Aircraft launching device

Abstract

This invention relates to the technical field of spacecraft launch, and more specifically, to a spacecraft launch device, comprising: a launcher, the launcher being provided with a slide rail and a support platform, the launcher being used to move along a launch track; a transition section, one end of the transition section being detachably connected to the tail of the spacecraft, and the other end being connected to the support platform; an adapter, one end of the adapter being detachably connected to the periphery of the spacecraft, and the other end being slidably connected to the slide rail; in the drive phase, the spacecraft is connected to the launcher via the transition section, and the combination of the launcher and the spacecraft accelerates, then the combination of the launcher and the spacecraft slides without power, entering a uniform motion phase. After reaching the designated position, the transition section and the spacecraft separate, and the spacecraft and the adapter slide off the launcher along the slide rail by inertia, and the adapter and the spacecraft separate, realizing a launch-by-push launch of the spacecraft. This enables large-scale launches of spacecraft and improves flight efficiency.

Description

Technical Field

[0001] This invention relates to the technical field of spacecraft launch, and more specifically, to a spacecraft launch device. Background Technology

[0002] Existing aircraft typically have tail nozzles and tail fins, which prevents them from being launched by push-launch vehicles, resulting in limited large-scale launches, slow initial takeoff speeds, and low takeoff efficiency.

[0003] Therefore, it is necessary to propose an aircraft launch device to at least partially solve the problems existing in the prior art. Summary of the Invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art or related art.

[0005] Therefore, the present invention provides an aircraft launching device.

[0006] In view of this, an aircraft launching device is proposed according to an embodiment of this application, comprising:

[0007] A pusher, which is provided with a slide rail and a support platform, is used to move along the pusher rail;

[0008] The adapter section has one end for detachable connection to the tail of the aircraft and the other end for connection to the support platform.

[0009] An adapter, one end of which is detachably connected to the periphery of the aircraft, and the other end is slidably connected to the slide rail;

[0010] During the propulsion phase, the aforementioned aircraft is connected to the aforementioned thruster via the aforementioned adapter section;

[0011] During the separation phase, the aforementioned transition section separates from the aforementioned housing, the assembly of the aforementioned aircraft and the aforementioned adapter slides out of the aforementioned rail, and the aforementioned adapter detaches from the aforementioned housing.

[0012] 2. In one feasible implementation, the aforementioned transition section includes:

[0013] The ring body has a first end connected to the support platform and a second end connected to the tail of the aircraft.

[0014] Separating components are spaced apart on the periphery of the second end of the ring body, and the separating components are used to connect the ring body to the tail of the aircraft.

[0015] During the separation phase, the separation component is disconnected to separate the transition section from the aircraft.

[0016] In one feasible implementation, the aforementioned separator includes:

[0017] Box body;

[0018] A separation bolt, along the axial direction of the aforementioned ring body, passes through the side wall of the aforementioned box body and is used to be screwed into the first threaded hole at the tail of the aforementioned aircraft.

[0019] A cover, which is fitted over the aforementioned box body;

[0020] The aforementioned separation bolt contains an explosive charge, which will break when the explosive charge is detonated.

[0021] In one feasible implementation, the aforementioned separator further includes:

[0022] A buffer pad is provided on the side of the aforementioned housing away from the aforementioned separation bolt.

[0023] In one feasible implementation, the aforementioned aircraft launching device further includes:

[0024] The fixing bolt is provided along the axial direction of the ring body. The first end of the ring body is provided with a plurality of through holes at intervals, and the corresponding position of the support platform is provided with a second threaded hole. The fixing bolt passes through the through holes and is screwed into the second threaded hole.

[0025] An installation window is provided on the periphery of the first end of the ring body, and the installation window is connected to the through hole. The fixing bolt is inserted into the through hole through the installation window.

[0026] In one feasible implementation, the adapter includes:

[0027] A semi-ring body, used to snap onto the periphery of the aforementioned aircraft;

[0028] A protrusion is provided at the bottom of the semi-ring body, and the protrusion is used to be inserted into the slide rail;

[0029] The gripping force of the semi-ring on the shell of the aircraft is less than the weight of the semi-ring itself.

[0030] In one feasible implementation, the adapter further includes:

[0031] The elastic element is provided with a mounting hole on the side of the semi-annular body facing the housing, and the elastic element is disposed in the mounting hole.

[0032] In one feasible implementation, the adapter further includes:

[0033] Anti-slip rubber pads are laid on the side of the semi-annular body facing the shell.

[0034] In one feasible implementation, multiple adapters are provided, and the multiple adapters are arranged at intervals around the periphery of the housing.

[0035] In one feasible implementation, the aforementioned aircraft launching device further includes:

[0036] The connecting rod is positioned along the axial direction of the semi-ring body, which has an interface. The two ends of the connecting rod are respectively inserted into the interfaces of adjacent semi-ring bodies.

[0037] Compared to existing technologies, the present invention offers at least the following advantages: The aircraft launching device proposed in this application includes a pusher, a transition section, and an adapter. The transition section is located at the tail of the aircraft, allowing the tail to be connected to the support platform of the pusher. The adapter is located on the periphery of the aircraft's shell and is slidable on a slide rail, allowing the aircraft to slide relative to the slide rail. This configuration enables the aircraft to be launched by the pusher. Specifically, during the driving phase, the aircraft is connected to the pusher via the transition section and slides on the slide rail via the adapter. The combination of the pusher and the aircraft accelerates along the pusher track. After reaching a preset speed, the combination of the pusher and the aircraft slides without power, entering a uniform motion phase. Upon reaching a designated position, the transition section separates from the aircraft, the pusher decelerates, and the aircraft and the adapter slide off the pusher along the slide rail due to inertia. The adapter and the aircraft then separate, achieving a push-launch of the aircraft. This enables large-scale launches of aircraft, improves launch efficiency, and increases the initial takeoff speed of aircraft, thereby improving flight efficiency.

[0038] The aircraft launching device of the present invention, other advantages, objectives and features of the present invention will be apparent in part from the following description, and in part will be understood by those skilled in the art through study and practice of the invention. Attached Figure Description

[0039] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit this specification. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0040] Figure 1 This application provides an assembly diagram of an aircraft launching device and an aircraft, as shown in the embodiments of the present application.

[0041] Figure 2 This is a schematic diagram of the structure of a pusher provided in an embodiment of this application;

[0042] Figure 3 This is a schematic diagram of the structure of a transition section provided in an embodiment of this application;

[0043] Figure 4 for Figure 3 A partially enlarged schematic diagram of the transition section shown;

[0044] Figure 5 This is a schematic diagram of the structure of an adapter provided in an embodiment of this application;

[0045] Figure 6 for Figure 5 The diagram shows the assembly of the adapter and connecting rod.

[0046] in, Figures 1 to 6 The correspondence between the reference numerals and component names in the attached drawings is as follows:

[0047] 100 Launcher, 110 Pusher, 111 Slide rail, 112 Support platform, 120 Adapter section, 121 Ring body, 1211 Through hole, 122 Separator, 1221 Box body, 1222 Separation bolt, 1223 Cover, 130 Adapter, 131 Semi-ring body, 1311 Mounting hole, 132 Protrusion, 140 Mounting window, 150 Connecting rod, 200 Launcher. Detailed Implementation

[0048] To better understand the above technical solutions, the technical solutions of the embodiments of this application will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of this application and the specific features in the embodiments are detailed descriptions of the technical solutions of the embodiments of this application, rather than limitations on the technical solutions of this application. In the absence of conflict, the embodiments of this application and the technical features in the embodiments can be combined with each other.

[0049] In some examples, such as Figures 1 to 6 As shown, an embodiment of this application proposes an aircraft launching device 100, comprising: a pusher 110, the pusher 110 being provided with a slide rail 111 and a support platform 112, the pusher 110 being used to move along a pusher track; a transition section 120, one end of the transition section 120 being detachably connected to the tail of the aircraft 200, and the other end being connected to the support platform 112; and an adapter 130, one end of the adapter 130 being detachably connected to the periphery of the aircraft 200, and the other end being slidably connected to the slide rail 111; wherein, during the driving phase, the aircraft 200 is connected to the pusher 110 via the transition section 120; during the separation phase, the transition section 120 separates from the housing, the assembly of the aircraft 200 and the adapter 130 slides out of the slide rail 111, and the adapter 130 detaches from the housing.

[0050] It is understood that the aircraft launching device 100 proposed in this application embodiment is provided with a pusher 110, a transition section 120, and an adapter 130. The transition section 120 is located at the tail of the aircraft 200, allowing the tail of the aircraft 200 to be connected to the support platform 112 of the pusher 110. The adapter 130 is located on the periphery of the aircraft 200's shell and is slidable on a slide rail 111, allowing the aircraft 200 to slide relative to the slide rail 111. With this configuration, the aircraft 200 can be launched by the pusher 110. Specifically, during the driving phase, the aircraft 200 is connected to the pusher 110 via the transition section 120 and slides on the slide rail 111 via the adapter 130. The combination of the pusher 110 and the aircraft 200 accelerates along the launch track, and after reaching a preset speed, the combination of the pusher 110 and the aircraft 200 slides without power, entering a uniform motion phase. Upon reaching the designated position, the transition section 120 separates from the aircraft 200, and the pusher 110 decelerates. The aircraft 200 and adapter 130 slide off the pusher 110 along the rail 111 due to inertia, and the adapter 130 separates from the aircraft 200, thus achieving a push-launch of the aircraft 200. This enables large-scale launches of the aircraft 200, improves launch efficiency, and increases the initial takeoff speed of the aircraft 200, thereby enhancing its flight efficiency.

[0051] It is understandable that, such as Figure 2 As shown, the support platform 112 of the pusher 110 is located in the extension direction of the slide rail 111, and the end point of the slide rail 111 is flush with the end face of the pusher 110. During the driving phase, the aircraft 200 rests on the support platform 112 via the adapter section 120, so that the support platform 112 pushes the aircraft 200 to move synchronously with the pusher 110. During the separation phase, the slide rail 111 provides guidance for the adapter 130 and ensures smooth sliding, reduces kinetic energy loss, and ensures that the combination of the aircraft 200 and the adapter 130 can smoothly slide out of the pusher 110.

[0052] In some examples, such as Figure 3 and Figure 4 As shown, the aforementioned transition section 120 includes: a ring body 121, the first end of which is connected to the support platform 112, and the second end of which is connected to the tail of the aircraft 200; and a separator 122, which is spaced apart around the second end of the ring body 121 and is used to connect the ring body 121 to the tail of the aircraft 200; wherein, during the separation phase, the separator 122 is disconnected to separate the transition section 120 from the aircraft 200.

[0053] It is understood that the transition section 120 may be provided with a ring 121 and a separator 122. The first end of the ring 121 is connected to the support platform 112, and the second end of the ring 121 is connected to the tail of the aircraft 200. Thus, the ring 121 is fitted over the tail nozzle of the aircraft 200, ensuring that the aircraft 200 can be connected to the support platform 112 via the ring 121, and protecting the tail nozzle. Furthermore, a separator 122 is provided at the second end of the ring 121. Specifically, multiple separators 122 may be provided, spaced apart at the second end of the ring 121, allowing the ring 121 to be connected to the aircraft 200. This ensures that during the drive phase, the aircraft 200 can be connected to the support platform 112 via the transition section 120, and the combination of the aircraft 200 and the thruster 110 can move synchronously. During the separation phase, the separator 122 is disconnected to separate the ring 121 from the aircraft 200, thereby separating the aircraft 200 from the thruster 110.

[0054] Understandably, setting multiple separators 122 can improve the tightness of the connection between the ring body 121 and the tail of the aircraft 200. Furthermore, the evenly distributed arrangement of multiple separators 122 ensures that the tail of the aircraft 200 and the ring body 121 are subjected to balanced forces, preventing deviation of the launch trajectory and improving accuracy.

[0055] In some examples, such as Figure 3 and Figure 4 As shown, the aforementioned separation component 122 includes: a housing 1221; a separation bolt 1222, which passes through the side wall of the housing 1221 along the axial direction of the ring 121 and is used to screw into the first threaded hole at the tail of the aircraft 200; and a cover 1223, which covers the housing 1221; wherein, explosives are embedded in the separation bolt 1222, and the separation bolt 1222 will break when the explosives are detonated.

[0056] It is understood that the separating component 122 includes a housing 1221, a separating bolt 1222, and a cover 1223. Specifically, the housing 1221 can be located on the periphery of the second end of the ring 121. The separating bolt 1222 passes through the side wall of the housing 1221 near the end of the aircraft 200 along the axial direction of the ring 121 and is screwed into the first threaded hole at the tail of the aircraft 200 to ensure the tightness of the connection between the aircraft 200 and the transition section 120 during the actuation phase. The cover 1223 can be placed over the housing 1221, and personnel can open the cover 1223 to operate the separating bolt 1222. The cover 1223 can be made of a transparent material to allow personnel to observe the situation inside the housing 1221. Explosives can be embedded inside the separating bolt 1222. During the separation phase, the explosives can be detonated to break the separating bolt 1222, thereby separating the aircraft 200 and the transition section 120. Furthermore, due to the sealing effect of the box 1221 and the cover 1223, the impact range of the explosive explosion can be controlled, the impact on the launch of the aircraft 200 can be reduced, and damage to the aircraft 200 can be avoided.

[0057] In some examples, such as Figure 3 and Figure 4 As shown, the separation component 122 further includes a buffer pad disposed on the side of the housing 1221 away from the separation bolt 1222.

[0058] Understandably, the separation component 122 is also equipped with a buffer pad. Specifically, the buffer pad can be located on the side of the housing 1221 away from the separation bolt 1222. After the separation bolt 1222 explodes and breaks, the broken separation bolt 1222 impacts the other end of the housing 1221. By setting up the buffer pad, the impact force is reduced, thereby reducing the impact on the launch of the aircraft 200 and avoiding damage to the aircraft 200.

[0059] In some examples, such as Figure 3 and Figure 4 As shown, the aforementioned aircraft launching device 100 further includes: a fixing bolt, along the axial direction of the aforementioned ring body 121, a plurality of through holes 1211 are spaced apart at the first end of the aforementioned ring body 121, and a second threaded hole is opened at the corresponding position of the aforementioned support platform 112, the aforementioned fixing bolt passes through the aforementioned through holes 1211 and is screwed into the aforementioned second threaded hole; a mounting window 140 is opened on the periphery of the aforementioned ring body 121, and the aforementioned mounting window 140 communicates with the aforementioned through holes 1211, through which the aforementioned fixing bolt is inserted into the aforementioned through holes 1211.

[0060] Understandably, the aircraft launch device 100 is also equipped with fixing bolts and mounting windows 140. Specifically, along the axial direction of the ring body 121, a plurality of through holes 1211 are spaced apart at the first end of the ring body 121, and a second threaded hole is correspondingly provided at the end face of the support platform 112. Fixing bolts can be passed through the through holes 1211 and screwed into the second threaded holes to connect the ring body 121 to the support platform 112, ensuring a secure connection. During the drive phase, the aircraft 200 can be connected to the support platform 112 via the ring body 121. During the separation phase, the second end of the ring body 121 separates from the tail of the aircraft 200, while the first end of the ring body 121 remains fixed to the support platform 112. Furthermore, an installation window 140 is provided on the periphery of the first end of the ring body 121, and the installation window 140 is connected to the through hole 1211. The fixing bolt is passed through the installation window 140 and inserted into the through hole 1211. By setting the installation window 140, the assembly efficiency of the fixing bolt is improved and the assembly difficulty is reduced.

[0061] In some examples, such as Figure 5 and Figure 6 As shown, the adapter 130 includes: a semi-ring 131 for snapping onto the periphery of the aircraft 200; and a protrusion 132 disposed at the bottom of the semi-ring 131 for inserting into the slide rail 111; wherein the gripping force of the semi-ring 131 on the shell of the aircraft 200 is less than the weight of the semi-ring 131 itself.

[0062] Understandably, the adapter 130 may be provided with a semi-ring 131 and a protrusion 132. Specifically, the periphery of the aircraft 200 can be inserted into the semi-ring 131 through the opening, and the semi-ring 131 will engage with the periphery of the aircraft 200. The protrusion 132 is located at the bottom of the semi-ring 131, and when the aircraft 200 is connected to the support platform 112 via the adapter section 120, the protrusion 132 can be inserted into the slide rail 111. During the driving phase, the support platform 112 pushes the aircraft 200 and the pusher 110 to move synchronously. During the separation phase, when the adapter section 120 and the aircraft 200 separate, the pusher 110 decelerates, and the assembly of the aircraft 200 and the adapter 130 slides towards the end point of the slide rail 111 due to inertia and flies out of the slide rail 111. During this process, the semi-ring 131 generates axial friction on the aircraft 200 to ensure that the adapter 130 can drive the aircraft 200 to slide synchronously, preventing the semi-ring and the aircraft 200 from shifting. After the aircraft 200 and the adapter 130 fly out of the pusher 110, the gripping force of the semi-ring on the aircraft 200 is less than the weight of the semi-ring and the protrusion 132, so that the semi-ring automatically detaches from the aircraft 200, realizing the push-launch of the aircraft 200.

[0063] For example, the semi-ring 131 can be composed of three blocks, which can be joined together by welding. This reduces processing difficulty and improves processing efficiency.

[0064] In some examples, such as Figure 5 and Figure 6 As shown, the adapter 130 further includes an elastic element, wherein the semi-ring 131 is provided with a mounting hole 1311 on the side facing the housing, and the elastic element is disposed in the mounting hole 1311.

[0065] Understandably, the adapter 130 also includes an elastic element. Specifically, the semi-ring 131 has a mounting hole 1311 on the side facing the aircraft 200 housing, and the elastic element can be disposed within the mounting hole 1311. When the elastic element is not under force, part of it protrudes from the mounting hole 1311. When the aircraft 200 is engaged with the semi-ring 131, the elastic element is compressed by the pressure of the aircraft 200. The compressed elastic element increases the contact friction of the aircraft 200 housing, ensuring sufficient friction between the semi-ring 131 and the aircraft 200 housing during the sliding phase of the slide rail 111, so that the adapter 130 and the aircraft 200 move synchronously. Furthermore, after the adapter 130 and aircraft 200 assembly flies out of the slide rail 111, the semi-ring 131 and the aircraft 200 separate under the action of the elastic element's rebound force and the adapter 130's own weight, increasing the separation force between the adapter 130 and the aircraft 200.

[0066] In some examples, such as Figure 5 and Figure 6 As shown, the adapter 130 also includes an anti-slip rubber pad, which is laid on the side of the semi-annular body 131 facing the housing.

[0067] Understandably, the adapter 130 is also equipped with an anti-slip rubber pad. Specifically, the anti-slip rubber pad is laid on the side of the semi-ring 131 facing the housing. This increases the axial friction between the semi-ring 131 and the housing of the aircraft 200. Furthermore, the anti-slip rubber pad has a certain degree of elasticity to prevent hard contact between the semi-ring 131 and the aircraft 200, thus preventing damage to the aircraft 200.

[0068] In some examples, such as Figure 5 and Figure 6 As shown, multiple adapters 130 are provided, and the multiple adapters 130 are arranged at intervals on the periphery of the housing.

[0069] It is understood that multiple adapters 130 can be provided, and the multiple adapters 130 can be arranged at intervals around the periphery of the shell. In this arrangement, the multiple adapters 130 work together to ensure the stability of the center of gravity of the aircraft 200 and the stability of the adapters 130 sliding on the slide rail 111. For example, a total of 5 adapters 130 can be provided.

[0070] In some examples, such as Figure 5 and Figure 6 As shown, the above-mentioned aircraft launching device 100 further includes: a connecting rod 150, which is located along the axial direction of the semi-ring 131. The semi-ring 131 has an interface, and the two ends of the connecting rod 150 are respectively inserted into the interfaces of the adjacent semi-ring 131.

[0071] Understandably, the aircraft launch device 100 is also equipped with a connecting rod 150. Multiple adapters 130 are connected in series via the connecting rod 150. Specifically, interfaces are provided on both sides of the semi-ring 131 along its axial direction, into which the connecting rod 150 can be inserted and secured with pins. This arrangement ensures that multiple adapters 130 are located on the same axis, ensuring smooth sliding of the multiple adapters 130 on the slide rail 111. Furthermore, after the adapter 130 and aircraft 200 assembly exits the launcher 110, the combined weight of the multiple adapters 130 and connecting rod 150 is increased. Moreover, after one adapter 130 detaches from the aircraft 200, the connecting rod 150 increases the downward force on the adapter 130, further enhancing the separation force between the adapter 130 and the aircraft 200.

[0072] In the description of this invention, it should be understood that the terms "upper," "lower," "left," "right," "front," "rear," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or unit referred to must have a specific orientation or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0073] In the description of this specification, the terms "one embodiment," "some embodiments," "specific embodiment," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0074] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A spacecraft launching device, characterized in that, include: A pusher, which is provided with a slide rail and a support platform, is used to move along the pusher rail; A connecting section, one end of which is detachably connected to the tail of the aircraft, and the other end of which is connected to the support platform; An adapter, one end of which is detachably connected to the periphery of the aircraft, and the other end of which is slidably connected to the slide rail; During the propulsion phase, the aircraft is connected to the pusher via the adapter section; During the separation phase, the transition section separates from the tail section of the aircraft, the assembly of the aircraft and the adapter slides off the rail, and the adapter detaches from the periphery of the aircraft. The transition section includes: A ring body, the first end of which is connected to the support platform, and the second end of which is used to connect to the tail of the aircraft; Separating components are spaced apart on the periphery of the second end of the ring body, and the separating components are used to connect the ring body to the tail of the aircraft; During the separation phase, the separation component is disconnected to separate the transition section from the aircraft. The separating element includes: Box body; A separation bolt, along the axial direction of the ring body, passes through the side wall of the box body and is used to be screwed into the first threaded hole at the tail of the aircraft; A cover, which is placed over the box body; The separating bolt contains an explosive charge, which will break when the explosive charge is detonated. The fixing bolt passes through the through holes along the axial direction of the ring body. The first end of the ring body is provided with multiple through holes at intervals, and the corresponding position of the support platform is provided with a second threaded hole. The fixing bolt passes through the through holes and is screwed into the second threaded hole. An installation window is provided on the periphery of the first end of the ring body, and the installation window is connected to the through hole, through which the fixing bolt is inserted into the through hole.

2. The aircraft launching device according to claim 1, characterized in that, The separating component also includes: A buffer pad is provided on the side of the housing away from the separating bolt.

3. The aircraft launching device according to any one of claims 1 to 2, characterized in that, The adapter includes: A semi-ring body, used to snap onto the periphery of the aircraft; A protrusion is provided at the bottom of the semi-ring body, and the protrusion is used to insert into the slide rail; The gripping force of the semi-ring on the aircraft's shell is less than the weight of the semi-ring itself.

4. The aircraft launching device according to claim 3, characterized in that, The adapter also includes: An elastic element is provided, wherein the semi-ring body is provided with a mounting hole on one side facing the housing, and the elastic element is disposed in the mounting hole.

5. The aircraft launching device according to claim 3, characterized in that, The adapter also includes: Anti-slip rubber pads are laid on the side of the semi-ring facing the housing.

6. The aircraft launching device according to claim 3, characterized in that, Multiple adapters are provided, and the multiple adapters are arranged at intervals around the periphery of the housing.

7. The aircraft launching device according to claim 6, characterized in that, Also includes: A connecting rod is provided along the axial direction of the semi-ring body, which has an interface. The two ends of the connecting rod are respectively inserted into the interfaces of adjacent semi-ring bodies.

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