CN114954952A - Hang fixed wing aircraft that hangs down of storehouse stability of receiving and releasing of hanging - Google Patents

Hang fixed wing aircraft that hangs down of storehouse stability of receiving and releasing of hanging Download PDF

Info

Publication number
CN114954952A
CN114954952A CN202210770681.4A CN202210770681A CN114954952A CN 114954952 A CN114954952 A CN 114954952A CN 202210770681 A CN202210770681 A CN 202210770681A CN 114954952 A CN114954952 A CN 114954952A
Authority
CN
China
Prior art keywords
hanging
cabin
stability
warehouse
wing aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202210770681.4A
Other languages
Chinese (zh)
Other versions
CN114954952B (en
Inventor
王勇
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Muyutian Aviation Technology Jiangsu Co ltd
Original Assignee
Shanghai Yutian Aviation Technology Co ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Yutian Aviation Technology Co ltd filed Critical Shanghai Yutian Aviation Technology Co ltd
Priority to CN202210770681.4A priority Critical patent/CN114954952B/en
Publication of CN114954952A publication Critical patent/CN114954952A/en
Application granted granted Critical
Publication of CN114954952B publication Critical patent/CN114954952B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • B64D9/003—Devices for retaining pallets or freight containers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • 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
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
    • B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
    • B66D1/02—Driving gear
    • B66D1/12—Driving gear incorporating electric motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
    • B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
    • B66D1/02—Driving gear
    • B66D1/14—Power transmissions between power sources and drums or barrels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
    • B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
    • B66D1/28—Other constructional details
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
    • B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
    • B66D1/28—Other constructional details
    • B66D1/40—Control devices
    • B66D1/48—Control devices automatic
    • B66D1/50—Control devices automatic for maintaining predetermined rope, cable, or chain tension, e.g. in ropes or cables for towing craft, in chains for anchors; Warping or mooring winch-cable tension control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B66—HOISTING; LIFTING; HAULING
    • B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
    • B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
    • B66D1/54—Safety gear
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D3/00—Control of position or direction
    • G05D3/10—Control of position or direction without using feedback
    • 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
    • B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
    • B64D2009/006—Rollers or drives for pallets of freight containers, e.g. PDU
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Emergency Lowering Means (AREA)
  • Warehouses Or Storage Devices (AREA)

Abstract

The invention discloses a vertical fixed wing aircraft for improving the folding and unfolding stability of a hanging warehouse, which comprises: a machine body, in which a cabin is formed; the hanging cargo bin is arranged in the cabin of the machine body; the hanging warehouse collecting and releasing mechanism is arranged in a cabin of the machine body, is connected with the hanging warehouse through a hanging cable and is used for controlling the hanging warehouse to be put down or put back; and the top surface of the hanging warehouse is provided with an active stabilizer for adjusting the posture and displacement of the hanging warehouse. The invention improves the stability of the hanging warehouse in the process of folding and unfolding.

Description

Hang fixed wing aircraft that hangs down of storehouse stability of receiving and releasing of hanging
Technical Field
The invention relates to the technical field of freight airplanes, in particular to a vertical fixed wing airplane capable of improving the folding and unfolding stability of a hanging warehouse.
Background
At present, a maritime freight aircraft usually adopts a drooping fixed-wing aircraft with a hanging cargo cabin to realize maritime freight, and the freight process is that the drooping fixed-wing aircraft flies to the upper side of a maritime freight platform of a ship, and then the hanging cargo cabin is put down through a hanging cable, so that the hanging cargo cabin falls on the maritime freight platform, and then the cargo loading and unloading operation is carried out. However, as the sea stormy waves are large, the hanging cargo cabin can shake or swing in the folding and unfolding process, the stability is poor, on one hand, the hovering state of the suspended fixed-wing aircraft during loading and unloading can be affected to a certain extent, the falling event can be caused seriously, on the other hand, the cargo in the hanging cargo cabin can be damaged, and meanwhile, the damage can be caused to the sea cargo platform.
To this end, the applicant has sought, through useful research and research, a solution to the above-mentioned problems, in the context of which the technical solutions to be described below have been made.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the utility model provides a hang fixed wing aircraft that hangs up that improves hanging storehouse and receive and release stability to prior art's not enough.
The technical problem to be solved by the invention can be realized by adopting the following technical scheme:
the utility model provides an improve and hang fixed wing aircraft that hangs down of storehouse stability of receiving and releasing, includes:
a machine body, in which a cabin is formed;
the hanging cargo bin is arranged in the cabin of the machine body; and
the hanging warehouse collecting and releasing mechanism is arranged in a cabin of the machine body, is connected with the hanging warehouse through a hanging cable and is used for controlling the hanging warehouse to be put down or put back; it is characterized in that the preparation method is characterized in that,
and the top surface of the hanging warehouse is provided with an active stabilizer for adjusting the posture and displacement of the hanging warehouse.
In a preferred embodiment of the present invention, the active stabilizer includes:
the stability augmentation mounting bracket is fixedly mounted on the top surface of the hanging warehouse;
a plurality of electric ducted fans which are circumferentially arranged on the stability augmentation mounting bracket at intervals; and
and the attitude controller is arranged on the stability augmentation mounting bracket and is respectively connected with each electric ducted fan.
In a preferred embodiment of the present invention, the number of the electric ducted fans is four, two electric ducted fans are a pair, two pairs of electric ducted fans are symmetrically arranged on the stability augmentation mounting bracket, and an axial included angle between each pair of electric ducted fans is 60 ° to 150 °.
In a preferred embodiment of the present invention, the hanging cargo compartment stowing and releasing mechanism includes a first driving motor, a first reduction gearbox, a first reel and a friction device, a driving output shaft of the first driving motor is connected to a driving input end of the first reduction gearbox, an output shaft of the first reduction gearbox is connected to the first reel through the friction device for driving the first reel to rotate, one end of the hanging cable is wound on the first reel, and the other end of the hanging cable is connected to the top surface of the hanging cargo compartment.
In a preferred embodiment of the present invention, a first fixed pulley is installed in the cabin of the machine body and directly above the hanging cargo compartment, one end of the hanging cable is wound on the first winding drum, and the other end of the hanging cable is connected to the top surface of the hanging cargo compartment after passing through the first fixed pulley.
In a preferred embodiment of the present invention, the hanging cargo compartment stowing and releasing mechanism includes a second driving motor, a second reduction gearbox, a second reel and a coil spring tensioner, a driving output shaft of the second driving motor is connected to a driving input end of the second reduction gearbox, an output shaft of the second reduction gearbox is connected to the second reel for driving the second reel to rotate, the coil spring tensioner is installed on a top surface of the hanging cargo compartment, one end of the hanging cable is wound on the second reel, and the other end of the hanging cable is connected to the coil spring tensioner.
In a preferred embodiment of the present invention, a second fixed pulley is installed in the cabin of the machine body and directly above the hanging cargo compartment, a third fixed pulley is installed on the top surface of the hanging cargo compartment and on one side of the coil spring tensioner, one end of the hanging cable is wound on the second winding drum, and the other end of the hanging cable passes through the second fixed pulley and the third fixed pulley in sequence and then is connected with the coil spring tensioner.
In a preferred embodiment of the present invention, the body includes:
the cabin is formed in the machine body, a retraction hatch for the hanging warehouse to get in and out is formed in the bottom of the cabin, and a lifting support frame is arranged at the bottom of the machine body;
the left main wing and the right main wing are symmetrically arranged on the middle part of the machine body, and a plurality of lift propellers and thrust propellers which are respectively connected with a flight control system are arranged on the left main wing and the right main wing at intervals along the length direction; and
and the tail wing is arranged on the tail part of the machine body.
In a preferred embodiment of the invention, a plurality of hanging cargo bin storing and releasing guide plates are arranged on the bottom surface of the machine body at intervals along the circumferential direction of the storing and releasing hatch.
In a preferred embodiment of the present invention, the tail is one of a V-shaped tail, an inverted V-shaped tail, a T-shaped tail, or an H-shaped tail.
Due to the adoption of the technical scheme, the invention has the beneficial effects that: according to the invention, the active stabilizer for adjusting the stability of the posture and the displacement of the hanging warehouse is arranged on the top surface of the hanging warehouse, so that the stability of the hanging warehouse in the folding and unfolding processes is improved. Meanwhile, the hanging cargo bin retracting mechanism tightens the hanging cable through the friction device or the coil spring tensioner, prevents the hanging cable from loosening and collapsing during cargo loading and unloading, and improves the safety of cargo loading and unloading.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a side view of a vertical fixed wing aircraft of the present invention.
FIG. 2 is a rear view of a vertical fixed wing aircraft of the present invention.
FIG. 3 is a top view of a vertical fixed wing aircraft of the present invention.
Fig. 4 is a schematic structural view of a vertical fixed-wing aircraft according to embodiment 1 of the present invention in a stowed state in a hangar.
Fig. 5 is a schematic structural view of a vertical fixed wing aircraft according to embodiment 1 of the present invention in a suspended cargo bay release state.
Fig. 6 is a schematic structural view of a hangar pick-and-place mechanism according to embodiment 1 of the vertical fixed wing aircraft of the present invention.
Fig. 7 is a schematic three-dimensional structure of an active stabilizer of embodiment 1 of the drooping fixed-wing aircraft of the present invention.
Fig. 8 is a side view of the active stabiliser of embodiment 1 of the drooping fixed-wing aircraft of the invention.
Fig. 9 is a top view of the active stabilizer of embodiment 1 of the drooping fixed-wing aircraft of the present invention.
Fig. 10 is a schematic structural view of a vertical fixed-wing aircraft according to embodiment 2 of the present invention in a stowed state in a hangar.
Fig. 11 is a schematic structural view of a vertical fixed wing aircraft according to embodiment 2 of the present invention in a suspended cargo bay release state.
Fig. 12 is an enlarged schematic view of a hangar portion of embodiment 2 of the vertical fixed wing aircraft of the present invention.
Fig. 13 is a schematic structural view of a hangar pick-and-place mechanism according to embodiment 2 of the vertical fixed-wing aircraft of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below by combining the specific drawings.
Example 1
Referring to fig. 1 to 5, a vertical fixed wing aircraft for improving the stowing stability of a hangar is shown, which includes a body 100, a hangar 200, a hangar stowing mechanism 300, and an active stabilizer 400.
The body 100 includes a body 110, left and right main wings 120 and 130, and a rear wing 140. A cabin 111 is formed in the fuselage 110, a storage hatch 112 for the hanging cargo bin 200 to enter and exit is formed at the bottom of the cabin 111, and a lifting support frame 113 is arranged at the bottom of the fuselage 110. In addition, a plurality of hanging cargo compartment storing guide plates 114 are provided at intervals along the circumferential direction of the storing hatch 112 on the bottom surface of the body 110 for guiding the hanging cargo compartment 200 into and out of the nacelle 111.
The left and right main wings 120 and 130 are symmetrically arranged on the middle part of the fuselage 110, a plurality of lift propellers 121 and thrust propellers 122 respectively connected with the flight control system are arranged on the left main wing 120 at intervals along the length direction, and a plurality of lift propellers 131 and thrust propellers 132 respectively connected with the flight control system are arranged on the right main wing 130 at intervals along the length direction. The lift propellers 121, 131 and thrust propellers 122, 132 provide the lift and thrust required for take-off and landing and flying, respectively, for a vertical-lift fixed-wing aircraft.
The rear wing 140 is provided on the rear portion of the body 110. In the present embodiment, the tail 140 is an inverted V-shaped tail structure, but may be one of a V-shaped tail, a T-shaped tail and an H-shaped tail.
A hangar 200 is disposed within the cabin 111 of the airframe 100 and is available for loading cargo.
The hanging cargo compartment retraction/extension mechanism 300 is installed in the cabin 111 of the machine body 100 and located at one side of the hanging cargo compartment 200, and is connected to the hanging cargo compartment 200 through a hanging cable 500 for controlling the hanging cargo compartment 200 to be retracted or extended. Specifically, referring to fig. 6 in conjunction with fig. 4 and 5, the hangar stowing mechanism 300 includes a drive motor 310, a reduction gearbox 320, a reel 330, and a friction device 340. The driving output shaft of the driving motor 310 is connected with the driving input end of the reduction box 320, and the output shaft of the reduction box 320 is connected with the winding drum 330 through a friction device 340 for driving the winding drum 330 to rotate. In the present embodiment, the reduction gearbox 320 is a clutch-type reduction gearbox structure. The tow cable 500 is wound on one end around a reel 330 and is attached at its other end to the top surface of the tow cargo compartment 200. The hanging cargo compartment retraction mechanism 300 tightens the hanging cable 500 through the friction device 340, so as to prevent the hanging cable 500 from collapsing when loading and unloading the cargo, and improve the safety of loading and unloading the cargo.
A fixed pulley 510 is installed in the cabin 111 of the machine body 100 directly above the hanging cargo compartment 200, one end of the hanging cable 500 is wound on the winding drum 330, and the other end is redirected by the fixed pulley 510 and then connected to the top surface of the hanging cargo compartment 200.
The friction device 340 has two operating states:
1. the output shaft of the reduction box 320 is meshed with the winding drum 330 by the friction plate in the friction device 340 to drive, at the moment, the winding drum 330 only transmits certain torque by friction force, and the torque is used for tightening the cable to prevent the cable from collapsing;
2. the output shaft of the reduction box 320 is in hard connection transmission with the winding drum 330 through a clutch bolt on the reduction box 320, the torque of the winding drum 330 is the same as the output of the reduction box 320, and the torque is used in the nacelle retraction process to provide retraction force.
The above two working states are switched by a clutch plug pin electric deflector rod on the reduction box 320.
The active stabilizer 400 is arranged on the top surface of the hanging warehouse 200, and is used for adjusting the posture and displacement of the hanging warehouse 200 and improving the stability of the hanging warehouse 200 in the folding and unfolding processes. Specifically, referring to fig. 7-9 in conjunction with fig. 4 and 5, the active stabilizer 400 includes a stabilizing mounting bracket 410, four electric ducted fans 420, and an attitude controller 430. The stability augmentation mounting bracket 410 is fixedly mounted on the top surface of the hanging cargo compartment 200, and may also serve as a connecting bracket between the hanging cargo compartment 200 and the hanging cable 500. The four electric ducted fans 420 are circumferentially installed on the stability augmentation mounting bracket 410 at intervals, two electric ducted fans 420 are in a pair, two pairs of electric ducted fans 420 are symmetrically arranged on the stability augmentation mounting bracket 410, and an axis included angle between each pair of electric ducted fans 420 is 60-150 degrees. Of course, the number of the electric ducted fans 420 is not limited to the number in the present embodiment, and may be set according to the requirements of posture and displacement adjustment. The attitude controller 430 is installed on the stability augmentation mounting bracket 410 and is connected with each of the electric ducted fans 420, respectively.
The electric ducted fan 420 provides adjusting forces in various directions, and the attitude controller 430 detects three-axis attitudes and displacements of the hanging cargo compartment 200, and controls the electric ducted fan 420 to output thrust to adjust to the set attitudes and displacements.
Example 2
The drooping fixed-wing aircraft in this embodiment has substantially the same structure as the drooping fixed-wing aircraft in embodiment 1, and is different therefrom in that:
referring to fig. 13 in conjunction with fig. 10 to 12, the hangar stowing mechanism 300a includes a drive motor 310a, a reduction gearbox 320a, a reel 330a, and a coil spring tensioner 340 a. The driving output shaft of the driving motor 310a is connected with the driving input end of the reduction box 320a, and the output shaft of the reduction box 320a is connected with the winding drum 330a and used for driving the winding drum 330a to rotate. A coil spring tensioner 340a is installed on the top surface of the hanging cargo compartment 200a, and one end of the hanging cable 500a is wound on the drum 330a and the other end thereof is connected to the coil spring tensioner 340 a. The coil spring tensioner 340a is composed of a coil spring and a winding drum, has a certain tightening force, and can contract the suspension cable 500a with a certain stroke. The hanging cargo compartment retraction mechanism 300a tightens the hanging cable 500a by the coil spring tensioner 340a, preventing the hanging cable 500a from being loosened and collapsed during cargo loading and unloading, and improving the cargo loading and unloading safety.
A fixed pulley 510a is installed in the nacelle 111a of the machine body 100a directly above the hanging cargo compartment 200a, a fixed pulley 520a is installed on the top surface of the hanging cargo compartment 200a on the side of the coil spring tensioner 340a, one end of the hanging cable 500a is wound around the winding drum 330a, and the other end thereof is connected to the coil spring tensioner 340a after passing through the fixed pulley 510a and the fixed pulley 520a in sequence.
The foregoing shows and describes the general principles and features of the present invention, together with the advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (10)

1. The utility model provides an improve and hang fixed wing aircraft that hangs down of storehouse stability of receiving and releasing, includes:
a machine body, in which a cabin is formed;
the hanging cargo bin is arranged in the cabin of the machine body; and
the hanging warehouse collecting and releasing mechanism is arranged in a cabin of the machine body, is connected with the hanging warehouse through a hanging cable and is used for controlling the hanging warehouse to be put down or put back; it is characterized in that the preparation method is characterized in that,
and the top surface of the hanging warehouse is provided with an active stabilizer for adjusting the posture and displacement of the hanging warehouse.
2. A droop-wing aircraft according to claim 1, wherein said active stabilizer comprises:
the stability augmentation mounting bracket is fixedly mounted on the top surface of the hanging warehouse;
a plurality of electric ducted fans which are circumferentially arranged on the stability augmentation mounting bracket at intervals; and
and the attitude controller is arranged on the stability augmentation mounting bracket and is respectively connected with each electric ducted fan.
3. A vertical fixed wing aircraft for improving the folding and unfolding stability of a hanging cargo cabin as claimed in claim 2, wherein the number of the electric ducted fans is four, two electric ducted fans are a pair, two pairs of electric ducted fans are symmetrically arranged on the stability augmentation mounting bracket, and the axial included angle between each pair of electric ducted fans is 60-150 °.
4. The vertical fixed wing aircraft for improving the folding and unfolding stability of the hanging cargo cabin according to claim 1, wherein the hanging cargo cabin folding and unfolding mechanism comprises a first driving motor, a first reduction gearbox, a first reel and a friction device, a driving output shaft of the first driving motor is connected with a driving input end of the first reduction gearbox, an output shaft of the first reduction gearbox is connected with the first reel through the friction device and used for driving the first reel to rotate, one end of the hanging cable is wound on the first reel, and the other end of the hanging cable is connected with the top surface of the hanging cargo cabin.
5. A suspended fixed wing aircraft as claimed in claim 4, wherein a first fixed pulley is mounted in the cabin of the aircraft body directly above the suspended cargo compartment, one end of the cable is wound around the first reel, and the other end of the cable is connected to the top surface of the suspended cargo compartment after passing through the first fixed pulley.
6. A vertical fixed wing aircraft for improving the folding and unfolding stability of a suspended cargo tank as claimed in claim 1, wherein the suspended cargo tank folding and unfolding mechanism comprises a second driving motor, a second reduction gearbox, a second winding drum and a coil spring tensioner, wherein a driving output shaft of the second driving motor is connected with a driving input end of the second reduction gearbox, an output shaft of the second reduction gearbox is connected with the second winding drum for driving the second winding drum to rotate, the coil spring tensioner is installed on the top surface of the suspended cargo tank, one end of the suspended cable is wound on the second winding drum, and the other end of the suspended cable is connected with the coil spring tensioner.
7. A vertical fixed wing aircraft for improving the folding and unfolding stability of a hanging cargo cabin as claimed in claim 6, wherein a second fixed pulley is installed in the cabin of the aircraft body right above the hanging cargo cabin, a third fixed pulley is installed on the top surface of the hanging cargo cabin on one side of the coil spring tensioner, one end of the hanging cable is wound on the second winding drum, and the other end of the hanging cable passes through the second fixed pulley and the third fixed pulley in sequence and then is connected with the coil spring tensioner.
8. A drop-off fixed wing aircraft for improving the stowing stability of a hangar as claimed in claim 1, wherein said airframe comprises:
the cabin is formed in the machine body, a retraction hatch for the hanging warehouse to get in and out is formed in the bottom of the cabin, and a lifting support frame is arranged at the bottom of the machine body;
the left main wing and the right main wing are symmetrically arranged on the middle part of the machine body, and a plurality of lift propellers and thrust propellers which are respectively connected with a flight control system are arranged on the left main wing and the right main wing at intervals along the length direction; and
and the tail wing is arranged on the tail part of the machine body.
9. The droop-raising fixed wing aircraft for improving the stowing stability of the suspended cargo compartment, according to claim 8, wherein a plurality of stowing guide plates for the suspended cargo compartment are provided at intervals along the circumferential direction of the stowing hatch on the bottom surface of the aircraft body.
10. A drooping fixed wing aircraft for improving the stowing stability of a hangar as claimed in claim 1 wherein said tail is one of a V-type tail, an inverted V-type tail, a T-type tail or an H-type tail.
CN202210770681.4A 2022-06-30 2022-06-30 Hanging fixed wing aircraft capable of improving folding and unfolding stability of hanging warehouse Active CN114954952B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210770681.4A CN114954952B (en) 2022-06-30 2022-06-30 Hanging fixed wing aircraft capable of improving folding and unfolding stability of hanging warehouse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210770681.4A CN114954952B (en) 2022-06-30 2022-06-30 Hanging fixed wing aircraft capable of improving folding and unfolding stability of hanging warehouse

Publications (2)

Publication Number Publication Date
CN114954952A true CN114954952A (en) 2022-08-30
CN114954952B CN114954952B (en) 2024-06-11

Family

ID=82966640

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210770681.4A Active CN114954952B (en) 2022-06-30 2022-06-30 Hanging fixed wing aircraft capable of improving folding and unfolding stability of hanging warehouse

Country Status (1)

Country Link
CN (1) CN114954952B (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102642623A (en) * 2012-05-11 2012-08-22 中国航空工业集团公司西安飞机设计研究所 Flying-wing cargo plane with externally-hung cargo hold
US20160340039A1 (en) * 2015-05-18 2016-11-24 Sikorsky Aircraft Corp. Systems and methods for lifting body vibration control
CN108657424A (en) * 2018-05-31 2018-10-16 江苏常探机器人有限公司 Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust
CN110789724A (en) * 2019-10-12 2020-02-14 哈尔滨飞机工业集团有限责任公司 Flexible towing nacelle retracting and releasing mechanism and method
EP3932803A1 (en) * 2020-06-30 2022-01-05 Airbus Helicopters Deutschland GmbH Load carrying assembly for a rotary wing aircraft
CN218055631U (en) * 2022-06-30 2022-12-16 上海羽天航空科技有限公司 Hang fixed wing aircraft of cabin folding and unfolding stability of goods that hangs in improvement

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102642623A (en) * 2012-05-11 2012-08-22 中国航空工业集团公司西安飞机设计研究所 Flying-wing cargo plane with externally-hung cargo hold
US20160340039A1 (en) * 2015-05-18 2016-11-24 Sikorsky Aircraft Corp. Systems and methods for lifting body vibration control
CN108657424A (en) * 2018-05-31 2018-10-16 江苏常探机器人有限公司 Rear single ducted fan formula composite wing cargo aircraft with the compound auxiliary wing of airscrew thrust
CN110789724A (en) * 2019-10-12 2020-02-14 哈尔滨飞机工业集团有限责任公司 Flexible towing nacelle retracting and releasing mechanism and method
EP3932803A1 (en) * 2020-06-30 2022-01-05 Airbus Helicopters Deutschland GmbH Load carrying assembly for a rotary wing aircraft
CN218055631U (en) * 2022-06-30 2022-12-16 上海羽天航空科技有限公司 Hang fixed wing aircraft of cabin folding and unfolding stability of goods that hangs in improvement

Also Published As

Publication number Publication date
CN114954952B (en) 2024-06-11

Similar Documents

Publication Publication Date Title
US9010683B2 (en) Rail recovery system for aircraft
US5799900A (en) Landing and take-off assembly for vertical take-off and landing and horizontal flight aircraft
CN109421939B (en) Rail recovery system for aircraft
CN109625305B (en) Unmanned aerial vehicle recovery unit
CN105966612B (en) Become posture VTOL unmanned plane
WO1998002350A9 (en) Landing and take-off assembly for vertical take-off and landing and horizontal flight aircraft
CN110589032B (en) Parachute system for aircraft recovery and parachute recovery method
CN218055631U (en) Hang fixed wing aircraft of cabin folding and unfolding stability of goods that hangs in improvement
CN110626516A (en) Ship landing device for vertical take-off and landing aircraft and ship
CN113277062A (en) Telescopic wing, wing interval adjusting module, aircraft and control method
US3226056A (en) Multiple span aircraft
CN108382578B (en) High-speed hybrid layout vertical take-off and landing aircraft
CN113277066A (en) Telescopic wing, aircraft comprising telescopic wing and aircraft control method
CN114954952B (en) Hanging fixed wing aircraft capable of improving folding and unfolding stability of hanging warehouse
CN210027961U (en) Unmanned aerial vehicle recovery unit
EP3736213B1 (en) Hybrid unmanned aerial vehicle
CN216887249U (en) Lifting device and aircraft
CN115675838A (en) Double-perch arm perching unmanned aerial vehicle and self-adaptive rising, falling and perching method
CN113665803B (en) Aircraft
CN217348209U (en) Aircraft
CN208134600U (en) A kind of aircraft with stretching, extension function
CN207931991U (en) A kind of rotatable rotor multifunction aircraft of solar energy
CN109263918A (en) A kind of tilting rotor fixed wing aircraft
CN217227894U (en) Variable-wing vertical take-off and landing self-grabbing aircraft
CN215707060U (en) Underwater unmanned aerial vehicle take-off and landing device

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
TA01 Transfer of patent application right
TA01 Transfer of patent application right

Effective date of registration: 20240131

Address after: 214116 Zone B2, Ehu Packaging City, Ehu Town, Xishan District, Wuxi City, Jiangsu Province 3379

Applicant after: Muyutian Aviation Technology (Jiangsu) Co.,Ltd.

Country or region after: China

Address before: Room 305-35, building 2, No. 2388, xiupu Road, Pudong New Area, Shanghai 201315

Applicant before: Shanghai Yutian Aviation Technology Co.,Ltd.

Country or region before: China

GR01 Patent grant
GR01 Patent grant