CN110775245A - Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing - Google Patents
Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing Download PDFInfo
- Publication number
- CN110775245A CN110775245A CN201911058716.6A CN201911058716A CN110775245A CN 110775245 A CN110775245 A CN 110775245A CN 201911058716 A CN201911058716 A CN 201911058716A CN 110775245 A CN110775245 A CN 110775245A
- Authority
- CN
- China
- Prior art keywords
- reinforcing frame
- side wall
- flange
- frame structure
- composite material
- 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.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Abstract
The invention relates to a composite material integral reinforcing frame structure applied to installation of unmanned aerial vehicle equipment, which is integrally manufactured by adopting a resin transfer molding process and comprises a side wall, an upper flange, a lower flange and a reinforcing rib, wherein the side wall is provided with lightening holes and is provided with a supporting plate nut and a T-shaped nut, and the side wall is connected with an aircraft skin or an aircraft body structure through screws; the flange is positioned in the reinforcing frame, an opening is formed in the flange and used for mounting airborne equipment, a T-shaped metal threaded sleeve is mounted in the opening of the lower flange part and used for mounting and leveling precise airborne equipment, and meanwhile, a circular opening is formed in the lower flange and used for allowing a pipeline to pass through; the reinforcing ribs are positioned between the flange and the side wall, and the number of the reinforcing ribs is determined according to design requirements so as to increase structural rigidity. The invention has the advantages of light weight, high rigidity, high strength, low assembly cost, high space utilization rate and the like.
Description
Technical Field
The invention relates to a composite material integral reinforcing frame structure applied to installation of unmanned aerial vehicle equipment, and belongs to the field of aircraft composite material structure design.
Background
Modern unmanned vehicles such as missiles and unmanned aerial vehicles develop towards the direction of high speed, high maneuverability and accurate guidance, and higher requirements are provided for the accuracy of corresponding airborne navigation guidance equipment. When the aircraft is in high maneuvering action, the error between the rotation angle of the aircraft attitude sensor and the body attitude angle is generally required to be within a few angular seconds (1 angular second is 1/3600 degrees), and the mounting structure of the airborne navigation guidance equipment is required to have great rigidity.
The existing installation structure of the navigation guidance equipment of the unmanned aircraft is generally made of metals such as aluminum, titanium and the like so as to meet the harsh requirement on rigidity, but the structure weight of the existing installation structure is often too large, so that the installation structure cannot meet the requirement of the modern aircraft on structure weight reduction.
The fiber reinforced composite material is widely applied to the field of aerospace due to the advantages of high specific strength, large specific stiffness, good fatigue performance and the like.
Disclosure of Invention
The invention solves the problems: the composite material integral reinforcing frame structure overcomes the defects of the existing metal mounting structure of the unmanned aerial vehicle airborne equipment, and is applied to the unmanned aerial vehicle equipment mounting, and has the advantages of light weight, high rigidity, high strength, low assembly cost and high space utilization rate.
The technical solution of the invention is as follows: the integral composite material reinforcing frame structure applied to installation of unmanned aerial vehicle equipment is made of carbon fiber reinforced resin matrix composite materials through a resin transfer molding process and comprises a side wall, an upper flange, a lower flange and reinforcing ribs. The airborne equipment is installed on the flange through the spiro union, installs layer board nut and T nut on the lateral wall, and the lateral wall passes through the screw and is connected with organism or covering. And reinforcing ribs are arranged between the lower flange and the side wall, and the number of the reinforcing ribs is determined according to the design requirement so as to increase the structural rigidity. The reinforcing frame material is a carbon fiber reinforced resin matrix composite material.
The shape of the reinforcing frame structure is selected according to the shape of the section of the machine body and comprises an elliptic table shape, a circular table shape or a cylindrical shape.
And a T-shaped metal threaded sleeve is installed on a part of the opening of the lower flange, and the upper surface of the T-shaped metal threaded sleeve is precisely milled and used for adjusting the installation plane of the precise airborne equipment.
And a circular opening is formed in the lower flange and used for allowing a pipeline to pass through.
The side wall is uniformly provided with lightening holes along the circumferential direction, the number of the lightening holes is determined after strength and rigidity analysis, and the requirements on the strength and rigidity of the structure are required to be met. The number of lightening holes is 12 in this embodiment.
The weight reducing holes are in the shape of round-angle rectangles, so that the weight reducing effect is guaranteed, machining is easy, and meanwhile stress concentration is reduced through round angles.
The appearance of the reinforcing frame is consistent with that of the inner surface of the aircraft body or the skin, so that the outer side of the reinforcing frame is attached to the inner surface of the aircraft body or the skin, the connection rigidity is improved, and the utilization rate of the inner space of the aircraft is improved.
The reinforcing frame is integrally formed, and the manufacturing process comprises a resin transfer molding forming process, an autoclave process and a die pressing process.
The invention has the advantages and beneficial effects that:
(1) according to the composite material integral reinforcing frame structure applied to installation of unmanned aerial vehicle equipment, the carbon fiber reinforced resin matrix composite material is adopted, and compared with a traditional metal structure, the weight can be reduced by more than 30%.
(2) The invention relates to a composite material integral reinforcing frame structure applied to installation of unmanned aerial vehicle equipment, which adopts a resin transfer molding integrated forming process. The traditional complex metal structure is usually manufactured in blocks and then manufactured by a method of assembling fasteners, so that the number of parts is large, and the assembly workload is large. The invention can form an integral structure at one time, and has the advantages of less parts and less assembly workload.
(3) The structure of the invention is determined by the inner surface of the body or the skin, can be processed into a structure with a complex curved surface appearance, has a regular curved surface appearance compared with a metal structure, and can fully utilize the inner space of the aircraft.
(4) The T-shaped metal thread sleeve is installed on a hole in the upper part of the structural flange, and a plane can be installed through precision milling equipment, so that the T-shaped metal thread sleeve is used for installing a high-precision instrument.
Drawings
FIG. 1 is a schematic structural diagram of an integral reinforcing frame made of a composite material according to an embodiment of the present invention;
FIG. 2 is a schematic top view of a composite material integrated stiffener structure according to an embodiment of the present invention;
FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a cross-sectional view taken along line B-B of FIG. 2, at 2 times magnification;
fig. 5 is a schematic diagram of a pallet nut provided by an embodiment of the present invention, referring to the aerospace industry standard qj.3079.14a-2011 of the people's republic of china;
FIG. 6 is a schematic view of a T-shaped metal insert according to an embodiment of the present invention;
FIG. 7 is a schematic view of a T-nut according to an embodiment of the present invention;
the flange structure comprises a flange body, a flange body and a flange, wherein the flange body comprises 1-side walls, 2-upper flanges, 3-lower flanges, 4-supporting plate nuts, 5-T-shaped nuts, 6-reinforcing ribs, 7-T-shaped metal threaded sleeves, 8-lightening holes, 9-lower flange pipeline through holes, 10-bolt holes, 11-lower flange equipment mounting bolt holes, 12.
Detailed Description
As shown in fig. 1 and 2, the present invention provides a composite material integral reinforced frame structure applied to installation of unmanned aerial vehicle equipment, which comprises an integral reinforced frame and corresponding connecting fitting pallet nuts 4 (shown in fig. 5), T-shaped nuts 5 (shown in fig. 6), and T-shaped metal turnbuckles 7 (shown in fig. 7). The appearance of the whole reinforcing frame is in an elliptical table shape as shown in figure 1, so that the outer surface of the reinforcing frame is attached to the inner surface of the skin, the connecting rigidity is improved, and the space utilization rate is improved. The reinforcing frame comprises a side wall 1, an upper flange 2, a lower flange 3 and four reinforcing ribs 6. Evenly be equipped with 12 lightening holes 8 along circumference on the lateral wall, the lightening hole shape is fillet rectangle to machining, the fillet is favorable to reducing stress concentration simultaneously. And a supporting plate nut 4 is arranged between two adjacent lightening holes, and as shown in figure 3, the number of the supporting plate nuts is 12 in total along the circumferential direction of the side wall. 12T shape nuts 5 are evenly installed along circumference respectively at the upper and lower edges of the side wall, and the reinforcing frame side wall is connected with the skin through these layer board nuts and T shape nuts which are evenly distributed along circumference, so that the connecting load can be dispersed, the reduction is required to be concentrated immediately, and the connecting rigidity is improved. The upper flange of the reinforcing frame is elliptical, and is uniformly provided with 12 bolt holes 10 along the circumferential direction for installing and connecting airborne equipment with an elliptical cross section. The middle of the lower flange of the reinforcing frame is provided with a larger rectangular opening 13 with the diameter of 150mm multiplied by 130mm, the four corners of the rectangular opening are provided with holes with the diameter of 8mm and are provided with T-shaped metal screw sleeves 7, and the upper surfaces of the four T-shaped metal screw sleeves can be precisely cut so as to install navigation guidance equipment with higher precision requirement. The left side of the rectangular opening in the center of the lower flange is provided with a circular hole with the diameter of 60mm for passing various pipelines, the other three sides of the rectangular opening are provided with two rectangular openings with the diameter of 120mm multiplied by 25mm and a smaller square opening with the diameter of 55mm multiplied by 55mm for installing other airborne equipment, and the openings are provided with round corners with the radius of 5mm for reducing stress concentration. 4 reinforcing ribs are arranged between the inner surface of the side wall and the upper surface of the lower flange, as shown in fig. 4, so as to improve the rigidity of the structure. The reinforcing rib is triangular in shape and 3mm thick, is arranged on the lower flange along the diagonal position of the rectangular opening, is close to the T-shaped metal thread sleeve at the top point of the lower flange, and is positioned below the supporting plate nut at the top point on the side wall. Fillets with the radius of 2mm are arranged between the side wall and the flange, between the reinforcing rib and the side wall and between the reinforcing rib and the lower flange, so that the composite material structure can be conveniently machined, and meanwhile, the stress concentration is reduced.
In the aspect of material selection, the composite material integral reinforcing frame mainly adopts a carbon fiber unidirectional belt and epoxy resin, and a layer of carbon fiber plain cloth is covered on the surface of the composite material integral reinforcing frame, so that the structural weight can be greatly reduced under the condition of meeting the requirements on strength and rigidity.
In the forming process, the integral composite material reinforcing frame adopts a resin transfer molding forming process, so that the integral forming of the reinforcing frame can be realized, and the number of parts and the assembly workload are reduced.
When the composite material integral reinforcing frame is installed and used, the concrete steps are as follows:
firstly, mounting a supporting plate nut at a corresponding position of a side wall of a reinforcing frame;
step two, mounting the T-shaped nuts at corresponding hole positions on the side wall of the reinforcing frame;
step three, mounting the T-shaped metal thread sleeves on four corner hole positions of a rectangular opening in the center of the lower flange;
fixing the reinforcing frame on a machine tool, and precisely cutting the upper surfaces of the four T-shaped metal screw sleeves to meet the requirements of flatness and the like;
step five, installing lower flange airborne equipment;
step six, installing flange airborne equipment;
seventhly, placing the reinforcing frame provided with the airborne equipment at a corresponding position in the skin or the body of the aircraft, and enabling the pipeline to penetrate through the circular hole of the lower flange;
and step eight, screwing in screws from the outer side of the skin or the body, and connecting and fastening the screws with the reinforcing frame supporting plate nuts and the T-shaped nuts to finish the installation of the reinforcing frame.
The specific modulus of the carbon fiber epoxy resin composite material used in the integral reinforcing frame structure of the composite material provided by the invention can reach 77-199 GPa/(g-cm)
-3) The specific strength can reach 857-1200 MPa/(g-cm)
-3) Compared with the steel commonly used in the traditional metal structure (the specific modulus is 27 GPa/(g.c)m
-3) Specific strength 154MPa/(g cm)
-3) Titanium (specific modulus 25GPa/(g cm)
-3) Specific strength 417MPa/(g cm)
-3) The specific rigidity and the specific strength are greatly improved. Under the condition of ensuring the structural rigidity and the strength, the effect of reducing weight by at least 30 percent compared with the metal reinforcing frame structure can be realized.
The above examples are provided only for the purpose of describing the present invention, and are not intended to limit the scope of the present invention. The scope of the invention is defined by the appended claims. Various equivalent substitutions and modifications can be made without departing from the spirit and principles of the invention, and are intended to be within the scope of the invention.
Claims (6)
1. The utility model provides a be applied to whole reinforced frame structure of combined material of unmanned vehicles equipment fixing which characterized in that: the material is a carbon fiber reinforced resin matrix composite material, is integrally manufactured by adopting a resin transfer molding process and comprises a side wall, an upper flange, a lower flange and reinforcing ribs; wherein, the side wall is provided with a supporting plate nut and a T-shaped nut and is connected with the skin or the airframe structure of the aircraft through a bolt; the flange is positioned inside the reinforcing frame, and is provided with an opening for mounting aircraft equipment; the reinforcing ribs are positioned between the lower flange and the side wall, and the number of the reinforcing ribs is determined according to design requirements so as to increase the structural rigidity.
2. The composite material integrated reinforcing frame structure applied to unmanned aerial vehicle equipment installation according to claim 1, wherein: the shape of the reinforcing frame structure is selected according to the shape of the section of the machine body and comprises an elliptic table shape, a circular table shape or a cylindrical shape.
3. The composite material integrated reinforcing frame structure applied to unmanned aerial vehicle equipment installation according to claim 1, wherein: and a T-shaped metal threaded sleeve is installed on a part of the opening of the lower flange, and the upper surface of the T-shaped metal threaded sleeve is precisely milled and used for adjusting the installation plane of the precise airborne equipment.
4. The composite material integrated reinforcing frame structure applied to unmanned aerial vehicle equipment installation according to claim 1, wherein: and a circular opening is formed in the lower flange and used for allowing a pipeline to pass through.
5. The composite material integrated reinforcing frame structure applied to unmanned aerial vehicle equipment installation according to claim 1, wherein: the side wall is uniformly provided with lightening holes along the circumferential direction, the number of the lightening holes is determined after strength and rigidity analysis, and the requirements on the strength and rigidity of the structure are required to be met.
6. The composite material integrated reinforcing frame structure applied to unmanned aerial vehicle equipment installation according to claim 5, wherein: the weight reducing holes are in the shape of round-angle rectangles, so that the weight reducing effect is guaranteed, machining is easy, and meanwhile stress concentration is reduced through round angles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911058716.6A CN110775245A (en) | 2019-11-01 | 2019-11-01 | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911058716.6A CN110775245A (en) | 2019-11-01 | 2019-11-01 | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110775245A true CN110775245A (en) | 2020-02-11 |
Family
ID=69388580
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911058716.6A Pending CN110775245A (en) | 2019-11-01 | 2019-11-01 | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110775245A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111776233A (en) * | 2020-06-24 | 2020-10-16 | 北京电子工程总体研究所 | Composite material base for aircraft |
| CN114671005A (en) * | 2022-04-28 | 2022-06-28 | 威海光晟航天航空科技有限公司 | Aircraft nose cone structure and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN202686767U (en) * | 2012-06-14 | 2013-01-23 | 北京中陆航星科技有限公司 | Airborne photoelectric pod mounting device |
| CN103318419A (en) * | 2013-05-20 | 2013-09-25 | 西安电子工程研究所 | Seal structure for sleeve connection of pod body and antenna housing of onboard electronic pod |
| CN105923141A (en) * | 2016-03-25 | 2016-09-07 | 哈尔滨飞机工业集团有限责任公司 | Photoelectric pod rack |
| RU2596706C1 (en) * | 2015-11-13 | 2016-09-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Detachable connection |
| CN206634197U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft wing equipment hanger |
| CN109533275A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of installation method of air remote sensing equipment aboard |
-
2019
- 2019-11-01 CN CN201911058716.6A patent/CN110775245A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202686767U (en) * | 2012-06-14 | 2013-01-23 | 北京中陆航星科技有限公司 | Airborne photoelectric pod mounting device |
| CN102729482A (en) * | 2012-06-29 | 2012-10-17 | 中国人民解放军国防科学技术大学 | Composite heatproof bearing cylinder and preparation method thereof |
| CN103318419A (en) * | 2013-05-20 | 2013-09-25 | 西安电子工程研究所 | Seal structure for sleeve connection of pod body and antenna housing of onboard electronic pod |
| RU2596706C1 (en) * | 2015-11-13 | 2016-09-10 | Федеральное государственное унитарное предприятие "Научно-производственное объединение им. С.А. Лавочкина" | Detachable connection |
| CN105923141A (en) * | 2016-03-25 | 2016-09-07 | 哈尔滨飞机工业集团有限责任公司 | Photoelectric pod rack |
| CN206634197U (en) * | 2017-03-14 | 2017-11-14 | 陕西爱维森航空工程有限责任公司 | A kind of aircraft wing equipment hanger |
| CN109533275A (en) * | 2018-12-07 | 2019-03-29 | 西安飞机工业（集团）有限责任公司 | A kind of installation method of air remote sensing equipment aboard |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111776233A (en) * | 2020-06-24 | 2020-10-16 | 北京电子工程总体研究所 | Composite material base for aircraft |
| CN114671005A (en) * | 2022-04-28 | 2022-06-28 | 威海光晟航天航空科技有限公司 | Aircraft nose cone structure and preparation method thereof |
| CN114671005B (en) * | 2022-04-28 | 2024-04-12 | 威海光晟航天航空科技有限公司 | Aircraft nose cone structure and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110775245A (en) | Be applied to whole reinforcing frame structure of combined material of unmanned vehicles equipment fixing | |
| JP5111068B2 (en) | Method for producing perforated fiber reinforced composite | |
| CN102923252A (en) | Full rotation steering oar device installation method | |
| US20080213034A1 (en) | Swivel fitting attachment apparatus | |
| CN102730182B (en) | Unmanned aerial vehicle wing and body connection apparatus | |
| US7997530B2 (en) | Airplane fairing panel adjustable fitting assembly, kit and method | |
| CN203185067U (en) | Rotary type indexing table | |
| US5849393A (en) | Structural element and method of making | |
| US6514593B1 (en) | Mechanically locking Z-pins | |
| CN203210063U (en) | Novel helicopter stern tube clamping device | |
| CN107081691B (en) | A kind of quick auxiliary transverse alignment device of three-dimensional coordinates measurement | |
| CN209776775U (en) | Propeller protective cover for autonomous underwater vehicle | |
| CN103434644B (en) | A kind of four axle agricultural aircraft combined type fuselages and rotor combine | |
| CN103466496B (en) | A kind of aircraft jack-up device | |
| CN209146270U (en) | A kind of mounting structure of horizontal lathe spindle belt pulley | |
| CN106493408A (en) | A kind of Large Aircraft Components dock self-positioning punching device | |
| CN207045665U (en) | A kind of aircraft plug-hole component | |
| CN207387165U (en) | A kind of turning tool for transfer case transparent cover | |
| CN218836180U (en) | Drilling die for titanium alloy wallboard-shaped part on airplane | |
| CN111003184A (en) | Aircraft external hanging article support | |
| CN213053689U (en) | Covering numerical control machining positioning device | |
| CN213390794U (en) | A fixed subassembly for gypsum board furred ceiling frame | |
| CN211162243U (en) | Tire rotating system for gear hobbing machine | |
| CN219932665U (en) | High-efficiency aerospace fastener | |
| CN108687386B (en) | Clamping structure of aviation thin-walled part |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200211 |