Gliding throwing device and assembly method

Abstract

The present application belongs to the technical field of throwing device, and particularly relates to a gliding throwing device and an assembling method. The device comprises a general cabin and optional modules, the optional modules comprise a guiding system, a main wing, a tail wing and a battery; the general cabin is connected with the optional modules and is used for placing a load; a guiding system interface is arranged at the front end of the general cabin, a left wing interface is arranged at the front end of one side of the general cabin, a right wing interface is arranged at the front end of the other side of the general cabin, and a tail wing interface is arranged at the rear of the general cabin; a battery compartment, a load compartment and a flight control module are arranged in the general cabin; a battery interface is arranged in the battery compartment and is used for connecting the battery; the load compartment is used for placing the load; and the flight control module is used for controlling the attitude and flight trajectory.

Description

Technical Field

[0001] This invention belongs to the field of throwing device technology, specifically relating to a gliding throwing device and its assembly method. Background Technology

[0002] In rescue, logistics, and many other fields, air-to-ground delivery devices play an indispensable role as an efficient and rapid means of material delivery. Currently, there are various types of air-to-ground delivery devices, mainly including traditional vertical airdrop, traditional parabolic airdrop, parachute airdrop, and gliding airdrop. Traditional vertical airdrop is typically performed by helicopters or rotorcraft while hovering in the air, with the delivery device falling along a free-fall trajectory. Traditional parabolic airdrop is mainly performed by fixed-wing aircraft during their flight path, with the delivery device following a parabolic trajectory. Parachute airdrop combines vertical and parabolic airdrop methods, using one or more parachutes. While this slows the descent speed, wind blowing against the parachutes can cause uncontrollable drift in the trajectory. Gliding airdrop utilizes wings, tail fins, or other lifting body components to achieve gliding. Compared to traditional airdrop methods, it allows for longer throw distances and improved accuracy, but its system design is more complex. These different types of air-to-ground delivery devices each have their own characteristics and are suitable for different scenarios and mission requirements.

[0003] Existing air-to-ground drop devices each possess distinct characteristics. Non-gliding airdrops primarily rely on parachutes for deceleration and landing point control; however, deceleration control and landing point control are contradictory, and reducing speed for landing often leads to significant dispersal errors. While gliding airdrops utilize wings and tail fins to adjust flight attitude and trajectory during gliding flight, parachutes are still necessary as a deceleration device in the terminal phase. Moreover, once the design of a gliding airdrop device is finalized, its overall lift-to-drag ratio characteristics are fixed, and the relationship between lift-to-drag ratio and angle of attack and flight Mach number is determined. Therefore, the constraints of lift and drag characteristics must be fully considered when designing the airdrop trajectory. Simultaneously, the flight envelope characteristics of gliding airdrop devices are also fixed, with fixed flight altitude and speed ranges. When put into use, constraints such as minimum and maximum flight speeds, drop altitudes, maximum gliding distances, and minimum gliding distances must be strictly adhered to. To achieve airdrop missions to different target locations, gliding airdrop devices can be adjusted by increasing the drop altitude, changing flight trim conditions, and manipulating control surfaces during flight.

[0004] While existing air-to-ground drop systems have played a role in their respective fields, they still suffer from numerous problems. Non-gliding airdrops, due to the inability to precisely control trajectory and landing point, are primarily used for probabilistic deployments and have high environmental requirements, only suitable for ideal environments with large areas, convenient transportation, and flat ground. Gliding airdrops are limited by the deterministic nature of flight performance, such as overall lift-to-drag ratio and flight envelope, resulting in a relatively fixed effective range. Although there is some adjustable range, airdrops exceeding this range cannot be reached. Furthermore, existing airdrop systems are inadequate in terms of cost-effectiveness. The widespread use of parachutes for deceleration in various airdrop devices increases system costs; the excessive use of main wings, tail fins, and batteries also contributes to increased costs, especially the main wings and tail fins, which have curved surfaces leading to higher manufacturing costs, and batteries, which constitute a large proportion of the electrical system. Moreover, airdrop device designs are typically intended to meet mission requirements within a certain distance and payload range. After the design of a gliding drop system is finalized, the use of large-area main wings and high-capacity batteries is not necessary for long-distance, low-payload airdrop missions, resulting in extremely low cost-effectiveness. These problems restrict the application and development of air-to-ground throwing devices in a wider range of scenarios and urgently need to be solved through technological innovation. Summary of the Invention

[0005] To overcome the problems in the prior art, the present invention proposes a gliding throwing device and its assembly method.

[0006] The technical solution of the present invention to solve the above-mentioned technical problems is as follows:

[0007] In a first aspect, the present invention provides a gliding throwing device, comprising a universal cabin and optional modules, wherein the optional modules include a guidance system, a main wing, a tail wing, and a battery; the universal cabin connects the optional modules and is used to hold a payload;

[0008] The universal cabin has a guidance system interface at the front, a left wing interface at the front left, a right wing interface at the front right, and a tail fin interface at the front rear. The universal cabin includes a battery compartment, a payload compartment, and a flight control module. The battery compartment has a battery interface, and the payload compartment is used to hold the payload. The flight control module is used for attitude and flight trajectory control.

[0009] The second aspect provides a method for assembling a gliding throwing device, including:

[0010] Determine the target distance, deployment altitude, flight environment, payload type, and payload weight;

[0011] Select the guidance system based on the flight environment;

[0012] Select the main wing and tail wing based on the target distance and deployment altitude;

[0013] The trim airspeed is determined based on the system weight, main wing reference area, and gliding trajectory angle.

[0014] Furthermore, based on the target distance and deployment altitude, the main wing and tail wing are selected, including:

[0015] Calculate the gliding trajectory angle based on the gliding initiation altitude and range;

[0016] Calculate lift and drag based on the gliding trajectory angle and mass, and calculate the first lift-to-drag ratio;

[0017] Simultaneously, lift is calculated based on the lift coefficient, main wing reference area, and power; drag is calculated based on the drag coefficient, main wing reference area, and power; and a second lift-to-drag ratio is calculated.

[0018] The first lift-to-drag ratio is equal to the second lift-to-drag ratio, and the lift-to-drag ratio is the ratio of the lift coefficient to the drag coefficient.

[0019] Calculate the lift coefficient and drag coefficient to obtain:

[0020] ;

[0021] In the above formula, The lift coefficient, This is the drag coefficient; The lift coefficient of the wing. The drag coefficient of the wing is... The lift coefficient of the fuselage. The drag coefficient of the fuselage. For reference area of ​​the fuselage, The lift coefficient of the tail fin is... The drag coefficient of the tail fin is... This is the reference area for the tail fin;

[0022] By adjusting the main wing reference area To achieve adjustment of the lift-to-drag ratio, the main wing reference area expression is:

[0023] ;

[0024] in, The wingspan of the main wing, The chord length of the main wing.

[0025] Furthermore, select a tail fin, including:

[0026] Based on the determined main wing reference area, determine the tail wing reference area:

[0027] ;

[0028] in, This is the distance from the point of application of the wing's lift force to the origin of the airframe coordinate system. The distance from the machine's center of mass to the origin of the machine's coordinate system. This is the distance from the point of application of the tail fin lift force to the origin of the airframe coordinate system. This is the distance from the point of application of the fuselage lift force to the origin of the fuselage coordinate system.

[0029] Furthermore, based on the system weight, main wing reference area, and lift coefficient, the trim airspeed is determined, including:

[0030] ;

[0031] In the above formula, To balance airspeed, m For quality; g It is the acceleration due to gravity. This refers to air density.

[0032] Compared with the prior art, the present invention has the following technical effects:

[0033] By employing a modular wing-tail and payload bay design, this aircraft exhibits exceptional adaptability. Different deployment distances and diverse mission requirements can be met through flexible adjustments to the modular assembly. Whether it's rapid short-range delivery of emergency supplies or precise long-range deployment of specialized equipment, simply changing the corresponding modules allows for rapid adaptation to mission requirements. This highly flexible design significantly improves the aircraft's versatility and mission execution efficiency, reducing the cost and time investment required to develop specialized equipment for different missions. Attached Figure Description

[0034] To more clearly illustrate the technical solutions and advantages in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0035] Figure 1 This is a schematic diagram of the gliding throwing device of the present invention;

[0036] Figure 2 This is a typical embodiment of the gliding throwing device of the present invention;

[0037] Figure 3 These are schematic diagrams illustrating different modular combinations of the gliding throwing device of the present invention;

[0038] Figure 4 This is a schematic diagram of the assembly process of the gliding throwing device of the present invention;

[0039] Figure 5 A method for airdropping gliding throwing devices to target points at different distances. Detailed Implementation

[0040] To further illustrate the technical means and effects adopted by the present invention to achieve its intended purpose, the specific implementation methods, structures, features, and effects of the technical solutions proposed according to the present invention are described in detail below with reference to the accompanying drawings and preferred embodiments. Specific features, structures, or characteristics in one or more embodiments may be combined in any suitable form. 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.

[0041] In one embodiment of the present invention, a gliding throwing device is provided, including a universal cabin and optional modules, the optional modules including a guidance system, a main wing, a tail wing, and a battery; the universal cabin connects the optional modules and is used to place the payload.

[0042] The various optional modules connect to the universal cabin using standardized interfaces. The universal cabin has a guidance system interface at the front, a left wing interface on one front side, a right wing interface on the other front side, and a tail fin interface at the rear. The universal cabin contains a battery compartment, a payload compartment, and a flight control module. The battery compartment has a battery interface for connecting batteries. The payload compartment holds payloads, including fire extinguishing agents, beacons, medical kits, emergency rations, and basic self-rescue tools. The flight control module controls attitude and flight trajectory.

[0043] In one embodiment of the present invention, Figure 4 This invention provides a specific process for using a gliding throwing device. A method for assembling a gliding throwing device is also provided, including:

[0044] Step 100: Determine the target distance, deployment altitude, flight environment, payload type, and payload weight.

[0045] These parameters form the basis for the subsequent selection and design of various components of the gliding throwing device. Different combinations of parameters will affect the overall performance and configuration of the device.

[0046] Step 200: Select the guidance system based on the flight environment.

[0047] Flight environment factors such as day / night, visibility, and electromagnetic interference determine the appropriate guidance system: GPS positioning guidance is suitable for open environments and scenarios without electromagnetic interference; visible light guidance is suitable for daytime scenarios with high target visibility; and infrared guidance is suitable for nighttime or low-visibility scenarios.

[0048] Step 300: Select the main wing and tail wing based on the target distance and deployment altitude.

[0049] In this embodiment, the main wing in the optional module calculates the gliding trajectory angle based on the gliding start altitude and range during balanced gliding:

[0050] (1)

[0051] In the above formula, This refers to the drop height (gliding start height). The target distance (range). The angle of the gliding trajectory.

[0052] During balanced gliding, lift and drag are calculated based on the gliding trajectory angle.

[0053] The lift and drag of an aircraft satisfy the following conditions:

[0054] (2)

[0055] In the above formula, L For lift; D As resistance; m For the overall quality of the machine; g This is the acceleration due to gravity.

[0056] Lift and drag can also be expressed as:

[0057] (3)

[0058] In the above formula, The lift coefficient, The drag coefficient, Main wing reference area, It is dynamic pressure.

[0059] Combining formulas (2) and (3), we know that the lift-to-drag ratio is the ratio of lift to drag:

[0060] (4)

[0061] Formula (1) shows that when the projection height is determined, choosing a suitable gliding trajectory angle can achieve different distance requirements; Formula (4) shows that in order to meet a specific gliding trajectory angle and thus meet different distance requirements, the gliding throwing device needs to meet different overall lift-to-drag ratio requirements. According to Formula (4), designing a modular gliding throwing device means designing the lift-to-drag ratio, which can achieve different gliding distance requirements.

[0062] According to the component assembly method, the lift coefficient and drag coefficient are respectively:

[0063] (5)

[0064] In the above formula, The lift coefficient of the wing. The drag coefficient of the wing is... The lift coefficient of the fuselage. The drag coefficient of the fuselage. For reference area of ​​the fuselage, The lift coefficient of the tail fin is... The drag coefficient of the tail fin is... This is the reference area for the tail fin.

[0065] Since the lift-to-drag ratio is the ratio of lift to drag, according to formula (5), we have

[0066] (6)

[0067] Since the lift-drag ratio of the fuselage and tail is usually relatively small, while that of the main wing is relatively large, according to formula (6), the overall lift-drag ratio can be adjusted by adjusting the reference area of ​​the main wing.

[0068] The main wing reference area expression is:

[0069] (7)

[0070] in, The wingspan of the main wing, This refers to the chord length of the main wing. To achieve a unified installation interface for different modular main wings, the design parameters are... A modular main wing design is achieved by fixing the wingspan and taking different wingspans b.

[0071] In this embodiment, the tail fin in the optional module, to ensure pitch stability during gliding flight, should satisfy the following expression:

[0072] (8)

[0073] in, For pitch acceleration, C is the pitch moment of the entire aircraft, and C7 is the corresponding moment of inertia (the pitch axis of the fuselage). Therefore, the torque balance condition is:

[0074] (9)

[0075] In the above formula, The lift generated by multiple components, including the wings, fuselage, and tail; This refers to the distance from the point of lift application of the corresponding component (wing, fuselage, tail) to the center of mass of the entire aircraft.

[0076] Based on the above torque balance conditions, we can conclude that:

[0077] (10)

[0078] Right now,

[0079] (11)

[0080] in, This is the distance from the point of application of the wing's lift force to the origin of the airframe coordinate system. The distance from the machine's center of mass to the origin of the machine's coordinate system. This is the distance from the point of application of the tail fin lift force to the origin of the airframe coordinate system. This is the distance from the point of application of the fuselage lift force to the origin of the fuselage coordinate system.

[0081] According to formula (11), in order to meet the flight stability requirements, after determining the main wing reference area based on the overall lift-to-drag ratio, the corresponding tail wing reference area is further determined or used. That's all.

[0082] Step 400: Determine the trim airspeed based on the system weight, main wing reference area, and gliding trajectory angle.

[0083] When using different main wing and tail wing combinations, the overall lift coefficient of the system will be different, so different trim airspeeds need to be used in conjunction.

[0084] According to formulas (2) and (3), we know that:

[0085] (11)

[0086] The expression for calculating dynamic pressure is as follows:

[0087] (12)

[0088] Therefore, the trim airspeed is:

[0089] (13);

[0090] In the above formula, To balance airspeed, m For quality; g It is the acceleration due to gravity. This refers to air density.

[0091] The gliding launcher's mission or parameters are set according to the different airdrop missions. According to formula (1), different airdrop distances correspond to different gliding trajectory angles, which need to be set accordingly during mission setup; according to formula (13), different system weights and main wing reference areas require different trim airspeeds, which need to be set accordingly during mission setup.

[0092] Different battery specifications are selected based on flight time.

[0093] Modular design methods can only provide a limited number of optional component combinations. In actual use, targets may be distributed at any distance within the maximum airdrop range. In this case, the coverage area can be divided according to different modular component combination schemes. A suitable component combination scheme can be selected within the target area, and then the aircraft's maneuverability can be used to airdrop the target point within the current area.

[0094] In a specific embodiment, Figure 1 This is a schematic diagram illustrating the components of a gliding throwing device according to the present invention. Figure 1 As shown, the gliding throwing device of the present invention includes a general-purpose cabin and optional modules. The optional modules include a guidance system, a main wing, a tail fin, and a battery. It should be noted that, in order to complete specific tasks, the gliding throwing device usually includes other auxiliary tools and equipment, such as remote control equipment and mission download equipment. However, these are common knowledge in the field of aircraft systems and will not be described in detail in this embodiment.

[0095] Figure 2 This is a specific modular design scheme of the present invention; Figure 3 These are schematic diagrams illustrating different modular combinations of the modular gliding and throwing device described in this invention. Figure 2 As shown, a typical design includes a universal hull, a guidance system, optional main wing-tail assembly 01, optional main wing-tail assembly 02, optional main wing-tail assembly 03, and adapter battery A, adapter battery B, and adapter battery C. Depending on the target distance to be delivered, three different main wing-tail assembly options can be selected; and then, three different battery specifications are selected according to the flight time.

[0096] exist Figure 5 The paper presents a method for airdropping targets at different distances using a modular gliding throwing device. For example... Figure 5 As shown, point A1 is the minimum distance, A7 is the maximum distance, and point B0 is the drop position. A1-A7 represent the distance range that the gliding throwing device can reach, covering a total of three segmented distance ranges: airdrop zone 1, airdrop zone 2, and airdrop zone 3.

[0097] like Figure 5 As shown, A2 is the target position that the gliding throwing device can reach when gliding stably at the trim point using the "optional main wing and tail wing combination 03"; A1-A3 correspond to airdrop interval 1, indicating the target distance range that can be reached by operating the glider control surfaces and adjusting the gliding trajectory angle when using the "optional main wing and tail wing combination 03".

[0098] Similarly, A4 represents the target position that the gliding thrower can reach when gliding stably at the trim point using the "optional main wing and tail wing combination 02"; A3-A5 correspond to airdrop zone 2, indicating the target distance range that can be reached by operating the glider control surfaces and adjusting the gliding trajectory angle when using the "optional main wing and tail wing combination 02".

[0099] Similarly, A6 represents the target position that the gliding thrower can reach when gliding stably at the trim point using the "optional main wing and tail wing combination 01"; A5-A7 correspond to airdrop range 3, indicating the target distance range that can be reached by operating the glider control surfaces and adjusting the gliding trajectory angle when using the "optional main wing and tail wing combination 01".

[0100] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A method for assembling a gliding throwing device, characterized in that, The gliding launcher comprises a universal cabin and optional modules. The optional modules include a guidance system, a main wing, a tail fin, and a battery. The universal cabin connects to the optional modules and houses the payload. The universal cabin has a guidance system interface at its front, a left wing interface on one front side, a right wing interface on the other front side, and a tail fin interface at its rear. The universal cabin contains a battery compartment, a payload compartment, and a flight control module. The battery compartment has a battery interface for connecting batteries. The payload compartment holds the payload. The flight control module controls the attitude and flight trajectory. The assembly method of the gliding throwing device includes: Determine the target distance, deployment altitude, flight environment, payload type, and payload weight; Select the guidance system based on the flight environment; Select the main wing and tail wing based on the target distance and deployment altitude; The trim airspeed is determined based on the system weight, main wing reference area, lift coefficient, and gliding trajectory angle. Among them, the main wing and tail wing are selected based on the target distance and deployment altitude, including: Calculate the gliding trajectory angle based on the gliding initiation altitude and range; Calculate lift and drag based on the gliding trajectory angle and system weight, and calculate the first lift-to-drag ratio; Simultaneously, lift is calculated based on the lift coefficient, main wing reference area, and power; drag is calculated based on the drag coefficient, main wing reference area, and power; and a second lift-to-drag ratio is calculated. The first lift-to-drag ratio is equal to the second lift-to-drag ratio, and the lift-to-drag ratio is the ratio of the lift coefficient to the drag coefficient. Calculate the lift coefficient and drag coefficient to obtain: ； In the above formula, The lift coefficient, This is the drag coefficient; The lift coefficient of the wing. The drag coefficient of the wing is... The lift coefficient of the fuselage. The drag coefficient of the fuselage. For reference area of ​​the fuselage, The lift coefficient of the tail fin is... The drag coefficient of the tail fin is... For the tail fin reference area, Main wing reference area; By adjusting the main wing reference area To achieve adjustment of the lift-to-drag ratio, the main wing reference area expression is: ； in, The wingspan of the main wing, The chord length of the main wing.

2. The assembly method of the gliding throwing device according to claim 1, characterized in that, Choose the tail fin, including: Based on the determined main wing reference area, determine the tail wing reference area: ； in, This is the distance from the point of application of the wing's lift force to the origin of the airframe coordinate system. The distance from the machine's center of mass to the origin of the machine's coordinate system. This is the distance from the point of application of the tail fin lift force to the origin of the airframe coordinate system. This is the distance from the point of application of the fuselage lift force to the origin of the fuselage coordinate system.

3. The assembly method of the gliding throwing device according to claim 1, characterized in that, The trim airspeed includes: ； In the above formula, To balance airspeed, m For system weight; g It is the acceleration due to gravity. air density, The angle of the gliding trajectory.

Images