An aircraft takeoff system

Abstract

The application belongs to the field of aircrafts, and particularly relates to an aircraft take-off system, which comprises a track, an aircraft and two blocks. The track is provided with a sliding groove penetrating to one end of the track, and the two blocks are relatively matched to form a sliding block in sliding cooperation with the sliding groove. At least one block is provided with an embedded groove on a matching surface, and the embedded groove and the matching surface of the other block form an embedded cavity after the two blocks are relatively matched. The aircraft is provided with a protrusion matched with the embedded cavity. After the protrusion and the embedded cavity are embedded, the relative movement of the protrusion and the embedded cavity in the length and width directions of the sliding groove is limited. After the sliding block is separated from the track from one end of the sliding groove, the two blocks are separated from each other and the embedded cavity is opened, and the protrusion is separated from the two blocks. After the aircraft takes off and the sliding block is separated from the sliding groove, the two blocks are separated from each other by gravity and are separated from the protrusion, so that the weight of the aircraft can be avoided to be increased on the premise that the take-off task is successfully completed.

Description

Technical Field

[0001] This invention belongs to the field of aircraft, specifically relating to an aircraft takeoff system. Background Technology

[0002] Currently, most aircraft take off using tracks, and their aircraft are equipped with sliders that cooperate with the tracks to achieve sliding cooperation. However, this increases the weight of the aircraft and damages its aerodynamic shape.

[0003] In addition, the tail section of a typical rocket is not rotatable. The tail fins are mounted on servos on the tail section, and the tail fins are driven to rotate by controlling the servos. However, there is a new type of rocket that is designed to be rotatable in order to eliminate the rolling moment during flight. The entire tail section can rotate relative to the rocket's axis. When this type of rocket is launched from a conventional orbit, the rotating tail fins will collide with the orbit, which poses a certain safety hazard. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an aircraft take-off system that can ensure the weight and aerodynamic shape of the aircraft while ensuring a smooth take-off.

[0005] This invention provides an aircraft takeoff system, comprising a track, an aircraft, and two blocks;

[0006] The track is provided with a sliding groove that extends to one end of the track. Two blocks can be fitted together and separated. When the two blocks are fitted together, they form a slider that slides in conjunction with the sliding groove.

[0007] At least one block has a fitting groove on its mating surface. After two blocks are mated, the fitting groove and the mating surface of another block enclose a fitting cavity. The aircraft is provided with a protrusion that mates with the fitting cavity. After the protrusion mates with the fitting cavity, it restricts the relative movement of the protrusion and the fitting cavity in the length and width directions of the slide.

[0008] After the slider disengages from one end of the groove, the two blocks separate from each other and the fitting cavity opens, and the protrusion disengages from the two blocks.

[0009] Furthermore, corresponding positions on opposite sides of the two blocks are provided with fitting grooves, and after the two blocks are fitted together, the two fitting grooves enclose each other to form the fitting cavity.

[0010] Furthermore, the fitting cavity includes a connecting cavity and a limiting cavity that are interconnected, with the other end of the connecting cavity penetrating through the end of the block. The protrusion includes a connecting block and a limiting block that are interconnected, and the connecting block is connected to the aircraft.

[0011] The limiting block cooperates with the limiting cavity to restrict the relative movement of the protrusion and the slider in all directions.

[0012] Furthermore, the aircraft is equipped with a reset mechanism that can drive the protrusion to retract into the aircraft or into the inner wall of the aircraft.

[0013] Furthermore, the aircraft fuselage has a groove at its bottom, and a through hole extending into the fuselage is provided at the bottom of the groove. The reset mechanism includes a sliding rod slidably disposed on the through hole and a reset spring sleeved on the part of the sliding rod located inside the fuselage. The reset spring drives the sliding rod to move toward the interior of the fuselage. A protrusion is disposed on the end of the sliding rod opposite to the reset spring, and the end face of the protrusion is adapted to the groove.

[0014] Furthermore, a limiting groove is provided in the sliding groove along the width direction of the sliding groove, and at least one of the blocks is provided with an anti-detachment block that cooperates with the limiting groove;

[0015] The anti-detachment block works in conjunction with the limiting groove to restrict the block from moving along the depth direction of the groove.

[0016] Furthermore, limit grooves are provided on both sides of the slide, and anti-detachment blocks are provided on the opposite sides of the two blocks.

[0017] Furthermore, a countersunk hole is provided on the mating surface of one of the blocks, and a spring is provided inside the countersunk hole, with the end of the spring abutting against another block.

[0018] Furthermore, the aircraft includes an interconnected rocket body and a rotating tail section, the rotating tail section being provided with the protrusion.

[0019] Furthermore, the rocket body is provided with protrusions.

[0020] The beneficial effect of this invention is that the aircraft completes the takeoff process through the cooperation of the track and the slider, enabling the aircraft to complete the takeoff process in various environments. In particular, for aircraft that require a runway for takeoff, such as fixed-wing UAVs and rockets, it can greatly simplify the takeoff difficulty.

[0021] In this invention, the slider is composed of two interlocking and separable blocks. When the two blocks are engaged, the resulting cavity can be used to engage with protrusions on the aircraft. After further engagement, the blocks are inserted into a groove, simultaneously constraining them. Through the constraints of the protrusions and the groove, the two blocks ultimately form a relatively stable slider assembly. At this point, the two blocks, as a whole, cannot move relative to each other within the groove; they can only slide as a single unit along the length of the groove, thus completing the sliding connection and fixation between the track and the aircraft. When the aircraft takes off and the slider disengages from the groove, the two blocks lose the constraint of the groove and separate from each other by gravity, simultaneously separating from the protrusions. This avoids increasing the weight of the aircraft while successfully completing the takeoff mission. Therefore, the aircraft provided by this invention can connect to the track after takeoff with only protrusions of small surface area and weight, ensuring the weight of the aircraft and reducing aerodynamic drag on the outer surface. Attached Figure Description

[0022] Appendix Figure 1 This is a schematic diagram of the first angle structure of the present invention;

[0023] Appendix Figure 2 This is a schematic diagram of the second angle structure of the present invention;

[0024] Appendix Figure 3 for Figure 1 A frontal sectional view in the direction of the orientation;

[0025] Appendix Figure 4 for Figure 3 A magnified view of a section at point A in the middle;

[0026] Appendix Figure 5 This is a schematic diagram of the aircraft after takeoff.

[0027] Appendix Figure 6 This is a schematic diagram of the structure of the track, slider, and protrusion in this invention;

[0028] Appendix Figure 7 for Figure 6 Top view;

[0029] Appendix Figure 8 for Figure 7 Sectional view along the BB direction;

[0030] Appendix Figure 9 for Figure 7 Central CC-direction sectional view (rotated 90°);

[0031] Appendix Figure 10 for Figure 6 A diagram showing the aircraft after takeoff;

[0032] Appendix Figure 11 This is a schematic diagram of the structure of the aircraft in this invention;

[0033] Appendix Figure 12 for Figure 11 Schematic diagram of the extended state of the protrusion at point D;

[0034] Appendix Figure 13 for Figure 11 A schematic diagram of the retracted state of the bump at point D.

[0035] In the diagram, 1-track; 11-slide groove; 12-limiting groove; 2-slider; 21-block; 211-fitting groove; 2111-connecting groove; 2112-limiting groove; 212-counterhead; 22-fitting cavity; 221-connecting cavity; 222-limiting cavity; 23-anti-detachment block; 24-spring; 3-aircraft; 31-protrusion; 311-connecting block; 312-limiting block; 32-groove; 33-through hole; 34-sliding rod; 341-spring fixing plate; 35-reset spring; 36-rocket body; 37-rotating tail section. Detailed Implementation

[0036] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0037] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0038] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0039] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0040] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0041] As attached Figure 1-13 As shown, the present invention provides an aircraft take-off system, including a track 1, an aircraft 3 and a slider 2, wherein the slider 2 is composed of two blocks 21 and is used to connect the track 1 and the aircraft 3;

[0042] The track 1 is provided with a groove 11 that extends to one end of the track 1. Two blocks 21 can be fitted together and separated. After the two blocks 21 are fitted together, they form a slider 2 that slides in cooperation with the groove 11. The slider 2 can slide out from one end of the groove 11, thereby causing the slider 2 to disengage from the track 1.

[0043] At least one block 21 has a fitting groove 211 on its mating surface. After two blocks 21 are mated, the fitting groove 211 and the mating surface of another block 21 enclose a fitting cavity 22. The aircraft 3 is provided with a protrusion 31 that mates with the fitting cavity 22. After the protrusion 31 is mated with the fitting cavity 22, it restricts the relative movement of the protrusion 31 and the fitting cavity 22 in the length and width directions of the slide groove 11. That is, after the two blocks 21 are mated, the protrusion 31 is limited and cannot move relatively linearly in the length and width directions of the slide groove 11. Therefore, it cannot rotate in any direction, so that the protrusion 31 will move synchronously with the slider 2. The protrusion 31 can also move along the depth direction of the fitting cavity 22 to simplify the installation difficulty of the protrusion 31.

[0044] refer to Figure 5 and Figure 10 After the slider 2 leaves the track 1 from one end of the slide groove 11, the two blocks 21 separate from each other and the fitting cavity 22 opens. The protrusion 31 separates from the two blocks 21. That is, after the aircraft 3 completes takeoff, the two blocks 21 will separate by gravity and detach from the aircraft 3.

[0045] In this invention, the aircraft 3 completes the takeoff process through the cooperation of the track 1 and the slider 2, enabling the aircraft 3 to complete the takeoff process in various environments. In particular, for aircraft 3 that require a runway for takeoff, such as fixed-wing drones and rockets, the takeoff difficulty can be greatly simplified.

[0046] Currently, conventional aircraft takeoffs from tracks typically involve a slider 2 fixedly mounted on the aircraft 3 to engage with the track 1, resulting in a sliding connection. However, this increases the weight of the aircraft 3 and compromises its aerodynamics. In this invention, the slider 2 is composed of two interlocking and separable blocks 21. When the two blocks 21 engage, the resulting cavity 22 engages with a protrusion 31 on the aircraft 3. After engagement, the blocks are inserted into a groove 11, simultaneously constraining the two blocks 21. Through the constraints of the protrusion 31 and the groove 11, the two blocks 21 ultimately form a relatively stable slider 2 as a whole. At this point, the two blocks 21, as a whole, cannot move relative to each other within the groove 11; they can only slide as a single unit along the length of the groove 11, thus achieving a sliding connection and fixation between the track 1 and the aircraft 3. When the aircraft 3 takes off and the slider 2 is separated from the slide 11, the two blocks 21 lose the constraint of the slide 11 and separate from each other by gravity and at the same time separate from the protrusion 31. Thus, the weight of the aircraft 3 can be avoided while successfully completing the takeoff mission. After takeoff, the aircraft 3 provided by the present invention can be connected to the track 1 with only protrusions 31 with small surface area and weight on its surface, which can ensure the weight of the aircraft 3 and reduce the aerodynamic drag of the outer surface.

[0047] In one specific embodiment, corresponding positions on opposite sides of the two blocks 21 are provided with fitting grooves 211. After the two blocks 21 are engaged, the two fitting grooves 211 enclose and form the fitting cavity 22. This arrangement has two advantages: First, the protrusion 31 engages with the two separable fitting grooves 211, reducing the contact area of ​​the protrusion 31 with a single fitting groove 211, thus reducing the tightness of the connection between the protrusion 31 and the fitting groove 211 to a certain extent. This improves the success rate of separation between the two blocks 21 and the protrusion 31 after the slider 2 is disengaged from the track 1. Second, the protrusion 31 is enclosed and engaged by the two fitting grooves 211. After the protrusion 31 engages with the two blocks 21, the protrusion 31 restricts the relative movement of the two protrusions 31 along the length direction of the slide groove 11, which can improve the overall integrity of the slider 2 after engagement.

[0048] refer to Figure 9 and Figure 10 In one specific embodiment, the fitting cavity 22 includes a connecting cavity 221 and a limiting cavity 222 that are connected to each other. The other end of the connecting cavity 221 passes through the end of the block 21. The protrusion 31 includes a connecting block 311 and a limiting block 312 that are connected to each other. The connecting block 311 is connected to the aircraft 3.

[0049] The limiting block 312 cooperates with the limiting cavity 222 to restrict the relative movement of the protrusion 31 and the slider 2 in all directions.

[0050] In this embodiment, the connecting block 311 is used to connect the limiting block 312 and the aircraft 3. The limiting block 312 cooperates with the limiting cavity 222, and the connecting block 311 cooperates with the connecting cavity 221. After the protrusion 31 cooperates with the two blocks 21, the protrusion 31 and the slider 2 cannot move relative to each other in any direction, thereby achieving rigid fixation of the slider 2 and the aircraft 3, improving connection stability, and at the same time not affecting the separation process. The two blocks 21 separate from each other, and the connecting cavity 221 and the limiting cavity 222 open to each other and separate from the protrusion 31.

[0051] Similarly, in this embodiment, the connecting cavity 221 and the limiting cavity 222 can be a connecting groove 2111 and a limiting groove 2112 provided on the mating surface of one of the blocks 21. After mating with the other block 21, they enclose to form the connecting cavity 221 and the limiting cavity 222. Preferably, the mating surfaces of the two blocks 21 are provided with corresponding connecting grooves 2111 and limiting grooves 2112. After mating with the other block 21, the two sets of connecting grooves 2111 and limiting grooves 2112 enclose to form the connecting cavity 221 and the limiting cavity 222, thereby improving the separation success rate and the overall integrity of the slider 2.

[0052] In one specific embodiment, a limiting groove 12 is provided in the sliding groove 11 along the width direction of the sliding groove 11, and at least one of the blocks 21 is provided with an anti-detachment block 23 that cooperates with the limiting groove 12.

[0053] The anti-detachment block 23 cooperates with the limiting groove 12 to restrict the block 21 from moving along the depth direction of the sliding groove 11.

[0054] In this embodiment, the slide groove 11 and the limiting groove 12 can be L-shaped as a whole, thereby preventing the slider 2 from disengaging along the depth direction of the slide groove 11, so that the slider 2 can only move along the length direction of the slide groove 11, thus improving the guiding performance of the track 1.

[0055] refer to Figure 6 In one specific embodiment, the sliding groove 11 is provided with limiting grooves 12 on both sides of the sliding groove 11, and anti-detachment blocks 23 are provided on the opposite sides of the two blocks 21. In this embodiment, the sliding groove 11 and the limiting grooves 12 can be T-shaped as a whole, and the slider 2 is T-shaped, so as to ensure the symmetry of the slider 2 and thus improve the smoothness of sliding.

[0056] refer to Figure 5In one specific embodiment, a countersunk hole 212 is provided on the mating surface of one of the blocks 21. A spring 24 is provided inside the countersunk hole 212, and the end of the spring 24 abuts against another block 21. By providing the spring 24, the two blocks 21 can be separated by the spring 24 after the slider 2 separates from the track 1, thereby improving the success rate of separation of the two blocks 21. (Refer to...) Figure 10 Alternatively, countersunk holes 212 can be provided on the mating surfaces of both blocks 21 to simplify the installation of the spring 24.

[0057] refer to Figures 1-4 In one specific embodiment, the aircraft 3 includes a rocket body 36 and a rotating tail section 37 connected to each other, the rotating tail section 37 being provided with the protrusion 31.

[0058] In this embodiment, the provided aircraft 3 is a rocket with a rotating tail section 37. This allows for more precise control of the rocket's attitude and direction, enabling more flexible control. However, currently, when rockets with rotating tail sections 37 take off using the track 1, the rotating tail section 37 also rotates during takeoff, meaning it rotates relative to the rocket's axis. This could cause the tail fins on the rotating tail section 37 to collide with the track 1, compromising the rocket's structural safety. In this embodiment, the rotating tail section 37 is connected to the slider 2 via a protrusion 31. This prevents the rotating tail section 37 from rotating during takeoff, avoiding the possibility of the tail fins colliding with the track 1, ensuring the safety of the rocket's structure, and eliminating potential hazards. Furthermore, the slider 2 is automatically discarded after takeoff and does not adhere to the rocket body, thus not affecting the rocket's structure.

[0059] For the rocket body 36, a conventional integral slider can be used for sliding connection with the track 1. In one specific embodiment, the rocket body 36 is provided with a protrusion 31, and the rocket body 36 is also slidably connected to the track 1 through a slider 2 composed of two blocks 21. In addition, the protrusion 31 on the rocket body 36 is preferably provided with a limit block 312, while the protrusion 31 on the rotating tail section 37 may not be provided with a limit block 312. This ensures the stability of the connection between the rocket body 36 and the slider 2, while also ensuring the success rate of the rotating tail section 37 disengaging from the slider 2.

[0060] refer to Figures 11-13 In one specific embodiment, the aircraft 3 is provided with a reset mechanism, which can drive the protrusion 31 to retract into the aircraft 3 or into the inner wall of the aircraft 3. By providing a reset mechanism, after the slider 2 disengages from the protrusion 31, the protrusion 31 retracts into the outer shell of the aircraft 3, ensuring the aerodynamic shape of the aircraft 3.

[0061] In one specific embodiment, a groove 32 is provided at the bottom of the fuselage of the aircraft 3, and a through hole 33 extending into the interior of the fuselage is provided at the bottom of the groove 32. The reset mechanism includes a sliding rod 34 slidably disposed on the through hole 33 and a reset spring 35 sleeved on the portion of the sliding rod 34 located inside the fuselage. In addition, a spring fixing plate 341 is provided at the end of the sliding rod 34 located inside the fuselage. One end of the reset spring 35 abuts against the spring fixing plate 341, and the other end abuts against the inner wall of the fuselage. The reset spring 35 drives the sliding rod 34 to move toward the interior of the fuselage. A protrusion 31 is disposed at the end of the sliding rod 34 opposite to the reset spring 35, and the end face of the protrusion 31 is adapted to the groove 32. With the above structure, no additional drive mechanism is required to drive the protrusion 31 to reset via the reset spring 35, so that the fuselage of the aircraft 3 remains intact and the aerodynamic shape is maintained. This embodiment is applicable to application scenarios where a limit block 312 is provided on the protrusion 31.

[0062] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. An aircraft takeoff system, characterized in that, It includes an orbit (1), a spacecraft (3), and two blocks (21); The track (1) is provided with a groove (11) that extends to one end of the track (1). Two blocks (21) can be fitted and separated. After the two blocks (21) are fitted, they form a slider (2) that slides in cooperation with the groove (11). At least one block (21) has a fitting groove (211) on its mating surface. After two blocks (21) are mated, the fitting groove (211) and the mating surface of another block (21) enclose each other to form a fitting cavity (22). The aircraft (3) is provided with a protrusion (31) that mates with the fitting cavity (22). After the protrusion (31) mates with the fitting cavity (22), it restricts the relative movement of the protrusion (31) and the fitting cavity (22) in the length and width directions of the slide groove (11). After the slider (2) is disengaged from one end of the slide groove (11) and the track (1), the two blocks (21) separate from each other and the fitting cavity (22) opens, and the protrusion (31) disengages from the two blocks (21); The aircraft (3) includes a rocket body (36) and a rotating tail section (37) connected to each other. The rotating tail section (37) is rotatable relative to the axis of the aircraft and is provided with the protrusion (31). The rocket body (36) is provided with protrusions (31).

2. The aircraft takeoff system as described in claim 1, characterized in that, Two blocks (21) are provided with corresponding positions on opposite sides of each other, and after the two blocks (21) are matched, the two fitting grooves (211) enclose each other to form the fitting cavity (22).

3. The aircraft takeoff system as described in claim 1 or 2, characterized in that, The fitting cavity (22) includes a connecting cavity (221) and a limiting cavity (222) that are connected to each other. The other end of the connecting cavity (221) passes through the end of the block (21). The protrusion (31) includes a connecting block (311) and a limiting block (312) that are connected to each other. The connecting block (311) is connected to the aircraft (3). The limiting block (312) cooperates with the limiting cavity (222) to restrict the relative movement of the protrusion (31) and the slider (2) in all directions.

4. The aircraft takeoff system as described in claim 3, characterized in that, The aircraft (3) is provided with a reset mechanism, which can drive the protrusion (31) to retract into the interior of the aircraft (3) or into the inner wall of the aircraft (3).

5. The aircraft takeoff system as described in claim 4, characterized in that, The aircraft (3) has a groove (32) at the bottom of its fuselage, and a through hole (33) at the bottom of the groove (32) that extends into the fuselage. The reset mechanism includes a sliding rod (34) that is slidably disposed on the through hole (33) and a reset spring (35) that is sleeved on the part of the sliding rod (34) located inside the fuselage. The reset spring (35) drives the sliding rod (34) to move toward the interior of the fuselage. The protrusion (31) is disposed at the end of the sliding rod (34) away from the reset spring (35), and the end face of the protrusion (31) is adapted to the groove (32).

6. The aircraft takeoff system as described in claim 1, characterized in that, A limiting groove (12) is provided in the sliding groove (11) along the width direction of the sliding groove (11), and at least one of the blocks (21) is provided with an anti-detachment block (23) that cooperates with the limiting groove (12). The anti-detachment block (23) cooperates with the limiting groove (12) to restrict the block (21) from moving along the depth direction of the slide groove (11).

7. The aircraft takeoff system as described in claim 6, characterized in that, Limiting grooves (12) are provided on both sides of the slide (11), and anti-detachment blocks (23) are provided on the opposite side of the two blocks (21).

8. The aircraft takeoff system as described in any one of claims 1, 2, 4-7, characterized in that, in one of them A countersunk hole (212) is provided on the mating surface of the block (21), and a spring (24) is provided in the countersunk hole (212). The end of the spring (24) abuts against another block (21).

Images