A flight control simulation rudder test heat preservation device
Patent Information
- Application Number
- CN202522563467.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-03
- Publication Date
- 2026-11-03
- Estimated Expiration
- 2035-12-03
AI Technical Summary
Traditional flight control surface system temperature testing requires placing the entire test bench into a temperature environment chamber, which causes the test bench and components to be affected by the environment, increasing test costs and equipment requirements, and it cannot independently simulate the rotational inertia and aerodynamic loads of the aircraft control surfaces.
Design a flight control simulation control surface test insulation device. The test specimen and test system are separated by the insulation device and the loading device. The insulation is achieved at the rotating shaft by a multi-layer sealing method, simulating the rotation of the control surface and operating independently of the environmental chamber.
It solves the environmental impact of traditional testing methods on test benches and components, reduces testing costs, and can independently simulate the rotational inertia and aerodynamic loads of aircraft control surfaces, improving the flexibility and efficiency of testing.
Smart Images
Figure CN224933649U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of aerospace technology, and in particular to a heat preservation device for flight control simulation control surface testing. Background Technology
[0002] Currently, the commonly used temperature environment testing scheme for flight control control surface systems in China involves placing the entire flight control control surface system test bench into a temperature environment test chamber to conduct tests. This simulates the operation of aircraft control surface actuators under complex operating conditions, and is used to test the operating status and performance of flight control control surface actuators in high and low temperature environments. This testing method requires that the size of the temperature environment test chamber and the test bench be compatible, ensuring that the test bench can fit inside the temperature environment test chamber. Furthermore, other components used in the test, such as loading devices, force sensors, angle sensors, bearings, and even the hydraulic power system used for loading, must all meet the requirements of high and low temperature environments to ensure the normal operation of the test. In flight control system control surface temperature tests of some large aircraft, the actuator installation method must be consistent with that of a real aircraft, and the test bench must be able to simulate physical quantities such as the moment of inertia and aerodynamic loads of the aircraft control surfaces. This test bench is designed to simulate the moment of inertia of the aircraft control surfaces by adjusting mass blocks and to simulate aerodynamic loads by loading devices. The test system also includes test components such as angle sensors, force sensors, and bearings. Traditionally, the test bench is moved entirely into an environmental chamber for flight control system control surface temperature testing. This method not only limits the test bench to the environmental chamber but also affects the temperature of other components within the test system, necessitating their selection to ensure normal operation under the corresponding temperature conditions, thus increasing test costs.
[0003] To address these issues, we propose a flight control simulation control surface insulation device. Utility Model Content
[0004] The purpose of this invention is to address the shortcomings of existing technologies by proposing a flight control simulation control surface test insulation device.
[0005] To achieve the above objectives, the present invention adopts the following technical solution: A flight control simulation control surface test insulation device includes an insulation device and a loading device. Inside the insulation device, one end of the control surface actuator under test is mounted via a fixed end support. The other end of the control surface actuator under test is hinged to a rotating shaft rocker arm. One end of the rotating shaft is installed inside a rotating shaft support, and an angle sensor is installed at the end of the rotating shaft passing through the rotating shaft support. The other end of the rotating shaft is connected to an adjustment mass block. The middle rocker arm of the rotating shaft is connected to the loading device, and a force sensor is installed on the surface of the loading device.
[0006] Preferably, the heat preservation device includes an upper heat preservation device and a lower heat preservation device, and mounting plates are fixed to the sides of both the upper and lower heat preservation devices, and the mounting plates are connected by bolts.
[0007] Preferably, the upper layer of the insulation device is inlaid with an upper layer sealing insert, and the lower layer of the insulation device is inlaid with a lower layer sealing insert.
[0008] Preferably, the upper and lower layers of the insulation device are all connected to the upper and lower sealing inserts of the insulation device by bolts.
[0009] Preferably, a felt and a sealing ring are installed at the end face of the rotating shaft that passes through the heat preservation device.
[0010] Preferably, the upper sealing insert and the lower sealing insert of the heat insulation device are connected to the sealing cover by bolts.
[0011] Compared with the prior art, the beneficial effects of this utility model are as follows: This device solves the limitations of traditional low-temperature environmental chambers on the test bench and the impact on other components in the test system by locally insulating the test control surface actuator in the flight control system. The insulation device designed in this device separates the test piece (actuator) from the rest of the test system at the rotating shaft. The structure adopts the principle of dynamic and static separation. The insulation device is in a stationary state, and the rotating shaft rotates through the circular hole on the insulation device to realize the transmission of the system. The separation surface is sealed with multiple layers to achieve insulation. Attached Figure Description
[0012] Figure 1 This is a three-dimensional schematic diagram of a flight control simulation control surface test heat preservation device proposed in this utility model; Figure 2 This is a three-dimensional cross-sectional schematic diagram of a flight control simulation control surface test heat preservation device proposed in this utility model; Figure 3 for Figure 1 A three-dimensional schematic diagram of the upper and lower layers of the insulation device in the middle; Figure 4 for Figure 1 A schematic diagram showing the three-dimensional separation of the upper and lower layers of the insulation device. Figure 5 for Figure 1 A front view cross-sectional diagram of the upper and lower layers of the insulation device in the middle; Figure 6 for Figure 5 A magnified 3D schematic diagram of the structure at point A.
[0013] In the figure: 1. Insulation device; 2. Test control surface actuator; 3. Adjustment mass block; 4. Loading device; 5. Rotating shaft; 6. Rotating shaft support; 7. Test actuator fixed end support; 8. Angle sensor; 9. Upper layer of insulation device; 10. Lower layer of insulation device; 11. Sealing cover; 12. Felt; 13. Sealing ring; 14. Upper layer sealing insert of insulation device; 15. Lower layer sealing insert of insulation device; 16. Force sensor. Detailed Implementation
[0014] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.
[0015] Reference Figure 1-6 A flight control simulation control surface test insulation device includes an insulation device 1 and a loading device 4. One end of a control surface actuator 2 is mounted inside the insulation device 1 via a test actuator fixing end support 7. The insulation device 1 includes an upper insulation layer 9 and a lower insulation layer 10. Mounting plates are fixed to the sides of both the upper and lower insulation layers 9 and 10, and these mounting plates are connected by bolts. Multiple bolts between the mounting plates increase the installation stability between the upper and lower insulation layers 9 and 10. An upper insulation layer sealing insert 14 is embedded in the upper insulation layer 9, and a lower insulation layer sealing insert 15 is embedded in the lower insulation layer 10. The upper and lower insulation layers 9 and 10 are all connected to the upper and lower insulation layer sealing inserts 14 and 15 by bolts, allowing for easy installation of the upper and lower insulation layer sealing inserts 14 and 15 respectively. Within the upper layer 9 of the heating device and the lower layer 10 of the insulation device, the upper layer sealing insert 14 and the lower layer sealing insert 15 of the insulation device are bolted to the sealing cover 11. The other end of the tested control surface actuator 2 is hinged to a rocker arm connected to a rotating shaft 5. Two tested control surface actuators 2 are symmetrically mounted on the surface of the rotating shaft 5, with the two actuators distributed on both sides of the rotating shaft 5. One end of the rotating shaft 5 is installed within a rotating shaft support 6, and a [missing information - likely a device or component] is installed at the end of the rotating shaft 5 that passes through the rotating shaft support 6. Angle sensor 8, a felt 12 and a sealing ring 13 are installed at the end face of the rotating shaft 5 that passes through the insulation device 1. When the rotating shaft 5 passes through the insulation device 1, it is sealed by the felt 12 and the sealing ring 13. The felt 12 and the sealing ring 13 can increase the sealing between the rotating shaft 5 and the upper layer 9 and the lower layer 10 of the insulation device. The other end of the rotating shaft 5 is connected to an adjusting mass block 3. The middle rocker arm of the rotating shaft 5 is connected to the loading device 4. A force sensor 16 is installed on the surface of the loading device 4.
[0016] The above is the complete working principle of this utility model.
[0017] In this utility model, the installation, connection or setting methods of all the components mentioned above are common mechanical methods, and the specific structure, model and coefficient index of all the components are their own technologies. As long as they can achieve their beneficial effects, they can be implemented, so they will not be described in detail.
[0018] The above embodiments are preferred embodiments of the present utility model, but the embodiments of the present utility model are not limited to the above embodiments. Any changes, modifications, substitutions, combinations, or simplifications made without departing from the spirit and principle of the present utility model shall be considered equivalent substitutions and shall be included within the protection scope of the present utility model.
[0019] In this utility model, unless otherwise stated, directional terms such as "up, down, left, right, front, back, inside, outside, and vertical and horizontal" in the terminology only represent the orientation of the term in its conventional use or are common names understood by those skilled in the art, and should not be regarded as limitations on the term. At the same time, numerals such as "first," "second," and "third" do not represent specific quantities or orders, but are only used to distinguish names. Moreover, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a series of elements includes not only those elements, but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.
Claims
1. A flight control simulation control surface test heat preservation device, comprising a heat preservation device (1) and a loading device (4), characterized in that: The heat preservation device (1) has one end of the test control surface actuator (2) installed inside through the test actuator fixed end support (7), and the other end of the test control surface actuator (2) is hinged to the rocker arm of the rotating shaft (5). One end of the rotating shaft (5) is installed in the rotating shaft support (6), and an angle sensor (8) is installed at the end of the rotating shaft (5) that passes through the rotating shaft support (6). The other end of the rotating shaft (5) is connected to the adjusting mass block (3). The rocker arm in the middle of the rotating shaft (5) is connected to the loading device (4), and a force sensor (16) is installed on the surface of the loading device (4).
2. The flight control simulation control surface test heat preservation device according to claim 1, characterized in that, The heat preservation device (1) includes an upper heat preservation device (9) and a lower heat preservation device (10). The sides of the upper heat preservation device (9) and the lower heat preservation device (10) are fixed with mounting plates, and the mounting plates are connected by bolts.
3. The flight control simulation control surface test heat preservation device according to claim 2, characterized in that, The upper layer (9) of the insulation device is inlaid with an upper layer sealing insert (14), and the lower layer (10) of the insulation device is inlaid with a lower layer sealing insert (15).
4. The flight control simulation control surface test heat preservation device according to claim 2, characterized in that, The upper layer (9) and lower layer (10) of the insulation device are all connected to the upper layer sealing insert (14) and lower layer sealing insert (15) of the insulation device by bolts.
5. The flight control simulation control surface test heat preservation device according to claim 1, characterized in that, The rotating shaft (5) is fitted with a felt (12) and a sealing ring (13) at the end face of the heat preservation device (1).
6. The flight control simulation control surface test heat preservation device according to claim 4, characterized in that, The upper sealing insert (14) and the lower sealing insert (15) of the heat insulation device are bolted together with the sealing cover (11).