A non-lobbing aircraft separation launcher

Abstract

The present application relates to a kind of non-throwing aircraft separation launching device, it includes: carrier, the carrier is rotatably mounted with two separation supports, the separation support is opened with gap, two the separation support is locked in closed state by separation bolt, and the cavity is formed between two the separation support, two the gap encloses installation port, the separation support is connected with the carrier, and the elastic member between the carrier tends to open two the separation support;The installation port installs aircraft one, the cavity installs aircraft two.Separation bolt explosion separation, release the limiting fixing of separation support, open separation support under the elastic force of elastic member, release the aircraft one in installation port, also prepare work for subsequent aircraft two separation;Separation support is connected with carrier, retains the rotating function, separation support does not throw after rotating, meet the requirement of not adding space junk to affect orbit safety in space launch activity.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace, in particular to a non-throwing type aircraft separation launching device. BACKGROUND

[0002] With the development of space technology and large-scale application of various aircrafts, double-aircraft launching and orbit deployment is one of the effective ways to improve the performance of the carrier vehicle and the task adaptability. In order to realize the reliable separation of the aircraft after entering the orbit, the double-aircraft separation scheme design plays an important role.

[0003] In the related art, the separation scheme of two aircrafts of the same size is mostly a longitudinal arrangement nested scheme. After the upper aircraft is separated, the bracket sleeve of the lower aircraft is unlocked and thrown away before the second aircraft is separated, which inevitably produces space garbage. SUMMARY

[0004] The embodiment of the present application provides a non-throwing type aircraft separation launching device to solve the problem that in the related art, after the upper aircraft is separated, the bracket sleeve of the lower aircraft is unlocked and thrown away before the second aircraft is separated, which inevitably produces space garbage.

[0005] The embodiment of the present application provides a non-throwing type aircraft separation launching device, which comprises:

[0006] A carrier vehicle, wherein two separation brackets are rotatably installed on the carrier vehicle, the separation brackets are provided with notches, the two separation brackets are locked in a closed state by separation bolts, a cavity is formed between the two separation brackets, two notches surround a mounting port, an elastic member is connected between the separation brackets and the carrier vehicle, and the elastic member tends to open the two separation brackets;

[0007] The mounting port is used for mounting an aircraft one, and the cavity is used for mounting an aircraft two.

[0008] In some embodiments, a side wall of the aircraft one is provided with an annular limiting groove;

[0009] A side wall of the mounting port is provided with an annular protruding portion;

[0010] When the two separation brackets are in the closed state, the annular protruding portion is located in the annular limiting groove, and the aircraft one is limited and fixed in the mounting port.

[0011] In some embodiments, a bottom of the aircraft one is provided with a sliding groove, a length direction of the sliding groove is consistent with a spacing direction between the two separation brackets, and the sliding groove penetrates to the outside of the aircraft one;

[0012] An inner side of the separation bracket is fixed with a connecting bracket, and the connecting bracket is fixed with a sliding block.

[0013] When the two separation brackets are opened by rotation, the slider enters the sliding slot and pushes the aircraft to separate from the mounting port.

[0014] In some embodiments, the mounting port is located at the top of the cavity.

[0015] In some embodiments, the slider comprises a spherical pad.

[0016] In some embodiments, the separation bracket is rotatably mounted to the carrier through a rotating shaft.

[0017] The elastic member comprises:

[0018] A torsion spring coaxially sleeved on the rotating shaft.

[0019] The torsion of the two torsion springs tends to open the two separation brackets.

[0020] In some embodiments, the elastic member comprises:

[0021] A spring located outside the cavity and fixed between the separation bracket and the carrier.

[0022] The pulling force of the two springs tends to open the two separation brackets.

[0023] In some embodiments, the elastic member comprises:

[0024] A spring located inside the cavity and fixed between the separation bracket and the carrier.

[0025] The elastic force of the two springs tends to open the two separation brackets.

[0026] In some embodiments, when the two separation brackets are in a closed state, at least one separation bolt is arranged on the same side of the two separation brackets.

[0027] In some embodiments, the length direction of the separation bolt is consistent with the spacing direction of the two separation brackets.

[0028] The technical solution provided by the present application has the following beneficial effects: through the explosion separation of the separation bolt, the limiting and fixing of the two separation brackets are released, and under the driving of the elastic force of the elastic member, the two separation brackets are opened, thereby releasing the aircraft I in the mounting port, completing the separation work of the aircraft I, and also preparing for the separation of the subsequent aircraft II. The separation bracket is connected with the carrier and retains the rotating function, and the separation bracket does not throw away after rotation, meeting the requirement of not increasing space junk to affect the safety of the orbit in the space launch activity. BRIEF DESCRIPTION OF DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced. Obviously, the drawings in the following description only represent some of the embodiments of the present application, and all other drawings obtained by those of ordinary skill in the art without creative effort based on these drawings also belong to the protection scope of the present application.

[0030] Figure 1 A front view structural schematic diagram of the non-throw-off aircraft separation launching device provided by the embodiment of the present application is shown in the figure.

[0031] Figure 2 A top view structural schematic diagram of the non-throw-off aircraft separation launching device provided by the embodiment of the present application is shown in the figure.

[0032] Figure 3 A structural schematic diagram of the separation support initially rotating to open provided by the embodiment of the present application is shown in the figure.

[0033] Figure 4 A partial structural schematic diagram of the non-throw-off aircraft separation launching device provided by the embodiment of the present application is shown in the figure.

[0034] Figure 5 A partial structural schematic diagram of the separation support completely rotating to open provided by the embodiment of the present application is shown in the figure.

[0035] In the figure: 1, carrier; 2, separation support; 21, notch; 211, annular protruding part; 22, cavity; 23, mounting port; 221, annular protruding part; 3, elastic member; 4, separation bolt; 5, aircraft one; 51, annular limiting groove; 52, sliding groove; 6, aircraft two; 7, connecting support; 8, sliding block. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be described clearly and completely below in combination with the drawings of the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, and not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort also belong to the protection scope of the present application.

[0037] The non-throw-off aircraft separation launching device provided by the embodiment of the present application solves the problem that in the related art, after the upper aircraft is separated, the support sleeve of the lower aircraft is inevitably thrown off after being unlocked, and then the second aircraft is separated, which inevitably produces space garbage.

[0038] As Figure 1 and Figure 2As shown, the embodiment of the present application provides a non-throwing aircraft separation launching device, which can include: a carrier 1, the carrier 1 is rotatably installed with two separation supports 2, the separation supports 2 are provided with notches 21, the two separation supports 2 are locked in a closed state by separation bolts 4, and a cavity 22 is formed between the two separation supports 2, the two notches 21 surround a mounting port 23, an elastic member 3 is connected between the separation supports 2 and the carrier 1, and the elastic member 3 tends to open the two separation supports 2; the mounting port 23 is mounted with an aircraft one 5, and the cavity 22 is mounted with an aircraft two 6.

[0039] Specifically, the carrier 1 enters a predetermined orbit, the control system issues a separation instruction of the aircraft one 5, the separation bolt 4 is detonated to be unlocked, the separation supports 2 are separated, the preset elastic force of the elastic member 3 makes the two separation supports 2 rotate to two sides, with the rotation of the separation supports 2, the aircraft one 5 in the mounting port 23 is unlocked, the separation work of the aircraft one 5 is realized, after the separation supports 2 are rotated to the position, a separation instruction of the aircraft two 6 is issued, the separation of the aircraft two 6 is completed, and the separation supports 2 are separated from the orbit together with the carrier 1. Among them, the separation work of the aircraft one 5 is completed, and preparation work for the separation of the subsequent aircraft two 6 is also completed; the separation supports 2 are connected with the carrier 1, the rotation function is retained, the separation supports 2 are not thrown after being rotated, and the requirement that the space debris is not increased in the space flight launching activity to affect the safety of the orbit is met.

[0040] As shown in some embodiments, Figure 2 and Figure 3 As shown, the side wall of the aircraft one 5 is provided with an annular limiting groove 51; the side wall of the mounting port 23 is provided with an annular protruding part 211, and specifically, as shown in Figure 2 the inner side wall of each notch 21 is provided with an arc-shaped protruding part, when the two separation supports 2 are closed, the annular protruding part 211 is formed; when the two separation supports 2 are in a closed state, the annular protruding part 211 is located in the annular limiting groove 51, and the aircraft one 5 is limited and fixed in the mounting port 23. Among them, the aircraft one 5 is limited and fixed in the mounting port 23 formed by the rotation and closing of the two separation supports 2 through the cooperation of the annular limiting groove 51 and the annular protruding part 211, when the two separation supports 2 are rotated and opened, the mounting port 23 is released, so that the limitation between the annular limiting groove 51 and the annular protruding part 211 is released, and the separation work of the aircraft one 5 is completed.

[0041] In some optional embodiments, the annular limiting groove 51 can be discontinuously and intermittently arranged, that is, a plurality of arc-shaped limiting grooves are arranged in the side wall of the aircraft one 5, and the plurality of arc-shaped limiting grooves are distributed in the circumferential direction of the aircraft one 5; the arc-shaped protruding parts in the two notches 21 can also be discontinuously and intermittently arranged, and the number thereof is equal to that of the arc-shaped limiting grooves, and the installation limiting work of the aircraft one 5 can also be completed.

[0042] In some embodiments, such as Figure 4 As shown, a chute 52 is defined at the bottom of the aircraft 5. The length of the chute 52 is aligned with the spacing between the two separation brackets 2, and the chute 52 extends to the outside of the aircraft 5. A connecting bracket 7 is fixed to the inner side of the separation bracket 2, and a slider 8 is fixed to the connecting bracket 7. When the two separation brackets 2 rotate open, the slider 8 enters the chute 52 and pushes the aircraft 5 out of the mounting opening 23. The rotation of the two separation brackets 2 causes the attached connecting bracket 7 to tilt outward, pushing the slider 8 thereon into the chute 52. This, along the trajectory of the chute 52, limits the rotational direction of the two separation brackets 2, preventing significant deviation. This, in turn, reliably pushes the aircraft 5 out of its position, completing the separation of the aircraft 5 and providing a certain initial separation velocity.

[0043] Furthermore, the installation port 23 is located at the top of the chamber 22. The installation port 23 is located at the top of the chamber 22, which can reliably push the aircraft 15 to move axially.

[0044] In some embodiments, the slider 8 may include a spherical pad. The spherical pad can prevent unnecessary damage to the aircraft 5 and provide flexible contact. The top of the spherical pad is curved, creating point contact with the inner bottom wall of the chute 52, reducing friction and ensuring smooth rotation and separation of the two separation brackets 2.

[0045] Of course, in some embodiments, the slider 8 can also be a ball, a pulley, etc.

[0046] In some embodiments, the separation bracket 2 is rotatably mounted on the carrier 1 via a rotating shaft. The elastic member 3 includes a torsion spring coaxially mounted on the rotating shaft. The torsion force of the two torsion springs tends to open the two separation brackets 2. The torsion springs have a certain torsional force that can reliably rotate the separation bracket 2 and ensure its smooth movement.

[0047] In some embodiments, the elastic member 3 may include a spring located outside the chamber 22 and fixed between the separation bracket 2 and the carrier 1 ; the tension of the two springs tends to open the two separation brackets 2 .

[0048] In some embodiments, the elastic member 3 may include a spring located in the chamber 22 and fixed between the separation bracket 2 and the carrier 1 ; the elastic force of the two springs tends to open the two separation brackets 2 .

[0049] Among them, when the elastic member 3 can be in the form of a spring, the spring can be located inside the chamber 22, and its elastic force pushes the two separation brackets 2 to rotate and separate; when located outside the chamber 22, its elastic force pulls the two separation brackets 2 to rotate and separate.

[0050] In some embodiments, at least one separation bolt 4 is arranged on the same side of the two separated supports 2 when the two separated supports 2 are in a closed state. Specifically, as shown in Figure 1 at least one separation bolt 4 is arranged on the rear side of the two separated supports 2, and at least one separation bolt 4 (not shown in the figure) is arranged on the front side of the two separated supports 2.

[0051] In some alternative embodiments, the number of separation bolts 4 on each side can be multiple, and the multiple separation bolts 4 are distributed along the height direction of the separation support 2.

[0052] In some embodiments, the length direction of the separation bolt 4 is consistent with the spacing direction of the two separated supports 2. By arranging the separation bolt 4 in the same direction as the spacing direction of the two separated supports 2, the explosion impact of the separation bolt 4 can be transmitted in the radial direction, which provides a certain initial speed for the separation of the two separated supports 2, optimizes the stability of the separation support 2 during operation, and ensures that the two separated supports 2 can be smoothly separated.

[0053] In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be a fixed connection, or it can be a detachable connection, or an integral connection; it can be a mechanical connection, or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or it can be the communication between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0054] It should be noted that in the present application, relational terms such as "first" and "second" and the like are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device. Without more limitations, the element defined by the statement "including a" does not exclude the presence of another identical element in the process, method, article or device including the element.

[0055] The foregoing is considered as illustrative only of the principles of the application. Numerous modifications and changes will readily occur to those skilled in the art, and it is intended to embrace all such modifications and changes that fall within the scope of the application. Accordingly, the application is not to be restricted in scope to the specific embodiments disclosed herein but is to be accorded the full scope that the principles and novel features request appropriately granted.

Claims

1. A non-jet-off aircraft separation and launch device, characterized in that: It includes: A carrier (1), wherein the carrier (1) is rotatably mounted with two separation brackets (2), the separation brackets (2) are provided with notches (21), the two separation brackets (2) are locked in a closed state by separation bolts (4), and a chamber (22) is formed between the two separation brackets (2), the two notches (21) enclose a mounting opening (23), an elastic member (3) is connected between the separation brackets (2) and the carrier (1), and the elastic member (3) tends to open the two separation brackets (2); The mounting opening (23) is used to mount aircraft one (5), and the chamber (22) is used to mount aircraft two (6); A slide groove (52) is provided at the bottom of the aircraft (5), the length direction of the slide groove (52) is consistent with the spacing direction of the two separation brackets (2), and the slide groove (52) passes through to the outside of the aircraft (5); A connecting bracket (7) is fixed on the inner side of the separation bracket (2), and a slider (8) is fixed to the connecting bracket (7); When the two separation brackets (2) are rotated and opened, the slider (8) enters the slide groove (52) and pushes the aircraft (5) to separate from the installation opening (23).

2. The non-jet-off type aircraft separation and launch device according to claim 1, characterized in that: The side wall of the aircraft (5) is provided with an annular limiting groove (51); The side wall of the installation opening (23) is provided with an annular protrusion (211); When the two separation brackets (2) are in a closed state, the annular protrusion (211) is located in the annular limiting groove (51), limiting and fixing the aircraft (5) to the installation opening (23).

3. The non-jet-off type aircraft separation and launch device according to claim 1, characterized in that: The mounting opening (23) is located at the top of the chamber (22).

4. The non-jet-off type aircraft separation and launch device according to claim 1, characterized in that: The slider (8) includes a spherical pad.

5. The non-jet-off type aircraft separation and launch device according to claim 1, characterized in that: The separation bracket (2) is rotatably mounted on the carrier (1) via a rotation shaft; The elastic member (3) comprises: a torsion spring, the torsion spring being coaxially sleeved on the rotating shaft; The torsion force of the two torsion springs tends to open the two separation brackets (2).

6. The non-jet-off type aircraft separation and launching device according to claim 1, characterized in that: The elastic member (3) comprises: a spring, the spring being located outside the chamber (22) and fixed between the separation bracket (2) and the carrier (1); The tension of the two springs tends to open the two separation brackets (2).

7. The non-jet-off type aircraft separation and launching device according to claim 1, characterized in that: The elastic member (3) comprises: a spring, the spring being located in the chamber (22) and being fixed between the separation bracket (2) and the carrier (1); The elastic force of the two springs tends to open the two separation brackets (2).

8. The non-jet-off type aircraft separation and launching device according to claim 1, characterized in that: When the two separation brackets (2) are in a closed state, at least one separation bolt (4) is provided on the same side of the two separation brackets (2).

9. The non-jet-off type aircraft separation and launching device according to claim 1, characterized in that: The length direction of the separation bolt (4) is consistent with the spacing direction of the two separation brackets (2).

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