A zero-length boost target machine with foldable cabin door

Abstract

The present application relates to a target machine, in particular to a zero-length boost type target machine with foldable cabin door. The target machine comprises a fuselage, a zero-length thrust structure, an automatic folding door and a zero-length boost rocket; a rocket launching port is arranged on the lower side of the fuselage near the tail; the zero-length thrust structure is installed inside the fuselage at a position near the nose at the rocket launching port; the mounting end of the zero-length boost rocket is connected with the zero-length thrust structure through the rocket launching port, the output end is arranged outside the rocket launching port, and an included angle is arranged between the axial direction of the zero-length boost rocket and the length direction of the fuselage; the automatic folding door is installed at the rocket launching port of the fuselage and is matched with the rocket launching port. The present application adopts the zero-length folding door scheme, before boost flight, the automatic folding door is opened, the zero-length boost rocket is filled in the folding door and connected with the zero-length thrust structure, after boost separation, the automatic folding door is closed, the target machine restores the normal aerodynamic shape, and the subsequent flight performance and stealth performance are not affected.

Description

TECHNICAL FIELD

[0001] The application relates to a zero-length boost type target machine, in particular to a zero-length boost type target machine with foldable cabin doors. BACKGROUND

[0002] At present, the ground launching of the target machine products in service at home is mainly zero-length launching, and when the traditional target machine is launched in zero-length, the target machine is placed on a launching frame, the thrust generated by a zero-length boost rocket is transmitted to the target machine through a thrust cone, and the target machine is pushed to take off on the ground.

[0003] However, the thrust cone of the traditional target machine is usually arranged outside the fuselage, and after the zero-length boost rocket is separated, the remaining thrust cone will damage the aerodynamic shape of the target machine, and will affect the flight performance and stealth performance of the target machine during the flight of the target machine. SUMMARY

[0004] The application aims to solve the technical problem that the thrust cone of the existing target machine is arranged outside the fuselage, and after the zero-length boost rocket is separated, the remaining thrust cone will damage the aerodynamic shape of the target machine, and will affect the flight performance and stealth performance of the target machine during the flight of the target machine, and provides a zero-length boost type target machine with foldable cabin doors.

[0005] To achieve the above-mentioned purpose, the technical scheme adopted by the application is as follows:

[0006] A zero-length boost type target machine with foldable cabin doors, which is characterized in that:

[0007] The zero-length boost type target machine comprises a fuselage, a zero-length thrust structure, an automatic folding door and a zero-length boost rocket.

[0008] The fuselage is provided with a rocket launching port at a position close to the tail on the lower side.

[0009] The zero-length thrust structure is installed inside the fuselage at a position close to the nose at the rocket launching port, the mounting end of the zero-length boost rocket passes through the rocket launching port and is connected with the zero-length thrust structure, the output end is arranged outside the rocket launching port, and an included angle is arranged between the axial direction of the zero-length boost rocket and the length direction of the fuselage.

[0010] The automatic folding door is installed at the rocket launching port of the fuselage and is matched with the rocket launching port, the automatic folding door is used to open when the zero-length boost rocket is connected with the zero-length thrust structure, and is used to automatically close after the zero-length boost rocket is cold separated from the zero-length thrust structure, so as to shield the rocket launching port and maintain the original aerodynamic shape of the target machine.

[0011] Further, the automatic folding door comprises a folding door plate, a torsional spring hinge, a quick-release lock and a quick-release lock locking mechanism.

[0012] The number of the folding door plates is two, which are oppositely arranged at the rocket launching port and have the length direction parallel to the length direction of the rocket launching port, and the two folding door plates are adapted to the rocket launching port in the closed state, and the folding door plates are used to open the rocket launching port when the zero-length boost rocket is installed to the zero-length thrust structure and shield the rocket launching port after the cold separation of the zero-length boost rocket and the zero-length thrust structure.

[0013] The torsion spring hinges are divided into two groups, each group including at least one torsion spring hinge, one end of the two groups of torsion spring hinges being respectively installed on the two folding doors, and the other end being respectively installed on the fuselage at the rocket launching port, for automatically closing the folding door plates after the cold separation of the zero-length boost rocket and the zero-length thrust structure.

[0014] The quick-release locks are divided into two groups, each group including at least one quick-release lock, and the two groups of quick-release locks being respectively installed on the inner walls of the two folding doors.

[0015] The quick-release lock locking mechanisms are divided into two groups, each group including at least one quick-release lock locking mechanism, and the two groups of quick-release lock locking mechanisms being respectively installed on the fuselage at the rocket launching port and being respectively arranged corresponding to the two groups of quick-release locks, for being correspondingly matched with the two groups of quick-release locks to lock the two folding door plates on the fuselage when the folding door plates are closed.

[0016] Further, the number of the quick-release locks and the quick-release lock locking mechanisms in each group is two.

[0017] The two quick-release locks in the same group are respectively installed on the folding door plates close to the fuselage close to the nose and the tail.

[0018] The two quick-release lock locking mechanisms in the same group are respectively installed on the rocket launching port of the fuselage close to the nose and the tail.

[0019] Further, the number of the torsion spring hinges in each group is two, and the two torsion spring hinges in the same group are arranged along the length direction of the folding door plate and are respectively located at both ends of the same side of the folding door plate.

[0020] Further, the zero-length thrust structure includes a force transmission structure and a thrust cone.

[0021] The force transmission structure is installed on the fuselage, the large end of the thrust cone is connected with the force transmission structure, and the small end is connected with the zero-length boost rocket.

[0022] The axial direction of the thrust cone is parallel to the axial direction of the zero-length boost rocket.

[0023] Further, the conical surface of the thrust cone is provided with a positioning sub-hole, which corresponds to and matches a positioning female hole of a mounting end of the zero-length boost rocket, so as to judge whether the zero-length boost rocket is mounted in place according to the coincidence degree of the positioning sub-hole and the positioning female hole.

[0024] Further, the included angle is 12°-18°.

[0025] The present application has the following beneficial effects:

[0026] 1. The present application has the ability to keep the aerodynamic shape after the zero-length launch boost separation, adopts a foldable zero-folding door scheme, the automatic folding door is opened before boost flight, the zero-length boost rocket is filled in the folding door and connected with the zero-length thrust structure, the automatic folding door is closed after boost separation, the target machine restores the normal aerodynamic shape, and the subsequent flight performance and stealth performance are not affected.

[0027] 2. The quick-release lock and the quick-release lock locking mechanism can lock the folding door plate on the fuselage after the folding door plate is closed, and improve the stability of the closed folding door plate.

[0028] 3. The present application has the measure of thrust cone alignment during boost filling, the positioning sub-hole is arranged on the thrust cone, the positioning female hole on the zero-length boost rocket and the positioning sub-hole on the thrust cone are judged to be completely coincident through a special zero-length pin after boost filling is completed, so as to judge whether the zero-length boost rocket is completely mounted in place. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is a state structure schematic view when the zero-length boost rocket is connected to the zero-length thrust structure in the embodiment of the present application;

[0030] Figure 2 is a state structure schematic view when the zero-length boost rocket is cold separated from the zero-length thrust structure in the embodiment of the present application;

[0031] Figure 3 is a state schematic view of the automatic folding door when the zero-length boost rocket is connected to the zero-length thrust structure in the embodiment of the present application;

[0032] Figure 4 is a state schematic view of the automatic folding door after the zero-length boost rocket is cold separated from the zero-length thrust structure in the embodiment of the present application;

[0033] Figure 5 is a structure schematic view of the zero-length thrust structure in the embodiment of the present application.

[0034] In the figure: 1 - fuselage, 2 - zero-length thrust structure, 21 - force transmission structure, 22 - thrust cone; 3 - automatic folding door, 31 - folding door panel, 32 - torsion spring hinge, 33 - quick-release lock, 34 - quick-release lock locking mechanism, 4 - zero-length boost rocket, 5 - rocket launch port. DETAILED DESCRIPTION

[0035] In order to make the purposes, advantages and characteristics of the present application clearer, a zero-length boost target aircraft with foldable cabin door is further described in detail below in combination with the drawings and specific embodiments. The advantages and characteristics of the present application will be clearer according to the following specific embodiments. It should be noted that: the drawings are all very simplified and use non-precise proportions, only for the purpose of facilitating and clarifying the description of the embodiments of the present application; secondly, the structures shown in the drawings are often part of the actual structure.

[0036] Referring to Figure 1 , the zero-length boost target aircraft with foldable cabin door of the embodiment includes a fuselage 1, a zero-length thrust structure 2, an automatic folding door 3 and a zero-length boost rocket 4.

[0037] The rocket launch port 5 is arranged at the position close to the tail of the lower side of the fuselage 1, so as to facilitate the installation of the zero-length boost rocket 4 to the target aircraft.

[0038] Specifically, the zero-length thrust structure 2 is installed inside the fuselage 1 at the position close to the nose of the rocket launch port 5, and then the installation end of the zero-length boost rocket 4 is connected with the zero-length thrust structure 2 through the rocket launch port 5, so that the output end is placed outside the rocket launch port 5, facilitating the boosting by the zero-length boost rocket 4.

[0039] Referring to Figure 5 , specifically, in the embodiment, the zero-length thrust structure 2 includes a force transmission structure 21 and a thrust cone 22; the force transmission structure 21 is installed on the fuselage 1, the large end of the thrust cone 22 is connected with the force transmission structure 21, and the small end is connected with the zero-length boost rocket 4; the axial direction of the thrust cone 22 is arranged in parallel with the axial direction of the zero-length boost rocket 4. The positioning sub-hole is arranged on the conical surface of the thrust cone 22, so that when the zero-length boost rocket 4 is connected, it can be matched with the positioning female hole of the installation end of the zero-length boost rocket 4, after the filling is completed, the external zero-length pin is passed through the positioning sub-hole and the positioning female hole, to determine whether the zero-length boost rocket 4 is installed in place, and after confirming that it is installed in place, the zero-length pin is pulled out. The number of positioning sub-holes is at least one, and can also be two or three, which can be specifically set according to the actual installation precision.

[0040] To ensure smooth separation of the zero-length booster rocket 4, the thrust cone 22 must have an appropriate angle. The present invention selects an angle of 12 to 18 degrees for the thrust cone 22, which allows for smooth separation of the zero-length booster rocket 4. The force transmission structure 21 transmits the thrust generated during boosting to the fuselage 1. The interface between the thrust cone 22 and the force transmission structure 21 is flat and bolted together. The thrust line can be adjusted by adding shims to the bolts at the interface.

[0041] See also Figure 2 、 Figure 3 and Figure 4 The automatic folding door 3 is installed at the rocket launching port 5 of the fuselage 1, and the automatic folding door 3 is adapted to the rocket launching port 5. The automatic folding door 3 can be opened when the zero-length booster rocket 4 is connected to the zero-length thrust structure 2, so as to facilitate the installation of the zero-length booster rocket 4. After the boosting work is completed, the zero-length booster rocket 4 and the fuselage 1 produce an acceleration difference and a speed difference, and the zero-length booster rocket 4 and the zero-length thrust structure 2 are separated, and the automatic folding door 3 automatically closes to cover the rocket launching port 5, and the target aircraft returns to its original aerodynamic shape.

[0042] Specifically, in this embodiment, the automatic folding door 3 includes a folding door panel 31 , a torsion spring hinge 32 , a quick-release lock 33 and a quick-release lock locking mechanism 34 .

[0043] There are two folding door panels 31, which are arranged relatively at the rocket launching port 5, and their length directions are arranged parallel to the length direction of the rocket launching port 5. When the two folding door panels 31 are in the closed state, they are adapted to the rocket launching port 5. The folding door panels 31 are used to open the rocket launching port 5 when the zero-length booster rocket 4 is installed to the rocket launching port 5, and under the action of the torsion spring hinge 32, the folding door panels 31 are overlapped on the outer shell of the zero-length booster rocket 4; after the zero-length booster rocket 4 is cold-separated from the zero-length thrust structure 2, it can automatically close, thereby covering the rocket launching port 5, so that the fuselage returns to its original aerodynamic shape, and will not affect the subsequent flight performance and stealth performance.

[0044] The torsion spring hinges 32 are divided into two groups, and each group has two torsion spring hinges 32. The two torsion spring hinges 32 in the same group are arranged along the length direction of the folding door panel 31, and are respectively located at the two ends of the same side of the folding door panel 31. The folding door panel 31 is automatically closed after the zero-length booster rocket 4 and the zero-length thrust structure 2 are cold-separated by the torsion spring hinge 32 itself.

[0045] The quick-release lock 33 in the embodiment adopts a southco M1-2A-handle pop-out door lock. The quick-release lock 33 is divided into two groups, each of which includes two quick-release locks 33; the two quick-release locks 33 of the same group are respectively installed at positions close to the nose and the tail of the fuselage 1 near the folding door plate 31; the quick-release lock locking mechanism 34 is a corresponding mature product of the same series as the quick-release lock 33, and the quick-release lock locking mechanism 34 is also divided into two groups, each of which includes two quick-release lock locking mechanisms 34; the two quick-release lock locking mechanisms 34 of the same group are respectively installed at positions close to the nose and the tail of the fuselage 1 near the rocket launching port 5, and are respectively arranged corresponding to the two groups of quick-release locks 33, and are used to lock the folding door plate 31 on the fuselage 1 by cooperating with the two groups of quick-release locks 33 when the folding door plate 31 is closed.

Claims

1. A zero-length booster target drone with a foldable hatch, characterized by: It includes a fuselage (1), a zero-length thrust structure (2), an automatic folding door (3) and a zero-length booster rocket (4); A rocket launching port (5) is provided on the lower side of the fuselage (1) near the tail; The zero-length thrust structure (2) is installed inside the fuselage (1) at a position near the nose of the aircraft at the rocket launch port (5); the installation end of the zero-length booster rocket (4) passes through the rocket launch port (5) and is connected to the zero-length thrust structure (2); the output end is placed outside the rocket launch port (5); and an angle is set between the axial direction of the zero-length booster rocket (4) and the length direction of the fuselage (1); The automatic folding door (3) is installed at the rocket launch port (5) of the fuselage (1) and is adapted to the rocket launch port (5). The automatic folding door (3) is used to open when the zero-length booster rocket (4) is connected to the zero-length thrust structure (2), and automatically close after the zero-length booster rocket (4) and the zero-length thrust structure (2) are cold-separated, thereby shielding the rocket launch port (5). The automatic folding door (3) comprises a folding door panel (31), a torsion spring hinge (32), a quick-release lock (33) and a quick-release lock locking mechanism (34); There are two folding door panels (31) arranged relative to each other on the fuselage at the rocket launch port (5). The folding door panels (31) are used to open the rocket launch port (5) when the zero-length booster rocket (4) is installed on the zero-length thrust structure (2), and to cover the rocket launch port (5) after the zero-length booster rocket (4) is cold-separated from the zero-length thrust structure (2) to maintain the original aerodynamic shape of the target drone. The torsion spring hinges (32) are divided into two groups, each group including at least one torsion spring hinge (32); one end of the two groups of torsion spring hinges (32) are respectively mounted on the two folding door panels (31), and the other end is respectively mounted on the fuselage (1) at the rocket launch port (5), and is used for automatically closing the folding door panels (31) after the zero-length booster rocket (4) and the zero-length thrust structure (2) are cold-separated; The quick-release locks (33) are divided into two groups, each group including at least one quick-release lock (33); the two groups of quick-release locks (33) are respectively installed on the inner walls of the two folding door panels (31); The quick-release lock mechanism (34) is divided into two groups, each group including at least one quick-release lock mechanism (34); the two groups of quick-release lock mechanisms (34) are respectively installed at the rocket launch port (5) of the fuselage (1), and are respectively arranged correspondingly with the two groups of quick-release locks (33), and are used to cooperate with the two groups of quick-release locks (33) when the folding door panels (31) are closed, so as to lock the two folding door panels (31) on the fuselage (1); The zero-length thrust structure (2) includes a force transmission structure (21) and a thrust cone (22); The force transmission structure (21) is installed on the fuselage (1), the large end of the thrust cone (22) is connected to the force transmission structure (21), and the small end is connected to the zero-length booster rocket (4); The axial direction of the thrust cone (22) is arranged parallel to the axial direction of the zero-length booster rocket (4); A positioning sub-hole is provided on the conical surface of the thrust cone (22), which corresponds to and matches the positioning mother hole at the installation end of the zero-length booster rocket (4) when the zero-length booster rocket (4) is connected, and is used to judge whether the zero-length booster rocket (4) and the thrust cone (22) are installed in place based on the overlap between the positioning sub-hole and the positioning mother hole.

2. The zero-length booster target drone with a foldable hatch according to claim 1, characterized in that: The number of each set of quick-release locks (33) and quick-release lock locking mechanisms (34) is two; Two quick-release locks (33) of the same group are respectively installed on the folding door panel (31) at positions close to the fuselage (1) and close to the front and tail of the fuselage; Two quick-release locking mechanisms (34) of the same group are respectively installed at the rocket launching port (5) of the fuselage (1) near the nose and tail of the fuselage.

3. The zero-length booster target drone with a foldable hatch according to claim 2, characterized in that: The number of the torsion spring hinges (32) in each group is two, and the two torsion spring hinges (32) in the same group are arranged along the length direction of the folding door panel (31) and are respectively located at the two ends of the same side of the folding door panel (31).

4. The zero-length booster target drone with a foldable hatch according to claim 1, characterized in that: The angle is 12°-18°.

Images