A high-speed aircraft pneumatic separation mechanism

Abstract

The present invention provides a high-speed aircraft pneumatic separation mechanism, belonging to the technical field of high-speed aircraft, comprising an aircraft body, wherein the aircraft body is in a cone-like shape and is separated at least once during flight, thereby forming a plurality of aircraft with a waverider configuration and independent of each other; and during the separation process, explosion separation is performed in sequence in a front-to-back order; after the explosion of the connecting mechanism, under the push of a separation spring, the front ends of the corresponding aircraft are separated from each other to form an airflow gap, and the ammunition loading area therein is exploded to complete the overall separation of the corresponding aircraft. The present invention combines a plurality of independent waverider configuration aircraft to form a cone-like aircraft body, and during the flight of the aircraft, the aircraft body can be separated according to mission requirements, and the separation of the above-mentioned aircraft is achieved under the auxiliary push of airflow, and has a simple structure, is stable and reliable, and greatly improves the flight envelope and mission range of the aircraft.

Description

Technical Field

[0001] The invention relates to the technical field of high-speed aircraft, in particular to a high-speed aircraft pneumatic separation mechanism. Background Art

[0002] At present, traditional aircraft designs are often limited by the structure of the aircraft, making it difficult to achieve precise target missions at high speeds. At the same time, the efficiency and flexibility of a single aircraft for multi-target missions also have certain limitations.

[0003] To this end, researchers have begun to explore high-speed aircraft with multiple aircraft, each with autonomous target recognition, positioning and mission achievement capabilities. This design can improve the mission efficiency and flexibility of the aircraft for achieving multiple targets and increase the flight envelope of the aircraft;

[0004] The multi-aircraft in the prior art is usually composed of a plurality of split sub-aircraft with the same appearance. The plurality of split sub-aircraft are neatly arranged in a mother cabin, and the mother cabin fairing is thrown away at the end of the flight, thereby separating the split sub-aircraft from the mother cabin, thereby achieving the purpose of releasing multiple targets at the same time. However, the above-mentioned split sub-aircraft and the mother cabin propulsion unit are composed of a segmented combination, and each of them carries different functions. Therefore, the structural utilization rate is not high, and it is difficult to meet the current functional complexity requirements. Summary of the invention

[0005] The object of the present invention is to provide a high-speed aircraft aerodynamic separation mechanism to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A high-speed aircraft pneumatic separation mechanism, comprising:

[0008] An aircraft body, the aircraft body being in a cone-like shape and being separated at least once during flight to form a plurality of independent aircrafts having a waverider configuration;

[0009] Each independent flying vehicle is connected to each other by a connecting mechanism at the front end of the flight and a connecting hinge at the rear end of the flight before separation. Both the connecting mechanism and the connecting hinge have an ammunition loading area, and are separated by explosion in a front-to-back order during the separation process.

[0010] A separation spring is also provided between each adjacent aircraft, and the separation spring is provided near the connection mechanism at the front end of the aircraft. After the connection mechanism explodes, the front ends of the corresponding aircraft are separated from each other under the push of the separation spring to form an airflow gap. During the flight of the aircraft, the airflow gap gradually increases to push the connection hinge to rotate around the axis.

[0011] When the connecting hinge is rotated to a preset angle, the ammunition loading area therein explodes to complete the overall separation of the corresponding aircraft.

[0012] Preferably, the aircraft body undergoes two synchronous separations during the flight, and after the first separation is completed, a pair of separation transition bodies with a semicircular bottom shape are formed. The second separation process is carried out on the basis of a pair of separation transition bodies, and finally an aircraft is formed. The aircraft includes a first aircraft with two triangular bottom surfaces and a second aircraft with four arched circular arc bottom surfaces.

[0013] Preferably, the preset bursting rotation angle of the connecting hinge is 60°.

[0014] Preferably, a blasting pressure plate is installed at the blade body rotation axis on one side of the connecting hinge, and the blasting pressure plate cooperates with the blasting contact installed at the blade body rotation axis on the other side of the connecting hinge. When the blasting pressure plate is folded 60° in the expanded state, it contacts the blasting contact to detonate the ammunition loading area inside the connecting hinge.

[0015] Preferably, the connecting mechanism connecting the separation transition bodies on both sides is a pair of arc locks, and the pair of arc locks are installed in the bolt connection grooves corresponding to the aircraft body through the first blasting bolts. After the arc locks on both sides are blasted, the front ends of the pair of separation transition bodies constituting the aircraft body are separated.

[0016] Preferably, the connection structure connecting the first aircraft and the second aircraft is a second blasting bolt, and the second blasting bolt combines the first aircraft and a pair of second aircraft to form a separation transition body.

[0017] Preferably, the separation spring includes a primary separation spring and a secondary separation spring, and the primary separation spring and the secondary separation spring are both installed in spring grooves corresponding to the aircraft body. The primary separation spring is used to achieve the separation of the separation transition bodies on both sides, and the secondary separation spring is used to achieve the separation of the first aircraft and the second aircraft.

[0018] Preferably, one end of the primary separation spring and the secondary separation spring are connected to the spring groove on the same side through an explosive block. After the corresponding separation transition bodies and the first aircraft and the second aircraft are completely separated, the corresponding explosive block works to make the primary separation spring or the secondary separation spring detach from the spring groove.

[0019] Preferably, the first blasting bolt and the second blasting bolt are blasted sequentially under the command control of a control system.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] The present invention combines multiple independent waverider configuration aircraft to form a cone-like aircraft body. During the flight of the aircraft, the aircraft bodies can be separated according to mission requirements, thereby forming multiple aircraft with special aerodynamic shapes. The separation of the above-mentioned aircraft is achieved with the auxiliary promotion of airflow, and has a simple structure, stable and reliable, which greatly improves the flight envelope and mission range of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the separation process of the aircraft body of the present invention;

[0023] Figure 2 It is an enlarged schematic diagram of the aircraft body and local structure of the present invention;

[0024] Figure 3 It is a schematic diagram of the cross section of the aircraft body of the present invention and its partial enlargement;

[0025] Figure 4 It is a schematic diagram of the connecting hinge structure of the present invention;

[0026] Figure 5 A schematic diagram of a first aircraft and a second aircraft of the present invention;

[0027] Figure 6 It is a schematic diagram of folding the connecting hinge of the present invention;

[0028] Figure 7 It is a schematic diagram of the first blasting bolt and its ammunition loading area of ​​the present invention;

[0029] Figure 8 It is a schematic diagram of the second blasting bolt and its ammunition loading area of ​​the present invention.

[0030] In the figure: 1 aircraft body, 2 connecting hinge, 3 ammunition loading area, 4 separation transition body, 5 first aircraft, 6 second aircraft, 7 blasting pressure plate, 8 blasting contact, 9 arc lock, 10 second blasting bolt, 11 primary separation spring, 12 secondary separation spring, 13 spring groove, 14 blasting block, 15 first blasting bolt. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0032] See also Figure 1-8 , the present invention provides a technical solution:

[0033] Embodiment 1:

[0034] A high-speed aircraft pneumatic separation mechanism, comprising:

[0035] The aircraft body 1 is in a cone-like shape and is separated at least once during the flight, thereby forming a plurality of independent aircrafts having a waverider configuration;

[0036] Each independent flying vehicle is connected to each other by a connecting mechanism at the front end of the flight and a connecting hinge 2 at the rear end of the flight before separation. Both the connecting mechanism and the connecting hinge 2 have an ammunition loading area 3, and are separated by explosion in a front-to-back order during the separation process.

[0037] A separation spring is also provided between each adjacent aircraft. The separation spring is provided near the connection mechanism at the front end of the aircraft. After the connection mechanism explodes, the front ends of the corresponding aircraft are separated from each other under the push of the separation spring to form an airflow gap. During the flight of the aircraft, the airflow gap gradually increases, thereby pushing the connection hinge 2 to rotate around the axis.

[0038] When the connecting hinge 2 is rotated to a preset angle, the ammunition loading area 3 therein explodes to complete the overall separation of the corresponding aircraft.

[0039] In this embodiment, the aircraft body 1 is in a cone-like shape. In this shape, the overall structure of the aircraft body 1 is similar to that of a conventional aircraft. Unlike the prior art, the aircraft body 1 in this embodiment can be separated multiple times during flight, thereby greatly improving the flight envelope of the aircraft and supporting simultaneous missions to multiple targets. In order to achieve the above technical effects, the aircraft body 1 will be synchronously separated more than once during flight, and finally form multiple independent aircraft. Figure 1 and 5The aircraft body 1 is synchronously separated twice during the flight. After the first separation is completed, a pair of separation transition bodies 4 with a semicircular bottom shape are formed. The second separation process is carried out on the basis of the pair of separation transition bodies 4, and finally an aircraft is formed. The aircraft includes two first aircraft 5 with triangular bottoms and four second aircraft 6 with arched arc bottoms. The first aircraft 5 and the second aircraft 6 have a waverider configuration that is more suitable for hypersonic flight. Its separation scheme is different from the mother cabin carrying multiple neatly arranged aircraft in the prior art. Its separation process is faster, and the independent aircraft form formed has a certain aerodynamic layout. The specific separation process generally includes: detonating the corresponding connecting mechanism from the head end of the aircraft body 1. Since a separation spring is provided between the adjacent independent aircrafts of the aircraft body 1, when the connecting mechanism releases the restriction on the corresponding connecting part, the corresponding separated part A certain gap is opened under the action of the spring thrust. Since the aircraft will be subject to air resistance during flight, when the separation part generates a gap under the push of the separation spring, gas enters the gap to further prompt the corresponding separation part to expand outward. At this time, the rear end of the separation part is still connected to the connecting hinge 2, and the connecting hinge 2 is folded at a certain angle. When the connecting hinge 2 is rotated to a preset angle, the ammunition loading area 3 therein is exploded to complete the overall separation of the corresponding aircraft. Specifically, the preset blasting rotation angle of the connecting hinge 2 is 60°. The separation trigger mechanism of the connecting hinge 2 specifically includes: a blasting pressure plate 7 is installed at the blade body rotation shaft on one side of the connecting hinge 2, and the blasting pressure plate 7 is movably matched with the blasting contact 8 installed at the blade body rotation shaft on the other side of the connecting hinge 2. When the blasting pressure plate 7 is folded 60° in the expanded state, it contacts the blasting contact 8 to detonate the ammunition loading area 3 inside the connecting hinge 2.

[0040] Embodiment 2:

[0041] The connection mechanism connecting the separation transition bodies 4 on both sides is a pair of arc locks 9, which are installed in the corresponding bolt connection grooves of the aircraft body 1 through the first blasting bolts 15. After the arc locks 9 on both sides are blasted, the front ends of the pair of separation transition bodies 4 constituting the aircraft body 1 are separated.

[0042] The connection structure connecting the first aircraft 5 and the second aircraft 6 is a second blasting bolt 10 , and the second blasting bolt 10 combines the first aircraft 5 and a pair of second aircraft 6 to form a separation transition body 4 .

[0043] The first blasting bolt 15 and the second blasting bolt 10 are blasted sequentially under the command control of the control system.

[0044] In this embodiment, the specific structure of the connecting structure is specifically disclosed, which includes an arc lock 9, a first blasting bolt 15 and a second blasting bolt 10. The first blasting bolt 15 and the second blasting bolt 10 are sequentially blasted under the command control of the control system, thereby realizing two separation processes, and finally separating the aircraft body 1 into 6 first aircraft 5 and second aircraft 6 with a waveriding configuration and independent of each other.

[0045] Embodiment three:

[0046] The separation spring includes a primary separation spring 11 and a secondary separation spring 12. The primary separation spring 11 and the secondary separation spring 12 are both installed in spring grooves 13 corresponding to the aircraft body 1. The primary separation spring 11 is used to achieve the separation of the separation transition bodies 4 on both sides, and the secondary separation spring 12 is used to achieve the separation of the first aircraft 5 and the second aircraft 6.

[0047] One end of the primary separation spring 11 and the secondary separation spring 12 are connected to the spring groove 13 on the same side through the explosion block 14. After the corresponding separation transition bodies 4 and the first aircraft 5 and the second aircraft 6 are completely separated, the corresponding explosion block 14 works to make the primary separation spring 11 or the secondary separation spring 12 disengage from the spring groove.

[0048] In this embodiment, a primary separation spring 11 and a secondary separation spring 12 for pushing the front end of each independent aircraft to separate are further disclosed. The primary separation spring 11 and the secondary separation spring 12 are compressed and arranged in the spring groove 13 corresponding to the first aircraft 5 and the second aircraft 6, and after the corresponding separation process is completed, the explosive block 14 arranged inside the primary separation spring 11 or the secondary separation spring 12 is detonated, thereby completing the separation of the separation spring and the aircraft. The separation of the separation spring and the aircraft occurs after the corresponding aircraft is completely separated, in order to prevent the separation spring from colliding with the corresponding aircraft body during the abandonment process, thereby ensuring the safety and reliability of the separation process. The above-mentioned explosive block 14 is also carried out under the command control of the control system.

[0049] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A high-speed aircraft pneumatic separation mechanism, characterized in that: include: An aircraft body, the aircraft body being in a cone-like shape and being separated at least once during flight to form a plurality of independent aircrafts having a waverider configuration; Each independent flying vehicle is connected to each other by a connecting mechanism at the front end of the flight and a connecting hinge at the rear end of the flight before separation. Both the connecting mechanism and the connecting hinge have an ammunition loading area, and are separated by explosion in a front-to-back order during the separation process. A separation spring is also provided between each adjacent aircraft, and the separation spring is provided near the connection mechanism at the front end of the aircraft. After the connection mechanism explodes, the front ends of the corresponding aircraft are separated from each other under the push of the separation spring to form an airflow gap. During the flight of the aircraft, the airflow gap gradually increases to push the connection hinge to rotate around the axis. When the connecting hinge is rotated to a preset angle, the ammunition loading area therein explodes to complete the overall separation of the corresponding aircraft; The main body of the aircraft undergoes two synchronous separations during the flight, and after the first separation is completed, a pair of separation transition bodies with a semicircular bottom shape are formed. The second separation process is carried out on the basis of a pair of separation transition bodies, and finally an aircraft is formed. The aircraft includes a first aircraft with two triangular bottom surfaces and a second aircraft with four arched circular arc bottom surfaces.

2. The high-speed aircraft aerodynamic separation mechanism according to claim 1, characterized in that: The preset bursting rotation angle of the connecting hinge is 60°.

3. The high-speed aircraft aerodynamic separation mechanism according to claim 2, characterized in that: A blasting pressure plate is installed at the blade body rotation axis on one side of the connecting hinge, and the blasting pressure plate cooperates with the blasting contact installed at the blade body rotation axis on the other side of the connecting hinge. When the blasting pressure plate is folded 60° in the unfolded state, it contacts the blasting contact to detonate the ammunition loading area inside the connecting hinge.

4. The high-speed aircraft aerodynamic separation mechanism according to claim 3, characterized in that: The connection mechanism connecting the separation transition bodies on both sides is a pair of arc locks, which are installed in the bolt connection grooves corresponding to the aircraft body through the first blasting bolts. After the arc locks on both sides are blasted, the front ends of the pair of separation transition bodies constituting the aircraft body are separated.

5. The high-speed aircraft aerodynamic separation mechanism according to claim 4, characterized in that: The connection structure connecting the first aircraft and the second aircraft is a second blasting bolt, and the second blasting bolt combines the first aircraft and a pair of second aircraft to form a separation transition body.

6. A high-speed aircraft aerodynamic separation mechanism according to claim 4 or 5, characterized in that: The separation spring includes a primary separation spring and a secondary separation spring, and both the primary separation spring and the secondary separation spring are installed in spring grooves corresponding to the aircraft body. The primary separation spring is used to separate the separation transition bodies on both sides, and the secondary separation spring is used to separate the first aircraft from the second aircraft.

7. The high-speed aircraft aerodynamic separation mechanism according to claim 6, characterized in that: One end of the primary separation spring and the secondary separation spring are connected to the spring groove on the same side through an explosive block. After the corresponding separation transition bodies and the first aircraft and the second aircraft are completely separated, the corresponding explosive block works to make the primary separation spring or the secondary separation spring detach from the spring groove.

8. The high-speed aircraft aerodynamic separation mechanism according to claim 7, characterized in that: The first blasting bolt and the second blasting bolt are blasted sequentially under the command control of the control system.

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