A double-row sub-aircraft ejection and automatic shifting mechanism for high-speed aircraft

Abstract

The present invention provides a mechanism for ejecting and automatically shifting double-row sub-aircraft of a high-speed aircraft, including a plurality of aircraft accommodating compartments, wherein a first-stage sub-aircraft and a second-stage sub-aircraft are arranged in sequence in the accommodating space, and each of the first-stage sub-aircraft and the second-stage sub-aircraft is provided with a corresponding protective cover at the outer end away from the opening of the accommodating space, and a reverse thrust sleeve is installed at the outer end of each of the protective covers, and after the second-stage sub-aircraft is separated from the aircraft accommodating compartment, the trim displacement sleeve remains in a relatively static state with the aircraft accommodating compartment after displacement. The present invention uses the aircraft accommodating compartment to install the aircraft and eject the aircraft backward, which greatly reduces the influence of the ejection process on the aerodynamic shape of the carrier aircraft. The sub-aircraft ejection mechanism has a simple layout, and during the ejection process of the front and rear sub-aircraft, the gravity in the cabin can be redistributed, thereby ensuring the stability of the high-speed aircraft before and after the sub-aircraft is released.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, in particular to a double-row sub-aircraft ejection and automatic shifting mechanism for high-speed aircraft. Background Art

[0002] High-speed aircraft generally refers to aerospace vehicles designed for high-speed flight, such as drones, airplanes, missiles, rockets or spacecraft. They have a variety of functions and have been widely used in many fields such as military, commercial aviation, space exploration, logistics and transportation, meteorology and fire fighting.

[0003] The prior art discloses a device and method for quickly separating the back of a two-stage orbital vehicle with a publication number of "CN112874822A". The device includes a jet generator formed on a carrier aircraft, which is used to provide an upward jet to a separation surface of a secondary vehicle connected to the carrier aircraft to offset part of the gravity of the secondary vehicle itself. The device can provide an upward jet to the secondary vehicle to form an upward thrust, so that the secondary vehicle can rotate relative to the carrier aircraft to make a head-up movement to form a first target inclination angle, increase the pitch angle of the secondary vehicle, and increase the local angle of attack so that the lift generated by the secondary vehicle increases rapidly, so that the secondary vehicle can quickly rise to a certain height to avoid colliding with the tail wing of the carrier aircraft. The jet generator does not have complex mechanical movements when working, so it has a fast startup speed. It can provide a jet to the secondary vehicle when it is started, which can greatly shorten the time required for the secondary vehicle to reach a safe height.

[0004] However, the above-mentioned aircraft separation device still has obvious defects during use: the above-mentioned sub-aircraft is installed on the outside of the main aircraft, which is not conducive to reducing wind resistance on the one hand; on the other hand, in the prior art, it is usually necessary to launch multiple aircraft according to demand, and the above-mentioned device is subject to the external installation method of the aircraft, which will greatly limit the layout of multiple aircraft and thus cannot meet the launch needs of multiple groups of aircraft. Summary of the invention

[0005] The object of the present invention is to provide a mechanism for ejecting and automatically shifting double-row sub-aircraft of a high-speed aircraft 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 mechanism for discharging and automatically shifting double-row sub-aircraft of a high-speed aircraft comprises a plurality of aircraft accommodating compartments, each of which is provided with an accommodating space with an opening at one end, wherein a first-stage sub-aircraft and a second-stage sub-aircraft are arranged in sequence front to back in the accommodating space.

[0008] The first-stage sub-aircraft and the second-stage sub-aircraft are each sleeved with a corresponding protective cover on the outside of one end away from the opening of the accommodation space, and the outer end of each protective cover is installed with a reverse thrust sleeve, and the reverse thrust sleeve is filled with reverse thrust gunpowder, and the reverse thrust gunpowder pushes the corresponding protective cover and the sub-aircraft to separate outward from the opening end of the accommodation space during the ignition and explosion process;

[0009] The first-stage sub-aircraft and its corresponding protective cover are also provided with a balancing displacement sleeve on the outside. After the second-stage sub-aircraft leaves the aircraft accommodation cabin, the balancing displacement sleeve is pushed by the balancing component to shift to the side close to the opening end of the accommodation space to adjust the gravity distribution in the aircraft accommodation cabin. After the shift is completed, the balancing displacement sleeve remains relatively stationary with the aircraft accommodation cabin.

[0010] Preferably, the first-stage sub-aircraft and the second-stage sub-aircraft both have a conical head end, and the protective cover is arranged on one side of the conical head end of the sub-aircraft.

[0011] Preferably, the protective cover is formed by splicing two symmetrically arranged arc-shaped panels, and a pneumatic separation baffle is also installed on the arc-shaped panels. When the protective cover is separated from the aircraft accommodation cabin, the arc-shaped panels on both sides move away from each other under the disturbance of airflow, thereby separating from the protection of the conical head end of the sub-aircraft.

[0012] Preferably, the balancing component that pushes the balancing displacement sleeve to shift is a pushing spring, and the pushing spring is sleeved on the outside of the balancing displacement sleeve. The balancing displacement sleeve is also integrally formed with a raised stop edge on the open end side close to the accommodating space. The two ends of the pushing spring respectively abut against the inner wall of the accommodating space and the raised stop edge. The pushing spring pushes the balancing displacement sleeve to move toward the open end close to the accommodating space in the absence of external force. The accommodating space is also provided with an inwardly contracted limit stop edge, and the limit stop edge is used to block the raised stop edge to limit the movement of the balancing displacement sleeve.

[0013] Preferably, an opening baffle is installed on one side of the opening end of the accommodating space through a plurality of blasting bolts.

[0014] Preferably, a flip baffle is installed on one side of the opening end of the balancing displacement sleeve close to the accommodating space through a rotating shaft. The flip baffle is used to block and protect the rear end of the balancing displacement sleeve in the initial state. The flip baffle flips outward and opens during the separation process of the first-stage sub-aircraft, and at this time the flip baffle is free from blocking the tail of the first-stage sub-aircraft.

[0015] Preferably, the flip baffle is hinged with a multi-section flip connecting rod, and the multi-section flip connecting rod extends to one side of the conical head end of the first-stage sub-aircraft and is fixedly connected to the action connecting rod. The action connecting rod is inserted into a reverse thrust sleeve arranged at the front end, and generates displacement during the ignition and explosion of the reverse thrust gunpowder therein, thereby pushing the flip baffle to rotate around the axis and open.

[0016] Preferably, the blasting bolts, the second-stage sub-vehicle and the thrust reverser gunpowder in the thrust reverser sleeves corresponding to the first-stage sub-vehicle are sequentially and controlledly blasted under the command control of the control system.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] The present invention installs the aircraft through the aircraft accommodating cabin and discharges the sub-aircraft backwards, which will greatly reduce the impact of the discharge process on the aerodynamic shape of the carrier aircraft. The aircraft adopts a spatial layout in which the aircraft is arranged in a front-to-back sequence, which will greatly reduce wind resistance. The sub-aircraft ejection mechanism has a simple layout, which is conducive to reducing the failure rate of ejection. In addition, during the ejection process of the front and rear sub-aircraft, the gravity in the cabin can be redistributed, thereby ensuring the stability of the high-speed aircraft before and after the sub-aircraft is released. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 The state diagram of the sub-aircraft distribution separation process of the present invention;

[0020] Figure 2 It is a partial enlarged schematic diagram of the protective cover and its connection structure of the present invention;

[0021] Figure 3 It is a partial enlarged schematic diagram of the balancing displacement sleeve and its connection structure of the present invention;

[0022] Figure 4 It is a schematic diagram of the raised retaining edge and the limiting retaining edge of the present invention.

[0023] In the figure: 1 aircraft accommodating cabin, 2 accommodating space, 3 first-stage sub-aircraft, 4 second-stage sub-aircraft, 5 protective cover, 6 reverse thrust sleeve, 7 balancing displacement sleeve, 8 arc-shaped enclosure, 9 pneumatic separation baffle, 10 pushing spring, 11 raised baffle edge, 12 limit baffle, 13 opening baffle, 14 rotating shaft, 15 flip baffle, 16 multi-section flip connecting rod, 17 action connecting rod. DETAILED DESCRIPTION

[0024] 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.

[0025] See also Figure 1-4 , the present invention provides a technical solution:

[0026] Embodiment 1:

[0027] A mechanism for ejecting and automatically shifting double-row sub-aircraft of a high-speed aircraft comprises a plurality of aircraft accommodating compartments 1, each of which is provided with an accommodating space 2 with an opening at one end, and a first-stage sub-aircraft 3 and a second-stage sub-aircraft 4 are arranged in sequence in front and back in the accommodating space 2;

[0028] The first-stage sub-aircraft 3 and the second-stage sub-aircraft 4 are both sleeved with corresponding protective covers 5 on the outside of the opening of the accommodating space 2, and the outer ends of the protective covers 5 are both installed with reverse thrust sleeves 6, and the reverse thrust sleeves 6 are filled with reverse thrust gunpowder. The reverse thrust gunpowder pushes the corresponding protective cover 5 and the sub-aircraft to separate outward from the opening end of the accommodating space 2 during the ignition and explosion process;

[0029] A balancing displacement sleeve 7 is also provided on the outside of the first-stage sub-aircraft 3 and the corresponding protective cover 5. After the second-stage sub-aircraft 4 is separated from the aircraft accommodating cabin 1, the balancing displacement sleeve 7 is shifted to the side close to the opening end of the accommodating space 2 under the push of the balancing component to adjust the gravity distribution in the aircraft accommodating cabin 1. After the shift is completed, the balancing displacement sleeve 7 remains relatively stationary with the aircraft accommodating cabin 1.

[0030] In this embodiment, the aircraft accommodating cabin 1 can be installed inside a high-speed aircraft, or it can be set in the form of an external pod. A accommodating space 2 for placing the aircraft is opened inside the aircraft accommodating cabin 1. The advantage of this arrangement is that the sub-aircraft is completely hidden inside the aircraft accommodating cabin 1, which can effectively reduce wind resistance. Different from the prior art, in this embodiment, two sub-aircraft are installed in each accommodating space 2. The sub-aircraft are placed in a front-to-back sequence, which can also reduce the wind-breaking area, thereby further reducing wind resistance. At the same time, in order to achieve controlled batch separation of the first-stage sub-aircraft 3 and the second-stage sub-aircraft 4, a protective cover 5 is also installed at the head end of the first-stage sub-aircraft 3 and the second-stage sub-aircraft 4. Both the first-stage sub-aircraft 3 and the second-stage sub-aircraft 4 have a conical head end. The protective cover 5 is arranged on one side of the conical head end of the sub-aircraft. The outer end of the protective cover 5 is installed with a reverse thrust sleeve 6, and the reverse thrust sleeve 6 is filled with reverse thrust gunpowder. During the ignition and explosion process, the gunpowder pushes the corresponding protective cover 5 and the sub-aircraft to separate outward from the open end of the accommodating space 2, wherein the protective cover 5 is to protect the head end of the sub-aircraft from damage during the ignition process, and since the first-stage sub-aircraft 3 and the second-stage sub-aircraft 4 are not released at the same time, when the second-stage sub-aircraft 4 is released, if the position of the first-stage sub-aircraft 3 does not change, it will affect the counterweight balance of the entire aircraft accommodating compartment 1. If the position of the first-stage sub-aircraft 3 is not adjusted in time, it will affect the overall flight stability of the aircraft. For this reason, in this embodiment, a balancing displacement sleeve 7 is further provided, and the balancing displacement sleeve 7 is arranged on the outside of the first-stage sub-aircraft 3. The displacement of the balancing displacement sleeve 7 drives the first-stage sub-aircraft 3 and its connecting components to produce a position, thereby readjusting the gravity distribution in the aircraft accommodating compartment 1, thereby effectively ensuring the overall flight stability of the device after the second-stage sub-aircraft 4 is separated.

[0031] Embodiment 2:

[0032] The protective cover 5 is composed of two symmetrically arranged arc-shaped panels 8, on which a pneumatic separation baffle 9 is also installed. When the protective cover 5 is separated from the aircraft compartment 1, the arc-shaped panels 8 on both sides move away from each other under the disturbance of the airflow, thereby separating from the protection of the conical head end of the aircraft.

[0033] In this embodiment, the protective cover 5 is formed by two arc-shaped panels 8, and a pneumatic separation baffle 9 is installed on the outside of the protective cover 5. When the protective cover 5 and the corresponding sub-aircraft connected thereto are separated from the aircraft accommodation cabin 1, the arc-shaped panels 8 move away from each other under the disturbance of the airflow and thus separate from the corresponding sub-aircraft.

[0034] Embodiment three:

[0035] The balancing component that pushes the balancing displacement sleeve 7 to shift is a pushing spring 10. The pushing spring 10 is sleeved on the outside of the balancing displacement sleeve 7. The balancing displacement sleeve 7 is also integrally formed with a raised stop edge 11 on the open end side close to the accommodating space 2. The two ends of the pushing spring 10 respectively abut against the inner wall of the accommodating space 2 and the raised stop edge 11. The pushing spring 10 pushes the balancing displacement sleeve 7 to move toward the open end side close to the accommodating space 2 in the absence of external force. An inwardly contracted limiting stop edge 12 is also provided in the accommodating space 2. The limiting stop edge 12 is used to block the raised stop edge 11 to limit the movement of the balancing displacement sleeve 7.

[0036] In this embodiment, the balancing displacement sleeve 7 and its internal structure are pushed by pushing the spring 10, so that they are displaced. The cleverness of this design lies in that the balancing operation can be completed by pushing only one component, the spring 10, and the cooperation of the raised retaining edge 11 and the limiting retaining edge 12 makes the balancing displacement sleeve 7 stop shifting at the set position. Therefore, the position of the limiting retaining edge 12 is set specifically, so that its internal structure can be quickly adjusted after the separation of the first-stage sub-aircraft, so as to ensure the stability of subsequent flight.

[0037] Embodiment 4:

[0038] An opening baffle 13 is also installed on one side of the opening end of the accommodating space 2 through a plurality of blasting bolts.

[0039] A flip baffle 15 is also installed on one side of the opening end of the balancing displacement sleeve 7 close to the accommodating space 2 through a rotating shaft 14. The flip baffle 15 is used to block and protect the rear end of the balancing displacement sleeve 7 in the initial state. The flip baffle 15 flips outward and opens during the separation process of the first-stage sub-aircraft 3. At this time, the flip baffle 15 is free from blocking the tail of the first-stage sub-aircraft 3.

[0040] In this embodiment, a blocking structure at the open end of the accommodating space 2 and a blocking structure at the tail end of the balancing displacement sleeve 7 are further disclosed, through which the first-stage sub-aircraft 3 and the second-stage sub-aircraft 4 are respectively limited to prevent them from leaving the aircraft accommodating cabin 1.

[0041] Embodiment five:

[0042] The flip baffle 15 is hinged with a multi-section flip connecting rod 16, which extends to one side of the conical head end of the first-stage sub-aircraft 3 and is fixedly connected with an action connecting rod 17. The action connecting rod 17 is inserted into a reverse thrust sleeve 6 arranged at the front end, and generates displacement during the ignition and explosion of the reverse thrust gunpowder therein, thereby pushing the flip baffle 15 to rotate around the axis and open.

[0043] In this embodiment, a reversing mechanism of the flip baffle 15 is further disclosed, which cleverly utilizes the reverse thrust gunpowder loaded in the reverse thrust sleeve 6 arranged at the front end of the first-stage sub-aircraft 3 as a power source. During the ignition and explosion of the reverse thrust gunpowder, the thrust generated thereby pushes the action connecting rod 17 to move, thereby causing the flip baffle 15 to flip open, and on the other hand, pushes the second-stage sub-aircraft 4 to detach from the open end of the accommodating space 2 to achieve the second-stage separation of the sub-aircraft.

[0044] Among them, the above-mentioned blasting bolts, the second-stage sub-aircraft 4 and the reverse thrust gunpowder in the reverse thrust sleeve 6 corresponding to the first-stage sub-aircraft 3 are sequentially controlled and blasted under the command control of the control system, thereby realizing sequential separation of the front and the back.

[0045] 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 mechanism for ejecting and automatically shifting double-row sub-aircraft of a high-speed aircraft, comprising a plurality of aircraft accommodating compartments, each of which is provided with an accommodating space with an opening at one end, wherein a first-stage sub-aircraft and a second-stage sub-aircraft are arranged in sequence in front and back in the accommodating space, characterized in that: The first-stage sub-aircraft and the second-stage sub-aircraft are each sleeved with a corresponding protective cover on the outside of one end away from the opening of the accommodation space, and the outer end of each protective cover is installed with a reverse thrust sleeve, and the reverse thrust sleeve is filled with reverse thrust gunpowder, and the reverse thrust gunpowder pushes the corresponding protective cover and the sub-aircraft to separate outward from the opening end of the accommodation space during the ignition and explosion process; The first-stage sub-aircraft and the corresponding protective cover are also provided with a trim displacement sleeve on the outside. After the second-stage sub-aircraft is separated from the aircraft accommodating cabin, the trim displacement sleeve is pushed by the trim assembly to shift to the side close to the opening end of the accommodating space so as to adjust the gravity distribution in the aircraft accommodating cabin. After the shift is completed, the trim displacement sleeve remains relatively stationary with the aircraft accommodating cabin. The balancing component that pushes the balancing displacement sleeve to shift is a pushing spring, and the pushing spring is sleeved on the outside of the balancing displacement sleeve. The balancing displacement sleeve is also integrally formed with a raised stop edge on the open end side close to the accommodating space. The two ends of the pushing spring respectively abut against the inner wall of the accommodating space and the raised stop edge. The pushing spring pushes the balancing displacement sleeve to move toward the open end of the accommodating space in the absence of external force. The accommodating space is also provided with an inwardly contracted limit stop edge, and the limit stop edge is used to block the raised stop edge to limit the movement of the balancing displacement sleeve.

2. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 1, characterized in that: The first-stage sub-aircraft and the second-stage sub-aircraft both have a conical head end, and the protective cover is arranged on one side of the conical head end of the sub-aircraft.

3. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 2, characterized in that: The protective cover is formed by two symmetrically arranged arc-shaped panels, on which a pneumatic separation baffle is also installed. When the protective cover is separated from the aircraft compartment, the arc-shaped panels on both sides move away from each other under the disturbance of the airflow, thereby separating from the protection of the conical head end of the sub-aircraft.

4. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 3, characterized in that: An opening baffle is also installed on one side of the opening end of the accommodating space through a plurality of blasting bolts.

5. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 4, characterized in that: A flip baffle is also installed on one side of the open end of the balancing displacement sleeve close to the accommodating space through a rotating shaft. The flip baffle is used to block and protect the rear end of the balancing displacement sleeve in the initial state. The flip baffle flips outward and opens during the separation process of the first-stage sub-aircraft, at which time the flip baffle is free from blocking the tail of the first-stage sub-aircraft.

6. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 5, characterized in that: The flip baffle is hinged with a multi-section flip connecting rod, which extends to one side of the conical head end of the first-stage sub-aircraft and is fixedly connected with an action connecting rod. The action connecting rod is inserted into a reverse thrust sleeve arranged at the front end, and generates displacement during the ignition and explosion of the reverse thrust gunpowder therein, thereby pushing the flip baffle to rotate around the axis and open.

7. The mechanism for ejecting and automatically shifting double-row sub-aircraft for high-speed aircraft according to claim 6, characterized in that: The blasting bolts, the second-stage sub-aircraft and the thrust reverser gunpowder in the thrust reverser sleeves corresponding to the first-stage sub-aircraft are sequentially and controlledly blasted under the command control of the control system.

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