An air transport support vehicle
Patent Information
- Application Number
- CN202611323935.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-08-28
- Publication Date
- 2026-11-03
AI Technical Summary
Current transport aircraft are easily detected, tracked and intercepted in high-threat environments, making it impossible for them to independently enter high-threat areas to carry out missions. Furthermore, they have low space utilization and large structural weight, making it difficult to meet both transportation and mission requirements.
It adopts a blended wing-body structure, internally mounted engines, symmetrical V-tail, and blended intake and exhaust system. The fuselage is divided into a cargo bay and an equipment system bay, with internally mounted engines and engine mounting bays. The wings and fuselage are integrated to eliminate radar reflection sources. The fuselage has a four-zone layered layout to achieve all-round stealth and improve space utilization.
It enables single-unit deep penetration into enemy territory to carry out missions in high-threat environments, reduces mission formation size and probability of loss, improves space utilization, integrates transportation and mission functions, and reduces radar and infrared detectability.
Smart Images
Figure CN123025927A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application belongs to the field of aircraft design, and particularly relates to an air transport support aircraft. BACKGROUND
[0002] The former military air transport equipment mainly takes the transport aircraft as the core, undertakes long-range delivery and air-drop of personnel, materials and equipment, and is the key logistics and assault support platform in the modern joint task system.
[0003] However, with the improvement of the scene air defense system and the wide deployment of precision guidance equipment, the survival ability, task adaptability and task efficiency of the traditional transport aircraft in a high threat environment face significant bottlenecks.
[0004] The active transport aircraft adopts a conventional cylindrical fuselage + flat wing + independent tail + external engine layout, the fuselage and the wing surface are abrupt, the engine, tail sling / wing sling structure forms a large number of strong radar reflection sources, the radar reflection cross section is large, and it is difficult to realize concealment and penetration. In the complex electromagnetic environment and the modern air defense system, it is easy to be detected, tracked and intercepted at a long distance, and it cannot independently enter a high threat area to perform a task. At the same time, the traditional transport aircraft only has the basic functions of transportation, air-drop and air-landing, and does not integrate the equipment mounting and launching system. When performing air-landing assault and deep delivery tasks, it cannot implement instant suppression on the ground defense, armored targets and target points, and needs to rely on the coordination of aircraft, aircraft and other escort forces during the task process, resulting in complex formation, high coordination cost, slow response speed and easy to miss the plane.
[0005] The existing transport aircraft also has an independent cargo compartment design, the inside of the fuselage is only used for cargo and personnel loading, the upper and lower spaces are not integrated and reused, the cargo compartment floor only bears a one-way bearing function, and has no expansion capabilities such as equipment mounting and launching, and storage of launched objects. The space utilization rate is low, the structure weight is large, and it is difficult to meet the dual requirements of transportation and task. SUMMARY
[0006] In order to solve the above problems, the present application provides an air transport support aircraft to solve the problems of low space utilization rate and large structure weight of the aircraft in the prior art.
[0007] The technical scheme of the present application is: an air transport support aircraft, comprising a fuselage, a wing and a buried engine;
[0008] The fuselage is provided with four functional areas, including a transport cargo compartment, an equipment system cabin and two engine mounting cabins, and the buried engine is arranged in the engine mounting cabin;
[0009] The transport cargo compartment and the equipment system cabin are arranged above and below, the transport cargo compartment is provided with cargo, the equipment system cabin is provided with a hanging equipment system, and the two engine mounting cabins are arranged on both sides of the transport cargo compartment and the equipment system cabin.
[0010] The transport cargo compartment and the equipment system compartment are connected by an integrated support structure.
[0011] Preferably, a large-opening cargo door is provided at the rear of the transport cargo compartment, corresponding to the position of the transport cargo compartment, and a lower compartment door is provided below the equipment system compartment, which contains launchable equipment.
[0012] Preferably, a cargo floor-equipment rack is provided between the transport cargo compartment and the equipment system compartment, and a cargo-airdrop track is provided above the cargo floor-equipment rack. The cargo-airdrop track is set corresponding to the large-opening cargo door, and a first electronically controlled lock mechanism is provided on the cargo-airdrop track.
[0013] Preferably, an equipment hoisting and electronic lock mechanism is provided below the cargo floor-equipment rack, and an equipment airdrop hatch is correspondingly provided below the equipment hoisting; the equipment hoisting and electronic lock mechanism is located directly above the lower hatch.
[0014] Preferably, the cargo floor-equipment rack is made of a high-strength alloy.
[0015] Preferably, the wing includes a main wing and a tail wing. The main wing is connected to the middle of the fuselage, and there are two tail wings symmetrically arranged on both sides of the fuselage to form a V-shaped tail wing.
[0016] Preferably, the main wing is provided with a blended intake and exhaust system, and a deflectable exhaust device is provided behind the blended intake and exhaust system along the fuselage heading. The deflectable exhaust device can blow its own exhaust towards the tail of the aircraft and cause the tail to deflect.
[0017] Preferably, the transport cargo hold includes a cockpit and a cargo hold, the cargo hold being located behind the cockpit and containing typical cargo.
[0018] Preferably, subsystem compartments are provided on both the front and rear sides of the equipment system compartment, and aircraft operation equipment is installed in the subsystem compartments. A detection and guidance system is also provided at the nose of the fuselage, and the detection and guidance system is arranged adjacent to the front subsystem compartment.
[0019] Preferably, the aircraft operating equipment includes a flight control system, which is electrically connected to the first electronic lock mechanism and the equipment hoisting and electronic lock mechanism.
[0020] The air transport support aircraft of this application has the following advantages:
[0021] The aircraft employs a blended wing-body main wing, a symmetrical V-tail, an internally mounted engine nacelle, and a blended intake and exhaust system. This eliminates strong radar reflection sources such as exposed engine nacelles, the right-angle junction of the fuselage and wing, and the independent vertical tail, thereby reducing the radar cross-section in all directions. At the same time, the V-tail shields the infrared heat source of the exhaust at the rear, and the internally mounted intake and exhaust reduce infrared radiation. The aircraft has significant low-detectability characteristics for both radar and infrared, allowing it to penetrate deep into enemy air defense threat areas on a single aircraft without the need for a multi-aircraft escort formation, greatly reducing the size of the mission formation and the probability of loss.
[0022] The fuselage is vertically divided into an upper cargo hold and a lower equipment systems compartment, with engine mounting compartments on both sides. Subsystem compartments are set up in the redundant space in front and behind the equipment compartment, making full use of the available space in the entire fuselage section to simultaneously accommodate airdropped supplies, airborne equipment, power equipment, flight control electrical systems, and detection and guidance equipment. This achieves a high degree of integration of transportation, attack, power, and airborne equipment, avoiding the waste of fuselage space caused by the separation of cargo hold, bomb bay, and equipment compartment in traditional aircraft. Attached Figure Description
[0023] Figure 1 This is a side view of the overall structure of this application;
[0024] Figure 2 for Figure 1 A magnified view of a portion of the image;
[0025] Figure 3 This is a top view of the overall structure of this application.
[0026] 1. Cargo hold; 2. Equipment systems compartment; 3. Subsystem compartment; 4. Lower hatch; 5. Large-opening cargo door; 6. Launchable equipment; 7. Detection and guidance system; 8. Typical cargo; 9. Integrated intake and exhaust system; 10. Deflectable exhaust device; 11. Tail fin; 12. Wing; 13. Cargo floor-equipment rack; 201. Equipment sling; 202. Equipment airdrop hatch; 203. Electrically controlled locking mechanism. Detailed Implementation
[0027] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0028] The first aspect of this application provides an air transport support aircraft that employs a blended wing-body structure to eliminate drag.
[0029] like Figures 1-3 It includes the fuselage, wings, and internal engines.
[0030] The fuselage has four functional areas, including: cargo compartment 1, equipment system compartment 2, and two engine mounting compartments, with the internal engines located in the engine mounting compartments;
[0031] The transport cargo hold 1 and the equipment system hold 2 are arranged vertically. The transport cargo hold 1 contains cargo, and the equipment system hold 2 contains the hoisting equipment system. Two engine mounting compartments are located on both sides of the transport cargo hold 1 and the equipment system hold 2.
[0032] The transport cargo compartment 1 and the equipment system compartment 2 are connected by an integrated support structure.
[0033] By incorporating internal engines and using engine nacelles on both sides, the exposed engine nacelles are eliminated. Combined with the partitioned layout of the fuselage, radar and infrared radiation signatures are reduced, achieving a basic low-detectability stealth configuration.
[0034] The fuselage is arranged in four layers and sides, integrating the three core functions of transportation, equipment and power, making full use of the internal space of the fuselage and improving the utilization rate of the fuselage space; the transport cargo compartment 1 and the equipment system compartment 2 are arranged in layers, which can carry airdropped supplies and equipment at the same time, realizing the integration of transportation and mission functions.
[0035] Preferably, a large-opening cargo door 5 is provided at the rear of the transport cargo hold 1, corresponding to the position of the transport cargo hold 1, and a lower hatch 4 is provided below the equipment system compartment 2. The equipment system compartment 2 is equipped with launchable equipment 6. The large-opening cargo door 5 is suitable for loading, unloading and airdropping of large equipment, personnel and containers, expanding the cargo access channel and improving the efficiency of material loading and airdrop operations.
[0036] Preferably, a cargo floor-equipment rack 13 is provided between the transport cargo hold 1 and the equipment system hold 2. A cargo-airdrop track is provided above the cargo floor-equipment rack 13, corresponding to the large-opening cargo hold door 5. A first electronically controlled locking mechanism 203 is provided on the cargo-airdrop track. The cargo-airdrop track provides sliding guidance for the cargo, allowing the cargo to slide smoothly backward along the track towards the cargo hold door, reducing airdrop resistance and improving the smoothness and accuracy of the drop.
[0037] Preferably, an equipment sling 201 and an electronically controlled locking mechanism 203 are provided below the cargo floor-equipment rack 13, and an equipment airdrop hatch 202 is correspondingly provided below the equipment sling 201; the equipment sling 201 and the electronically controlled locking mechanism 203 are located directly above the lower hatch 4. The equipment sling 201 mechanism enables stable mounting of multiple types of launchers, has a strong load-bearing capacity, and is compatible with a variety of equipment.
[0038] Preferably, the cargo floor-equipment rack 13 is made of high-strength alloy. High-strength alloy combines high load-bearing capacity with lightweight characteristics. The upper part can support heavy vehicles and large quantities of airdropped supplies, while the lower part can suspend large-tonnage launchers, meeting the requirements for heavy-duty dual-load bearing.
[0039] Preferably, the wing 12 includes a main wing 12 and a tail 11. The main wing 12 is connected to the middle of the fuselage, and there are two tail 11s symmetrically arranged on both sides of the fuselage, forming a V-shaped tail 11. The main wing 12 is integrated with the middle of the fuselage to form a blended wing-body aerodynamic shape, eliminating the right-angle reflective surface at the junction of the fuselage and wing 12, reducing the radar cross-section, and improving stealth performance.
[0040] Preferably, a blended intake and exhaust system 9 is installed within the main wing 12, employing an integrated power flow channel. A deflectable exhaust device 10 is positioned behind the blended intake and exhaust system 9 along the fuselage heading. The deflectable exhaust device 10 directs its exhaust towards the tail fin 11, increasing local airflow velocity and thus enhancing handling efficiency. Specifically, the deflectable exhaust device 10 is a vectoring nozzle. The blended intake and exhaust system 9 is completely embedded within the main wing 12, with no exposed air ducts, eliminating radar reflections and infrared heat sources from the intake and exhaust systems, thus enhancing the overall stealth effect of the aircraft.
[0041] Preferably, the transport cargo hold 1 includes a cockpit and a cargo hold, with the cargo hold located behind the cockpit and containing typical cargo 8. The cockpit and cargo hold are separated into front and rear sections, ensuring independent operating space for the pilots, and preventing airdrops and cargo sliding from interfering with flight control, thus improving flight operation safety.
[0042] Preferably, subsystem compartments 3 are provided on both the front and rear sides of the equipment system compartment 2. The subsystem compartments 3 are equipped with aircraft operating equipment, and a detection and guidance system 7 is also provided at the nose of the fuselage. The detection and guidance system 7 is arranged adjacent to the front subsystem compartments 3. The subsystem compartments 3 make full use of the unused space in front and behind the equipment compartment to centrally house airborne equipment such as flight control, electrical, and hydraulic systems, avoiding the occupation of the core transport and equipment compartments, and further optimizing the utilization rate of the fuselage space.
[0043] Preferably, the aircraft operating equipment includes a flight control system, which is electrically connected to the first electronically controlled locking mechanism 203 and the equipment sling 201 and electronically controlled locking mechanism 203. The flight control system uniformly manages the two electronically controlled mechanisms for cargo locking and launch object locking, realizing integrated electronic control of the entire mission, eliminating the need for two independent control systems and simplifying the airborne electrical wiring.
[0044] In summary, this application has the following advantages:
[0045] The aircraft employs a blended wing-body main wing, a symmetrical V-tail, an internally mounted engine nacelle, and a blended intake and exhaust system. This eliminates strong radar reflection sources such as exposed engine nacelles, the right-angle junction of the fuselage and wing, and the independent vertical tail, thereby reducing the radar cross-section in all directions. At the same time, the V-tail shields the infrared heat source of the exhaust at the rear, and the internally mounted intake and exhaust reduce infrared radiation. The aircraft has significant low-detectability characteristics for both radar and infrared, allowing it to penetrate deep into enemy air defense threat areas on a single aircraft without the need for a multi-aircraft escort formation, greatly reducing the size of the mission formation and the probability of loss.
[0046] The fuselage is vertically divided into an upper cargo hold and a lower equipment systems compartment, with engine mounting compartments on both sides. Subsystem compartments are set up in the redundant space in front and behind the equipment compartment, making full use of the available space in the entire fuselage section to simultaneously accommodate airdropped supplies, airborne equipment, power equipment, flight control electrical systems, and detection and guidance equipment. This achieves a high degree of integration of transportation, attack, power, and airborne equipment, avoiding the waste of fuselage space caused by the separation of cargo hold, bomb bay, and equipment compartment in traditional aircraft.
[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. An air transport support aircraft, characterized in that, Includes the fuselage, wings (12), and internally mounted engines; The fuselage has four functional areas, including: a cargo hold (1), an equipment system compartment (2) and two engine mounting compartments, with the internally mounted engine located in the engine mounting compartment; The transport cargo hold (1) and the equipment system hold (2) are arranged vertically. The transport cargo hold (1) contains cargo, and the equipment system hold (2) contains a hoisting equipment system. Two engine mounting bays are located on both sides of the transport cargo hold (1) and the equipment system hold (2). The transport cargo compartment (1) and the equipment system compartment (2) are connected by an integrated support structure.
2. The air transport support aircraft as described in claim 1, characterized in that, A large-opening cargo door (5) is provided at the rear of the transport cargo compartment (1) corresponding to the position of the transport cargo compartment (1), and a lower hatch (4) is provided below the equipment system compartment (2). The equipment system compartment (2) is equipped with launchable equipment (6).
3. The air transport support aircraft as described in claim 2, characterized in that, A cargo floor-equipment rack (13) is provided between the transport cargo compartment (1) and the equipment system compartment (2). A cargo-airdrop track is provided above the cargo floor-equipment rack (13). The cargo-airdrop track is set corresponding to the large-open cargo door (5). A first electronic lock mechanism (203) is provided on the cargo-airdrop track.
4. The air transport support aircraft as described in claim 3, characterized in that, Below the cargo floor-equipment rack (13) is an equipment hoist (201) and an electric lock mechanism (203), and below the equipment hoist (201) is a corresponding equipment airdrop hatch (202); the equipment hoist (201) and the electric lock mechanism (203) are located directly above the lower hatch (4).
5. The air transport support aircraft as described in claim 3, characterized in that, The cargo floor-equipment rack (13) is made of high-strength alloy.
6. The air transport support aircraft as claimed in claim 1, characterized in that, The wing (12) includes a main wing (12) and a tail wing (11). The main wing (12) is connected to the middle of the fuselage. There are two tail wings (11) which are symmetrically arranged on both sides of the fuselage to form a V-shaped tail wing (11).
7. The air transport support aircraft as described in claim 6, characterized in that, The main wing (12) is equipped with a blended intake and exhaust system (9). The main wing (12) is equipped with a deflectable exhaust device (10) behind the blended intake and exhaust system (9) along the fuselage heading. The deflectable exhaust device (10) can blow its own exhaust towards the tail fin (11) of the aircraft and drive the tail fin (11) to deflect.
8. The air transport support aircraft as claimed in claim 7, characterized in that, The transport cargo hold (1) includes a cockpit and a cargo hold, the cargo hold being located behind the cockpit and containing typical cargo (8).
9. The air transport support aircraft as claimed in claim 4, characterized in that, The equipment system compartment (2) is provided with subsystem compartments (3) on both the front and rear sides. The subsystem compartments (3) are equipped with aircraft operation equipment. The fuselage is also provided with a detection and guidance system (7) at the front. The detection and guidance system (7) is arranged adjacent to the subsystem compartments (3) at the front.
10. The air transport support aircraft as claimed in claim 9, characterized in that, The aircraft operating equipment includes a flight control system, which is electrically connected to the first electronic lock mechanism (203), the equipment hoist (201), and the electronic lock mechanism (203).