High-strength wing skid integrated fusion structure
Through the integrated fusion structure of high-strength wingskids and combined with the design of thrust rods and flanges, the problems of single-track vibration overload and dual-track aerodynamic resistance are solved, the stability and thrust-to-weight ratio of rocket skis are improved, and the large load and ultra-high-speed wings are met. Requirements for rocket sled tests.
Patent Information
- Application Number
- CN202411637901.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-15
- Publication Date
- 2024-12-31
AI Technical Summary
In the prior art, the monorail rocket ski has large vibration overload, the dual-rail rocket ski has a large aerodynamic resistance, small thrust-to-weight ratio and high test costs, which cannot meet the needs of large-load and ultra-high-speed wing rocket ski tests.
Adopt a high-strength wingskid integrated fusion structure, including thrust sled, product sled and flange structure, which is connected to the hollow cylinder of the flange through the thrust rod. The flange has a wing design and sliding boots, and the main beam and product sled are integrated processing, optimized Pneumatic transmission routes and reduce the risk of weld connections.
It improves the overall stiffness and strength of the rocket ski system, enhances system stability, reduces the quality and complexity of the ski body, increases the thrust-to-weight ratio, reduces vibration, and meets the needs of large-load and ultra-high-speed wing rocket ski tests.
Smart Images
Figure CN119223109A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of military product range test and mainly relates to a high-strength wing-shaped rocket sled structure; Background Art
[0002] The rocket sled is a large-scale ground dynamic test facility, powered by a rocket engine. The rocket sled is used as a carrier to carry the test object, and it slides at high speed along a special slide rail. It can simulate the dynamic working conditions of the test object's actual flight on the ground and assess its working efficiency. The rocket sled test breaks through the constraints of the size and weight of the test object, and can achieve the effective recovery of the test object. It is the most reliable ground test method connecting heaven and earth. The rocket sled can increase the test object to the required speed, acceleration and other conditions according to the pre-designed conditions, and can test the dynamic parameters of the test object through the sled-mounted test equipment and ground test equipment, and can recover the test object non-destructively in orbit through a specially designed braking device. The rocket sled test mainly simulates the dynamic environment during flight to solve many technical problems related to high speed and high acceleration conditions in the development of aircraft, missiles, aerospace vehicles, etc. Rocket sled tests are very flexible and are basically not limited by the volume and weight of the test pieces. They can be used to test anything from full-size aircraft or missile parts to small components such as electrical appliances. The weight of the rocket sled can be as small as a few dozen kilograms or as large as more than ten tons. The rocket sled's gliding speed can range from subsonic to transonic, supersonic, and even more than seven times the speed of hypersonic. At present, for penetrating and armor-piercing warhead rocket sled tests, a single-track rocket sled system is used under low loads. It has the advantages of low resistance, high thrust-to-weight ratio, and low test cost, but it has high vibration overloads. Under high loads, a double-track rocket sled solution is generally used. The double-track rocket sled system has good stability, high aerodynamic resistance, low thrust-to-weight ratio, and low vibration overloads, but it has high test costs. In the current domestic multi-stage propulsion wing rocket sled tests, the product sled adopts a wing structure, and the thrust sled adopts a monorail structure or a wing structure. Although it can meet the needs of most rocket sled tests, for large-load, ultra-high-speed wing rocket sled tests, the monorail structure cannot meet the needs of wing rocket sled tests, and the wing structure is too complex, and the high mass will lead to a decrease in the thrust-to-weight ratio of the rocket sled system. Therefore, there is an urgent need for a wing-sled integrated fusion structure that can improve the thrust-to-weight ratio, effectively reduce the vibration of the sled body, and increase the structural strength of the sled body to meet the needs of scientific research experiments. Summary of the invention
[0003] In order to overcome the deficiencies of the prior art and solve the problems of large vibration overload of the single-track rocket sled and large aerodynamic resistance, low thrust-to-weight ratio and high testing cost of the double-track rocket sled in the prior art, the present invention provides a high-strength wing-skid integrated fusion structure.
[0004] A high-strength wing-skid integrated fusion structure comprises a thrust sled 1, a product sled 4 and a wing structure; the thrust sled 1 and the product sled 4 both comprise a front snap ring fixing structure and a rear snap ring fixing structure; the wing structure comprises a thrust rod 2 and a wing 3; the thrust rod 2 is a hollow cylinder; one end face of the thrust rod 2 is fixedly connected to the engine front snap ring fixing structure of the thrust sled 1; the other end face of the thrust rod 2 is fixedly connected to the rear snap ring fixing structure of the product sled 4; the thrust sled 1, the thrust rod 2 and the product sled 4 constitute a monorail rocket sled; a wing 3 is arranged on one side of the forward direction of the thrust rod 2; the wing 3 is an airfoil structure; a sliding shoe is arranged at the wingtip end of the wing 3.
[0005] Furthermore, the side wing 3 includes an upper wing surface, a lower wing surface, a main beam 7, a front secondary beam 6, a second front secondary beam 6', a rear secondary beam 5, a first rear secondary beam 5', a rib 8 and a skin; the lower wing surface of the side wing 3 is parallel to the horizontal plane; the upper wing surface of the side wing 3 is a curved surface; the upper and lower wing surfaces are covered with skin; the sweep angle of the side wing 3 is α; the main beam 7 is arranged at 60% of the chord direction of the side wing 3; the rear secondary beam 5 is arranged at 100% of the chord direction of the side wing 3; the first rear secondary beam 5' is arranged at 75% of the chord direction of the side wing 3; the front secondary beam 6 is arranged at 15% of the chord direction of the side wing 3; the side wing 3 is arranged at 30% of the chord direction a second front secondary beam 6'; a chord-wise wing rib 8 is arranged between the main beam 7, the front secondary beam 6 and the rear secondary beam 5; the main beam 7 is fixedly connected to the rear clamp fixing structure of the product sled 4; the front secondary beam 6 and the second front secondary beam 6' are both fixedly connected to the longitudinal beam of the product sled 4; the rear secondary beam 5 is fixedly connected to the engine front clamp fixing structure of the thrust sled 1; the first rear secondary beam 5' is fixedly connected to the thrust rod 2; the thickness of the upper wing surface gradually decreases from the wing root to the wing tip along the wingspan direction; the thickness of the upper wing surface gradually decreases to zero along the chord direction to the leading edge direction with the main beam 7 as the starting point; the thickness of the upper wing surface gradually decreases along the chord direction to the trailing edge direction with the main beam 7 as the starting point.
[0006] Furthermore, the maximum thickness of the wing root of the side wing 3 does not exceed the height of the longitudinal beam of the product skid.
[0007] Furthermore, the angle α is 66 degrees.
[0008] Furthermore, the wingspan is 1.5 meters.
[0009] Furthermore, the wing root chord length is 1.2 meters.
[0010] Furthermore, the main beam 7 and the product skid are processed in an integrated manner, which not only optimizes the transmission path of the aerodynamic force on the wing, but also reduces the risk of connecting the main beam through welds.
[0011] Compared with the prior art, the advantages of the present invention are:
[0012] 1. The advantage of the present invention is that it adopts an integrated fusion structure, which can integrate the product skid, thrust skid, thrust rod and wing structure into one, thereby improving the overall rigidity and strength of the skid body and effectively improving the stability of the system.
[0013] 2. The advantage of the present invention is that compared with the conventional wing-shaped skid structure, the integrated fusion structure of the wing skid optimizes the product skid and the thrust skid from having one wing structure each to having one wing structure shared by both, thereby reducing the mass and complexity of the system and improving the thrust-to-weight ratio of the system. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the integrated fusion structure of the wing skid of the present invention;
[0015] Figure 2 It is a schematic diagram of the wing structure;
[0016] Figure 3 A schematic diagram of the thrust sled head of the present invention;
[0017] Figure 4 Schematic diagram of the thrust rod of the present invention;
[0018] In the figure, 1 is the thrust sled, 2 is the thrust rod, 3 is the side wing, 4 is the product sled, 5 is the rear secondary beam, 5' is the first rear secondary beam, 6 is the front secondary beam, 6' is the second front secondary beam, 7 is the main beam, 8 is the wing rib, 9 is the lower half of the front clamp ring of the thrust sled, 10 is the thrust rod, DETAILED DESCRIPTION
[0019] A high-strength wing sled integrated fusion structure, comprising a thrust sled 1, a product sled 4 and a wing structure; the thrust sled 1 and the product sled 4 both comprise a front snap ring fixing structure and a rear snap ring fixing structure; the wing structure comprises a thrust rod 2 and a wing 3; the thrust rod 2 is a hollow cylinder; one end face of the thrust rod 2 is fixedly connected to the engine front snap ring fixing structure of the thrust sled 1; the other end face of the thrust rod 2 is fixedly connected to the rear snap ring fixing structure of the product sled 4; the thrust sled 1, the thrust rod 2 and the product sled 4 constitute a monorail rocket sled; a wing 3 is arranged on one side of the thrust rod 2 in the forward direction; the wing 3 is an airfoil structure; a sliding shoe is arranged at the wing tip end of the wing 3;
[0020] The side wing 3 comprises an upper wing surface, a lower wing surface, a main beam 7, a front secondary beam 6, a rear secondary beam 5, a rib 8 and a skin;
[0021] The lower wing surface of the side wing 3 is parallel to the horizontal plane; the upper wing surface of the side wing 3 is a curved surface; a main beam 7 is arranged at 60% of the chord direction of the side wing 3; a rear secondary beam 5 is arranged at 100% of the chord direction of the side wing 3; a first rear secondary beam 5' is arranged at 75% of the chord direction of the side wing 3; a front secondary beam 6 is arranged at 15% of the chord direction of the side wing 3; a second front secondary beam 6' is arranged at 30% of the chord direction of the side wing 3; a chord-wise rib 8 is arranged between the main beam 7, the front secondary beam 6 and the rear secondary beam 5; the main beam 7 is fixedly connected to the rear clamp fixing structure of the product skid 4; the front secondary beam 6 and the second front secondary beam 6' are both fixedly connected to the longitudinal beam of the product skid 4; the rear secondary beam 5 is fixedly connected to the engine front clamp fixing structure of the thrust skid 1; the first rear secondary beam 5' is fixedly connected to the thrust rod 2; the thickness of the upper wing surface gradually decreases from the wing root to the wing tip along the wingspan direction; the thickness of the upper wing surface gradually decreases to zero along the chord direction to the leading edge direction with the main beam 7 as the starting point; the thickness of the upper wing surface gradually decreases along the chord direction to the trailing edge direction with the main beam 7 as the starting point; the maximum thickness of the wing root of the side wing 3 does not exceed the height of the longitudinal beam of the product skid; the upper and lower wing surfaces are covered with skin;
[0022] This connection method disperses the aerodynamic force on the wing to the product skid and thrust rod 2. Since the product skid and thrust rod have high rigidity, the safety and reliability of the wing structure in orbit are ensured. The wing 3 provides downward pressure, and during the operation of the rocket sled, the sled structure is pressed on the track, thereby achieving the purpose of reducing vibration.
[0023] The sweep angle of the wing 3 is α;
[0024] The α is 66 degrees;
[0025] The wingspan is 1.5 meters;
[0026] The wing root chord length is 1.2 meters;
[0027] The main beam 7 is integrated with the product skid, which not only optimizes the transmission path of the aerodynamic force on the wing, but also reduces the risk of connecting the main beam through welds;
[0028] The high-strength wing skid integrated fusion structure is applied to a double-track track, and a thrust skid 1, a thrust rod 2 and a product skid 4 are arranged on one track of the double-track track; the other track of the double-track track is connected to the sliding shoe of the wing tip of the side wing 3;
[0029] The present invention is further described below in conjunction with the accompanying drawings and embodiments.
[0030] The present invention combines the characteristics of low aerodynamic resistance of a single track and good stability of a double track to design an asymmetric wing-shaped rocket sled test platform, with a single track as the main load, and adopts an embedded connection method to enhance the connection strength between the wing and the main structure of the rocket sled. The wing-shaped sled structure is between the single track sled and the double track sled, integrating the advantages of both the single track rocket sled and the double track rocket sled, and is a cheap and effective rocket sled test method and test device for the terminal effect of the missile ignition system.
[0031] The purpose of the present invention is to solve the problem that in the current multi-stage propulsion wing-shaped rocket sled test, the product sled and the thrust sled are usually designed and arranged separately. When the thrust sled is a single-track structure, it has a bad mechanical environment and the sled body is prone to instability and damage. When the thrust sled is a wing-shaped structure, the system mass is increased, resulting in a relatively low thrust-to-weight ratio of the rocket sled system. Therefore, a product sled, thrust sled, and side wing integrated fusion structure is designed. The structure has high rigidity and strength, and reduces the mass of the sled body. It can be applied to the terminal effect wing-shaped rocket sled test of various missile and rocket ignition systems, providing a more stable propulsion force for the entire system to meet the needs of the wing-shaped rocket sled test.
[0032] The present invention is a wing-skid integrated fusion structure, which is mainly used for multi-stage propulsion wing-shaped rocket sled testing. It is a new structure connecting a product sled, a thrust sled and a side sliding shoe. Its integrated structure inherits the advantages of a conventional multi-stage propulsion wing-shaped rocket sled, reduces the structural complexity, improves the system thrust-to-weight ratio, and increases the system stability.
[0033] The present invention is described in detail below:
[0034] The present invention is a wing-skid integrated fusion structure, including an integrated design of a wing structure, a thrust rod, a product skid and a thrust sled, and has high overall stiffness and strength. The structure is mainly used for multi-stage propulsion wing-shaped rocket sled testing, and its characteristic is that after using the structure, the product skid and the thrust sled are connected as a whole through the thrust rod and the wing structure, thereby increasing the stability of the entire rocket sled system.
[0035] The present invention is also realized in that: the side wing structure shape is aerodynamically optimized and finally determines a large wing aerodynamic shape with a wingspan of 1.5 meters and a root chord length of 1.2 meters. By adjusting the side wing shape dimensions, it is ensured that the downward pressure on the side wing structure during the on-orbit operation of the rocket sled can steadily press the sled structure on the track, reduce the overall vibration level of the sled structure, and improve the safety and stability of the sled structure.
[0036] The present invention is also realized in that the wing structure includes a main beam, a front secondary beam, a rear secondary beam, a wing rib and a skin, and the whole is a welded structure. The main beam separates the wing into two parts, the front secondary beam is embedded in the product skid beam as a whole, and the rear secondary beam is embedded in the thrust rod, so that the aerodynamic force exerted on the wing is dispersedly transmitted to the product skid beam and the thrust rod, which are structural parts with large overall rigidity, ensuring the safety and reliability of the wing structure in orbit.
[0037] The present invention is also realized in that: the main beam is a 12mm thick BS 960 steel plate, which is processed as a whole with the front support plate of the rear clamp ring of the product skid, which not only optimizes the transmission path of the aerodynamic force exerted on the wing, but also reduces the risk of connecting the main beam through welds.
[0038] The present invention is also achieved in that: the secondary beam and the rib are BS 960 steel plates with a thickness of 4 mm, and the upper part thereof is designed in a serrated shape. In order to reduce the influence of welding deformation, the skin can be divided along the secondary beam when the skin is finally welded, ensuring that the serrated structure matches the reserved holes on the skin.
[0039] The present invention is also implemented in that: the lower half ring of the front retaining ring of the thrust sled engine is of semi-closed design, the thrust rod is a structural member, the rear of the thrust rod is connected to the lower half ring of the front retaining ring of the engine, and the front of the thrust rod is connected to the rear retaining ring support plate at the tail of the product sled, ensuring that the engine thrust received by the thrust sled during the on-orbit operation of the rocket sled is effectively transmitted to the product sled.
[0040] The present invention is also implemented in that: the lower half ring of the front retaining ring of the thrust sled is a slotted structure, which is used to install the engine head anti-recoil ring to prevent the engine from falling out backwards when the thrust sled engine decelerates during on-orbit operation.
[0041] Example:
[0042] In a certain wing-shaped warhead terminal effect rocket sled test, according to the overall test requirements, the test adopts two-stage propulsion, the first-stage thrust sled is a monorail sled, the second-stage sled and the product sled adopt a high-strength wing sled integrated fusion structure, and the test object is fixed on the main rail sled body. Through rigidity and dynamics analysis, it is determined that the rigidity and strength of the present invention meet the test requirements. During the test, the test object and the sled body run to the end of the trajectory to achieve the test purpose.
[0043] In summary, the high-strength wing sled integrated fusion structure of the present invention is simple, can effectively improve the thrust-to-weight ratio, effectively reduce the vibration of the sled body, and increase the structural strength of the sled body. The airfoil structure can be adjusted according to the specific requirements of the test to improve the aerodynamic force distribution and meet the needs of the rocket sled test.
[0044] Through the application of the present invention, the smooth progress of a rocket sled test of a terminal effect of a certain wing-shaped warhead is ensured, and reliable technical support is provided for the test of a large-mass supersonic wing-shaped rocket sled.
Claims
1. A high-strength wing-skid integrated fusion structure, comprising a thrust skid (1) and a product skid (4), wherein the thrust skid (1) and the product skid (4) both comprise a front snap ring fixing structure and a rear snap ring fixing structure; characterized in that: The invention comprises a wing structure; the wing structure comprises a thrust rod (2) and a wing (3); the thrust rod (2) is a hollow cylinder; one end face of the thrust rod (2) is fixedly connected to the engine front clamping ring fixing structure of the thrust sled (1); the other end face of the thrust rod (2) is fixedly connected to the rear clamping ring fixing structure of the product sled (4); the thrust sled (1), the thrust rod (2) and the product sled (4) constitute a monorail rocket sled; a wing (3) is arranged on one side of the thrust rod (2) in the forward direction; the wing (3) is an airfoil structure; and a sliding shoe is arranged at the wing tip end of the wing (3).
2. The high-strength wing-skid integrated fusion structure according to claim 1, characterized in that: The side wing (3) comprises an upper wing surface, a lower wing surface, a main beam (7), a front secondary beam (6), a second front secondary beam (6'), a rear secondary beam (5), a first rear secondary beam (5'), a rib (8) and a skin; the lower wing surface of the side wing (3) is parallel to a horizontal plane; the upper wing surface of the side wing (3) is a curved surface; the upper wing surface and the lower wing surface are covered with skin; the sweep angle of the side wing (3) is α; the main beam (7) is arranged at a position of 60% of the chord direction of the side wing (3); the rear secondary beam (5) is arranged at a position of 100% of the chord direction of the side wing (3); the first rear secondary beam (5') is arranged at a position of 75% of the chord direction of the side wing (3); the front secondary beam (6) is arranged at a position of 15% of the chord direction of the side wing (3); the rear secondary beam (5') is arranged at a position of 30% of the chord direction of the side wing (3) a second front secondary beam (6'); chord-wise wing ribs (8) are arranged between the main beam (7), the front secondary beam (6) and the rear secondary beam (5); the main beam (7) is fixedly connected to the rear clamping ring fixing structure of the product skid (4); the front secondary beam (6) and the second front secondary beam (6') are both fixedly connected to the longitudinal beam of the product skid (4); the rear secondary beam (5) is fixedly connected to the engine front clamping ring fixing structure of the thrust skid (1); the first rear secondary beam (5') is fixedly connected to the thrust rod (2); the thickness of the upper wing surface gradually decreases from the wing root to the wing tip along the wingspan direction; the thickness of the upper wing surface gradually decreases to zero along the chord direction to the leading edge direction with the main beam (7) as the starting point; the thickness of the upper wing surface gradually decreases along the chord direction to the trailing edge direction with the main beam (7) as the starting point.
3. The high-strength wing-skid integrated fusion structure according to claim 2, characterized in that: The maximum thickness of the wing root of the side wing (3) does not exceed the height of the longitudinal beam of the product skid.
4. The high-strength wing-skid integrated fusion structure according to claim 2, characterized in that: The α is 66 degrees.
5. The high-strength wing-skid integrated fusion structure according to claim 2, characterized in that: The wingspan is 1.5 meters.
6. The high-strength wing-skid integrated fusion structure according to claim 2, characterized in that: The wing root chord length is 1.2 meters.
7. The high-strength wing-skid integrated fusion structure according to claim 2, characterized in that: The main beam (7) and the product skid are processed in an integrated manner.