Tilted launch support orientation device and launch method using same
By combining guide rails, adapters, and missile body supports, the problems of nose-down disturbance and sinking during inclined launch of rockets and missiles are solved, achieving a compact and reliable inclined launch effect, and improving launch safety and control efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF TECH
- Filing Date
- 2022-09-08
- Publication Date
- 2026-06-09
AI Technical Summary
Existing inclined launch systems for rockets and missiles have difficulty simultaneously suppressing nose-down disturbances and descent in their support structure design, resulting in large initial disturbances, complex structures, and reduced flight control efficiency.
The system employs a combination structure of guide rails, adapters, and projectile feet. The guide rails cooperate with the projectile feet, the adapters provide upward support, and the projectile feet provide downward support, thus constraining the projectile's nose-down disturbance and sinking.
It effectively suppresses nose-down disturbance and descent during the inclined launch of rockets and missiles. It has a compact structure, reliable operation, and minimal impact on missile flight, thus improving the safety and reliability of launch.
Smart Images
Figure CN116294799B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to rocket and missile launching devices, mainly used to achieve support and orientation of rocket and missile launching devices, and to suppress sinking and nose-down disturbances caused by tilted launches. Background Technology
[0002] Inclined launch, due to its high aiming accuracy and the elimination of complex turning control algorithms and propulsion systems, has always been an important method for launching rockets and missiles. During inclined launch, the directional support method has a significant impact on the initial disturbance of the rocket or missile launch, thereby affecting subsequent flight trajectory and control efficiency.
[0003] Currently, the directional supports for inclined launches of rockets and missiles mainly employ two forms: non-simultaneous deorbiting and simultaneous deorbiting. During non-simultaneous deorbiting, after the missile's center of mass leaves the directional support structure, the torque generated by the missile's gravity at the rear support position causes the rocket or missile to experience a significant nose-down angle and angular velocity, resulting in substantial initial launch disturbance. During simultaneous deorbiting, the support structure slides away simultaneously as the missile moves within the launch device, effectively reducing nose-down disturbance. However, since the missile remains inside the launch device after the rear support deorbits, the overall sinking of the missile under gravity requires a large clearance distance from the launch device, necessitating a larger structural dimension in the vertical direction. The nose-down disturbance of non-simultaneous deorbiting and the sinking distance of simultaneous deorbiting have become crucial factors restricting the design of inclined launch systems for rockets and missiles.
[0004] Commonly used support structures for launch devices include guide legs, adapters, and missile belts. Traditional support structures often employ a relatively simple support form. During launch, the support load on the missile body is mainly used to balance gravity and constrain motion disturbances outside the launch direction. There is little consideration for the comprehensive application of the support structure and support load. Regardless of the single form of support structure used, it is difficult to simultaneously suppress launch nose-down disturbances and sinking.
[0005] For the reasons mentioned above, the inventors have conducted in-depth research on tilted launch mechanisms in order to design a tilted launch support orientation device and a launch method using the same device that can solve the above problems. Summary of the Invention
[0006] To overcome the above problems, the inventors conducted intensive research and designed an inclined launch support orientation device and a launch method using it. In this device, by setting up a specially designed guide rail, adapter, and projectile support feet, the guide rail and projectile support feet cooperate to constrain the lateral movement and circumferential rotation of the projectile. The adapter provides an upward support force to the projectile, and the projectile support feet provide a downward support force to the projectile, thereby constraining the projectile's nose-down disturbance and sinking amount. It has the characteristics of simple structure, reliable operation, and minimal impact on the projectile's aerodynamics, and can provide a guarantee for safe and reliable inclined launch; thus, the present invention is completed.
[0007] Specifically, the purpose of this invention is to provide an inclined launch support orientation device, which includes a guide rail 2, on which an adapter 3 supporting the projectile 1 is disposed.
[0008] The projectile body 1 is provided with projectile support legs 4, which cooperate with the guide rail 2 to constrain the lateral movement and circumferential rotation of the projectile body 1.
[0009] During the launch of the projectile, the adapter 3 provides an upward support force to the projectile, and the projectile legs 4 provide a downward support force to the projectile, thereby constraining the nose-down disturbance and the amount of sinking of the projectile 1.
[0010] The guide rail 2 has a groove 21 formed in its middle along its length.
[0011] Vertical plates 22 extending upward are provided on both sides of the slot 21, and horizontal plates 23 extending inward are provided on the top of the vertical plates 22.
[0012] Lateral and deflection movements of the adapter are constrained by inserting the bottom of the adapter into the slot 21.
[0013] The adapter 3 has a concave arc shape at its top end to support the projectile.
[0014] The bottom end of the adapter 3 is a downward-extending boss.
[0015] Preferably, the cross-sectional shape of the boss is consistent with the cross-sectional shape of the guide rail groove 21.
[0016] More preferably, the boss and the guide rail groove 21 are in clearance fit.
[0017] The projectile support leg 4 is fixedly attached to the projectile 1 at its top.
[0018] The projectile support leg 4 is generally C-shaped, meaning that its side center is recessed inward to form a groove 41.
[0019] The horizontal plate 23 is embedded in the groove 41, and the cooperation between the horizontal plate 23 and the groove 41 constrains the lateral movement and circumferential rotation of the projectile 1.
[0020] The bottom surface of the horizontal plate 23 is in contact with the bottom of the groove 41, and the horizontal plate 23 provides a downward force to the projectile support leg 4 and the projectile 1.
[0021] Among them, there are two adapters 3, one of which is the front adapter 5 located near the warhead and the other is the rear adapter 6;
[0022] The projectile support legs 4 are provided with four legs, two of which are front legs 7 located near the projectile head, and the other two are rear legs 8; and the two projectile support legs on the same side are positioned opposite each other.
[0023] Preferably, the arrangement order from front to back along the projectile axis is: front adapter 5, front support leg 7, rear adapter 6, and rear support leg 8.
[0024] The center of mass of the projectile 1 is located between the front support leg 7 and the rear adapter 6.
[0025] The present invention also provides a method for launching a projectile on an inclined launch support orientation device.
[0026] Before the projectile is launched, the front adapter 5, the front support leg 7, the rear adapter 6, and the rear support leg 8 are placed on the guide rail in the order from front to back, so that the center of gravity of the projectile 1 is between the front support leg 7 and the rear adapter 6.
[0027] Before the center of mass deviates from the track, the adapter 3 and the guide rail 2 work together to support the projectile, and the support leg 4 and the guide rail 2 work together to constrain the projectile from jumping upward and rotating circumferentially, so that the projectile is in a state of equilibrium under force.
[0028] After the center of mass deviates from the track, the projectile is subjected to a downward force of gravity G, an upward support force of the rear adapter 6, and a downward support force of the rear support leg 8, thus constraining the pitching disturbance and the amount of sinking.
[0029] After the rear adapter derails, the projectile is mainly subjected to the downward force of gravity and the downward force of the guide rail on the rear support leg (8). At this time, the projectile will not tilt down significantly. Since the rear support leg (8) is located close to the tail of the projectile, it can effectively suppress the projectile from tilting down and sinking until the projectile is completely derailed.
[0030] The beneficial effects of this invention include:
[0031] (1) The inclined launch support orientation device and the launch method using it provided by the present invention can meet the requirements of small initial disturbance of inclined launch, compact structure, reliable operation and small impact on the flight of the projectile.
[0032] (2) The inclined launch support orientation device and the launch method using it provided by the present invention realize the simultaneous derailment and inclined launch of rockets or missiles by combining adapters and feet, which helps to reduce the nose-down angle disturbance during the launch phase of the missile body; the cooperation of adapters, feet and guide rails simultaneously constrains the vertical and lateral movement and rotational degrees of freedom of the missile body, reducing the complexity of the launch device structure. Attached Figure Description
[0033] Figure 1 This diagram shows the overall structure of the tilted launch support orientation device of this application;
[0034] Figure 2 This application shows a side view of the tilted launch support orientation device;
[0035] Figure 3 Show Figure 2 A magnified view of a portion of the image;
[0036] Figure 4 This diagram illustrates the forces acting on the projectile before its center of mass derails during the launch phase, when the projectile is launched from the launch box or launch tube on an inclined launch support or directional device.
[0037] Figure 5 This diagram illustrates the forces acting on the projectile after its center of mass deviates from its orbit during the launch phase, when the projectile is launched from the launch box or launch tube on an inclined launch support or directional device. Attached Figure Description
[0039] 1-Projectile
[0040] 2-Guide rail
[0041] 21-Gap
[0042] 22-Upright Board
[0043] 23-Horizontal Plate
[0044] 3-Adaptor
[0045] 4-Projectile support legs
[0046] 41-groove
[0047] 5-Front adapter
[0048] 6-Post-fit adapter
[0049] 7-Front feet
[0050] 8-Rear support leg Detailed Implementation
[0051] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Through these descriptions, the features and advantages of the present invention will become clearer and more apparent.
[0052] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments. Although various aspects of embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated otherwise.
[0053] The tilted launch support orientation device provided by the present invention, such as Figure 1 , Figure 2 and Figure 3 As shown in the figure; the device includes a guide rail 2, which is a long strip-shaped structure made of a material with sufficient strength, such as metal, with a length that is basically the same as the cylindrical part of the projectile, and the cross-sectional shape of each position is consistent.
[0054] An adapter 3 supporting the projectile 1 is provided on the guide rail 2. The adapter is made of foam material and can move synchronously with the projectile on the guide rail, that is, move along the length of the guide rail, and can detach from the guide rail when it moves to a certain position.
[0055] The projectile body 1 is provided with a projectile support leg 4 that cooperates with the guide rail 2 to constrain the lateral movement and circumferential rotation of the projectile body 1. The projectile support leg is a fixed structure on the outside of the projectile body and can move synchronously with the projectile body.
[0056] During the launch of the projectile, the adapter 3 provides an upward support force to the projectile, and the projectile legs 4 provide a downward support force to the projectile, thereby constraining the nose-down disturbance and sinking of the projectile 1, thus solving the nose-down and sinking problems during the launch of rockets or missiles.
[0057] In a preferred embodiment, a notch 21 is provided in the middle of the guide rail 2 along its length direction, and the length of the notch is basically the same as the length of the guide rail.
[0058] Vertically extending upright plates 22 are provided on both sides of the notch 21, that is, there are two upright plates 22. A horizontal plate 23 extending inward is provided on the top of the upright plates 22; that is, the upright plates and the horizontal plate are arranged perpendicular to each other. Preferably, the upright plates 22, the horizontal plates 23 and the structural parts that make up the notch 21 are all integrally formed.
[0059] The adapter's lateral and deflection movements are constrained by inserting the bottom of the adapter into the slot 21, so that the adapter can only reciprocate along the length of the guide rail.
[0060] In a preferred embodiment, the top of the adapter 3 has a concave arc shape to support the projectile; the arc shape is consistent with the outer contour arc of the projectile's cross-section, so that when the projectile is placed on the adapter, the top of the adapter 3 is in full contact with the projectile, ensuring the stability of the projectile installation.
[0061] The bottom end of the adapter 3 is a downward-extending boss.
[0062] Preferably, the cross-sectional shape of the boss is consistent with the cross-sectional shape of the guide rail groove 21;
[0063] More preferably, the boss and the guide rail slot 21 are in clearance fit. The cross-sectional shape of the slot 21 and the boss is a dovetail-like structure, which can limit the boss in the vertical direction and further improve the stability of the adapter and the projectile.
[0064] In a preferred embodiment, the top of the projectile support leg 4 is fixedly attached to the projectile 1.
[0065] The projectile support leg 4 is generally C-shaped, meaning that its side center is recessed inward to form a groove 41.
[0066] The horizontal plate 23 is embedded in the groove 41, and the cooperation between the horizontal plate 23 and the groove 41 constrains the lateral movement and circumferential rotation of the projectile 1.
[0067] Furthermore, the top and bottom of the inner side of the groove are both flat structures, which can fully contact the horizontal plate 23 and have a sufficiently large contact area, i.e. the force-bearing area, so as to smoothly transmit a large force.
[0068] The bottom surface of the horizontal plate 23 is in low contact with the bottom of the inner side of the groove 41. The horizontal plate 23 provides a downward force to the projectile support leg 4 and the projectile 1. This downward force can effectively suppress problems such as projectile tilting and sinking.
[0069] In a preferred embodiment, two adapters 3 are provided, one of which is the front adapter 5 located near the warhead, and the other is the rear adapter 6; the front adapter 5 and the rear adapter 6 have completely identical structural shapes.
[0070] The projectile support legs 4 are provided with four, two of which are front support legs 7 located near the projectile head, and the other two are rear support legs 8. The four projectile support legs 4 have completely identical structural shapes. The two projectile support legs located on the same side are arranged opposite each other. Preferably, they are arranged symmetrically along the projectile axis in the direction of the projectile cross section. That is, the two front support legs 7 are mirror images of each other, and the opening direction of their C-shaped groove 41 faces outward.
[0071] Preferably, the arrangement order from front to back along the projectile axis is: front adapter 5, front support leg 7, rear adapter 6, and rear support leg 8.
[0072] The center of mass of the projectile 1 is located between the front support leg 7 and the rear adapter 6.
[0073] Preferably, the distance between the adapter and the center of gravity, and the distance between the projectile's support feet and the center of gravity, are determined by the projectile's weight and dimensions to ensure that the projectile structure does not collide with the launch box, launch tube, or guide rail during its movement within the launch box; the support foot installation height is determined by machining and assembly errors to ensure sufficient clearance to meet the requirements for bore engagement.
[0074] The present invention also provides a method for launching a projectile on an inclined launch support orientation device, wherein,
[0075] Before the projectile is launched, the front adapter 5, the front support leg 7, the rear adapter 6, and the rear support leg 8 are placed on the guide rail in the order from front to back, and the center of gravity of the projectile 1 is located between the front support leg 7 and the rear adapter 6; so that the projectile is stably placed on the guide rail, and the overall structure of the projectile and the guide rail can be moved and transported for a relatively long time.
[0076] After the projectile is ignited and launched, as Figure 4 As shown, before the center of mass deviates from the track, the adapter 3 and the guide rail 2 cooperate to support the projectile, and the support leg 4 and the guide rail 2 cooperate to constrain the projectile's upward jumping and circumferential rotation; during this process, the support force provided by the adapter is balanced with the weight of the projectile, and the projectile is in a state of equilibrium under force.
[0077] After the center of mass deviates from its orbit, such as Figure 5 As shown, the projectile is subjected to a downward force of gravity G, an upward support force of the rear adapter 6, and a downward support force of the rear support leg 8. In the conventional scheme, the projectile will have a relatively obvious nose-down disturbance and sinking amount at this stage. However, in the scheme of this application, the torques on both sides of the rear adapter 6 are balanced at this stage, the projectile will not nose-down, and the adapter can also provide sufficient support force, so there is no sinking amount.
[0078] After the rear adapter derails, the projectile is mainly subjected to the downward force of gravity and the downward force of the guide rail on the rear support leg 8. At this time, the projectile will not tilt down significantly. Since the rear support leg 8 is located close to the tail of the projectile, it can effectively suppress the projectile from tilting down and sinking until the projectile is completely derailed.
[0079] The rear adapter is located relatively close to the tail of the projectile. The time taken from the rear adapter leaving the rail to the projectile leaving the rail completely is less than the time taken from the center of gravity leaving the rail to the rear adapter leaving the rail. Therefore, from an overall perspective, by setting the rear adapter and rear support legs, the launch phase time during the projectile launch process that causes nose-down and sinking can be greatly shortened, thereby making the final nose-down and sinking amount of the projectile smaller.
[0080] The present invention has been described above with reference to preferred embodiments; however, these embodiments are merely exemplary and illustrative. Various substitutions and modifications can be made to the present invention based on these embodiments, all of which fall within the scope of protection of the present invention.
Claims
1. A tilting launch support orientation device, characterized in that, The device includes a guide rail (2), on which an adapter (3) supporting the projectile (1) is provided. The projectile (1) is provided with projectile support legs (4) that cooperate with the guide rail (2) to constrain the lateral movement and circumferential rotation of the projectile (1). During the launch of the projectile, the adapter (3) provides an upward support force to the projectile, and the projectile legs (4) provide a downward support force to the projectile, thereby constraining the pitching disturbance and sinking amount of the projectile (1). The guide rail (2) has a groove (21) in the middle along its length. Vertical plates (22) extending upward are provided on both sides of the notch (21), and horizontal plates (23) extending inward are provided on the top of the vertical plates (22). Lateral and deflection movements of the adapter are constrained by inserting the bottom of the adapter into the notch (21); The top of the adapter (3) has a concave arc shape to support the projectile. The adapter (3) has a downward-extending boss at its bottom end. The cross-sectional shape of the boss is consistent with the cross-sectional shape of the guide rail groove (21); The boss is fitted with the guide rail groove (21) with a clearance. The top of the projectile support leg (4) is fixed to the projectile (1). The projectile support (4) is generally C-shaped, that is, its side center is recessed inward to form a groove (41). The horizontal plate (23) is embedded in the groove (41), and the cooperation between the horizontal plate (23) and the groove (41) constrains the lateral movement and circumferential rotation of the projectile (1); The bottom surface of the horizontal plate (23) abuts against the bottom of the groove (41), and the horizontal plate (23) provides a downward force to the projectile support (4) and the projectile (1); The adapter (3) is provided in two parts, one of which is the front adapter (5) located near the warhead and the other is the rear adapter (6); The projectile support (4) is provided with four legs, two of which are located on the side closer to the projectile head and are front legs (7), and the other two are rear legs (8); and the two projectile support legs on the same side are symmetrically arranged. The arrangement order along the projectile axis from front to back is: front adapter (5), front support (7), rear adapter (6), and rear support (8); the rear adapter is located relatively close to the tail of the projectile, and the time taken from the rear adapter leaving the track to the projectile leaving the track completely is less than the time taken from the center of mass leaving the track to the rear adapter leaving the track. The center of mass of the projectile (1) is located between the front support (7) and the rear adapter (6).
2. A method for launching a projectile on an inclined launch support orienting device, the method being implemented based on the inclined launch support orienting device of claim 1, characterized in that, Before the projectile is launched, the front adapter (5), the front support (7), the rear adapter (6), and the rear support (8) are placed on the guide rail in the order from front to back, so that the center of mass of the projectile (1) is between the front support (7) and the rear adapter (6). Before the center of mass deviates from the track, the adapter (3) and the guide rail (2) work together to support the projectile, and the support leg (4) and the guide rail (2) work together to constrain the projectile from jumping upward and rotating in the circumferential direction. The projectile is in a state of equilibrium under force. After the center of mass deviates from the orbit, the projectile is subjected to the downward force of gravity G, the upward support force of the rear adapter (6), and the downward support force of the rear support leg (8), thus constraining the pitching disturbance and the amount of sinking. After the rear adapter leaves the rail, the projectile is mainly subjected to the downward force of gravity and the downward force of the guide rail on the rear support (8). At this time, the projectile will not tilt down significantly. Since the rear support (8) is located close to the tail of the projectile, it can effectively suppress the projectile from tilting down and sinking until the projectile is completely off the rail.