A wearable flight system based on microturbine jet engine drive

Abstract

The application discloses a kind of wearable flight system based on micro turbine jet engine driving, including ejector outer sleeve and adjusting sleeve, the ejector outer sleeve coaxial fixed connection is connected in the tail nozzle outside of micro turbine jet engine, the tail nozzle of micro turbine jet engine is set below wearable backpack, annular ejector airflow passage is formed between the ejector outer sleeve and tail nozzle, the air inlet is set in the front end of the ejector outer sleeve, the air inlet hole is opened on the ejector outer sleeve and adjusting sleeve, by the annular passage between the ejector outer sleeve and tail nozzle, the negative pressure effect generated by high-speed gas is used to suck external air and mix with gas and discharge, increase exhaust mass flow to improve thrust under the premise of not additional fuel consumption, while the mixing of cold air makes exhaust temperature significantly reduced, reduces heat radiation and jet noise, realizes the synergistic effect of waste heat utilization and heat protection, noise reduction.

Description

Technical Field

[0001] This invention relates to the field of wearable aircraft technology, and more particularly to a wearable flight system driven by a micro-turbojet engine. Background Technology

[0002] With the increasing strategic value of individual soldier aerial mobility, wearable aircraft have become a hot research and development area in the aviation equipment field of various countries. These aircraft use micro-turbojet engines as their core power source, integrating the engine system into a human-mounted backpack-like structure. This allows individual soldiers to overcome terrain limitations, achieving vertical takeoff and landing, low-altitude flight, and rapid advance, demonstrating broad application prospects in military reconnaissance, emergency rescue, special operations, and civilian general aviation. Micro-turbojet engines, with their high thrust-to-weight ratio, compact size, and rapid response, are widely recognized as one of the most suitable power solutions for wearable aircraft.

[0003] During operation, the exhaust gas temperature at the combustion chamber outlet of a micro turbojet engine typically reaches over 600°C. The high-speed exhaust gas from the tailpipe possesses high kinetic and thermodynamic energy. Under conventional settings, this high-temperature, high-speed exhaust gas completes only one thrust operation before being directly discharged into the atmosphere, resulting in unused residual heat and kinetic energy and energy waste. For wearable aircraft, the energy efficiency of the propulsion system directly affects fuel consumption, range, and payload capacity. However, micro turbojet engines, limited by their overall size and weight, have relatively limited thrust margins, making further efficiency improvements urgent. Furthermore, the high-temperature exhaust gas exerts thermal radiation on the wearer, and the jet noise generated by the high-speed exhaust is detrimental to stealth and auditory health. In addition, the exhaust systems of existing wearable aircraft are mostly fixed, lacking adaptability to the varying requirements for thrust output, thermal protection, and noise suppression at different flight stages.

[0004] Therefore, it is necessary to provide a wearable flight system based on a micro-turbojet engine to solve the above-mentioned technical problems. Summary of the Invention

[0005] In response to the above situation and to overcome the shortcomings of the existing technology, this invention provides a wearable flight system based on a micro-turbojet engine. Through the annular channel between the ejector jacket and the tail nozzle, external air is drawn in and mixed with the exhaust gas by the negative pressure effect generated by the high-speed gas. This increases the exhaust mass flow rate to improve thrust without consuming additional fuel. At the same time, the mixing of cold air significantly reduces the exhaust temperature, thereby reducing heat radiation and jet noise. This achieves a synergistic effect of waste energy utilization, thermal protection, and noise reduction.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] A wearable flight system driven by a micro turbojet engine includes an ejector outer tube and an adjustment tube. The ejector outer tube is coaxially fixed to the outside of the tail nozzle of the micro turbojet engine, which is located below the wearable backpack. An annular ejector airflow channel is formed between the ejector outer tube and the tail nozzle. An air inlet is provided at the front end of the ejector outer tube. The adjustment tube is coaxially sleeved on the outside of the ejector outer tube and can rotate relative to the ejector outer tube. Corresponding air inlets are provided on the ejector outer tube and the adjustment tube. The adjustment tube is equipped with an adjustment mechanism to drive its rotation.

[0008] Preferably, the ejector outer sleeve is fixedly installed on the outside of the tail nozzle via a connecting flange and a support plate.

[0009] Preferably, the first air inlet on the ejector outer sleeve is distributed circumferentially, and the second air inlet on the adjusting sleeve matches the number of the first air inlet, corresponds to its position, and is distributed circumferentially.

[0010] Preferably, the adjustment mechanism includes a toothed ring, a drive wheel, a mounting shaft, an operating rod, a conical block, a slider, a sliding sleeve, and a disc spring. The toothed ring is sleeved on the outside of the adjustment sleeve. The drive wheel is rotatably mounted on the outer sleeve of the ejector and meshes with the toothed ring. The drive wheel is positioned and mounted via the mounting shaft. The end of the operating rod is axially slidably connected to the mounting shaft via a square insert.

[0011] Preferably, a conical block is fixedly sleeved on the operating rod, a matching conical groove is opened on the outer tube of the ejector, friction pads are provided on the mating surfaces of the conical block and the conical groove, and the operating rod is rotatably connected to a slider that is slidably installed inside the outer tube of the ejector.

[0012] Preferably, a sliding sleeve is provided between the slider and the ejector outer tube, and the two ends of the sliding sleeve are fixedly connected to the slider and the ejector outer tube respectively. A fixed disc spring is sleeved on the outside of the sliding sleeve, and the disc spring drives the conical block to embed into the conical groove to achieve position locking in the initial state.

[0013] Preferably, both the ejector outer sleeve and the adjusting sleeve are made of high-temperature resistant stainless steel, the air inlet of the ejector outer sleeve is provided with an arc transition structure, and the first air inlet and the second air inlet are both circumferentially uniformly arranged.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] (1) This invention sets up an ejector outer tube coaxial with the tail nozzle, forming an annular ejector airflow channel between the outer tube and the tail nozzle. Utilizing the negative pressure effect generated by the high-speed exhaust gas discharged from the tail nozzle within the channel, ambient air is actively drawn in from the air inlet at the front end of the outer tube, mixed with the high-temperature exhaust gas, and then discharged together. Compared with pure exhaust gas, the mixed exhaust significantly increases the mass flow rate, achieving an effective increase in thrust without consuming additional fuel. At the same time, the mixed cold air significantly reduces the exhaust temperature, mitigating the heat radiation impact on the wearer, and also suppressing jet noise to a certain extent, achieving a synergistic effect of waste energy recovery and utilization with thermal protection and noise reduction.

[0016] (2) This invention uses a rotatable adjusting sleeve coaxially fitted outside the ejector outer tube, and opens corresponding air inlets on the two sleeves respectively. The adjusting mechanism drives the adjusting sleeve to rotate to change the degree of overlap of the two sets of air inlets, thereby controlling the amount of air introduced into the ejector airflow channel from the side. During takeoff or heavy-load flight, the opening can be adjusted to the maximum to obtain the maximum ejection gain. During cruise or landing, the opening can be appropriately reduced to balance thrust and thermal protection, so that the same ejector device can adapt to the differentiated needs of different flight conditions. At the same time, the entire adjusting mechanism is a purely mechanical structure, which does not require electric or hydraulic drive, has few parts, does not increase the weight burden significantly, and has high reliability, which is suitable for the requirements of lightweight and high reliability of wearable aircraft. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0018] Figure 2 This is a schematic diagram of the back structure of the wearable backpack of the present invention;

[0019] Figure 3 This is a schematic diagram of the ejector outer sleeve of the present invention;

[0020] Figure 4 This is a schematic diagram of the internal structure of the ejector outer sleeve of the present invention;

[0021] Figure 5 This is a schematic diagram of the cross-sectional structure of the ejector outer sleeve of the present invention;

[0022] Figure 6 For the present invention Figure 5 - Enlarged structural diagram at point A.

[0023] The corresponding names of the reference numerals in the attached drawings are as follows: 1. Tail nozzle; 2. Ejector outer sleeve; 21. First air inlet; 3. Ejector airflow channel; 4. Adjusting sleeve; 41. Second air inlet; 5. Adjusting mechanism; 51. Operating lever; 52. Square insert rod; 53. Conical block; 54. Conical groove; 55. Sliding block; 56. Sliding sleeve; 57. Disc spring; 7. Wearable backpack; 8. Gear ring; 9. Drive wheel; 10. Mounting shaft. Detailed Implementation

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments. The embodiments of the present invention include, but are not limited to, the following embodiments.

[0025] First embodiment:

[0026] like Figure 1-6 As shown, the wearable flight system based on a micro-turbojet engine provided by the present invention includes an ejector outer tube 2 and an adjusting sleeve 4. The ejector outer tube 2 is coaxially fixedly connected to the outside of the tail nozzle 1 of the micro-turbojet engine. An annular ejector airflow channel 3 is formed between the ejector outer tube 2 and the tail nozzle 1. An air inlet is provided at the front end of the ejector outer tube 2. The adjusting sleeve 4 is coaxially sleeved on the outside of the ejector outer tube 2 and can rotate relative to the ejector outer tube 2. Air inlets are correspondingly opened on the ejector outer tube 2 and the adjusting sleeve 4. The adjusting sleeve 4 is equipped with an adjusting mechanism 5 to drive its rotation.

[0027] During operation, after the micro-turbojet engine starts, high-temperature, high-speed exhaust gas is ejected rearward through the tail nozzle 1. Due to the annular gap between the ejector sleeve 2 and the tail nozzle 1, a negative pressure zone is formed within this gap. Ambient air is actively drawn in through the air inlet at the front of the sleeve, mixes with the high-temperature exhaust gas, and is then expelled rearward together. This increases the exhaust mass flow rate without consuming additional fuel, thus boosting thrust. Simultaneously, the mixing of cold air lowers the exhaust temperature, reducing heat radiation to the wearer and suppressing jet noise to some extent. In conditions requiring high thrust, such as takeoff or heavy load, the adjusting sleeve 4 is rotated via the adjusting mechanism 5 to ensure complete overlap of the two sets of air inlets. At this point, the side air intake area is maximized, the ejected air volume is maximized, and the thrust gain reaches its maximum. During cruise or landing, the adjusting sleeve 4 is rotated in the opposite direction via the adjusting mechanism 5 to partially offset the two sets of air inlets, reducing the side air intake area and appropriately decreasing the ejected air volume, achieving a more balanced state between thrust and exhaust temperature.

[0028] Second embodiment:

[0029] like Figure 1-6As shown, the ejector outer tube 2 is fixedly installed on the outside of the tail nozzle 1 through the connection flange and the support plate. The first air inlet 21 on the ejector outer tube 2 is distributed circumferentially. The second air inlet 41 on the adjusting sleeve 4 matches the number and position of the first air inlet 21 and is distributed circumferentially. Both the ejector outer tube 2 and the adjusting sleeve 4 are made of high temperature resistant stainless steel. The air inlet of the ejector outer tube 2 is provided with an arc transition structure. The first air inlet 21 and the second air inlet 41 are both circumferentially uniformly arranged structures.

[0030] During use, the installation method of connecting flange and support plate ensures the coaxiality between the ejector outer sleeve 2 and the tail nozzle 1, and the gap of the annular ejector airflow channel 3 is uniform, resulting in a more even distribution of the ejector airflow in the circumferential direction, which is beneficial to improving ejection efficiency. The arc transition structure at the air inlet reduces the flow resistance when air enters, making it easier for external air to be drawn into the annular channel. The first air inlet 21 and the second air inlet 41 are evenly distributed in the circumferential direction, with the same number and corresponding positions, ensuring that the air intake area of ​​the regulating sleeve 4 changes consistently at various angles during rotation, making the adjustment more linear and smooth. The ejector outer sleeve 2 and the regulating sleeve 4 are made of high-temperature resistant stainless steel, which can maintain sufficient structural strength and dimensional stability even under long-term exposure to high-temperature gas erosion, ensuring the service life of the device.

[0031] Third embodiment:

[0032] like Figure 1-6 As shown, the adjusting mechanism 5 includes a gear ring 8, a drive wheel 9, a mounting shaft 10, an operating rod 51, a conical block 53, a slider 55, a sliding sleeve 56, and a disc spring 57. The gear ring 8 is sleeved on the outside of the adjusting sleeve 4. The drive wheel 9 is rotatably mounted on the ejector outer sleeve 2 and meshes with the gear ring 8. The drive wheel 9 is positioned by the mounting shaft 10. The end of the operating rod 51 is axially slidably connected to the mounting shaft 10. The conical block 53 is fixedly sleeved on the operating rod 51. An opening is formed on the ejector outer sleeve 2. The tapered groove 54 is adapted, and friction pads are provided on the mating surfaces of the tapered block 53 and the tapered groove 54. The operating rod 51 is rotatably connected to the slider 55, which is slidably installed in the outer tube 2 of the ejector. A sliding sleeve 56 is provided between the slider 55 and the outer tube 2 of the ejector. The two ends of the sliding sleeve 56 are fixedly connected to the slider 55 and the outer tube 2 of the ejector, respectively. A fixed disc spring 57 is sleeved on the outside of the sliding sleeve 56. In the initial state, the disc spring 57 drives the tapered block 53 to embed into the tapered groove 54 to achieve position locking.

[0033] In use, when adjusting the ejector air volume, the wearer first pushes the operating lever 51 axially, causing the conical block 53 to disengage from the conical groove 54 against the spring force of the disc spring 57. Simultaneously, the slider 55 slides along the sliding sleeve 56 away from the outer sleeve, releasing the lock between the conical block 53 and the conical groove 54. The wearer then rotates the operating lever 51, which drives the drive wheel 9 to rotate via the mounting shaft 10. The drive wheel 9, through its meshing toothed ring 8, rotates the entire adjusting sleeve 4 relative to the ejector outer sleeve 2, changing the overlap of the two sets of air inlets and thus adjusting the air intake area. After adjustment, the wearer releases the operating lever 51. Under its own elastic force, the disc spring 57 pushes the slider 55 back to its original position via the sliding sleeve 56. The slider 55 then causes the operating lever 51, along with the conical block 53, to re-enter the conical groove 54. The friction pad between the conical block 53 and the conical groove 54 generates sufficient friction under the pressure of the disc spring 57, reliably locking the position of the adjusting sleeve 4. The adjustment mechanism 5 is a fully mechanical structure that can adjust and lock the ejector coefficient without the need for additional power or hydraulic power sources, and can maintain a stable working position even in a vibration environment.

[0034] Working Principle: When the micro-turbojet engine is operating, high-temperature, high-speed exhaust gas is ejected rearward at high speed through the tail nozzle 1. Since the ejector sleeve 2 is coaxially fitted onto the outside of the tail nozzle 1, with an annular ejector airflow channel 3 between them, the high-speed injected exhaust gas creates a negative pressure zone within this channel. This draws ambient air into the ejector airflow channel 3 from the air inlet at the front end of the ejector sleeve 2 and the air inlets on the side wall. The drawn-in ambient air mixes with the high-speed exhaust gas in the channel and is then discharged rearward together, thereby increasing the exhaust mass flow rate and achieving thrust enhancement without increasing additional fuel consumption. When it is necessary to adjust the ejector air volume, the adjusting sleeve 4 is rotated relative to the ejector sleeve 2 via the adjusting mechanism 5, changing the overlap of the two sets of air inlets: a larger overlap area increases the side air intake and improves the ejection coefficient; a smaller overlap area decreases the side air intake and reduces the ejection coefficient. Through this method, the present invention achieves on-demand adjustment of the ejector lift enhancement effect.

[0035] The above embodiments are merely one of the preferred embodiments of the present invention and should not be used to limit the scope of protection of the present invention. Any modifications or refinements made to the main design concept and spirit of the present invention that are not of substantial significance, but solve the same technical problem as the present invention, should be included within the scope of protection of the present invention.

Claims

1. A wearable flight system based on a micro-turbojet engine, characterized in that, The device includes an ejector outer tube (2) and an adjusting sleeve (4). The ejector outer tube (2) is coaxially fixed to the outside of the tail nozzle (1) of the micro turbojet engine. The tail nozzle (1) of the micro turbojet engine is located below the backpack (7). An annular ejector airflow channel (3) is formed between the ejector outer tube (2) and the tail nozzle (1). An air inlet is provided at the front end of the ejector outer tube (2). The adjusting sleeve (4) is coaxially sleeved on the outside of the ejector outer tube (2) and can rotate relative to the ejector outer tube (2). Air inlets are correspondingly opened on the ejector outer tube (2) and the adjusting sleeve (4). The adjusting sleeve (4) is equipped with an adjusting mechanism (5) to drive its rotation.

2. The wearable flight system based on a micro-turbojet engine as described in claim 1, characterized in that, The ejector outer tube (2) is fixedly installed on the outside of the tail nozzle (1) by connecting flange and support plate.

3. A wearable flight system based on a micro-turbojet engine as described in claim 1, characterized in that, The first air inlet (21) on the ejector outer sleeve (2) is distributed circumferentially, and the second air inlet (41) on the adjusting sleeve (4) matches the number of the first air inlet (21), corresponds to its position, and is distributed circumferentially.

4. A wearable flight system based on a micro-turbojet engine as described in claim 1, characterized in that, The adjustment mechanism (5) includes a toothed ring (8), a drive wheel (9), a mounting shaft (10), an operating lever (51), a conical block (53), a slider (55), a sliding sleeve (56), and a disc spring (57). The toothed ring (8) is sleeved on the outside of the adjustment sleeve (4). The drive wheel (9) is rotatably mounted on the ejector outer sleeve (2) and meshes with the toothed ring (8). The drive wheel (9) is positioned and mounted through the mounting shaft (10). The end of the operating lever (51) is axially slidably connected to the mounting shaft (10) through a square insert (52).

5. A wearable flight system based on a micro-turbojet engine as described in claim 4, characterized in that, A conical block (53) is fixedly sleeved on the operating rod (51), and a matching conical groove (54) is opened on the outer tube (2) of the ejector. Friction pads are provided on the mating surfaces of the conical block (53) and the conical groove (54). The operating rod (51) is rotatably connected to a slider (55) that is slidably installed inside the outer tube (2) of the ejector.

6. A wearable flight system based on a micro-turbojet engine according to claim 5, characterized in that, A sliding sleeve (56) is provided between the slider (55) and the ejector outer sleeve (2). The two ends of the sliding sleeve (56) are fixedly connected to the slider (55) and the ejector outer sleeve (2) respectively. A fixed disc spring (57) is sleeved on the outside of the sliding sleeve (56). In the initial state, the disc spring (57) drives the conical block (53) to embed into the conical groove (54) to achieve position locking.

7. A wearable flight system based on a micro-turbojet engine as described in claim 1, characterized in that, Both the ejector outer sleeve (2) and the adjusting sleeve (4) are made of high-temperature resistant stainless steel. The air inlet of the ejector outer sleeve (2) is provided with an arc transition structure. The first air inlet (21) and the second air inlet (41) are both circumferentially uniformly arranged structures.

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