Force storage adaptation device for simulating projectile launching
By designing a power-accelerating adaptation device for the simulated missile launch, and utilizing shear pins and guiding inclined surfaces to cut the shear pins, the problem of uncontrollable booster thrust was solved, enabling the simulated missile to take off safely and fly stably, thus ensuring flight safety.
Patent Information
- Application Number
- CN202422697063.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-06
- Publication Date
- 2025-10-31
- Estimated Expiration
- 2034-11-06
AI Technical Summary
In existing simulated missile launch systems, the thrust of the booster is uncontrollable, resulting in insufficient or overloaded takeoff thrust, posing safety hazards and making it difficult to ensure stable climb and cruise of the simulated missile during the takeoff phase.
A power-accelerating adapter device for simulating missile launch was designed, comprising an adapter and a shear pin. The shear pin is cut off by a guiding inclined surface. After the shear pin breaks, it is avoided by a shearing rod and a swing rod, ensuring an instantaneous increase in thrust and enabling the safe takeoff of the simulated missile.
The thrust during takeoff of the simulated missile was increased to ensure flight safety. The shear pins broke and separated reliably, avoiding the risk of the simulated missile stalling and crashing, and achieving safe separation of the simulated missile from the booster.
Smart Images
Figure CN223500251U_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of simulated missile technology, and specifically relates to a power-accelerating adapter device for simulating missile launch. Background Technology
[0002] The adapter is the connecting carrier between the booster and the target missile (or missile). The booster is supported by the adapter at the rear of the center of mass of the simulated missile's belly. When the booster is ignited, the thrust generated is transmitted to the simulated missile along the thrust line through the adapter and the center of mass of the simulated missile, providing thrust for the simulated missile's climb during the takeoff phase.
[0003] The existing booster installation process has safety hazards. The initial takeoff thrust depends entirely on the booster parameters, without any power storage or safety measures. The simulated missile's takeoff thrust is set at 5500N. Only by exceeding this thrust and continuously accelerating to the booster's customized limit can the missile's wings generate lift to maintain cruise under engine thrust at high speed. At the moment of booster ignition, the thrust generated in the initial stage of fuel combustion is uncontrollable. If the booster thrust just offsets the missile's weight before propelling it off the delivery platform, but fails to exceed 5500N at takeoff and continuously increase to improve the missile's speed, it could cause a stall and crash, hindering the widespread use of boosters. Summary of the Invention
[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide a power-accelerating adapter for simulating missile launch.
[0005] The technical solution adopted in this invention is: a power-accumulating adapter for simulating missile launch, the key technical points of which are: an adapter, the front end of which is machined with a duckbill-shaped protrusion adapted to the interface of the simulated missile's belly, the rear end of which is machined with a shear pin mounting hole, the center edge of which is machined with a guiding inclined surface, and the guiding inclined surface is located on both sides of the cut of the shear pin inserted into the shear pin mounting hole. When subjected to thrust, the guiding inclined surface acts as a cutting edge that cuts off the cut of the shear pin and contacts the cut of the shear pin; shearing rods are respectively installed on both sides of the shear pin to cause the broken shear pin to unfold to both sides to avoid collision.
[0006] In the above scheme, the shearing pin includes a fine-pitch screw rod with a shearing notch in the middle. Fine-pitch nuts are threaded to both ends of the fine-pitch screw rod and are tightened and fixed by the fine-pitch nuts respectively.
[0007] In the above scheme, the lower end of the shearing rod is inserted into the mounting hole of the swing arm and locked by adjusting the length with a wing nut.
[0008] In the above scheme, a center of gravity adjustment slot is also provided inside the adapter at the rear end of the shear pin mounting hole. The longitudinal center of gravity of the adapter is made to coincide with the thrust line by adjusting the depth of the center of gravity adjustment slot.
[0009] In the above scheme, the swing arm is equipped with a torsion spring for safe avoidance after the shear pin breaks.
[0010] In the above scheme, a mechanical interface for connecting to the booster is also machined at the end of the adapter.
[0011] In the above scheme, the shearing rod is arranged with an outward tilt, and its force direction is parallel to the thrust line.
[0012] The beneficial effects of this invention are as follows: The power-accumulating adapter for the simulated missile launch includes an adapter. The front end of the adapter is machined with an adapter interface that has a duckbill-shaped protrusion. A shear pin mounting hole is provided behind the adapter interface. The shear pin is installed in the shear pin mounting hole. The guide inclined surface provided in the shear pin mounting hole is used as a cutting edge to cut the shear pin. When the booster thrust increases to the set shearing stress of the shear pin, the shear pin breaks and releases the simulated missile, which improves the instantaneous thrust of the simulated missile during takeoff and ensures flight safety and reliability. Attached Figure Description
[0013] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0014] Figure 1 A front view of a power storage adapter device for a simulated projectile;
[0015] Figure 2 A side view of a power storage adapter device for a simulated projectile;
[0016] Figure 3 A cross-sectional view of the shear section of a simulated projectile's power storage adapter device;
[0017] Figure 4 This is the front view of the adapter of this utility model;
[0018] Figure 5 This is a top view of the adapter of this utility model;
[0019] Figure 6 This is a side view of the adapter of this utility model;
[0020] Figure 7 This is a cross-sectional view of the shear hole in the adapter of this utility model;
[0021] Figure 8 This is the main view of the shear pin of this utility model;
[0022] Figure 9 This is the main view of the shearing tie rod of this utility model;
[0023] Figure 10 This is a top view of the shear tie rod of this utility model;
[0024] Figure 11 This is the main view of the swing arm of this utility model;
[0025] Figure 12 This is a side view of the swing arm of this utility model;
[0026] Figure 13 This is a top view of the swing arm of this utility model;
[0027] The serial numbers are explained as follows: 1. Adapter, 2. Shear pin, 3. Shear rod, 4. Swing rod, 5. Torsion spring, 6. Adapter interface, 7. Shear pin mounting hole, 8. Mechanical interface, 9. Center of gravity adjustment slot, 10. Guide tilt surface. Detailed Implementation
[0028] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the following description is provided in conjunction with the accompanying drawings. Figures 1-13 The present invention will be further described in detail below with reference to specific embodiments.
[0029] This embodiment provides a power-charging adapter for simulating projectile launch, including an adapter 1 manufactured by CNC forming. The front end of the adapter 1 has a duckbill-shaped protrusion-shaped adapter interface 6. The adapter interface 6 is connected to the target projectile using a wedge-shaped hinge structure, ensuring that the adapter can autonomously fall and separate from the target projectile. A shear pin mounting hole 7 is machined slightly behind the front end of the adapter 1, and a shear pin 2 is inserted into the shear pin mounting hole 7. In this embodiment, a [missing information - likely a design element] is machined at the center edge of the shear pin mounting hole 7. Diffusion The guide inclined surface 10 (firstly, two pyramidal bodies are formed inside the adapter, and one edge of each pyramidal body is taken as the guide inclined surface 10. The guide inclined surface 10 adopts an inclined angle similar to that of the shearing rod. The inclined surface is machined flat to ensure smooth and reliable guidance). The guide inclined surface 10 acts as a cutting edge, which contacts the cutting edge of the shearing pin after being subjected to thrust and cuts off the cutting edge of the shearing pin.
[0030] In this embodiment, a center of gravity adjustment slot 9 is machined inside the adapter 1 located at the rear end of the shear pin mounting hole 7. There can be multiple center of gravity adjustment slots 9. The depth of the center of gravity adjustment slots 9 is controlled to ensure that the longitudinal center of gravity of the adapter coincides with the thrust. A mechanical interface 8 with fine thread is machined on the inner surface of the inner wall of the tail end of the adapter 1. The mechanical interface 8 is locked to the booster by a threaded connection.
[0031] In this embodiment, the shear pin 2 is inserted into the shear hole 7 of the adapter. The shearing rod 3 is installed at both ends of the shear pin 2 and locked with nuts. The other end of the shearing rod 3 is inserted into the mounting hole of the swing rod 4 and locked with a wing nut to adjust the length. The torsion spring 5 is installed in the sinker of the swing rod 4. When the shear pin breaks, the separation rod and the broken shear pin quickly unfold along both sides of the guide inclined surface 10. When it unfolds to the limit position, the rebound generated is constrained by the torsion of the pre-installed reverse torsion spring, preventing the rebounding rod from colliding with the projectile. In this embodiment, the shearing rod 3 is arranged with an outward swing inclination, and its force direction should be parallel to the thrust line.
[0032] The working principle of the power-accumulating adapter device for the simulated missile launch in this embodiment is as follows: First, the front screw of the booster (not shown) is connected to the mechanical interface 8 of the adapter 1. Then, the adapter interface 6 is inserted into the slot on the belly of the target missile. The booster tail nozzle is placed on the booster bracket. The shear pin 2 is inserted into the shear hole 7 of the adapter. The two ends of the shear pin 2 are fixed to the launch platform by the shearing rod 3 and the swing rod 4. When the booster ignites and the thrust reaches the shear stress of the shear pin 2 (e.g., 5500N), the shear pin 2 breaks, releasing the simulated missile for takeoff. The guide inclined surfaces 10 on both sides of the shear pin mounting hole 7 and the auxiliary shearing rod 3 quickly separate the broken shear pin 2 to both sides to avoid it. After the booster fuel burns out and loses power, the booster and adapter 1 will flip downwards and detach from the simulated missile by the torsional torque generated by their own weight. This embodiment can be implemented by replacing the shear pin with one that has the corresponding shear stress according to different takeoff thrusts. The ultimate thrust of the booster is not limited here.
[0033] The power storage adapter used in this embodiment has completed design, development, and prototype production. Ground-based testing has been completed. The adapter is simple and convenient to install and operate, fully meeting the requirements of the simulated missile and booster. In the nine completed simulated missile launch tests, the missile's launch phase was stable with sufficient power storage. Separation after the shear pin broke was reliable. The adapter safely separated from the simulated missile during the booster's final thrust phase, achieving the intended objectives. Visual inspection and structural measurements of the recovered adapter confirmed its structural integrity, showing no deformation or damage due to the immense thrust experienced during the simulated missile launch. The parameter settings for the power storage verification test in this embodiment are as follows:
[0034] The parameters of the power storage adapter are set as follows: a. Material grade: 45 steel (HRC35); b. Total mass: 5.38kg±0.2kg; c. Theoretical centroid: X=165mm, Y=0, Z=0; d. Mechanical interface: M40×2 fine thread.
[0035] The shear pin parameters are set as follows: a. Material grade: 5A06; b. Shear diameter: ∅6mm±0.01mm; c. Release shear force: 5500N±250N.
[0036] To verify the feasibility of this embodiment, a shear pin tensile test fixture was designed according to the structure of the target missile launch platform. The shear separation structure in the fixture is the same as the power storage adapter device for the simulated missile launch in this embodiment. During the test phase, 72 shear pins were processed and manufactured, of which 62 were used for shear tests. The test data confirmed that the shear stress values of the shear pins were real and reliable, ensuring that the instantaneous thrust of the target missile during takeoff was not less than 5500N. The remaining shear pins have been used for target missile launch.
[0037] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A power-accelerating adapter for simulating projectile launch, characterized in that, The device includes an adapter. The front end of the adapter has a duckbill-shaped protrusion that adapts to the interface of a simulated projectile belly. The rear end of the adapter has a shear pin mounting hole. The shear pin is installed in the shear pin mounting hole. A guide inclined surface is machined on the outer center edge of the shear pin mounting hole, and the guide inclined surface is located on both sides of the cut of the shear pin mounting hole. When the shear pin is subjected to thrust, the guide inclined surface will act as the shearing edge of the shear pin and contact the broken surface of the shear pin. Shearing rods are installed on both sides of the shear pin to allow the broken shear pin to spread out to the sides for clearance.
2. The power-accelerating adapter for simulating missile launch as described in claim 1, characterized in that, The shearing pin includes a fine-pitch screw with a shearing notch in the middle, and fine-pitch nuts are threaded to both ends of the fine-pitch screw and locked in place by the fine-pitch nuts respectively.
3. The power-accelerating adapter for simulating missile launch as described in claim 1, characterized in that, The lower end of the shearing rod is inserted into the mounting hole of the swing arm and locked by adjusting the length with a wing nut.
4. The power-accelerating adapter for simulating missile launch as described in claim 1, characterized in that, Inside the adapter at the rear end of the shear pin mounting hole, there is also a center of gravity adjustment slot. By adjusting the depth of the center of gravity adjustment slot, the longitudinal center of gravity of the adapter is made to coincide with the thrust line.
5. The energy storage adapter for simulating missile launch as described in claim 1, characterized in that, The swing arm is equipped with a torsion spring for safe avoidance after the shear pin breaks.
6. The energy storage adapter for simulating missile launch as described in claim 1, characterized in that, A mechanical interface for connecting to the booster is also machined at the end of the adapter.
7. The energy storage adapter for simulating missile launch as described in claim 1, characterized in that, The shearing rod is arranged with an outward tilt, and its force direction is parallel to the thrust line.