Aircraft carrying platform capable of carrying task load

Abstract

The invention provides an aircraft carrying platform capable of carrying a mission load, and relates to the technical field of aircrafts, the aircraft carrying platform comprises a fuselage main body, a load cabin used for installing the mission load is arranged in the fuselage main body, a solid engine providing power for the fuselage main body is arranged at one end of the fuselage main body, and a first empennage is further arranged at the top of the fuselage main body; two canard rudders and two wings are symmetrically arranged on the two sides of the fuselage main body, and the canard rudders and the wings control the pitching posture and the rolling posture of the fuselage main body respectively; the fuselage main body with the load cabin is arranged, meanwhile, the solid engine can provide boosting power for the fuselage main body, and the canard rudder, the wings and the first empennage are used for controlling the flight attitude of the fuselage main body. According to the aerial carrier platform provided by the invention, the working performance, reliability and adaptability of the load can be tested under the real high-altitude flight condition by carrying the task load, the test error caused by the fact that the real flight environment cannot be reproduced in the simulation test can be effectively avoided, and the accuracy of the test result is ensured.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an aircraft platform capable of carrying mission payloads. Background Technology

[0002] Before being mounted on aircraft and put into use, aviation equipment must undergo high-altitude performance testing to verify its performance, reliability, and adaptability under high-altitude flight conditions. In existing technologies, high-altitude performance testing is mainly conducted through ground simulation, using relevant testing equipment to simulate the high-altitude environment during flight, thereby testing the operational performance of aviation equipment. However, ground simulation testing cannot fully reproduce the complex conditions in the real flight environment. For example, simulation test benches can simulate air pressure and temperature conditions at high altitudes, but cannot fully simulate the combined effects of inertial overload, aerodynamic load, and temperature load on aviation equipment during flight. Microgravity environment simulation also has similar problems. Due to limitations, the testing time in microgravity environments is extremely short (usually only a few seconds), which cannot meet the research needs of long-term microgravity effects. Summary of the Invention

[0003] The purpose of this application is to address the above problems by providing a carrier platform capable of carrying mission payloads, comprising: The fuselage body has a payload compartment inside, which is used to install mission payloads; A solid rocket motor is located at one end of the fuselage body along a first direction and is used to provide power to the fuselage body. Two canard rudders are symmetrically arranged on both sides of the fuselage body along the second direction to control the pitch attitude of the fuselage body. The second direction is perpendicular to the first direction. The wings, two of which are symmetrically arranged on both sides of the fuselage body along the second direction, are used to control the roll attitude of the fuselage body; The first tail fin is located on top of the solid rocket motor.

[0004] According to the technical solutions provided in certain embodiments of this application, the fuselage body includes a nose section, a control section, a payload section, and an adapter section connected in sequence. The nose section and the control section are provided with the canards. The control section is provided with control equipment, which is used to control the canards and the wings, thereby realizing the control of the pitch, roll, and yaw attitudes of the fuselage body. The payload section is provided with the wings, and the payload section contains the payload bay. The adapter section is used to connect the payload section and the solid rocket motor.

[0005] According to the technical solutions provided in certain embodiments of this application, the wing includes a fixed wing, and two fixed wings are symmetrically arranged on both sides of the load compartment along the second direction. One side of the fixed wing is provided with a wingtip rudder, which can rotate relative to the fixed wing, thereby realizing the control of the roll attitude of the fuselage body.

[0006] According to the technical solutions provided in certain embodiments of this application, the solid rocket motor extends at least partially into the adaptable compartment.

[0007] According to the technical solutions provided in certain embodiments of this application, the bottom of the payload compartment has a first opening, and the first opening connects the payload compartment and the external environment.

[0008] According to the technical solutions provided in certain embodiments of this application, the projected areas of the head section, the control section, the payload section, and the adapter section along the first direction are the same in size and shape, and are all rectangular.

[0009] According to the technical solutions provided in certain embodiments of this application, the head section, the control section, the payload section, and the adapter section have the same size and shape of projected area along the first direction, and are all circular.

[0010] According to the technical solutions provided in certain embodiments of this application, the projected area of ​​the adapter section along the first direction completely covers the projected area of ​​the solid rocket motor along the first direction.

[0011] According to the technical solutions provided in certain embodiments of this application, the solid rocket motor is provided with second tail fins on both sides along the second direction.

[0012] According to the technical solutions provided in certain embodiments of this application, the top of the load compartment and the adapter compartment are jointly provided with a vertical wing.

[0013] Compared with the prior art, the beneficial effects of this application are as follows: This application provides a carrier platform capable of carrying mission payloads, including a fuselage body with a payload bay inside the fuselage body for mounting mission payloads. A solid-propellant engine is provided at one end of the fuselage body along a first direction to provide power to the fuselage body. A first tail fin is also provided on its top. Two canards and two wings are symmetrically arranged on both sides of the fuselage body along a second direction. The canards are used to control the pitch attitude of the fuselage body, and the wings are used to control the roll attitude of the fuselage body. By setting a payload bay on the fuselage body to carry mission payloads, and the solid-propellant engine to provide boost propulsion to the fuselage body, the fuselage body can quickly reach a specified speed and altitude. The canards, wings, and first tail fin are used to control the flight attitude of the fuselage body. Compared with traditional high-altitude performance tests conducted on the ground in a simulated manner, the carrier platform provided by this application can carry mission payloads and test the working performance, reliability, and adaptability of the payloads under real high-altitude flight conditions. This can effectively avoid the test errors caused by the inability of simulation tests to reproduce the real flight environment, and ensure the accuracy of the test results.

[0014] It should be understood that the descriptions of technical features, technical solutions, beneficial effects, or similar language in this application do not imply that all features and advantages can be achieved in any single embodiment. Rather, it is understood that the description of a feature or beneficial effect means that a specific technical feature, technical solution, or beneficial effect is included in at least one embodiment. Therefore, the descriptions of technical features, technical solutions, or beneficial effects in this specification do not necessarily refer to the same embodiment. Furthermore, the technical features, technical solutions, and beneficial effects described in this embodiment can be combined in any suitable manner. Those skilled in the art will understand that embodiments can be implemented without one or more specific technical features, technical solutions, or beneficial effects of a particular embodiment. In other embodiments, additional technical features and beneficial effects may be identified in specific embodiments that do not embody all embodiments. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A front view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts a first external structure; Figure 2 A top view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts the first external structure; Figure 3 A bottom view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts the first external structure; Figure 4 A side view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts a first external structure; Figure 5 A front view of a carrier platform capable of carrying mission payloads provided in this application embodiment, wherein the fuselage body adopts a first external shape structure and is provided with a second tail fin; Figure 6 A top view of a carrier platform capable of carrying mission payloads provided in this application embodiment, wherein the fuselage body adopts a first external shape structure and is provided with a second tail fin; Figure 7 A bottom view of the fuselage of a carrier platform capable of carrying mission payloads provided in this application embodiment, when the main body adopts a first external shape structure and is provided with a second tail fin; Figure 8 A side view of the fuselage of a carrier platform capable of carrying mission payloads provided in this application embodiment, wherein the fuselage adopts a first external structure and is provided with a second tail fin; Figure 9 A front view of the fuselage body of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the second external shape structure is adopted; Figure 10 A top view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts a second external structure; Figure 11 A bottom view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts the first external structure; Figure 12 A side view of the fuselage of a carrier platform capable of carrying mission payloads, provided in an embodiment of this application, when the fuselage adopts a first external structure.

[0017] The text labels in the image represent: 1. Main fuselage; 2. Solid engine; 3. Canard; 4. Wing; 5. First tail; 6. Second tail; 7. Vertical wing; 8. Mission payload; 11. Head section; 12. Control section; 13. Payload section; 14. Adaptor section; 41. Fixed wing; 42. Wingtip rudder; 131. Payload bay. Detailed Implementation

[0018] To enable those skilled in the art to better understand the technical solutions of this application, the technical solutions in the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. The descriptions in this section are merely illustrative and explanatory, and should not be construed as limiting the scope of protection of this application. Specifically, the described embodiments are only some embodiments of this application, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this application.

[0019] It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such process, method, product, or apparatus.

[0020] As mentioned in the background section, in order to solve the problems existing in the prior art, this application provides a carrier platform capable of carrying mission payloads, including: The fuselage body 1 has a payload compartment 131 inside, which is used to install the mission payload 8. Solid engine 2 is located at one end of the fuselage body 1 along the first direction and is used to provide power to the fuselage body 1. Two canard rudders 3 are symmetrically arranged on both sides of the fuselage body 1 along the second direction to control the pitch attitude of the fuselage body 1. The second direction is perpendicular to the first direction. Wings 4, two wings 4 are symmetrically arranged on both sides of the fuselage body 1 along the second direction, used to control the roll attitude of the fuselage body 1; The first tail fin 5 is located on top of the solid rocket motor 2.

[0021] like Figure 1-12As shown, the first direction is the length direction of the fuselage body 1, and the second direction is the width direction of the fuselage body 1. The fuselage body 1 can be made of profiles and plates through machining and splicing, which has the advantages of low cost and short manufacturing cycle. The fuselage body 1 is also equipped with control equipment, which can control the canard rudder 3 and the wing 4 respectively. The canard rudder 3 is located at the end of the fuselage body 1 away from the solid rocket motor 2. By controlling the canard rudder 3, the pitch attitude of the fuselage body 1 can be adjusted. The wing 4 is located in the middle of the fuselage body 1, between the canard rudder 3 and the solid rocket motor 2. By controlling the wing 4, the roll attitude of the fuselage body 1 can be adjusted. The first tail fin 5 is located on the top of the solid rocket motor 2 and is used to realize the lateral strong static stability aerodynamic characteristics of the carrier platform. In this embodiment, no rudder is set on the first tail fin 5. The heading attitude control of the carrier platform is realized by controlling the canard rudder 3 and the wing 4 simultaneously through the control equipment. Through the above settings, the number of servo hardware on the carrier platform can be effectively reduced, further reducing the manufacturing cost of the carrier platform and shortening the manufacturing cycle.

[0022] By setting a payload bay 131 on the fuselage body 1 to carry the mission payload 8, and the solid rocket motor 2 to provide booster thrust to the fuselage body 1, the fuselage body 1 can quickly reach the specified speed and altitude. The canard rudder 3, wings 4 and first tail fin 5 are used to control the flight attitude of the fuselage body 1. Compared with traditional high-altitude performance tests conducted on the ground in a simulated manner, the carrier platform provided in this application can carry the mission payload 8 to test the working performance, reliability and adaptability of the payload under real high-altitude flight conditions. It can effectively avoid the test errors caused by the inability of simulation tests to reproduce the real flight environment and ensure the accuracy of the test results.

[0023] In a preferred embodiment, the fuselage body 1 includes a nose section 11, a control section 12, a payload section 13, and an adapter section 14 connected in sequence. The nose section 11 and the control section 12 are equipped with canards 3. The control section 12 is equipped with control equipment for controlling the canards 3 and the wings 4, thereby controlling the pitch, roll, and yaw attitudes of the fuselage body 1. The payload section 13 is equipped with wings 4, and has a payload bay 131 inside. The adapter section 14 is used to connect the payload section 13 and the solid rocket motor 2.

[0024] like Figure 1-12 As shown, the main fuselage 1 includes a nose section 11, a control section 12, a payload section 13, and an adapter section 14, which are sequentially spliced ​​and fixed along its length. The nose section 11 and the control section 12 are internally connected, and control equipment and electrical components are installed inside the nose section 11 and the control section 12. The canard rudder 3 is fixed to both the nose section 11 and the control section 12. The wing 4 is fixed to the payload section 13. The payload section 13 is used to install the mission payload 8 for testing. The adapter section 14 is used to connect the payload section 13 and the solid rocket motor 2.

[0025] In a preferred embodiment, the wing 4 includes a fixed wing 41, with two fixed wings 41 symmetrically arranged on both sides of the load compartment 13 along the second direction. A wingtip rudder 42 is provided on one side of the fixed wing 41, and the wingtip rudder 42 can rotate relative to the fixed wing 41, thereby realizing the control of the roll attitude of the fuselage body 1.

[0026] like Figure 2 , Figure 6 and Figure 10 As shown, the fixed wing 41 is approximately a triangular planar structure. The two fixed wings 41 are symmetrically arranged on both sides of the payload compartment 13 along the second direction. The positive angle of attack of the fixed wing 41 can provide lift when the carrier platform is in flight, enabling the carrier platform to glide at a certain altitude. The trailing edge of the fixed wing 41 is provided with a wingtip rudder 42. The end of the wingtip rudder 42 can deflect upward or downward, thereby generating an upward or downward torque, and thus realizing the control of the roll attitude of the fuselage body 1.

[0027] In a preferred embodiment, the solid rocket motor 2 extends at least partially into the adaptable compartment 14.

[0028] In a preferred embodiment, the projected area of ​​the adapter section 14 along the first direction completely covers the projected area of ​​the solid rocket motor 2 along the first direction.

[0029] like Figure 3 , Figure 7 and Figure 11 As shown, the solid rocket motor 2 is installed inside the adapter section 14 at one end near the payload compartment 13. When different specifications of solid rocket motor 2 are replaced according to different mission payload 8 requirements, causing the total length of solid rocket motor 2 to change, the total length of the carrier platform can be kept constant by adjusting the length of solid rocket motor 2 placed in the adapter section 14 or by adjusting the length of the adapter section 14 itself. Furthermore, the projected area of ​​the adapter section 14 along the first direction completely covers the projected area of ​​solid rocket motor 2 along the first direction. When replacing solid rocket motor 2, the aerodynamic characteristics caused by the change in the diameter of solid rocket motor 2 are within the deviation range, and there is no need to recalculate the aerodynamic characteristics.

[0030] In a preferred embodiment, the bottom of the payload compartment 13 has a first opening that connects the payload compartment 131 to the external environment.

[0031] like Figure 3 , Figure 7 and Figure 9 As shown, the first opening is located at the bottom of the payload compartment 13, which facilitates the deployment of the mission payload 8 during flight of the carrier platform.

[0032] The main body 1 can have different external shapes and structures.

[0033] like Figure 1-8 As shown, it adopts the first type of external structure, in which the head section 11, control section 12, load section 13 and adapter section 14 have the same size and shape of projected area along the first direction, and are all rectangular.

[0034] Specifically, the control section 12, load section 13, and adapter section 14 are all rectangular parallelepipeds. These rectangular parallelepiped sections can be directly assembled and fixed using profiles and sheet metal during manufacturing. Compared to traditional cylindrical structures, the machining process for rectangular parallelepiped structures is more convenient and simpler, facilitating personnel operation. Furthermore, when installing the mission payload 8 into a traditional cylindrical section, due to its curved surface, an additional fixing bracket is required inside the section as the mounting carrier for the mission payload 8. However, the rectangular parallelepiped load section 13 does not require such a fixing bracket; the mission payload 8 can be directly fixed to the load section. On the inner wall of 13, the rectangular load compartment 13 has a larger volume and carrying capacity, while further reducing manufacturing costs; the control compartment 12, load compartment 13 and adapter compartment 14 have the same size and shape of projected area along the first direction, which can give the three the same aerodynamic shape; the head compartment 11 is approximately a triangular prism structure, and one side of the head compartment 11 is connected to the control compartment 12. Similarly, the head compartment 11 and the other three compartments have the same size and shape of projected area along the first direction, which can effectively reduce the impact of aerodynamic shape on the fuselage body 1. The triangular prism structure of the head compartment 11 can reduce the impact of aerodynamic drag while ensuring ease of manufacturing and processing.

[0035] Furthermore, the solid rocket motor 2 is provided with a second tail fin 6 on each side along the second direction, and the top of the payload section 13 and the adapter section 14 are provided with a vertical fin 7.

[0036] For details, please refer to Figure 5-8 Two second tail fins 6 are located on both sides of the solid rocket motor 2 along the second direction and form an angle with the horizontal direction respectively. The second tail fins 6 can increase the longitudinal static stability of the carrier platform during flight and ensure that the flight process will not lose control. Two vertical wings 7 are symmetrically located on the top of the payload section 13 and the adapter section 14. They can increase the lateral static stability of the carrier platform during flight and ensure that the carrier platform maintains stable flight when it encounters crosswind interference.

[0037] like Figure 9-12 As shown, it adopts a second external structure, in which the head section 11, control section 12, load section 13 and adapter section 14 have the same size and shape of projected area along the first direction, and are all circular.

[0038] Specifically, both the payload section 13 and the adapter section 14 are cylindrical in shape. The cylindrical structure of the payload section 13 and the adapter section 14 can enhance the ability of the carrier platform to resist loads during flight and ensure the stability of the carrier platform. The nose section 11 is approximately conical in shape, and the control section 12 is approximately frustum in shape. The nose section 11, the control section 12, the payload section 13 and the adapter section 14 have the same size and shape of projected area along the first direction, which can make the fuselage body 1 have the same aerodynamic shape as a whole and reduce the impact of aerodynamic drag.

[0039] Furthermore, the solid rocket motor 2 is provided with second tail fins 6 on both sides along the second direction.

[0040] For details, please refer to Figure 9 and Figure 10 Two second tail fins 6 are located on both sides of the solid rocket motor 2 along the second direction and form an angle with the horizontal direction respectively. The second tail fins 6 can increase the longitudinal static stability of the carrier platform during flight and ensure that the flight process will not go out of control.

[0041] Working principle: The mission payload 8 is installed in the payload compartment 131. The solid rocket motor 2 provides booster propulsion to the carrier platform. Simultaneously, under the lift provided by the wing 4, the carrier platform can quickly climb to the designated altitude and fly at a set speed. During the flight of the carrier platform, the pitch attitude of the carrier platform can be adjusted by controlling the canard rudder 3 through the control equipment, the roll attitude of the carrier platform can be adjusted by controlling the wing 4 through the control equipment, and the heading attitude of the carrier platform can be adjusted by controlling both the canard rudder 3 and the wing 4 through the control equipment. The carrier platform provided in this embodiment, under the premise of ensuring high-altitude flight and attitude adjustment, uses commercially available profiles and plates for the main body. The materials are widely available, low in cost, have a short processing cycle, and simple manufacturing process. It also further reduces the number of servo hardware and increases the volume of the payload compartment 13, which has high universality and is easy to mass-produce.

[0042] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. The above descriptions are only preferred embodiments of this application. It should be noted that due to the limitations of written expression, while there are objectively infinite specific structures, those skilled in the art can make several improvements, modifications, or changes without departing from the principles of this application, and can also combine the above technical features in an appropriate manner. These improvements, modifications, changes, or combinations, or the direct application of the inventive concept and technical solution to other situations without modification, should all be considered within the scope of protection of this application.

Claims

1. A carrier platform capable of carrying mission payloads, characterized in that, include: The fuselage body (1) has a payload compartment (131) inside, which is used to install mission payloads (8). Solid engine (2), the solid engine (2) is located at one end of the fuselage body (1) along a first direction, and is used to provide power to the fuselage body (1); Canard rudders (3), two canard rudders (3) are symmetrically arranged on both sides of the fuselage body (1) along the second direction, and are used to control the pitch attitude of the fuselage body (1), the second direction being perpendicular to the first direction; Wings (4), two wings (4) are symmetrically arranged on both sides of the fuselage body (1) along the second direction, for controlling the rolling attitude of the fuselage body (1); The first tail fin (5) is located on top of the solid rocket motor (2).

2. The carrier platform capable of carrying mission payloads according to claim 1, characterized in that, The fuselage body (1) includes a head section (11), a control section (12), a payload section (13), and an adapter section (14) connected in sequence. The head section (11) and the control section (12) are equipped with canards (3). The control section (12) is equipped with control equipment, which is used to control the canards (3) and the wings (4), thereby realizing the control of the pitch, roll, and yaw attitudes of the fuselage body (1). The payload section (13) is equipped with the wings (4), and the payload section (13) contains the payload bay (131). The adapter section (14) is used to connect the payload section (13) and the solid rocket motor (2).

3. The carrier platform capable of carrying mission payloads according to claim 2, characterized in that, The wing (4) includes a fixed wing (41), and two fixed wings (41) are symmetrically arranged on both sides of the load compartment (13) along the second direction. A wingtip rudder (42) is provided on one side of the fixed wing (41). The wingtip rudder (42) can rotate relative to the fixed wing (41), thereby realizing the control of the rolling attitude of the fuselage body (1).

4. The carrier platform capable of carrying mission payloads according to claim 2, characterized in that, The solid rocket motor (2) extends at least partially into the adaptable section (14).

5. A carrier platform capable of carrying mission payloads according to claim 2, characterized in that, The load compartment (13) has a first opening at the bottom, which connects the load compartment (131) to the external environment.

6. A carrier platform capable of carrying mission payloads according to claim 2, characterized in that, The head section (11), the control section (12), the payload section (13), and the adapter section (14) have the same size and shape of projected area along the first direction, and are all rectangular.

7. A carrier platform capable of carrying mission payloads according to claim 2, characterized in that, The head section (11), the control section (12), the payload section (13), and the adapter section (14) have the same size and shape of projected area along the first direction, and are all circular.

8. A carrier platform capable of carrying mission payloads according to claim 6 or 7, characterized in that, The projected area of ​​the adapter section (14) along the first direction completely covers the projected area of ​​the solid rocket motor (2) along the first direction.

9. A carrier platform capable of carrying mission payloads according to claim 6 or 7, characterized in that, The solid rocket motor (2) is provided with a second tail fin (6) on both sides along the second direction.

10. A carrier platform capable of carrying mission payloads according to claim 6, characterized in that, The top of the load section (13) and the adapter section (14) are both provided with a vertical wing (7).

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