CN118129542A - Cross-folded diamond-shaped back missile wing structure and unfolding method thereof - Google Patents
Cross-folded diamond-shaped back missile wing structure and unfolding method thereof Download PDFInfo
- Publication number
- CN118129542A CN118129542A CN202410572144.8A CN202410572144A CN118129542A CN 118129542 A CN118129542 A CN 118129542A CN 202410572144 A CN202410572144 A CN 202410572144A CN 118129542 A CN118129542 A CN 118129542A
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- missile wing
- wing
- missile
- sliding block
- fixed
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 229910003460 diamond Inorganic materials 0.000 claims abstract description 21
- 239000010432 diamond Substances 0.000 claims abstract description 21
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 claims description 3
- 230000002146 bilateral effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention belongs to the field of transonic aerodynamics, and discloses a crossed and folded diamond-shaped back missile wing structure and an unfolding method thereof. The front missile wing of the diamond back missile wing structure comprises a first front missile wing and a second front missile wing which are hinged on a base and are bilaterally symmetrical; the rear missile wing comprises a first rear missile wing and a second rear missile wing which are hinged on the sliding block and are bilaterally symmetrical; the front end of the guide rail is fixed on the bottom surface of the base, the rear end of the guide rail is fixed with a rear seat, and stroke limit keys are arranged on two sides of the rear seat; the guide rail is provided with a sliding groove, a sliding block is clamped in the sliding groove, and a locking piece corresponding to the travel limit key is arranged at the rear side of the sliding block. When the front missile wing is unfolded, the sliding block moves backwards along the guide rail to drive the rear missile wing to open, and the rear missile wing drives the front missile wing to unfold through the support column; when the sliding block moves to the position of the rear seat, the locking piece presses the stroke limiting key until the locking piece is clamped and fixed with the stroke limiting key. The missile wing structure and the unfolding method thereof have simple structure, are simple, convenient and feasible, have high reliability and have engineering practical value.
Description
Technical Field
The invention belongs to the field of transonic aerodynamics, and particularly relates to a crossed and folded diamond-shaped back missile wing structure and an unfolding method thereof.
Background
At present, the diamond back missile wing structure is a combined missile wing layout which connects the front wing surface and the rear wing surface through a hinge and can be folded and unfolded. With the increasing requirements of weapon range and increasing weight, the area of the airfoil is required to be large enough to provide the lift force required in the flight process from the view of flight dynamics; the diamond back missile wing surface size is greatly constrained due to the space limitation of self layout and mounting, and the side-by-side folding mode adopted by the existing diamond back missile wing folding technology has the problems of small missile wing area, complex movement mechanism and the like.
In order to improve the aerodynamic performance of the diamond-shaped back missile wing and overcome the problem of small usable area of the wing surface, currently, development of a cross-folded diamond-shaped back missile wing structure and an unfolding method thereof are needed.
Disclosure of Invention
The invention aims to provide a cross-folded diamond-shaped back missile wing structure, and the other technical problem to be solved is to provide a cross-folded diamond-shaped back missile wing structure unfolding method for overcoming the defects of the prior art.
The invention relates to a crossed and folded diamond back missile wing structure, which is characterized by comprising a front missile wing and a rear missile wing;
the front missile wing comprises a first front missile wing and a second front missile wing which are bilaterally symmetrical, wing roots of the first front missile wing and the second front missile wing are hinged and fixed on the base, the first front missile wing is arranged on the base, and the second front missile wing is arranged on the lower side;
the rear missile wing comprises a first rear missile wing and a second rear missile wing which are bilaterally symmetrical, wing roots of the first rear missile wing and the second rear missile wing are hinged and fixed on the sliding block, the first rear missile wing is arranged on the upper part, and the second rear missile wing is arranged on the lower part;
The first front missile wing is arranged at the upper part, the first rear missile wing is arranged at the lower part, the wing tip of the first front missile wing extends out of the wing tip of the first rear missile wing, a supporting column is arranged at the contact point of the first front missile wing and the first rear missile wing, and the first front missile wing and the first rear missile wing are hinged on the supporting column;
The wing tip of the second front missile wing extends out of the wing tip of the second rear missile wing, a supporting column is arranged on the contact point of the second front missile wing and the second rear missile wing, and the second front missile wing and the second rear missile wing are both hinged on the supporting column;
The front end of the guide rail is fixed on the bottom surface of the base, the rear end of the guide rail is fixed with a square rear seat, and the two sides of the rear seat are provided with left-right symmetrical travel limit keys; the guide rail is provided with a sliding groove, a sliding block is clamped in the sliding groove, and the rear side of the sliding block is provided with a bilateral symmetry locking piece corresponding to the bilateral symmetry travel limit key; when the sliding block moves to the rear seat, the locking piece of the sliding block is clamped and fixed with the stroke limiting key of the rear seat.
Further, the diamond-shaped back missile wing structure has an unfolding form and a folding form;
the base, the guide rail and the rear seat are fixed in the elastic body;
in the unfolded configuration, the first front missile wing, the second front missile wing, the first rear missile wing and the second rear missile wing extend out of the projectile body; the first front missile wing and the second front missile wing are bilaterally symmetrical, the first rear missile wing and the second rear missile wing are bilaterally symmetrical, the sliding block is backwards, and the locking piece of the sliding block is clamped and fixed with the stroke limiting key of the rear seat; the sweepback angle of the front missile wing is larger than the sweepback angle of the rear missile wing;
in the folded state, the first front missile wing, the second front missile wing, the first rear missile wing and the second rear missile wing are overlapped from top to bottom and hidden in the missile body; the slide block is forward and close to the base.
The invention discloses a method for unfolding a crossed and folded diamond-shaped back missile wing structure, which comprises the following steps of:
S10, installing a diamond back missile wing structure in a hull of a gliding type aircraft according to the situation that the base is arranged at the front and the rear seats;
s20, installing a cylinder in a body of the gliding type aircraft, wherein the cylinder takes fuel gas in the body as a power source, and fixedly connecting the cylinder with a sliding block;
S30, when the aircraft is unfolded, the sliding block is pushed by the actuating cylinder to move backwards along the guide rail to drive the first rear missile wing and the second rear missile wing to be unfolded; according to the motion principle of the connecting rod mechanism, the rear missile wing drives the front missile wing to open through the supporting column, and meanwhile, the first front missile wing and the second front missile wing rotate around the base; when the sliding block moves to the position of the rear seat, the locking piece presses the stroke limiting key until the locking piece is clamped and fixed with the stroke limiting key.
Further, a compression spring is arranged in the locking piece.
The crossed and folded diamond back missile wing structure solves the problem of insufficient missile wing area through the crossed and folded mode that the front missile wing and the rear missile wing are connected by the support columns, and has the characteristics of simple structure, light overall weight, stable flying state and convenience in use and maintenance.
The unfolding method of the crossed and folded diamond-shaped back missile wing structure is simple, convenient and feasible, high in reliability and has engineering practical value.
Drawings
FIG. 1 is an expanded schematic view of a cross-folded diamond back missile wing structure in accordance with the present invention;
FIG. 2a is a schematic folding view (perspective view) of a cross-folded diamond back missile wing structure according to the present invention;
FIG. 2b is a folded schematic view (front view) of a cross-folded diamond back missile wing structure in accordance with the present invention;
FIG. 3 is a schematic view of a rear seat structure in a cross-folded diamond back missile wing structure according to the present invention;
FIG. 4 is a schematic view of a support column in a cross-folded diamond back missile wing structure according to the present invention.
In the figure, 1. A base; 2. a guide rail; 3. a chute; 4. a slide block; 5. a locking member; 6. a first front missile wing; 7. a second front missile wing; 8. a support column; 9. a first rear missile wing; 10. a second rear missile wing; 11. a rear seat; 12. and a travel limit key.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Examples:
the cross-folded diamond back missile wing structure of the embodiment is characterized in that, as shown in fig. 1, 2a, 2b, 3 and 4, the diamond back missile wing structure comprises a front missile wing and a rear missile wing;
The front missile wing comprises a first front missile wing 6 and a second front missile wing 7 which are bilaterally symmetrical, wing roots of the first front missile wing 6 and the second front missile wing 7 are hinged and fixed on the base 1, the first front missile wing 6 is arranged on the upper part, and the second front missile wing 7 is arranged on the lower part;
The rear missile wing comprises a first rear missile wing 9 and a second rear missile wing 10 which are bilaterally symmetrical, wing roots of the first rear missile wing 9 and the second rear missile wing 10 are hinged and fixed on the sliding block 4, the first rear missile wing 9 is arranged on the upper part, and the second rear missile wing 10 is arranged on the lower part;
the first front missile wing 6 is arranged on the upper part, the first rear missile wing 9 is arranged on the lower part, the wing tip of the first front missile wing 6 extends out of the wing tip of the first rear missile wing 9, a supporting column 8 is arranged at the contact point of the first front missile wing 6 and the first rear missile wing 9, and the first front missile wing 6 and the first rear missile wing 9 are hinged on the supporting column 8;
The wing tip of the second front missile wing 7 extends out of the wing tip of the second rear missile wing 10, a supporting column 8 is arranged at the contact point of the second front missile wing 7 and the second rear missile wing 10, and the second front missile wing 7 and the second rear missile wing 10 are hinged on the supporting column 8;
The front end of the guide rail 2 is fixed on the bottom surface of the base 1, the rear end of the guide rail 2 is fixed with a square rear seat 11, and the two sides of the rear seat 11 are provided with left-right symmetrical travel limit keys 12; the guide rail 2 is provided with a chute 3, a sliding block 4 is clamped in the chute 3, and a left-right symmetrical locking piece 5 corresponding to a left-right symmetrical travel limit key 12 is arranged at the rear side of the sliding block 4; when the sliding block 4 moves to the rear seat 11, the locking piece 5 of the sliding block 4 is clamped and fixed with the travel limit key 12 of the rear seat 11.
Further, the diamond-shaped back missile wing structure has an unfolding form and a folding form;
the base 1, the guide rail 2 and the rear seat 11 are fixed in the elastic body;
In the deployed configuration, the first front missile wing 6, the second front missile wing 7, the first rear missile wing 9 and the second rear missile wing 10 extend out of the projectile bodies; the first front missile wing 6 and the second front missile wing 7 are bilaterally symmetrical, the first rear missile wing 9 and the second rear missile wing 10 are bilaterally symmetrical, the sliding block 4 is backwards, and the locking piece 5 of the sliding block 4 is clamped and fixed with the stroke limit key 12 of the rear seat 11; the sweepback angle of the front missile wing is larger than the sweepback angle of the rear missile wing;
In the folded configuration, the first front missile wing 6, the second front missile wing 7, the first rear missile wing 9 and the second rear missile wing 10 are overlapped from top to bottom and hidden in the missile body; the slide 4 is directed forward, close to the base 1.
The unfolding method of the cross-folded diamond-shaped back missile wing structure of the embodiment comprises the following steps:
s10, installing a diamond back missile wing structure in a hull of a gliding type aircraft according to the situation that the base 1 is arranged at the back of the front seat and the back seat 11;
S20, installing a cylinder in a body of a gliding type aircraft, wherein the cylinder takes fuel gas in the body as a power source, and fixedly connecting the cylinder with a sliding block 4;
S30, when the aircraft is unfolded, the sliding block 4 is pushed by the actuating cylinder to move backwards along the guide rail 2 to drive the first rear missile wing 9 and the second rear missile wing 10 to be unfolded; according to the motion principle of the connecting rod mechanism, the rear missile wing drives the front missile wing to open through the supporting column 8, and simultaneously, the first front missile wing 6 and the second front missile wing 7 rotate around the base 1; when the sliding block 4 moves to the position of the rear seat 11, the locking piece 5 presses the stroke limiting key 12 until the locking piece 5 is clamped and fixed with the stroke limiting key 12.
Further, a compression spring is arranged in the locking piece 5.
Although embodiments of the invention have been disclosed in the foregoing description and illustrated in the drawings, it will be understood by those skilled in the art that the present invention is not limited to the specific details and illustrations of features and steps set forth herein, and that all features of the invention disclosed, or steps of the method or process, except for mutually exclusive features and/or steps, may be combined in any manner without departing from the principles of the invention.
Claims (4)
1. The crossed and folded diamond back missile wing structure is characterized by comprising a front missile wing and a rear missile wing;
The front missile wing comprises a first front missile wing (6) and a second front missile wing (7) which are bilaterally symmetrical, wing roots of the first front missile wing (6) and the second front missile wing (7) are hinged and fixed on the base (1), the first front missile wing (6) is arranged on the base, and the second front missile wing (7) is arranged below the base;
The rear missile wing comprises a first rear missile wing (9) and a second rear missile wing (10) which are bilaterally symmetrical, wing roots of the first rear missile wing (9) and the second rear missile wing (10) are hinged and fixed on the sliding block (4), the first rear missile wing (9) is arranged above, and the second rear missile wing (10) is arranged below;
The first front missile wing (6) is arranged on the upper part, the first rear missile wing (9) is arranged on the lower part, the wing tip of the first front missile wing (6) extends out of the wing tip of the first rear missile wing (9), a supporting column (8) is arranged at the contact point of the first front missile wing (6) and the first rear missile wing (9), and the first front missile wing (6) and the first rear missile wing (9) are hinged on the supporting column (8);
The wing tip of the second front missile wing (7) extends out of the wing tip of the second rear missile wing (10), a supporting column (8) is arranged on the contact point of the second front missile wing (7) and the second rear missile wing (10), and the second front missile wing (7) and the second rear missile wing (10) are both hinged on the supporting column (8);
the front end of the guide rail (2) is fixed on the bottom surface of the base (1), the rear end of the guide rail (2) is fixed with a square rear seat (11), and the two sides of the rear seat (11) are provided with left-right symmetrical travel limit keys (12); a sliding groove (3) is arranged on the guide rail (2), a sliding block (4) is clamped in the sliding groove (3), and a locking piece (5) which is symmetrical left and right and corresponds to a stroke limit key (12) which is symmetrical left and right is arranged at the rear side of the sliding block (4); when the sliding block (4) moves to the rear seat (11), the locking piece (5) of the sliding block (4) is clamped and fixed with the travel limit key (12) of the rear seat (11).
2. The cross-folded diamond back missile wing structure according to claim 1, wherein the diamond back missile wing structure has an expanded configuration and a folded configuration;
the base (1), the guide rail (2) and the rear seat (11) are fixed in the elastic body;
in the unfolded configuration, the first front missile wing (6), the second front missile wing (7), the first rear missile wing (9) and the second rear missile wing (10) extend out of the projectile body; the first front missile wing (6) and the second front missile wing (7) are bilaterally symmetrical, the first rear missile wing (9) and the second rear missile wing (10) are bilaterally symmetrical, the sliding block (4) is backwards, and the locking piece (5) of the sliding block (4) is clamped and fixed with the stroke limit key (12) of the rear seat (11); the sweepback angle of the front missile wing is larger than the sweepback angle of the rear missile wing;
In the folded state, the first front missile wing (6), the second front missile wing (7), the first rear missile wing (9) and the second rear missile wing (10) are overlapped from top to bottom and are hidden in the missile body; the sliding block (4) is forwards close to the base (1).
3. A method of unfolding a cross-folded diamond back missile wing structure according to claim 2, wherein the method comprises the steps of:
s10, installing a diamond back missile wing structure in a hull of a gliding type aircraft according to the situation that the base (1) is arranged behind the front seat and the rear seat (11);
s20, installing a cylinder in a body of the gliding type aircraft, wherein the cylinder takes fuel gas in the body as a power source, and fixedly connecting the cylinder with a sliding block (4);
S30, when the aircraft is unfolded, the sliding block (4) is pushed by the actuating cylinder to move backwards along the guide rail (2) to drive the first rear missile wing (9) and the second rear missile wing (10) to be unfolded; according to the motion principle of the connecting rod mechanism, the rear missile wing drives the front missile wing to open through the supporting column (8), and meanwhile, the first front missile wing (6) and the second front missile wing (7) rotate around the base (1); when the sliding block (4) moves to the position of the rear seat (11), the locking piece (5) presses the travel limit key (12) until the locking piece (5) is clamped and fixed with the travel limit key (12).
4. A method of unfolding a cross-folded diamond back missile wing structure according to claim 3, characterized in that the locking member (5) is internally provided with a compression spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410572144.8A CN118129542B (en) | 2024-05-10 | 2024-05-10 | Cross-folded diamond-shaped back missile wing structure and unfolding method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410572144.8A CN118129542B (en) | 2024-05-10 | 2024-05-10 | Cross-folded diamond-shaped back missile wing structure and unfolding method thereof |
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| Publication Number | Publication Date |
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| CN118129542A true CN118129542A (en) | 2024-06-04 |
| CN118129542B CN118129542B (en) | 2024-07-16 |
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Citations (7)
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| US20100282917A1 (en) * | 2006-02-16 | 2010-11-11 | O'shea Hank | Aerial vehicle with variable aspect ratio deployable wings |
| CN103837045A (en) * | 2014-02-24 | 2014-06-04 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
| CN108100247A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | One kind can the long endurance unmanned vehicle layout of folding and unfolding VTOL |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
| US20190322365A1 (en) * | 2018-04-18 | 2019-10-24 | Bell Helicopter Textron Inc. | Aircraft having M-Wing and Gull Wing Configurations |
| CN111998738A (en) * | 2020-09-23 | 2020-11-27 | 中国工程物理研究院总体工程研究所 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
| US11613343B1 (en) * | 2019-07-12 | 2023-03-28 | Piasecki Aircraft Corporation | Unmanned flying wing aircraft having foldable and stackable wings |
-
2024
- 2024-05-10 CN CN202410572144.8A patent/CN118129542B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100282917A1 (en) * | 2006-02-16 | 2010-11-11 | O'shea Hank | Aerial vehicle with variable aspect ratio deployable wings |
| CN103837045A (en) * | 2014-02-24 | 2014-06-04 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
| CN108202861A (en) * | 2016-12-16 | 2018-06-26 | 中国航天科工飞航技术研究院 | A kind of fold mechanism and its control method for aircraft |
| CN108100247A (en) * | 2018-01-29 | 2018-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | One kind can the long endurance unmanned vehicle layout of folding and unfolding VTOL |
| US20190322365A1 (en) * | 2018-04-18 | 2019-10-24 | Bell Helicopter Textron Inc. | Aircraft having M-Wing and Gull Wing Configurations |
| US11613343B1 (en) * | 2019-07-12 | 2023-03-28 | Piasecki Aircraft Corporation | Unmanned flying wing aircraft having foldable and stackable wings |
| CN111998738A (en) * | 2020-09-23 | 2020-11-27 | 中国工程物理研究院总体工程研究所 | Lock hook type cylinder shooting patrol missile wing unfolding and locking mechanism |
Non-Patent Citations (1)
| Title |
|---|
| 李永红;黄勇;陈建中;苏继川;: "曲面形栅格翼气动特性研究", 空气动力学学报, no. 04, 15 August 2016 (2016-08-15), pages 536 - 540 * |
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| Publication number | Publication date |
|---|---|
| CN118129542B (en) | 2024-07-16 |
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