Self-adaptive variable-length equipment cabin

Abstract

The invention belongs to the field of aircraft design, and particularly relates to a self-adaptive variable-length equipment cabin. One end of the rear wall face of the cabin body is hinged to the bottom face of the cabin body. One end of the retractable assembly is connected with the fuselage structure, and the other end of the retractable assembly is connected with the rear wall surface of the cabin body; the self-adaptive variable-length equipment cabin has an open state and a closed state; in the opening state, the rear wall face of the cabin body is controlled to rotate by a preset angle around the bottom face of the cabin body through the folding and unfolding assembly; and in a closed state, the rear wall surface of the cabin body is vertical to the bottom surface of the cabin body. According to the self-adaptive variable-length equipment cabin, through self-adaptive opening of the rear wall face of the cabin body, collision between airflow and the rear wall face of the cabin body is avoided, the pressure of accessories on the rear wall face of the cabin body is reduced, meanwhile, self-excitation oscillation of the airflow is weakened, and therefore pressure distribution and pressure pulsation in the cabin are improved, and the service life of the cabin is prolonged. The noise level in the aircraft built-in equipment cabin is effectively reduced, the separation posture of the equipment out of the cabin is improved, and the throwing precision is improved.

Description

Technical Field

[0001] This application belongs to the field of aircraft design, and specifically relates to an adaptive variable length equipment bay. Background Technology

[0002] Compared to traditional external attachments, internal equipment loading offers advantages such as low drag and high stealth, making it a crucial mounting method for modern special mission aircraft. However, the coupling effect between the internal cavity, bulkhead, and equipment creates a complex flow field within the internal equipment bay, resulting in high-intensity noise and pressure pulsations. This can easily lead to fatigue damage to the bay structure. Furthermore, the uneven flow field within the bay can make equipment ejection difficult, causing attitude instability and affecting separation safety and launch accuracy.

[0003] In the existing technology, the flow control measures for conventional internal weapon compartments are divided into active control measures and passive control measures. Active control measures are complex and have low reliability, while conventional passive control measures require damage to the outer surface of the aircraft platform, which reduces flight performance to some extent.

[0004] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention

[0005] The purpose of this application is to provide an adaptive variable length equipment compartment to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An adaptive variable-length equipment compartment, comprising:

[0008] The rear wall of the cabin, one end of which is hinged to the bottom surface of the cabin;

[0009] The retraction assembly has one end connected to the fuselage structure and the other end connected to the rear wall of the cabin.

[0010] The adaptive variable length equipment compartment has an open state and a closed state;

[0011] In the open state, the retraction assembly controls the rear wall of the cabin to rotate around the bottom surface of the cabin by a predetermined angle.

[0012] In the closed state, the rear wall of the cabin is perpendicular to the bottom surface of the cabin.

[0013] In at least one embodiment of this application, the retraction component includes:

[0014] The fixed end includes a fixed rod and a base, the base being fixedly installed on the body structure, and the fixed rod being fixedly installed on the base;

[0015] A spring, which is sleeved on the fixed rod and one end of the spring is fixedly connected to the base;

[0016] A movable rod, one end of which is connected to the spring, and the other end of which is connected to the rear wall of the cabin.

[0017] In at least one embodiment of this application, an airflow channel is provided between the adaptive variable length equipment compartment and the fuselage structure, and the airflow flows from the airflow channel to the rear wall of the compartment.

[0018] In at least one embodiment of this application, the airflow channel is connected to system equipment inside the fuselage structure.

[0019] In at least one embodiment of this application, the airflow passage is connected to an engine inside the fuselage structure.

[0020] In at least one embodiment of this application, when the adaptive variable length equipment compartment is in the open state, the predetermined angle of rotation of the rear wall of the compartment is determined based on the difference between the incoming flow pressure and the spring force.

[0021] In at least one embodiment of this application, when the adaptive variable length equipment compartment is closed, the rear wall of the compartment is seamless with the outer surface of the fuselage.

[0022] In at least one embodiment of this application, the adaptive variable length equipment compartment is in a closed state when the incoming flow pressure is less than a set value.

[0023] The invention has at least the following beneficial technical effects:

[0024] The adaptive variable-length equipment bay of this application presents a simple airflow control measure that does not affect the flight performance of the aircraft. By adaptively opening the rear wall of the bay, the collision between the airflow and the rear wall is avoided, the pressure on the rear wall accessories is reduced, and the self-excited oscillation of the airflow is also weakened. This improves the pressure distribution and pressure pulsation inside the bay, effectively reduces the noise level inside the aircraft's embedded equipment bay, improves the equipment's exit attitude, and increases the delivery accuracy. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the adaptive variable length equipment compartment in the open state according to one embodiment of this application;

[0026] Figure 2 This is a schematic diagram of the adaptive variable length equipment compartment in the closed state according to one embodiment of this application;

[0027] Figure 3 This is a schematic diagram of a retractable component according to one embodiment of this application;

[0028] Figure 4 This is a schematic diagram of the airflow channel of an adaptive variable length equipment compartment in the open state according to one embodiment of this application.

[0029] in:

[0030] 1. Rear wall of the cabin; 2. Retraction and extension assembly; 3. Fixed end; 4. Spring; 5. Fixed rod; 6. Base; 7. Movable rod. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0032] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0033] The following is in conjunction with the appendix Figures 1 to 4 This application will be described in further detail.

[0034] This application provides an adaptive variable length equipment cabin, including: a rear wall 1 of the cabin and a retraction assembly 2.

[0035] One end of the rear wall 1 of the cabin is hinged to the bottom of the cabin; the retraction assembly 2 has one end connected to the fuselage structure and the other end connected to the rear wall 1 of the cabin; the rear wall 1 of the cabin and the retraction assembly 2 together form a flow control structure, under the control of the flow control structure, the adaptive variable length equipment cabin has an open state and a closed state.

[0036] like Figure 1 As shown, in the open state, the rear wall 1 of the cabin is rotated around the bottom surface of the cabin by a predetermined angle through the retraction assembly 2.

[0037] like Figure 2 As shown, in the closed state, the rear wall 1 of the cabin is perpendicular to the bottom surface of the cabin.

[0038] In the preferred embodiment of this application, such as Figure 3 As shown, the retraction assembly 2 includes: a fixed end 3, a spring 4, and a movable rod 7. The fixed end 3 includes a fixed rod 5 and a base 6. The base 6 is fixedly installed on the fuselage structure, and the fixed rod 5 is fixedly installed on the base 6. The spring 4 is sleeved on the fixed rod 5, and one end of the spring 4 is fixedly connected to the base 6. One end of the movable rod 7 is connected to the spring 4, and the other end is connected to the rear wall 1 of the cabin.

[0039] In the preferred embodiment of this application, such as Figure 4 As shown, an airflow channel is provided between the adaptive variable-length equipment compartment and the fuselage structure, and the airflow flows from the airflow channel to the rear wall 1 of the compartment. It can be understood that the airflow channel is connected to the system equipment or engine inside the fuselage structure. When the adaptive variable-length equipment compartment is in the open state, the airflow enters the fuselage through the airflow channel. This airflow is a low-temperature airflow, which can be led to the system equipment or engine inside the fuselage for cooling.

[0040] The adaptive variable-length equipment compartment of this application, when the rear wall 1 of the compartment is impacted by an incoming flow, in the open state, controls the rear wall 1 of the compartment to rotate around the bottom surface of the compartment by a predetermined angle via the retraction assembly 2. The predetermined angle of rotation of the rear wall 1 is determined based on the difference between the incoming flow pressure and the spring force. When the incoming flow pressure increases, the rear wall 1 of the compartment will increase its rotation angle to a new equilibrium position under the action of the spring force. When the incoming flow pressure decreases, the rear wall 1 of the compartment will decrease its rotation angle to a new equilibrium position under the action of the spring force.

[0041] The adaptive variable length equipment compartment of this application has no gap between its rear wall 1 and the outer surface of the fuselage when it is closed. The adaptive variable length equipment compartment is closed when the incoming flow pressure is less than a set value.

[0042] The adaptive variable-length equipment compartment of this application operates on the following principle:

[0043] 1. The flow control structure is located in the fuselage behind the equipment bay, without damaging the aircraft's external surface or affecting the overall aerodynamic performance. It also does not occupy space in the equipment bay, and the retraction mechanism is simple and highly efficient.

[0044] 2. The self-adaptive characteristic of the flow control structure is as follows: When the rear wall 1 of the cabin is impacted by the incoming flow, the flow control structure is in the open state, and the rear wall 1 rotates around the bottom of the cabin by a certain angle, the rotation angle being determined by the difference between the incoming flow pressure and the spring force. When the incoming flow pressure decreases, under the action of the spring force, the rear wall 1 will reduce the rotation angle to a new equilibrium position. When the incoming flow pressure is less than the set value, the rear wall 1 will return to the closed state.

[0045] 3. The adaptive opening of the rear wall 1 of the cabin avoids the collision between the airflow and the rear wall of the equipment cabin, thereby improving the airflow inside the cabin.

[0046] The adaptive variable-length equipment compartment of this application avoids airflow collision with the rear wall of the equipment compartment by adaptively opening the rear wall 1, reducing the pressure on the rear wall accessories and making the pressure distribution inside the equipment compartment more uniform. This improves the equipment separation attitude and increases the accuracy of deployment; it also reduces the self-excited oscillation of the airflow, improves the pressure pulsation inside the compartment, effectively reduces the noise level inside the compartment, increases the fatigue life of the structure, and reduces the structural weight. At the same time, the airflow enters the fuselage through the airflow channel formed by the rear wall and the fuselage, and this low-temperature airflow can be directed to the system equipment or engine inside the fuselage for cooling. The structure of this application is simple, and after loading, it can adaptively adjust according to the environmental pressure to achieve the best control effect without damaging the aircraft's external surface or affecting the overall aerodynamic performance.

[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An adaptive variable-length equipment compartment, characterized in that, include: The rear wall of the cabin (1) is hinged at one end to the bottom surface of the cabin. The retraction assembly (2) has one end connected to the fuselage structure and the other end connected to the rear wall of the cabin (1); The adaptive variable length equipment compartment has an open state and a closed state; In the open state, the retraction assembly (2) controls the rear wall (1) of the cabin to rotate around the bottom surface of the cabin by a predetermined angle; In the closed state, the rear wall (1) of the cabin is perpendicular to the bottom surface of the cabin.

2. The adaptive variable length equipment compartment according to claim 1, characterized in that, The retracting and extending component (2) includes: Fixed end (3), the fixed end (3) includes a fixed rod (5) and a base (6), the base (6) is fixedly installed on the body structure, and the fixed rod (5) is fixedly installed on the base (6); Spring (4), the spring (4) is sleeved on the fixed rod (5), and one end of the spring (4) is fixedly connected to the base (6); Movable rod (7), one end of which is connected to the spring (4), and the other end is connected to the rear wall (1) of the cabin.

3. The adaptive variable length equipment compartment according to claim 2, characterized in that, An airflow channel is provided between the adaptive variable length equipment compartment and the fuselage structure, and the airflow flows from the airflow channel to the rear wall of the compartment (1).

4. The adaptive variable length equipment compartment according to claim 3, characterized in that, The airflow channel is connected to the system equipment inside the fuselage structure.

5. The adaptive variable length equipment compartment according to claim 4, characterized in that, The airflow channel is connected to the engine inside the fuselage structure.

6. The adaptive variable length equipment compartment according to claim 5, characterized in that, When the adaptive variable length equipment compartment is in the open state, the predetermined angle of rotation of the rear wall surface (1) of the compartment is determined according to the difference between the incoming flow pressure and the spring force.

7. The adaptive variable length equipment compartment according to claim 6, characterized in that, When the adaptive variable length equipment compartment is closed, the rear wall (1) of the compartment is seamless with the outer surface of the fuselage.

8. The adaptive variable length equipment compartment according to claim 7, characterized in that, When the incoming flow pressure is less than the set value, the adaptive variable length equipment compartment is in the closed state.

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