apply to the present invention, and equivalents and modifications thereof are intended to be included in the scope of the present invention.
Claims (7)
1. An aircraft is characterized in that a jolt middle energy extraction mechanism and a boosting mechanism are arranged at the bottom of the aircraft;
the jounce energy extraction mechanism includes:
a rigid chamber provided with a bending section; the top of the bending section is provided with more than two through holes, and a liquid sealing part is stored in the bending section;
the swinging plate can be arranged above the bending section in a swinging way, and the plane where the swinging plate is arranged is vertical; a rotating shaft is arranged at the bottom of the swinging plate;
the flexible bag is more than two; the inside of the two or more flexible bags are correspondingly communicated with the two or more through holes one by one; the outer wall of at least one flexible bag is fixedly connected with one side surface of the swinging plate, and the outer wall of at least one flexible bag is fixedly connected with the other side surface of the swinging plate; the interior of each flexible bladder and the interior of the rigid chamber store fluid;
when the rigid chamber swings, the liquid sealing part flows along the inner wall of the rigid chamber, so that the fluid on one side of the liquid sealing part flows into the flexible bag arranged on one side of the swinging plate, and the fluid on the other side of the liquid sealing part flows out of the flexible bag arranged on the other side of the swinging plate, and further the flexible bag arranged on one side of the swinging plate is gradually inflated, and the flexible bag arranged on the other side of the swinging plate is gradually contracted; the flexible bags arranged on the two opposite sides of the swinging plate respectively push and pull the swinging plate to swing;
the boosting mechanism is arranged at one end of the rotating shaft and is in transmission connection with the rotating shaft; the swinging energy can be effectively extracted by the jolt energy extraction mechanism, and the swinging energy is converted into mechanical energy which can be output through the rotating shaft; the jolt energy extraction mechanism is matched with the boosting mechanism, so that the swing energy can be converted into the boosting force of the aircraft, and the advancing energy consumption of the aircraft is reduced; when the aircraft is just started or in the running process, the boosting force can reduce the energy consumption required by starting or running;
the boosting mechanism comprises:
the first gear is sleeved at one end of the rotating shaft;
the two second gears are arranged below the first gear, and the side walls of the two second gears are respectively connected with the side walls of the first gear in a meshed manner;
the two transmission blocks are connected with the two second gears in a one-to-one correspondence manner;
the first transmission arms are two; one end of one first transmission arm is connected with one transmission block, and the other end of the first transmission arm is connected with one end of one second transmission arm; one end of the other first transmission arm is connected with the other transmission block, and the other end of the other first transmission arm is connected with one end of the other second transmission arm;
the two swing webs are arranged, and the planes of the two swing webs are respectively parallel to the axis of the first gear; one end of one of the swing webs is fixedly connected with the side wall of one of the second transmission arms, and one end of the other swing web is fixedly connected with the side wall of the other second transmission arm;
when the first gears rotate clockwise along with the rotating shaft, the two second gears are driven to rotate anticlockwise, one of the swing webs is driven to swing upwards, and one of the swing webs is driven to swing downwards; when the first gears rotate anticlockwise along with the rotating shaft, the two second gears are driven to rotate clockwise, one of the swing webs is driven to swing upwards, and one of the swing webs is driven to swing downwards.
2. The aircraft of claim 1, wherein the fluid on both sides of the liquid seal is a predetermined volume of gas or liquid.
3. The aircraft of claim 1, wherein a partition is provided within the rigid chamber to divide the interior of the rigid chamber into two upper flow channels and one lower flow channel;
the liquid seal part is stored in the lower flow channel;
one of the upper flow passages is communicated with the inside of the flexible bag arranged on one side of the swing plate through the through hole, and the other upper flow passage is communicated with the inside of the flexible bag arranged on the other side of the swing plate through the through hole;
the fluid is stored in the lower flow channel, the upper flow channel, and the flexible bladder.
4. An aircraft according to any one of claims 1 to 3, wherein the cross section of each flexible bladder is of a two-sided rectilinear, one-sided arcuate configuration, one rectilinear side being fixedly connected to the top of the bending section and the other rectilinear side being fixedly connected to the swinging plate;
the bottom of the swinging plate is rotationally connected with the top of the bending section.
5. The vehicle of claim 4, wherein the arcuate side of each flexible bladder is provided with a plurality of folds.
6. The aircraft of claim 1, wherein the first gear has a larger diameter than the second gear.
7. The aircraft of claim 1, wherein a middle portion within the aircraft is provided with a bulkhead, and wherein the bulkhead is located above the flexible bladder and the swing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310986762.2A CN116928050B (en) | 2023-08-07 | 2023-08-07 | Jolt middle energy extraction mechanism and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310986762.2A CN116928050B (en) | 2023-08-07 | 2023-08-07 | Jolt middle energy extraction mechanism and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116928050A CN116928050A (en) | 2023-10-24 |
| CN116928050B true CN116928050B (en) | 2024-01-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202310986762.2A Active CN116928050B (en) | 2023-08-07 | 2023-08-07 | Jolt middle energy extraction mechanism and aircraft |
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| CN (1) | CN116928050B (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2379619Y (en) * | 1997-10-25 | 2000-05-24 | 凌则钧 | Self power supply type engine for vehicle or ship |
| KR101912101B1 (en) * | 2017-09-07 | 2018-10-26 | 한국해양대학교 산학협력단 | Self-charging drone |
| CN209838608U (en) * | 2018-11-01 | 2019-12-24 | 倍能科技（广州）有限公司 | Arc tooth type energy recovery device |
| CN115929579A (en) * | 2023-01-04 | 2023-04-07 | 北京赛智新创科技有限公司 | New energy automobile anti-rolling power generation mechanism and power generation device with same |
| CN116238686A (en) * | 2021-12-08 | 2023-06-09 | 中国矿业大学 | Flapping wing flying robot driver and flapping wing flying robot |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12006919B2 (en) * | 2018-09-13 | 2024-06-11 | Preciflex Sa | Energy harvesting with fluids |
-
2023
- 2023-08-07 CN CN202310986762.2A patent/CN116928050B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2379619Y (en) * | 1997-10-25 | 2000-05-24 | 凌则钧 | Self power supply type engine for vehicle or ship |
| KR101912101B1 (en) * | 2017-09-07 | 2018-10-26 | 한국해양대학교 산학협력단 | Self-charging drone |
| CN209838608U (en) * | 2018-11-01 | 2019-12-24 | 倍能科技（广州）有限公司 | Arc tooth type energy recovery device |
| CN116238686A (en) * | 2021-12-08 | 2023-06-09 | 中国矿业大学 | Flapping wing flying robot driver and flapping wing flying robot |
| CN115929579A (en) * | 2023-01-04 | 2023-04-07 | 北京赛智新创科技有限公司 | New energy automobile anti-rolling power generation mechanism and power generation device with same |
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| CN116928050A (en) | 2023-10-24 |
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