Power device, aircraft and test system

Abstract

The invention discloses a power device, an aircraft and a test system, the power device comprises a phase change power unit, an excitation device, a pressure relief device, a pipeline and spray pipes arranged in pairs, the power device is installed on the aircraft, the test system comprises a test device and a power device, the test device comprises a rack, a bearing, a bearing seat and the power device, and the power device is installed on the rack. Two ends of the power device are rotatably mounted on the frame through a bearing and a bearing seat, the phase change medium is liquid CO2 with certain pressure, and the liquid CO2 can be safely stored in an environment of-50 DEG C to 70 DEG C. When the power device is started, a liquid CO2 medium in the phase change chamber absorbs heat to be subjected to phase change and expansion boosting, and when the pressure reaches a pressure threshold value of the pressure relief device, high-pressure CO2 gas is released to the primary containing chamber and forms a stable and uniform high-pressure gas source after being subjected to pressure reduction and pressure equalization through the primary containing chamber, and meanwhile the high-pressure gas source is released outwards from the symmetrically-arranged spray pipes; thrust generated by gas injection enables the aircraft to rotate at a high speed.

Description

Technical Field

[0001] This invention relates to the field of aircraft propulsion technology, and in particular to a propulsion device for aircraft, an aircraft, and a testing system. Background Technology

[0002] Modern aerial bombs and high-speed spacecraft require agile and efficient propulsion systems to maintain and adjust to favorable flight attitudes and achieve higher speeds after detaching from the main body. Current propulsion systems typically use gas combustion to generate rotational power, offering advantages such as simple structure, high power, and rapid response. However, their high operating temperatures and significant infrared signature are insurmountable drawbacks, and they also impose stringent heat protection requirements on the aircraft's components. Summary of the Invention

[0003] To address the shortcomings of the existing technology, this invention proposes a device that overcomes the high temperature problem of traditional aircraft power units without reducing performance, and generates rotational power by expanding carbon dioxide through a liquid-gas phase change.

[0004] The technical solution of this invention: A power unit, comprising: a phase change power unit, an excitation device, a pressure relief device, pipes, and symmetrically arranged nozzles. The phase change power unit has a structure with an internal phase change chamber. One end of the phase change power unit is closed and installed on the aircraft shell, and the other end of the phase change power unit is open and provided with a pressure diaphragm. The pressure relief device includes a primary chamber and a pipe sleeved outside the primary chamber. One end of the pressure relief device is installed on the aircraft shell, and the other end of the pressure relief device is connected to the phase change power unit. The pressure diaphragm is used to separate the phase change chamber from the primary chamber. At least two nozzles communicating with the primary chamber are provided outside the aircraft shell. The excitation device is connected to the phase change chamber and is used to induce a liquid-gas phase change in the medium inside the phase change chamber. When the gas pressure inside the phase change chamber reaches a threshold, it breaks through the pressure diaphragm, and the gas enters the primary chamber and is ejected through the symmetrically arranged nozzles, generating rotational power and causing the aircraft to rotate at high speed.

[0005] The liquid CO2 medium in the phase change chamber absorbs heat and undergoes a phase change, expanding and increasing in pressure. When the pressure reaches the pressure threshold of the pressure diaphragm, the pressure diaphragm is ruptured, and the high-pressure CO2 gas is released into the primary chamber. After pressure reduction and equalization in the primary chamber, a stable and uniform high-pressure gas source is formed.

[0006] In one embodiment, the excitation device includes an exciter and an activator. The exciter is located at the end of the phase change chamber away from the initial chamber. The exciter is connected to the activator, which extends into the phase change chamber. The activator contains an activating agent. When the exciter is energized, it activates the activating agent in the activator. The activating agent burns to generate heat, and the liquid CO2 medium in the phase change chamber absorbs heat and undergoes a phase change.

[0007] In one embodiment, the activator is a hollow rod-shaped structure with a through-hole on its sidewall communicating with the phase change chamber. The hollow rod-shaped structure facilitates the filling of different dosages of activator, and the through-hole is designed to provide a heat outlet after the activator burns, thereby causing the liquid CO2 in the phase change chamber to absorb heat, undergo a phase change, expand, and increase in pressure.

[0008] In one embodiment, the phase change chamber is provided with a liquid injection port. The liquid injection port is provided for filling the phase change chamber with liquid CO2 medium.

[0009] Based on the same inventive concept, the present invention also proposes an aircraft that includes the power unit as described above.

[0010] Based on the same inventive concept, the present invention also proposes an aircraft power unit testing system, including a testing device and the aforementioned power unit. The testing device includes a frame and a flywheel. Bearings and bearing seats are respectively provided at both ends of the frame. The flywheel is sleeved on the power unit and rotates coaxially with the power unit. The power unit is rotatably connected to the frame through the bearings and bearing seats.

[0011] The phase change medium filled in the phase change power unit of this invention is liquid CO2 at a certain pressure, which can be safely stored in an environment of -50℃ to 70℃. When the power unit is started, the exciter at the end of the phase change power unit is energized and activates the activator in the activator. The activator burns and generates heat. The liquid CO2 medium in the phase change chamber absorbs heat and undergoes a phase change, expanding and increasing in pressure. When the pressure reaches the pressure threshold of the pressure relief device, the high-pressure CO2 gas is released into the primary chamber. After being depressurized and equalized in the primary chamber, a stable and uniform high-pressure gas source is formed, which is released outward from the nozzle. The thrust generated by the gas injection causes the power unit to rotate at high speed.

[0012] The desired rotational speed and kinetic energy are obtained by setting and changing input conditions such as the mass of the injected phase change medium, the mass of the activator in the activator, and the pressure threshold of the pressure diaphragm. This invention uses liquid CO2 as the phase change medium, which operates at a low temperature during the phase change reaction, overcoming the problem of high temperatures in traditional bomber propulsion systems. Attached Figure Description

[0013] Figure 1 This is an exploded view of the power unit structure of the present invention; Figure 2 This is a front view of the power unit structure of the present invention; Figure 3 for Figure 2 Sectional view at point AA; Figure 4 A schematic diagram of an aircraft structure with a power unit installed; Figure 5 for Figure 4 Sectional view at point BB; Figure 6 This is an axial view of the aircraft of the present invention; Figure 7 This is a schematic diagram of the test system structure of the present invention; In the diagram, 1 is the aircraft shell, 2 is the phase change power unit, 3 is the initial chamber, 4 is the pipe, 5 is the exciter, 6 is the activator, 7 is the front bearing, 8 is the rear bearing, 9 is the nozzle, 10 is the nozzle, 11 is the injection port, 12 is the aircraft, 13 is the frame, 14 is the bearing, 15 is the bearing housing, 16 is the flywheel, 201 is the phase change chamber, and 202 is the pressure diaphragm. Detailed Implementation

[0014] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0015] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "or / and" as used herein includes any and all combinations of one or more of the associated listed items.

[0016] like Figures 1 to 3 As shown, this embodiment discloses a power unit, including an aircraft shell 1, a phase change power unit 2, a pressure relief device, and an excitation device.

[0017] In this embodiment, the phase change power unit 2 is a rotating shaft structure with a phase change chamber 201 inside. One end of the phase change power unit 2 is closed and rotatably mounted on the aircraft shell 1, and the other end of the phase change power unit 2 is open and equipped with a pressure diaphragm 202. The pressure relief device includes a primary chamber 3 and two pipes 4 sleeved outside the primary chamber 3. The two pipes 4 are symmetrically distributed and are connected to the primary chamber 3. One end of the pressure relief device is rotatably mounted on the aircraft shell 1. The primary chamber 3 of the pressure relief device is threadedly connected to the phase change power unit 2. The pressure diaphragm 202 is used to separate the phase change chamber 201 from the primary chamber 3.

[0018] The phase change chamber 201 and the primary chamber 3 are separated by a pressure diaphragm 202. The liquid CO2 medium in the phase change chamber 201 absorbs heat and undergoes a phase change, expanding and increasing in pressure. When the pressure reaches the pressure threshold of the pressure diaphragm 202, the pressure diaphragm 202 is ruptured, and the high-pressure CO2 gas is released into the primary chamber 3. After pressure reduction and equalization in the primary chamber 3, a stable and uniform high-pressure gas source is formed.

[0019] In this embodiment, the two ends of the aircraft shell 1 are respectively provided with a front bearing 7 and a rear bearing 8, and the phase change power unit 2 and the initial chamber 3 are rotatably connected to the aircraft shell 1 through the front bearing 7 and the rear bearing 8 respectively.

[0020] In this embodiment, there are nozzles 9 with the same number and one-to-one correspondence as the pipes 4. Each nozzle is equipped with a nozzle 10. The two nozzles 10 are oriented in opposite directions. The stable and uniform high-pressure gas source formed in the initial chamber 3 after pressure reduction and equalization is released outward from the two symmetrically arranged nozzles 10. The thrust generated by the gas jet causes the power device to rotate at high speed.

[0021] Preferably, if three or more nozzles are provided, each nozzle is distributed at an equal angle along the end face of the power flywheel.

[0022] In this embodiment, the excitation device includes an exciter 5 and an activator 6. The exciter 5 is located at the end of the phase change chamber 201 away from the initial chamber 3. The exciter 5 is connected to the activator 6, which extends into the phase change chamber 201 and contains an activating agent. When the exciter 5 is energized, it excites the activating agent in the activator 6. The activating agent burns and generates heat, and the liquid CO2 medium in the phase change chamber 201 absorbs heat and undergoes a phase change.

[0023] The activator 6 is a hollow rod-shaped structure with a through hole on its side wall that communicates with the phase change chamber 201. The hollow rod-shaped structure facilitates the filling of different doses of activator, and the through hole is designed to provide a heat outlet after the activator is burned, so that the liquid CO2 in the phase change chamber 201 absorbs heat and undergoes a phase change, expanding and increasing pressure.

[0024] In this embodiment, the phase change chamber 201 is provided with a liquid injection port 11. The liquid injection port 11 is provided for filling the phase change chamber 201 with liquid CO2 medium.

[0025] like Figures 4-6 As shown, this embodiment, based on the same inventive concept, also discloses an aircraft 12, with the aforementioned power device installed at the tail of the aircraft 12. The power device generates high-speed rotation to propel the aircraft 12.

[0026] like Figure 7 As shown, this embodiment, based on the same inventive concept, also discloses an aircraft power unit testing system, including a testing device and the aforementioned power unit. The testing device includes a frame 13 and a flywheel 16. The two ends of the frame 13 are respectively provided with a bearing 14 and a bearing seat 15. The flywheel 16 is sleeved on the power unit and rotates coaxially with the power unit. The power unit is rotatably connected to the frame 13 through the bearing 14 and the bearing seat 15.

[0027] The power unit testing system is mainly used to test and study the relationship between input conditions such as the quality of the working medium, release pressure, and activator thermal equivalent, and physical properties such as the power unit's speed, acceleration, kinetic energy, and temperature. A ground-based testing device with a structure similar to the power unit is designed and manufactured, using a frame, bearings, and bearing housing instead of the aircraft shell. The main functional components can be made of common materials. The testing principle is the same as that of the aforementioned rotating power unit. During testing, multiple sets of test input conditions can be set by changing flywheels with different moments of inertia, phase change power units with different capacities, primary chambers with different capacities, and pressure diaphragms of various specifications.

[0028] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A power device, characterized in that, include: A phase change power unit, wherein the phase change power unit has a structure with a phase change chamber inside, one end of the phase change power unit is closed and installed on the aircraft shell, and the other end of the phase change power unit is open and equipped with a pressure diaphragm; An excitation device, connected to the phase change chamber, is used to induce a liquid-gas phase change in the medium within the phase change chamber; The pressure relief device includes a primary chamber and a pipe sleeved outside the primary chamber. One end of the pressure relief device is installed on the aircraft shell, and the other end of the pressure relief device is connected to the phase change power unit. The pressure diaphragm is used to separate the phase change chamber from the primary chamber. At least two nozzles communicating with the primary chamber are provided outside the aircraft shell. When the gas pressure in the phase change chamber reaches the threshold, it breaks through the pressure diaphragm, and the gas enters the primary chamber and is ejected through the nozzle, generating rotational power and causing the power unit to operate at high speed.

2. The power unit according to claim 1, characterized in that: The excitation device includes an exciter and an activator. The exciter is located at the end of the phase change chamber away from the initial chamber. The exciter is connected to the activator. The activator extends into the phase change chamber and contains an activating agent.

3. The power unit according to claim 2, characterized in that: The activator is a hollow rod-shaped structure with through holes on its sidewalls that communicate with the phase change chamber.

4. The power unit according to claim 1, characterized in that: The phase change chamber is equipped with a liquid injection port.

5. The power unit according to claim 1, characterized in that: The nozzles are symmetrically distributed at intervals along the aircraft shell, and each nozzle is equipped with a nozzle.

6. An aircraft, characterized in that: The aircraft includes the power unit as described in any one of claims 1-5.

7. A power unit testing system, characterized in that: The device includes a testing apparatus and a power unit as described in any one of claims 1-5. The testing apparatus includes a frame and a flywheel. Bearings and bearing seats are respectively provided at both ends of the frame. The flywheel is sleeved on the power unit and rotates coaxially with the power unit. The power unit is rotatably connected to the frame through the bearings and bearing seats.

Images