Air-cooled power supply load box for aircraft test flight
By adopting air-cooled design and multiple sets of load elements in the aircraft power load box, combined with temperature sensors and control systems, the problem of poor heat dissipation in the existing technology is solved, efficient heat dissipation and precise power regulation are achieved, and test flights are ensured. Safety and reliability of the process.
Patent Information
- Application Number
- CN202420430037.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-03-06
- Publication Date
- 2024-12-31
- Estimated Expiration
- 2034-03-06
AI Technical Summary
The existing aircraft power load box has poor heat dissipation effect during the test flight, which affects the safety of the simulated power load system and the internal test environment of the aircraft.
An air-cooled power load box is designed, using multiple cooling fans and a large number of heat dissipation holes, combining multiple sets of load components and temperature sensors, and achieving efficient heat dissipation and precise power regulation through an external control system, and is equipped with load control switches and circuit breakers. to ensure safety.
It significantly improves the heat dissipation efficiency and safety of the load box, realizes high-precision generator output power regulation and emergency protection, and ensures the safety and reliability of the test flight process.
Smart Images
Figure CN222283755U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to an air-cooled power supply load box used for aircraft flight test, belonging to the technical field of aircraft power supply test. Background Art
[0002] In order to verify that the output power of the power system generator of the aircraft (especially large aircraft) reaches the target state during the test flight and meets the airworthiness requirements, it is necessary to install a set of simulated power load test modification equipment. By controlling the electrical load to connect and disconnect from the aircraft power grid, the output power of the aircraft generator can be adjusted to meet the test state requirements.
[0003] The simulated power load is realized by adding a resistive load box to the aircraft, and the resistive load unit inside the load box is adjusted to make the output power of the aircraft generator reach a specific state. Accurately connecting and disconnecting the resistive load to the aircraft power grid is the core of the load box design. Since the power loaded by the power load box is large, a large amount of heat will be generated after connecting to the aircraft power grid. If this heat cannot be effectively dissipated, it will not only affect the characteristics and safety of the simulated power load system itself, but also affect the internal test environment and safety of the aircraft. Therefore, solving the heat dissipation problem of the onboard power load box is the key to the design of the onboard power load box. Utility Model Content
[0004] One purpose of the utility model is to provide an air-cooled power load box for aircraft flight testing, which can overcome the defects of the prior art, has good heat dissipation effect, and is safe and reliable in operation.
[0005] The above objects of the utility model are achieved by an air-cooled power supply load box for aircraft flight test, the air-cooled power supply load box for aircraft flight test comprises a load box shell, the load box shell is generally rectangular, and comprises a load box front cover plate, a load box rear cover plate, a load box first side panel and a load box second side panel;
[0006] The first side panel of the load box is provided with a cooling fan, and the second side panel of the load box is provided with cooling holes.
[0007] According to the above technical scheme, the air-cooled power load box for aircraft flight test of the utility model can achieve the following beneficial technical effects: good heat dissipation effect, safe and reliable operation. Specifically, through the load box heat dissipation fan, the hot air inside the load box can be pumped to the outside, which greatly improves the heat dissipation efficiency of the load box, has high safety and good heat dissipation effect.
[0008] Preferably, the number of the cooling fans is a first plurality, and the number of the cooling holes is a second plurality. By providing the first plurality of cooling fans and the second plurality of cooling holes, the cooling efficiency of the load box is further improved, the safety is high, and the cooling effect is good.
[0009] Preferably, the air-cooled power supply load box for aircraft flight test is internally provided with multiple groups of load elements for accessing the aircraft power grid to increase the output power of the generator. The utility model load box is internally provided with multiple groups of load elements for multi-level power grading design. The target loading value is set by an external control system, and the resistive load is connected to the aircraft power grid to increase the output power of the generator, so that the output power of the generator finally reaches and is maintained near the target loading value, and has the characteristics of high loading accuracy.
[0010] Preferably, a temperature sensor is also provided inside the air-cooled power supply load box for aircraft flight test to monitor the internal temperature of the load box. The utility model provides a temperature sensor inside the load box to monitor the internal temperature of the load box in real time. When the temperature exceeds the normal range, the resistive load inside the load box can be disconnected to ensure the safety of the aircraft.
[0011] Preferably, the air-cooled power supply load box for aircraft flight test also includes a load control box and a load control switch arranged outside the load box housing, and the load control switch can control the three-phase contactor inside the load control box to be attracted or disconnected, and the three-phase contactor corresponds to the load element; when the load control switch is closed, the corresponding three-phase contactor is attracted, and the corresponding load element is connected to the power grid; when the load control switch is disconnected, the corresponding three-phase contactor is disconnected, and the corresponding load element is cut out of the power grid. The resistive load in the load box of the utility model is controlled to load and unload through the load control switch, realizing the load-adding and unloading function of the simulated electric load, that is, realizing the connection and disconnection of the internal load; the load control switch (also called the load-adding and unloading switch) can also realize the load loading and unloading step by step.
[0012] Preferably, a circuit breaker is also provided inside the load control box, which is used to quickly cut the load out of the aircraft power grid when the simulated load line exceeds the rated current. The circuit breaker on the load control box of the utility model adopts a panel installation form, which can realize emergency protection of the generator extraction interface.
[0013] Preferably, the air-cooled power load box for aircraft flight test also includes a load one-key unloading switch arranged outside the load box housing, which is used to realize one-key unloading of the load under the loaded state. The load box of the utility model has an emergency protection one-key unloading function. When an abnormal situation is identified, the emergency protection function can provide a manual operation of the load one-key unloading switch to cut the electric load system out of the aircraft power grid.
[0014] Preferably, the air-cooled power supply load box for aircraft flight test further comprises a load box mounting base, and the load box housing and the load control box are both mounted on the load box mounting base.
[0015] Preferably, the load box rear cover is provided with an electrical connection interface at its lower portion.
[0016] Preferably, each load element is U-shaped, and spiral heat sinks are arranged on the surface. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 This is a first overall appearance diagram of an air-cooled power load box for aircraft flight testing according to an embodiment of the utility model.
[0018] Figure 2 This is a second overall appearance diagram of an air-cooled power load box for aircraft flight testing according to an embodiment of the utility model.
[0019] Figure 3 The present invention is a schematic diagram of the air cooling function of an air-cooled power load box for aircraft flight testing according to an embodiment of the present invention.
[0020] Figure 4 This is a structural diagram of a load element of an air-cooled power load box for aircraft flight testing according to an embodiment of the utility model.
[0021] Figure 5 This is a load box assembly diagram of an air-cooled power load box for aircraft flight testing according to an embodiment of the utility model.
[0022] Figure 6 The present invention is a load box working principle diagram of an air-cooled power load box for aircraft flight testing according to an embodiment of the present invention.
[0023] Figure 7 The present invention is a schematic diagram of the resistive load installation principle of an air-cooled power load box for aircraft flight testing according to an embodiment of the present invention.
[0024] Figure 8 The utility model is a schematic diagram of the electrical load addition and reduction principle of an air-cooled power supply load box used for aircraft flight testing according to an embodiment of the utility model.
[0025] Reference numerals list
[0026] 1. Load box housing; 2. Cooling fan; 3. Load box mounting base; 4. Electrical connection interface; 5. Load control box; 6. Second side panel of load box; 7. Front cover of load box; 8. Load element; 9. First load element fixing bracket; 10. Second load element fixing bracket; 11. Rear cover of load box; 12. Temperature sensor. DETAILED DESCRIPTION
[0027] The specific implementation methods of the utility model will be described below. It should be noted that in the specific description of these implementation methods, in order to make a concise description, it is impossible for this specification to describe all the features of the actual implementation methods in detail. It should be understood that in the actual implementation of any implementation method, just as in the process of any engineering project or design project, in order to achieve the specific goals of the developer and to meet system-related or business-related restrictions, various specific decisions are often made, and this will also change from one implementation method to another. In addition, it can also be understood that although the efforts made in this development process may be complex and lengthy, for ordinary technicians in the field related to the content disclosed by the utility model, some changes in design, manufacturing or production based on the technical content disclosed in this disclosure are just conventional technical means, and should not be understood as insufficient content of this disclosure.
[0028] Unless otherwise defined, the technical or scientific terms used in the claims and the specification shall have the usual meaning understood by persons with ordinary skills in the technical field to which the utility model belongs. The words "first", "second" and similar words used in the patent application specification and the claims of the utility model do not indicate any order, quantity or importance, but are only used to distinguish different components. "One" or "one" and other similar words do not indicate a quantitative limitation, but indicate the existence of at least one. "Include" or "comprises" and other similar words mean that the elements or objects appearing before "include" or "comprises" include the elements or objects listed after "include" or "comprises" and their equivalent elements, and do not exclude other elements or objects. "Connect" or "connected" and other similar words are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.
[0029] In the following description, in order to clearly demonstrate the structure and working mode of the utility model, many directional words will be used for description, but the words "front", "back", "left", "right", "outside", "inside", "outward", "inward", "up", "down", etc. should be understood as convenient terms and should not be understood as restrictive terms.
[0030] like Figure 1 , 2 As shown, according to one embodiment of the utility model, an air-cooled power supply load box for aircraft flight test includes a load box housing 1, which is generally rectangular and includes a load box front cover plate 7, a load box rear cover plate 11, a load box first side panel and a load box second side panel 6; wherein a cooling fan 2 is installed on the load box first side panel, and a cooling hole is opened on the load box second side panel 6 (therefore, the load box second side panel can also be called a heat sink).
[0031] The load box housing 1 and the load control box 5 can be mounted on the load box mounting base 3. The load box front cover 7 can be a detachable component and is mounted on the load box.
[0032] The number of the cooling fans 2 may be a first plurality, and the number of the cooling holes may be a second plurality. For example, eight cooling fans 2 are installed on the first side panel of the load box, and the cooling fans 2 are arranged side by side in pairs from top to bottom. A second plurality of cooling holes may be densely provided on the second side panel 6 of the load box, and the cooling holes are circular in shape. For example, the number of the cooling holes may be 100 to 1000.
[0033] The load box rear cover 11 may be provided with an electrical connection interface 4 at its lower portion, which is electrically interconnected with an external control and monitoring system to realize load control of the load box internal load and monitoring of the internal temperature environment of the load box, as well as real-time monitoring of the voltage and current status of the generator.
[0034] Figure 3 This is a schematic diagram of the installation of the cooling fan and the air duct. When the load is loaded, a large amount of heat will be generated inside the load box. The cooling fan 2 can draw the hot air inside the load box to the passenger compartment through the heat dissipation holes on the second side panel 6 of the load box, and draw the relatively low temperature air outside the load box into the load box, thereby achieving the heat dissipation function.
[0035] Figure 4 The structure diagram of the load element of the utility model. Multiple groups of load elements 8 can be arranged inside the load box of the utility model to connect to the aircraft power grid and increase the output power of the generator. Each load element 8 is U-shaped, which has the function of saving installation space. The surface of the load element is provided with spiral heat sinks to increase the heat dissipation area of the load element and facilitate heat dissipation.
[0036] For example, a total of 60 load elements 8 are arranged inside the load box of the present invention. The assembly diagram of its internal structure and the load box housing is shown in FIG. Figure 5 As shown, the load elements are arranged horizontally side by side along the first load element fixing bracket 9 (the first load element fixing bracket 9 is arranged vertically), and multiple groups of first load element fixing brackets 9 are evenly assembled with four second load element fixing brackets 10 (the second load element fixing brackets 10 are arranged horizontally), and the four second load element fixing brackets 10 are fixed on the load box beam arm. The first load element fixing bracket 9, the second load element fixing bracket 10, and the load box beam arm cooperate with each other to play the role of fixing and supporting the internal structure of the load box.
[0037] A temperature sensor 12 may also be provided inside the load box to monitor the internal temperature of the load box. For example, temperature sensors 12 are installed from left to right between the load elements inside the load box to detect the temperatures of the air inlet, the middle of the load box, and the air outlet, respectively.
[0038] Combination Figure 1 and Figure 8 As shown, a load control box 5 can also be provided on the load box mounting base 3 of the utility model, and a circuit breaker and a three-phase contactor are provided inside the load control box 5. When the simulated load circuit exceeds the rated current, the circuit breaker can quickly cut the load out of the aircraft power grid. By closing the external load access control switch (also called the load control switch), the three-phase contactor coil can be energized, thereby connecting the load to the aircraft power grid, and disconnecting the external load access control switch can cut the load out of the aircraft power grid.
[0039] The load box of the utility model can be integrated with an external test system to simulate an electric load system, and the voltage and current data of the aircraft generator and the internal ambient temperature parameters of the load box can be monitored in real time through the external test system when the load box is working.
[0040] When the load box of the utility model is working, Figure 6 As shown, the load box can mainly realize the connection and disconnection of its internal load elements through the external load control box 5 and the load control switch. The load box is provided with components such as a resistive load (i.e., a load element 8), a cooling fan 2, and a temperature sensor 12. The resistive load is installed on the side wall of the load box for connecting to the aircraft power grid to increase the output power of the generator; the cooling fan 2 is used to dissipate the heat inside the load box to the outside of the load box, thereby realizing the heat dissipation inside the load box; the temperature sensor 12 is placed inside the load box for monitoring the internal temperature of the load box.
[0041] The load control box 5 may include components such as a three-phase circuit breaker and a three-phase contactor. The circuit breaker on the load control box 5 is panel-mounted to realize emergency protection of the generator extraction interface, and the three-phase contactor is used to control the resistive load to access or cut out of the aircraft power grid. The load control switch includes a load adding and reducing switch, through which the load adding and reducing switch can realize step-by-step loading and unloading of the load. The load box may also include a load one-key unloading switch arranged outside the load box housing 1, which is used to realize one-key unloading of the load in the loaded state.
[0042] In addition, the output voltage and current of the aircraft generator can be detected through the power supply special test system. The load box temperature parameters and the aircraft generator voltage and current parameters are finally transmitted to the onboard monitoring screen and the ground telemetry screen through the airborne test system, which is convenient for monitoring personnel to intuitively capture real-time test data.
[0043] Combination Figure 7 , Figure 8 As shown, when the generator enters the test flight mode, the generator only supplies power to the load box, and the power is graded inside the load box. The load is divided into two groups, for example, and the loading and unloading are controlled by the first load-on / unload switch and the second load-on / unload switch. Each switch can control the three-phase contactor inside the load control box 5 to be attracted or disconnected, and each three-phase contactor corresponds to a resistive load. When the first load-on / unload switch and / or the second load-on / unload switch are closed, the corresponding three-phase contactor is attracted, and the corresponding resistive load is connected to the power grid. When the first load-on / unload switch and / or the second load-on / unload switch are disconnected, the corresponding three-phase contactor is disconnected, and the corresponding resistive load is cut out of the power grid, thereby realizing the load-on / unload function of the simulated electrical load.
[0044] The load box cooling fan is powered by 28V DC, for example. Before the load box works, the load box cooling fan 2 must be turned on first, and then the load is controlled by the load-on / load-off switch. The load-on / load-off switch controls the three-phase contactor inside the load control box 5 to close, and the corresponding resistive load is connected to the power grid. A large amount of heat will be generated inside the load box, and the hot air inside the load box will be pumped into the cabin through the cooling fan 2, and the relatively low temperature air outside the load box will be pumped into the load box, thereby achieving the heat dissipation function. After the load box is finished working, the load-on / load-off switch is disconnected, the corresponding resistive load is cut out of the power grid, and then the load box cooling fan 2 is turned off.
[0045] When the load box is working, the internal temperature of the load box is monitored by a temperature sensor 12 arranged inside the load box. When the internal temperature of the load box exceeds a predetermined acceptable temperature, the load in the load box can be cut out of the aircraft power grid by operating an external one-touch unloading switch (i.e., closing the one-touch unloading switch).
[0046] The specific implementation modes of the present invention are described above, but those skilled in the art will understand that the above specific implementation modes do not constitute limitations to the present invention, and those skilled in the art can make various modifications based on the above disclosure without exceeding the scope of the present invention.
Claims
1. An air-cooled power load box for aircraft flight testing, characterized in that: The air-cooled power supply load box for aircraft flight test comprises a load box housing, which is generally in the shape of a rectangular parallelepiped and comprises a load box front cover plate, a load box rear cover plate, a load box first side panel and a load box second side panel; Wherein, a cooling fan is installed on the first side panel of the load box, and a cooling hole is opened on the second side panel of the load box.
2. The air-cooled power load box for aircraft flight test according to claim 1, characterized in that: The number of the heat dissipation fans is a first plurality, and the number of the heat dissipation holes is a second plurality.
3. The air-cooled power supply load box for aircraft flight test according to claim 1, characterized in that: The air-cooled power load box used for aircraft flight test is internally provided with multiple groups of load elements for accessing the aircraft power grid to increase the output power of the generator.
4. The air-cooled power supply load box for aircraft flight test according to claim 1, characterized in that: A temperature sensor is also arranged inside the air-cooled power supply load box used for aircraft flight test to monitor the internal temperature of the load box.
5. The air-cooled power supply load box for aircraft flight test as claimed in claim 3, characterized in that: The air-cooled power supply load box for aircraft flight test also includes a load control box and a load control switch arranged outside the load box housing, wherein the load control switch can control the three-phase contactor inside the load control box to be closed or disconnected, and the three-phase contactor corresponds to a load element; When the load control switch is closed, the corresponding three-phase contactor is energized, and the corresponding load element is connected to the power grid; When the load control switch is disconnected, the corresponding three-phase contactor is disconnected and the corresponding load element is cut out of the power grid.
6. The air-cooled power load box for aircraft flight test according to claim 5, characterized in that: A circuit breaker is also provided inside the load control box, which is used to quickly cut the load out of the aircraft power grid when the current in the simulated load circuit exceeds the rated current.
7. The air-cooled power load box for aircraft flight test according to claim 5, characterized in that: The air-cooled power supply load box for aircraft flight test also includes a load one-key unloading switch arranged outside the load box housing, which is used to realize one-key unloading of the load in the loaded state.
8. The air-cooled power supply load box for aircraft flight test according to claim 5, characterized in that: The air-cooled power supply load box for aircraft flight test also includes a load box mounting base, and the load box housing and the load control box are both mounted on the load box mounting base.
9. The air-cooled power load box for aircraft flight test according to claim 1, characterized in that: The load box rear cover is provided with an electrical connection interface at its lower portion.
10. The air-cooled power load box for aircraft flight test according to claim 3, characterized in that: Each load element is U-shaped, and a spiral heat sink is arranged on the surface.