Zero-length boosting type target drone with foldable cabin door

Abstract

The invention relates to a target drone, in particular to a zero-length boosting type target drone with a foldable cabin door. The target drone comprises a drone body, a zero-length thrust structure, an automatic folding door and a zero-length booster rocket, a rocket launching port is formed in the lower side of the fuselage close to the tail; the zero-length thrust structure is mounted at the position, close to the nose, of the rocket launching opening in the fuselage, the mounting end of the zero-length booster rocket penetrates through the rocket launching opening to be connected with the zero-length thrust structure, the output end of the zero-length booster rocket is arranged outside the rocket launching opening, and an included angle is formed between the axial direction of the zero-length booster rocket and the length direction of the fuselage; the automatic folding door is installed at a rocket launching opening of the fuselage and matched with the rocket launching opening. A foldable zero folding door scheme is adopted, before boosting flight, an automatic folding door is opened, a zero-length boosting rocket is filled in the folding door to be connected with a zero-length thrust structure, after boosting separation, the automatic folding door is closed, the target drone recovers to the normal aerodynamic configuration, and the subsequent flight performance and stealth performance are not affected.

Description

Technical Field

[0001] The invention relates to a zero-length boost type target drone, in particular to a zero-length boost type target drone with a foldable cabin door. Background Art

[0002] At present, the ground launch of target drone products in service in China is mainly based on zero-length launch. During zero-length launch, the traditional target drone is placed on the launch pad, and the thrust generated by the zero-length booster rocket is transmitted to the target drone through the thrust cone, pushing the target drone to take off from the ground.

[0003] However, the thrust cone of a traditional target drone is usually placed outside the fuselage. After the zero-length booster rocket separates, the remaining thrust cone will destroy the aerodynamic shape of the target drone, affecting its flight performance and stealth performance during flight. Summary of the invention

[0004] The purpose of the present invention is to solve the technical problem that the thrust cone of the existing target drone is placed outside the fuselage. After the zero-length boost rocket separates, the remaining thrust cone will destroy the aerodynamic shape of the target drone, which will affect the flight performance and stealth performance of the target drone during the flight of the target drone, and to provide a zero-length boost target drone with a foldable door.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is:

[0006] A zero-length booster target drone with foldable doors, which is special in that:

[0007] Includes fuselage, zero-length thrust structure, automatic folding doors and zero-length booster rockets;

[0008] A rocket launching port is provided on the lower side of the fuselage near the tail;

[0009] The zero-length thrust structure is installed inside the fuselage at a position near the rocket launch port and the nose of the fuselage, the installation end of the zero-length booster rocket passes through the rocket launch port and is connected to the zero-length thrust structure, the output end is placed outside the rocket launch port, and an angle is set between the axial direction of the zero-length booster 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 adapted to the rocket launching port. The automatic folding door is used to open when the zero-length booster rocket is connected to the zero-length thrust structure, and automatically close after the zero-length booster rocket is cold-separated from the zero-length thrust structure, thereby covering the rocket launching port and maintaining the original aerodynamic shape of the target aircraft.

[0011] Further, the automatic folding door comprises a folding door panel, a torsion spring hinge, a quick release lock and a quick release lock locking mechanism;

[0012] There are two folding door panels, which are arranged opposite to each other at the rocket launch port, and their length directions are arranged parallel to the length direction of the rocket launch port. When the two folding door panels are in a closed state, they are adapted to the rocket launch port. The folding door panels are used to open the rocket launch port when the zero-length booster rocket is installed on the zero-length thrust structure, and to cover the rocket launch port after the zero-length booster rocket is cold-separated from the zero-length thrust structure.

[0013] The torsion spring hinges are divided into two groups, each group includes at least one torsion spring hinge; one end of the two groups of torsion spring hinges are respectively installed on the two folding doors, and the other end is respectively installed on the fuselage at the rocket launch port, for automatically closing the folding door panels after the zero-length booster rocket is cold-separated from the zero-length thrust structure;

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

[0015] The quick-release lock locking mechanism is divided into two groups, each group includes at least one quick-release lock locking mechanism; the two groups of quick-release lock locking mechanisms are respectively installed at the rocket launching port of the fuselage, and are respectively arranged corresponding to the two groups of quick-release locks, and are used to cooperate with the two groups of quick-release locks when the folding door panels are closed to lock the two folding door panels on the fuselage.

[0016] Further, the number of each set of quick release locks and quick release lock locking mechanisms is two;

[0017] Two quick-release locks of the same group are installed on the folding door panel close to the fuselage near the nose and tail respectively;

[0018] The two quick-release locking mechanisms of the same group are installed at the rocket launching port of the fuselage near the nose and tail respectively.

[0019] Furthermore, the number of 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 panel and are respectively located at two ends of the same side of the folding door panel.

[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 to the force transmission structure, and the small end is connected to the zero-length booster rocket;

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

[0023] Furthermore, a positioning sub-hole is provided on the conical surface of the thrust cone, which corresponds to the positioning mother hole at the mounting end of the zero-length booster rocket when the zero-length booster rocket is connected, and is used to judge whether the zero-length booster rocket and the thrust cone are installed in place according to the degree of overlap between the positioning sub-hole and the positioning mother hole.

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

[0025] The beneficial effects of the present invention are:

[0026] 1. The present invention has the ability to maintain the aerodynamic shape after the zero-length launch boost separation, and adopts a foldable zero-folding door solution. Before the boost flight, the automatic folding door opens, the zero-length boost rocket is loaded into the folding door and connected to the zero-length thrust structure, and the automatic folding door closes after the boost separation, and the target aircraft restores its normal aerodynamic shape without affecting the subsequent flight performance and stealth performance.

[0027] 2. The quick-release lock and the quick-release lock locking mechanism provided in the present invention can lock the folding door panel on the fuselage after the folding door panel is closed, thereby improving the stability of the folding door panel after closing.

[0028] 3. The present invention has a measure for aligning the thrust cone during booster loading. By setting a positioning sub-hole on the thrust cone, after the booster loading is completed, a special zero-length pin is used to determine whether the positioning mother hole on the zero-length booster rocket and the positioning sub-hole on the thrust cone are completely overlapped, so as to determine whether the zero-length booster rocket is completely installed in place. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the state structure when the zero-length booster rocket is connected to the zero-length thrust structure in an embodiment of the present invention;

[0030] Figure 2 2 is a schematic diagram of the state structure of the zero-length booster rocket and the zero-length thrust structure when cold separation occurs in an embodiment of the present invention;

[0031] Figure 3 is a schematic diagram of the state of the automatic folding door in an embodiment of the present invention when the zero-length booster rocket is connected to the zero-length thrust structure;

[0032] Figure 4 is a schematic diagram of the state of the automatic folding door in the embodiment of the present invention after the zero-length booster rocket and the zero-length thrust structure are cold separated;

[0033] Figure 5 Schematic diagram of the structure of the zero-length thrust structure in an embodiment of the present invention.

[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 booster rocket, 5-rocket launching port. DETAILED DESCRIPTION

[0035] In order to make the purpose, advantages and features of the present invention clearer, the following is a further detailed description of a zero-length booster target drone with a foldable hatch proposed by the present invention in combination with the accompanying drawings and specific embodiments. According to the following specific implementation methods, the advantages and features of the present invention will be clearer. It should be noted that: the drawings are all in a very simplified form and use non-precise proportions, which are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention; secondly, the structure shown in the drawings is often a part of the actual structure.

[0036] See also Figure 1 The present embodiment provides a zero-length booster target drone with a foldable door, comprising a fuselage 1, a zero-length thrust structure 2, an automatic folding door 3 and a zero-length booster rocket 4.

[0037] A rocket launching port 5 is provided at a position near the tail of the lower side of the fuselage 1, so as to facilitate installation of the zero-length booster rocket 4 on the target drone.

[0038] Specifically, the zero-length thrust structure 2 is installed inside the fuselage 1 at a position near the rocket launching port 5 close to the nose, and then the mounting end of the zero-length booster rocket 4 is passed through the rocket launching port 5 to be connected to the zero-length thrust structure 2, so that the output end is placed outside the rocket launching port 5, so as to facilitate the boosting through the zero-length booster rocket 4.

[0039] See also Figure 5 Specifically, in this 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 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 arranged on the conical surface of the thrust cone 22, so that when the zero-length booster rocket 4 is connected, it can be matched with the positioning mother hole at the installation end of the zero-length booster rocket 4. After the filling is completed, the external zero-length pin is passed through the positioning sub-hole and the positioning mother hole to determine whether the zero-length booster rocket 4 is installed in place. 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 2 or 3, which can be specifically set according to the actual installation accuracy required.

[0040] In order to enable the zero-length booster rocket 4 to separate smoothly, the cone angle of the thrust cone 22 should be selected appropriately. The present invention selects the angle of the thrust cone 22 to be 12 to 18 degrees, and the zero-length booster rocket 4 can separate smoothly at this angle. The force transmission structure 21 transmits the thrust generated during the boosting operation to the fuselage 1. The butt joint between the thrust cone 22 and the force transmission structure 21 is a plane, which is connected and fixed by bolts. The thrust line can be adjusted by adding a gasket at the bolts of the butt joint.

[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 accordingly. 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 the present 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 relatively arranged 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 a 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 be automatically closed, thereby covering the rocket launching port 5, so that the fuselage is restored 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, each group of torsion spring hinges 32 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 by the torque of the torsion spring hinge 32 itself after the zero-length booster rocket 4 and the zero-length thrust structure 2 are cold separated.

[0045] The quick release lock 33 in this embodiment adopts a Southco M1-2A-handle pop-up door lock. The quick release lock 33 is divided into two groups, each group includes two quick release locks 33; the two quick release locks 33 in the same group are respectively installed at the folding door panel 31 near the fuselage 1 near the front and tail positions; the quick release lock locking mechanism 34 is a corresponding mature product of the same series of the quick release lock 33, and the quick release lock locking mechanism 34 is divided into two groups, each group includes two quick release lock locking mechanisms 34; the two quick release lock locking mechanisms 34 in the same group are respectively installed at the rocket launch port 5 of the fuselage 1 near the front and tail positions, and are respectively arranged corresponding to the two groups of quick release locks 33, and are used to lock the folding door panel 31 on the fuselage 1 through mutual cooperation with the two groups of quick release locks 33 when the folding door panel 31 is closed.

Claims

1. A zero-length booster target drone with foldable doors, characterized in that: It comprises 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 rocket launch port (5) and the nose of the fuselage; 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 launching port (5) of the fuselage (1) and is adapted to the rocket launching 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) is cold-separated from the zero-length thrust structure (2), thereby shielding the rocket launching port (5).

2. A zero-length booster target drone with foldable doors according to claim 1, characterized in that: 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); The folding door panels (31) are two in number and are arranged on the fuselage at the rocket launch port (5) opposite to each other. 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 comprising at least one torsion spring hinge (32); one end of the two groups of torsion spring hinges (32) are respectively mounted on 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 to automatically close 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 includes 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 to 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).

3. A zero-length booster target drone with foldable doors according to claim 2, 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 at positions of the folding door panel (31) close to the fuselage (1) and close to the front and rear 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) at positions close to the nose and tail of the fuselage.

4. The zero-length booster target drone with foldable hatch according to claim 3, characterized in that: The number of 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 two ends of the same side of the folding door panel (31).

5. A zero-length booster target drone with foldable doors according to any one of claims 1 to 4, characterized in that: The zero-length thrust structure (2) comprises 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).

6. A zero-length booster target drone with foldable doors according to claim 5, characterized in that: A positioning sub-hole is provided on the conical surface of the thrust cone (22), which, when connected to the zero-length booster rocket (4), corresponds to and matches the positioning mother hole at the mounting end of the zero-length booster rocket (4), and is used to determine 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.

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

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