CN114013634B - Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft - Google Patents
Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft Download PDFInfo
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- CN114013634B CN114013634B CN202111401537.5A CN202111401537A CN114013634B CN 114013634 B CN114013634 B CN 114013634B CN 202111401537 A CN202111401537 A CN 202111401537A CN 114013634 B CN114013634 B CN 114013634B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/06—Undercarriages fixed
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- 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
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- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The application discloses mounting structure and fixed wing aircraft of fixed wing aircraft undercarriage for fix leaf spring type undercarriage on the fuselage, leaf spring type undercarriage includes the landing leg, be equipped with the installation department on the landing leg, be equipped with on the installation department and play outer braced frame and play in the main braced frame, play outer braced frame and fix the landing leg through first coupling assembling on the fuselage, play in the main braced frame and fix the landing leg on the fuselage through second coupling assembling, play outer braced frame and play in the main braced frame through setting up on the installation department, realize that play in the main braced frame and leaf spring type undercarriage's one end is connected in the fuselage, play outer braced frame and leaf spring type undercarriage's one end is connected on the fuselage, further increase leaf spring type undercarriage and connect stability, set up elastomeric element between play outer braced frame and installation department in the main, realize eliminating the clearance between outer braced frame and the installation department and absorb the vibration that the landing leg produced.
Description
Technical Field
The invention relates to the field of flying instruments, in particular to a mounting structure of a landing gear of a fixed-wing aircraft and the fixed-wing aircraft.
Background
In the prior art, the plate spring type landing gear is used in the fixed wing aircraft of part, when the plate spring type landing gear of installation, the connecting piece position at fuselage and landing gear is fixed through the mode that uses the abate, thereby the abate is not hard up to have the clearance to lead to the landing gear between abate and the landing gear to appear easily, still plate spring type landing gear, in order to avoid above-mentioned not hard up, can adopt more structures to fix on the landing gear, not only increase the weight of aircraft, still can lead to the error value grow of accumulation because of the increase of part quantity, increase the degree of difficulty of repairing.
Disclosure of Invention
The invention aims at the problems and provides a mounting structure of a fixed wing aircraft landing gear.
The technical scheme adopted by the invention is as follows: a mounting structure for a fixed wing aircraft landing gear for securing a leg of the landing gear to a fuselage, comprising:
the support leg is provided with a mounting part;
the main outer supporting frame is arranged on the machine body, the supporting legs are fixed on the machine body through a first connecting component, and the main outer supporting frame is made of a composite material;
the main outer supporting frame comprises a fixed frame, the pressing block is fixed on the fixed frame, a through groove is formed between the pressing block and the fixed frame, and the through groove is used for the supporting leg to pass through;
an elastic member disposed between the main outer support frame and the mounting portion, the elastic member being for eliminating a gap between the main outer support frame and the mounting portion and absorbing vibration generated by the leg;
the main support frame that plays, the main support frame that plays sets up on the fuselage, the main support frame that plays will through second coupling assembling the landing leg is fixed on the fuselage, the main support frame that plays in with the installation department passes through second coupling assembling and can dismantle and link to each other, the main support frame that plays all adopts combined material to make.
The main outer supporting frame and the main inner supporting frame are arranged on the mounting part, so that one end of the main inner supporting frame and one end of the plate-type landing gear are connected in the machine body, one end of the main outer supporting frame and one end of the plate-type landing gear are connected on the machine body, and the plate-type landing gear is connected on the machine body through the two parts of the outer supporting frame and the main inner supporting frame, so that the connection stability of the plate-type landing gear is further improved; by arranging the elastic part, the vibration generated between the fixed frame and the supporting leg and the vibration generated between the pressing block and the supporting leg are effectively reduced, the gap between the outer main supporting frame and the mounting part is eliminated, and the purposes of improving the landing safety and the comfort of the fixed wing aircraft are realized; through the arrangement of the through groove, the purpose of limiting the installation part is realized, the installation difficulty is reduced, and the convenient installation is realized; the pressing block, the mounting part, the fixed frame and the main outer supporting frame are detachably connected by arranging the first connecting component; the mounting part is connected with the inner supporting frame through the second connecting component, so that the stability of the connection between the plate-type landing gear and the machine body is further improved; the main outer support frame and the main inner support frame are made of composite materials, so that the purposes of increasing the specific strength and specific modulus of the main outer support frame and the main inner support frame are achieved, and the service life is prolonged.
Preferably, the bolts sequentially penetrate through the pressing block, the mounting part, the fixing frame and the main outer supporting frame and then are locked through the threaded backing plate.
During the in-service use, first bolt passes briquetting, installation department, fixed frame in proper order and plays outer braced frame back through the screw thread backing plate locking, uses bolted connection, and is stable firm, and bolt convenient to detach is favorable to the maintenance or the change of spare part simultaneously.
Preferably, two elastic components are arranged in the through groove, and the mounting part is positioned between the two elastic components.
By arranging the two buffer parts, vibration generated between the fixed frame and the supporting leg and between the pressing block and the supporting leg is effectively reduced, and the safety and the comfort of the landing of the fixed wing aircraft are improved; in addition, after the first connecting piece locks the pressing block, the mounting part, the fixing frame and the main outer supporting frame, due to the contractibility of the elastic component, the gap between the pressing block and the mounting part and between the fixing frame and the mounting part is eliminated, and the loss of the parts caused by vibration is further reduced.
Preferably, the elastic member is a polyurethane shock absorbing sheet.
The polyurethane has wide hardness range, high strength, high wear resistance, wide performance regulating range, long service life and high shock absorbing performance.
Preferably, the second connecting assembly comprises a second bolt and a locking nut, and the second bolt sequentially penetrates through the mounting part and the main inner supporting frame and then is fixed through the locking nut.
When in actual use, the second bolt passes through the mounting part and the main internal supporting frame from bottom to top, and the part of the second bolt which passes through the main internal supporting frame is fixed by using the locking nut; the locking nut has high installation accuracy and good vibration resistance, and is not easy to loosen when in mechanical vibration.
The application also discloses a fixed wing aircraft comprising the landing gear mounting structure described above.
The beneficial effects of the invention are as follows: the main outer supporting frame and the main inner supporting frame are arranged on the mounting part, one ends of the main inner supporting frame and the plate spring type landing gear are connected in the machine body, one ends of the main outer supporting frame and the plate spring type landing gear are connected on the machine body, the plate spring type landing gear is connected on the machine body through the two parts of the outer supporting frame and the main inner supporting frame, the stability of the connection of the plate spring type landing gear is further improved, and due to the arrangement of the elastic parts, the elastic parts have contractility, the clearance between the pressing block and the mounting part and the clearance between the fixing frame and the mounting part are eliminated, and the loss of parts caused by vibration is further reduced; through the outer braced frame of main beginning and the inner braced frame installation landing leg of main beginning, the precision that conventional installation can reach is good cooperation, reduces part quantity simultaneously, avoids the error accumulation that part quantity leads to more.
Description of the drawings:
FIG. 1 is a schematic view of the overall plate-type landing gear;
FIG. 2 is a schematic view of a leaf spring landing gear split;
fig. 3 is a schematic view of another angle of the leaf spring landing gear.
The reference numerals in the drawings are as follows:
1. a support leg; 3. a mounting part; 4. an outer supporting frame is mainly lifted; 5. an inner supporting frame is mainly lifted; 6. a first connection assembly; 7. an elastic member; 8. briquetting; 9. a fixed frame; 10. penetrating a groove; 11. a threaded backing plate; 12. and a second connection assembly.
The specific embodiment is as follows:
the present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1 and 2, a mounting structure of a landing gear of a fixed wing aircraft for fixing a leg 1 of the landing gear to a fuselage, comprises:
the support leg 1, the support leg 1 is provided with a mounting part 3;
the main outer supporting frame 4 is arranged on the machine body, the main outer supporting frame 4 fixes the supporting leg 1 on the machine body through the first connecting component 6, and the main outer supporting frame 4 is made of a composite material;
the first connecting component 6 comprises a block, a first bolt and a threaded base plate 11, the main outer supporting frame 4 comprises a fixed frame 9, a pressing block 8 is fixed on the fixed frame 9, a through groove 10 is formed between the pressing block 8 and the fixed frame 9, and the through groove 10 is used for the supporting leg 1 to pass through;
an elastic member 7, the elastic member 7 being disposed between the main outer support frame 4 and the mounting portion 3, the elastic member 7 being for eliminating a gap between the main outer support frame 4 and the mounting portion 3 and absorbing vibration generated by the leg 1;
the main support frame 5, the main support frame 5 sets up on the fuselage, and the main support frame 5 passes through second coupling assembling 12 and fixes landing leg 1 on the fuselage, and main support frame 5 passes through second coupling assembling 12 with installation department 3 and can dismantle continuous, and main support frame 5 all adopts combined material to make.
The main outer supporting frame 4 and the main inner supporting frame 5 are arranged on the mounting part 3, so that one end of the main inner supporting frame 5 and one end of the plate spring type landing gear are connected in the machine body, one end of the main outer supporting frame 4 and one end of the plate spring type landing gear are connected on the machine body, and the plate spring type landing gear is connected on the machine body through the two parts of the outer supporting frame and the main inner supporting frame 5, so that the connection stability of the plate spring type landing gear is further improved; through the arrangement of the elastic component 7, vibration between the fixed frame 9 and the supporting leg 1 and vibration between the pressing block 8 and the supporting leg 1 are effectively reduced, the purposes of improving the safety of landing of the fixed wing aircraft and improving the comfort are achieved by eliminating a gap between the outer main lifting supporting frame and the mounting part 3, the purposes of limiting the mounting part 3 are achieved by arranging the through groove 10, the mounting difficulty is reduced, and convenient mounting is achieved; through setting up first coupling assembling 6, realize getting up briquetting 8, installation department 3, fixed frame 9 and main outer braced frame 4 detachably and connect, through setting up second coupling assembling 12, realize linking to each other installation department 3 and interior braced frame, further increase leaf spring type undercarriage and the stability that the fuselage is connected, make main outer braced frame 4 and main interior braced frame 5 through adopting combined material, realize increasing main outer braced frame 4 and main interior braced frame 5's specific strength and the purpose of specific modulus, increase main outer braced frame 4 and main interior braced frame 5's life.
As shown in fig. 2, the bolts pass through the press block 8, the mounting part 3, the fixing frame 9 and the main outer support frame 4 in sequence and then are locked by the threaded backing plate 11.
During the in-service use, first bolt passes briquetting 8, installation department 3, fixed frame 9 in proper order and plays outer braced frame 4 back through screw thread backing plate 11 locking, uses bolted connection, and is stable firm, and bolt convenient to detach is favorable to the maintenance or the change of spare part simultaneously.
Two elastic components 7 are arranged in the through groove 10, and the mounting part 3 is positioned between the two elastic components 7.
By arranging two buffer parts, vibration generated between the fixed frame 9 and the supporting leg 1 and between the pressing block 8 and the supporting leg 1 is effectively reduced, and the landing safety and the landing comfort of the fixed wing aircraft are improved; in addition, after the first connecting piece locks the pressing block 8, the mounting part 3, the fixing frame 9 and the main outer supporting frame 4, due to the contractibility of the elastic component 7, the clearance between the pressing block 8 and the mounting part 3 and between the fixing frame 9 and the mounting part 3 is eliminated, and the loss of parts caused by vibration is further reduced.
The elastic member 7 is a polyurethane damper sheet.
The polyurethane has wide hardness range, high strength, high wear resistance, wide performance regulating range, long service life and high shock absorbing performance.
As shown in fig. 3, the second connection assembly 12 includes a second bolt and a locking nut, and the second bolt is fixed by the locking nut after passing through the mounting part 3 and the main inner support frame 5 in order.
When in actual use, the second bolt passes through the mounting part 3 and the main internal supporting frame 5 from bottom to top, and the part of the second bolt which passes through the main internal supporting frame 5 is fixed by using a locking nut; the locking nut has high installation accuracy and good vibration resistance, and is not easy to loosen when in mechanical vibration.
The application also discloses a fixed wing aircraft comprising the above landing gear mounting structure.
The installation and a use method of the invention are that firstly, a main outer supporting frame 4 and a main inner supporting frame 5 are installed on a machine body, a fixed frame 9 is installed on the main outer supporting frame 4, a pressing block 8 is pre-installed on the fixed frame 9, then a supporting leg 1 passes through a through groove 10 between the fixed frame 9 and the pressing block 8, the penetrated part is fixed on the main inner supporting frame 5 through a second connecting component 12, then an elastic component 7 is arranged between the fixed frame 9 and the supporting leg 1, an elastic component 7 is arranged between the pressing block 8 and the supporting leg 1, and finally the pressing block 8, the installation part 3, the fixed frame 9 and the main outer supporting frame 4 are locked through the second connecting component 12; when the aircraft lands, the landing leg 1 of the aircraft firstly contacts the bottom surface, the landing leg 1 receives huge impact force and generates intense vibration, at the moment, the plate spring type landing gear absorbs a part of vibration, the elastic part 7 further absorbs the vibration, and the aircraft jumps on the ground to jump and go forward until slowly stopping, so that the fixed wing aircraft lands perfectly.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather is intended to cover all equivalent structures as modifications within the scope of the invention, either directly or indirectly, as may be contemplated by the present invention.
Claims (4)
1. A mounting structure for a fixed wing aircraft landing gear for securing a leg of the landing gear to a fuselage, comprising:
the support leg is provided with a mounting part;
the main outer supporting frame is arranged on the machine body, the supporting legs are fixed on the machine body through a first connecting component, and the main outer supporting frame is made of a composite material;
the main outer supporting frame comprises a fixed frame, the pressing block is fixed on the fixed frame, a through groove is formed between the pressing block and the fixed frame, and the through groove is used for the supporting leg to pass through;
an elastic member disposed between the main outer support frame and the mounting portion, the elastic member being for eliminating a gap between the main outer support frame and the mounting portion and absorbing vibration generated by the leg;
the main internal supporting frame is arranged on the machine body, the supporting legs are fixed on the machine body through a second connecting component, the main internal supporting frame is detachably connected with the mounting part through a second connecting component, and the main internal supporting frame is made of composite materials;
the first bolt sequentially passes through the pressing block, the mounting part, the fixing frame and the main outer supporting frame and then is locked by the threaded backing plate;
two elastic components are arranged in the through groove, and the mounting part is positioned between the two elastic components.
2. A mounting structure for a fixed wing aircraft landing gear according to claim 1, wherein the resilient member is a polyurethane shock absorbing sheet.
3. The mounting structure of a fixed wing aircraft landing gear according to claim 1, wherein the second connection assembly includes a second bolt and a lock nut, and the second bolt is fixed by the lock nut after passing through the mounting portion and the main inner support frame in sequence.
4. A fixed wing aircraft, characterized in that the landing gear mounting structure is any one of claims 1 to 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111401537.5A CN114013634B (en) | 2021-11-19 | 2021-11-19 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111401537.5A CN114013634B (en) | 2021-11-19 | 2021-11-19 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114013634A CN114013634A (en) | 2022-02-08 |
| CN114013634B true CN114013634B (en) | 2023-07-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111401537.5A Active CN114013634B (en) | 2021-11-19 | 2021-11-19 | Mounting structure of fixed wing aircraft landing gear and fixed wing aircraft |
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Citations (11)
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| Publication number | Priority date | Publication date | Assignee | Title |
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2021
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| CN112407254A (en) * | 2020-10-27 | 2021-02-26 | 江西玉祥智能装备制造有限公司 | Unmanned aerial vehicle with buffering undercarriage |
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| CN114013634A (en) | 2022-02-08 |
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