CN115127826B - Aircraft, engine high-altitude flight test system and engine - Google Patents

Abstract

The invention provides an aircraft, a high-altitude flight test run system of an engine and the engine, wherein the aircraft comprises: an aircraft body, a first engine and a second engine; the first engine and the second engine are respectively arranged on the aircraft body; the first engine is a power engine for powering the aircraft; the second engine is an engine to be tested and is detachably connected with the aircraft; and after the first engine pushes the aircraft to a target track, performing vacuum test on the second engine at least at the target track. According to the invention, the engine to be tested is sent into the space, so that ignition and test run of the engine to be tested in a vacuum environment are realized, the cost is saved, and the accuracy of the test run process of the engine to be tested is improved.

Description

Aircraft, engine high-altitude flight test system and engine

technical field

The invention relates to the technical field of rocket engines, in particular to an aircraft, an engine high-altitude flight test system and an engine.

Background technique

At present, the engines used in the second stage and above of the existing launch vehicles need to be ignited and started in a vacuum environment, and they are in a harsh environment of low pressure, low temperature and microgravity. In such a harsh environment, the filling, atomization, combustion and other processes of the engine propellant and the working characteristics of the engine will change, and the engine performance cannot be verified through ground tests and simulation analysis.

Therefore, since the 1960s, the research and construction of high-altitude simulation test benches have been gradually carried out, that is, the flight environment within the entire flight envelope of the engine is simulated through large-scale experimental facilities on the ground, and the vacuum ignition, startup, shutdown, and vacuum performance of the engine are simulated. Tests are conducted to ensure the safety and reliability of the rocket system during formal flight tests. However, due to the complex structure of the high-altitude simulation test bench on the ground, the cost is extremely expensive. Especially for high-thrust engines, a high-altitude simulation test bench that meets their needs will cost tens of billions of dollars, and cannot simulate a microgravity environment. At present, there is a lack of high-model test benches for high-thrust rocket engines, which brings difficulties to the high-altitude simulated test runs of high-thrust rocket engines.

Contents of the invention

The invention provides an aircraft, an engine high-altitude flight test system and an engine, which are used to solve the defects of the existing high-altitude simulation test platform on the ground, such as complex structure, extremely expensive cost, and inability to simulate a microgravity environment.

An aircraft provided according to the first aspect of the present invention includes: an aircraft body, a first engine and a second engine; the first engine and the second engine are respectively arranged on the aircraft body; the first engine is The power engine is used to provide power for the aircraft; the second engine is the engine to be tested, and is detachably connected with the aircraft; wherein, after the first engine pushes the aircraft to the target orbit, at least The target track performs a vacuum test run on the second engine.

Optionally, it also includes: a power assembly, the power assembly is arranged on the aircraft body; wherein, the power assembly is respectively connected to the first engine and the second engine, and is used to provide the first The engine and the second engine provide fuel; or, the power assembly is connected to the second engine, and is used to provide fuel for the second engine to test run in a vacuum state.

Optionally, the power assembly includes: a fuel supply module, an oxidant supply module, a propellant supply module, a gas distribution module and pipelines; the fuel supply module, the oxidant supply module, the propellant supply module and the The gas distribution module is respectively connected to the first engine and the second engine through the pipeline; or, the fuel supply module, the oxidant supply module, the propellant supply module and the gas distribution module The modules are respectively connected with the second engine through the pipelines.

Optionally, it further includes: a test bench, the test bench is connected to the aircraft, and the second engine is detachably connected to the test bench.

The test bench includes: a first position and a second position; in the first position, the second engine is tested in a vacuum state; in the second position, the second engine is used for Power is provided for propulsion of the aircraft.

Optionally, it also includes: a recovery mode, in the recovery mode, and the test bench is in the second position, the second engine provides power for recovery of the aircraft.

Optionally, the vehicle is a recoverable liquid rocket.

Optionally, the target orbit is a sub-orbit.

According to the second aspect of the present invention, there is provided an engine high-altitude flight test run system, which includes the above-mentioned aircraft.

Optionally, it also includes: a first control module on the ground and a second control module on the ground; the first control module on the ground is at least connected to the first engine, and is used to control the propulsion of the aircraft; the second control module on the ground is at least connected to The second engine is connected, and is used for controlling the second engine to perform a test run in a vacuum state.

According to the engine provided by the third aspect of the present invention, the above-mentioned aircraft or the above-mentioned high-altitude flight test system for the engine is used when the engine is tested.

The above-mentioned one or more technical solutions in the present invention have at least one of the following technical effects: an aircraft, a high-altitude flight test system for an engine and an engine provided by the present invention, by sending the engine to be tested into space, it realizes the The ignition and test run of the test engine in a vacuum environment saves costs and improves the accuracy of the test engine test process.

Description of drawings

In order to illustrate the present invention or the technical solution in the prior art more clearly, the accompanying drawings that need to be used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the accompanying drawings in the following description are the present invention. For some embodiments of the invention, those skilled in the art can also obtain other drawings based on these drawings without creative effort.

Fig. 1 is one of the schematic diagrams of the assembly relationship of the aircraft provided by the present invention;

Fig. 2 is the second schematic diagram of the assembly relationship of the aircraft provided by the present invention;

Fig. 3 is one of the layout relationship diagrams of the first engine, the second engine, the power assembly, the first control module on the ground and the second control module on the ground in the aircraft provided by the present invention;

Fig. 4 is the second schematic diagram of the arrangement relationship of the first engine, the second engine, the power assembly, the first ground control module and the second ground control module in the aircraft provided by the present invention.

Reference signs:

10. Aircraft body;

20. The first engine;

30. The second engine;

40. Power component; 41. Fuel supply module; 42. Oxidant supply module; 43. Propellant supply module; 44. Gas distribution module; 45. Pipeline;

50. Test bench;

60. The first ground control module;

70. The second ground control module.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of embodiments of the present invention, but not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right" , "vertical", "horizontal", "top", "bottom", "inner", "outer" and other indicated orientations or positional relationships are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing this The embodiments and simplified descriptions of the invention do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the embodiments of the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and should not be construed as indicating or implying relative importance.

The present invention will be specifically described below with reference to FIGS. 1 to 4 .

Fig. 1 and Fig. 2 are the schematic diagrams of the assembly relationship of the aircraft provided by the present invention, as can be seen from Fig. 1 and Fig. 2, the end of the aircraft body 10 is provided with a first motor 20 and a second motor 30, and the first motor 20 is Power engine, the second engine 30 is the engine to be tested.

Possibly, as shown in FIG. 2 , the second engine 30 is connected to the test bench 50 to realize switching between the first position and the second position, and a power assembly 40 is also arranged in the aircraft body 10 to realize the second position. A motor 20 and/or a second motor 30 provide power.

Possibly, as shown in Fig. 1 and Fig. 2, Fig. 1 is the first position of test bench 50, and the second engine 30 carries out vacuum test run at the first position, Fig. 2 is the second position of test bench 50, the second The engine 30 provides power to the aircraft body 10 in the second position.

Possibly, as shown in Fig. 3 and Fig. 4, in the aircraft provided by the present invention, the arrangement relationship of the first engine 20, the second engine 30, the power assembly 40, the first ground control module 60 and the second ground control module 70 The schematic diagram shows the connection relationship between the power assembly 40 and the first engine 20 and the second engine 30, as well as the setting relationship of the first ground control module 60 and the second ground control module 70 of the ground control center.

Possibly, in FIG. 3 , the power assembly 40 is independently connected to the first engine 20 and the second engine 30 .

Possibly, in FIG. 4 , the power assembly 40 is optionally connected with the first engine 20 and the second engine 30 .

Possibly, as shown in FIGS. 3 and 4 , the first control module 60 on the ground is at least connected to the first engine 20 for controlling the propulsion of the aircraft; the second control module 70 on the ground is at least connected to the second engine 30 for controlling the first engine 20 . The second engine 30 is tested in a vacuum state.

The present invention will be specifically described below in combination with specific embodiments.

In some specific embodiments of the present invention, as shown in Fig. 1 to Fig. 4, this scheme provides an aircraft, comprising: an aircraft body 10, a first engine 20 and a second engine 30; the first engine 20 and the second engine 30 are respectively arranged on the aircraft body 10; the first engine 20 is a power engine, which is used to provide power for the aircraft; the second engine 30 is an engine to be tested, and is detachably connected with the aircraft; wherein, the first engine 20 pushes the aircraft to the target After the track, the second engine 30 is vacuum-tested at least on the target track.

It should be noted that the present invention sends the engine to be tested into space through an aircraft, and tests the engine to be tested in a vacuum environment. The test run can be carried out in a real vacuum environment, which is convenient for obtaining relevant parameters of the engine to be tested in the vacuum actual operation, and provides real data support for the optimization of the engine in the later stage.

In a possible implementation, a controller is also included. After the controller controls the first engine 20 to push the aircraft to the target orbit, the controller at least controls the corresponding power assembly 40 to perform a vacuum test on the second engine 30 on the target orbit.

In some possible embodiments of the present invention, it also includes: a power assembly 40, the power assembly 40 is arranged on the aircraft body 10; wherein, the power assembly 40 is respectively connected with the first engine 20 and the second engine 30, and is used for the first engine 20 and the second engine 30, respectively. The engine 20 and the second engine 30 provide fuel; or, the power assembly 40 is connected with the second engine 30 to provide fuel for the second engine 30 to test run in a vacuum state.

Specifically, this embodiment provides an implementation of the power assembly 40. The setting of the power assembly 40 enables the first engine 20 and/or the second engine 30 to provide the power required for starting, and meets the needs of the aircraft during flight. The power demand, and the power demand of the engine to be tested in the test run.

In a possible implementation, the power assembly 40 provides power for the first engine 20, and the first engine 20 is used as a power engine of the aircraft to provide power for the flight of the aircraft. The power assembly 40 is the fuel, oxidizer, propellant And the corresponding components of gas distribution, to meet the supply of corresponding power required during the starting process of the first engine 20 .

In a possible implementation, the power assembly 40 provides power for the second engine 30, and the second engine 30 is used as the engine to be tested. After the aircraft enters the target orbit, the test run of the corresponding project is carried out according to the corresponding power provided by the power assembly 40. The power assembly 40 is the corresponding components of fuel, oxidant, propellant and gas distribution of the second engine 30, which meet the corresponding power supply required by the second engine 30 during the test run.

In a possible implementation, the power assembly 40 provides power for the first engine 20 and the second engine 30 respectively. The pipeline 45 connected to the second engine 30 is switched to satisfy the propulsion of the aircraft by the first engine 20 and the test run of the second engine 30 in the target orbit.

In a possible implementation, the power assembly 40 provides power for the first engine 20 and the second engine 30 respectively. The pipeline 45 connected to the second engine 30 is switched to satisfy the propulsion of the aircraft by the first engine 20 , the test run of the second engine 30 in the target track, and the propulsion of the aircraft by the second engine 30 .

In some possible embodiments of the present invention, the power assembly 40 includes: a fuel supply module 41, an oxidant supply module 42, a propellant supply module 43, a gas distribution module 44 and a pipeline 45; the fuel supply module 41, the oxidizer supply module 42, The propellant supply module 43 and the gas distribution module 44 are respectively connected to the first engine 20 and the second engine 30 through pipelines 45; or, the fuel supply module 41, the oxidant supply module 42, the propellant supply module 43 and the gas distribution module 44 They are respectively connected to the second engine 30 through pipelines 45 .

Specifically, this embodiment provides an implementation of a fuel supply module 41, an oxidant supply module 42, a propellant supply module 43, a gas distribution module 44, and a pipeline 45. The fuel supply module 41, the oxidant supply module 42, the propellant The agent supply module 43 and the gas distribution module 44 provide corresponding fuel, oxidant, propellant and gas medium for the first engine 20 and/or the second engine 30 through the pipeline 45, satisfying the flight requirements of the aircraft, and the engine to be tested test drive requirements.

In a possible implementation, the power assembly 40 can provide propellant for the engine to be tested, and can realize the sinking of the propellant, and can also provide high-pressure and low-pressure gases such as helium and nitrogen for the engine to be tested.

In some possible embodiments of the present invention, it further includes: a test bench 50 connected to the aircraft, and the second engine 30 is detachably connected to the test bench 50 .

The test bench 50 includes: a first position and a second position; in the first position, the second engine 30 is used for testing in a vacuum state; in the second position, the second engine 30 is used to provide power for propulsion of the aircraft.

Specifically, this embodiment provides an implementation of a test bench 50. By setting the test bench 50, the second engine 30 can be switched between the first position and the second position, so that the second engine 30 It can also provide power support for the aircraft while conducting the test run.

In a possible implementation, the test bench 50 includes a frame connected to the second engine 30 and a power unit that drives the power of the frame. The test bench 50 changes the Switching of the second engine 30 between test run and power supply.

In a possible implementation, the test bench 50 also includes corresponding moving rails and sensing components, so as to switch the second engine 30 between the test position and the power supply position, so as to ensure the safe operation of the equipment.

In a possible implementation, the test bench 50 is arranged inside the aircraft, and in the first position, the second engine 30 is partly inside the aircraft body 10 or completely inside the aircraft body 10 or entirely outside the aircraft body 10 , in the second position, the test bench 50 pushes the second engine 30 to a corresponding position to ensure that the aircraft is powered, and the corresponding position can be the end of the aircraft body 10 or the circumferential direction of the aircraft body 10 side.

In some possible embodiments of the present invention, it also includes: a recovery mode. In the recovery mode, and the test bench 50 is in the second position, the second engine 30 provides power for recovery of the aircraft.

Specifically, this embodiment provides an implementation of the recovery mode. By setting the recovery mode, the second engine 30 can provide power for the recovery of the aircraft. When switching to the recovery mode, the test bench 50 needs to be moved from The first position is switched to the second position to ensure that the second engine 30 can provide power for the recovery of the aircraft.

Furthermore, in the recovery mode, when the test bench 50 is in the first position, the first engine 20 provides power for recovery of the aircraft.

In some possible embodiments of the invention, the vehicle is a recoverable liquid rocket.

Specifically, this embodiment provides an implementation of an aircraft. By setting the aircraft as a recoverable liquid rocket, it is convenient for the repeated use of the aircraft, improves the utilization rate of the equipment, and reduces the cost of use. At the same time, the engine to be tested is set in On the aircraft, the simulation effect of the engine to be tested in the actual operating environment has also been improved.

It should be noted that rockets are divided into solid rockets and liquid rockets. Liquid rockets are easy to recover and reuse. At the same time, the same power assembly 40 can be shared between the liquid rocket and the engine to be tested, which further reduces the cost of the test platform.

In a possible implementation, the aircraft is a liquid rocket that can be recovered vertically, so as to realize the repeated use of the test platform of the engine to be tested.

In a possible implementation, the aircraft is a suborbital rocket that can be recovered vertically, so as to realize the repeated use of the test platform of the engine to be tested.

In some possible embodiments of the present invention, the target orbit is a sub-orbit.

Specifically, this embodiment provides an implementation of the target orbit, and by sending the aircraft into the sub-orbit, it is convenient for the test run of the engine to be tested and the recovery of the aircraft.

It should be noted that the sub-orbit is at an altitude above 100km. In the sub-orbit, the aircraft is in a vacuum environment, which is convenient to provide guarantees for the test run of the engine to be tested under the actual working environment. At the same time, the fuel supply module 41, the oxidant supply module 42, The propellant supply module 43 and the gas distribution module 44 provide fuel for the engine to be tested, and realize the ignition and test run of the engine to be tested in a vacuum environment.

In some specific embodiments of the present invention, as shown in FIGS. 1 to 4 , the present solution provides an engine high-altitude flight test system, including the above-mentioned aircraft.

In some possible embodiments of the present invention, it also includes: a first control module 60 on the ground and a second control module 70 on the ground; the first control module 60 on the ground is at least connected with the first engine 20 for controlling the propulsion of the aircraft; The control module 70 is at least connected with the second engine 30 and is used for controlling the second engine 30 to perform a test run in a vacuum state.

Specifically, this embodiment provides an implementation of the first ground control module 60 and the second ground control module 70. By setting the first ground control module 60 and the second ground control module 70, the The first engine 20 and the second engine 30 of the aircraft are controlled to ensure the power propulsion of the aircraft and the smooth progress of the test run of the second engine 30 .

In a possible implementation, it also includes corresponding sensing modules, communication modules, fault modules and alarm modules, etc., and the sensing modules, communication modules, fault modules and alarm modules are respectively arranged in the aircraft and the ground control center, so as to facilitate the control from the ground The center controls the aircraft to realize safe flight and safe test run.

In some specific embodiments of the present invention, the solution provides an engine. When the engine is tested, the above-mentioned aircraft or the above-mentioned high-altitude flight test system for the engine is used.

In the description of the embodiments of the present invention, it should be noted that unless otherwise specified and limited, the terms "connected" and "connected" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection, Or integrated connection; it can be mechanical connection or electrical connection; it can be direct connection or indirect connection through an intermediary. Those of ordinary skill in the art can understand the specific meanings of the above terms in the embodiments of the present invention according to specific situations.

In the description of this specification, descriptions with reference to the terms "one embodiment", "some embodiments", "mode", "specific ways", or "some ways" mean specific features described in conjunction with the embodiment or mode , structure, material or feature is included in at least one embodiment or mode of the embodiments of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or mode. Furthermore, the described specific features, structures, materials or characteristics may be combined in any suitable manner in any one or more embodiments or modes. In addition, those skilled in the art can combine and combine different embodiments or modes and features of different embodiments or modes described in this specification without conflicting with each other.

Finally, it should be noted that: the above embodiments are only used to illustrate the present invention, but not to limit the present invention. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art should understand that various combinations, modifications or equivalent replacements of the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention, and all should cover Within the scope of the claims of the present invention.

Claims (8)

1. An aircraft, characterized in that it comprises: an aircraft body (10), a first engine (20), a second engine (30) and a test bench (50); The first engine (20) and the second engine (30) are respectively arranged on the aircraft body (10); The first engine (20) is a power engine, used to provide power for the aircraft; The second engine (30) is the engine to be tested; The test bench (50) is connected to the aircraft, and the second engine (30) is detachably connected to the test bench (50); The test bench (50) includes: a first position and a second position; In the first position, the second engine (30) is tested in a vacuum state; In the second position, the second engine (30) is used to power the propulsion of the aircraft; Wherein, after the first engine (20) pushes the aircraft to the target track, at least vacuum test is performed on the second engine (30) on the target track; The target orbit is a suborbit. 2. The aircraft according to claim 1, further comprising: a power assembly (40), the power assembly (40) being arranged on the aircraft body (10); Wherein, the power assembly (40) is respectively connected with the first engine (20) and the second engine (30), and is used to provide the first engine (20) and the second engine (30) respectively ) to provide fuel; Alternatively, the power assembly (40) is connected to the second engine (30), and is used to provide fuel for the second engine (30) to test run in a vacuum state. 3. The aircraft according to claim 2, characterized in that the power assembly (40) comprises: a fuel supply module (41), an oxidant supply module (42), a propellant supply module (43), a gas distribution module ( 44) and pipeline (45); The fuel supply module (41), the oxidant supply module (42), the propellant supply module (43) and the gas distribution module (44) are respectively connected to the first An engine (20) is connected to the second engine (30); Alternatively, the fuel supply module (41), the oxidizer supply module (42), the propellant supply module (43) and the gas distribution module (44) communicate with the The second motor (30) is connected. 4. The aircraft according to any one of claims 1 to 3, further comprising: a recovery mode, in the recovery mode, and the test bench (50) is in the second position, the The second engine (30) provides power for recovery of the aircraft. 5. The aircraft according to any one of claims 1 to 3, wherein the aircraft is a recoverable liquid rocket. 6. A high-altitude flight test run system for an engine, comprising the aircraft according to any one of claims 1 to 5. 7. The high-altitude flight test system according to claim 6, further comprising: a first ground control module (60) and a second ground control module (70); The first ground control module (60) is at least connected to the first engine (20), and is used to control the propulsion of the aircraft; The second ground control module (70) is at least connected to the second engine (30), and is used to control the second engine (30) to perform a test run in a vacuum state. 8. An engine, characterized in that, when the engine is tested, the aircraft according to any one of the above-mentioned claims 1 to 5, or the high-altitude flight test system of the engine according to the above-mentioned claims 6 or 7 are used.

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