Hypersonic aircraft seeker
By designing a conical structure in the seeker head of a hypersonic vehicle and utilizing the specific angle between the blades and the motor shaft mounting to create a local low-pressure area, the wind resistance problem caused by the central vacuum at the air inlet of the hypersonic vehicle was solved, thereby increasing flight speed and reducing energy consumption.
Patent Information
- Application Number
- CN202520765330.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-22
- Publication Date
- 2026-02-17
- Estimated Expiration
- 2035-04-22
AI Technical Summary
In existing technologies, a local vacuum can easily form at the center of the air intake when a hypersonic vehicle is flying at high speed, which increases wind resistance and affects flight efficiency.
Design a hypersonic aircraft seeker that uses a conical motor shaft mounting component connected to a hub ring via blades to form a conical structure. The included angle between the blades and the motor shaft mounting component is 30-60 degrees, creating a local low-pressure or near-vacuum region to reduce wind resistance.
By reducing wind resistance in localized low-pressure or near-vacuum regions, the speed performance of aircraft at maximum speeds can be improved and energy consumption reduced.
Smart Images
Figure CN223923325U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of aircraft guidance technology, and specifically relates to a hypersonic aircraft guidance head. Background Technology
[0002] The applicant has developed a spherical centrifugal impeller, namely the spherical centrifugal impeller disclosed in patent CN222163007U. During the airflow performance test of the spherical centrifugal impeller, it was found that when the speed and airflow of the spherical centrifugal impeller are large enough, a small local vacuum or low-pressure environment will be generated at the front end of the center of the air inlet. The local vacuum environment will reduce wind resistance. Therefore, the applicant wants to apply a similar structure to supersonic aircraft and make applicability improvements. Utility Model Content
[0003] This invention provides a hypersonic aircraft seeker that can solve the problems pointed out in the background art.
[0004] A hypersonic vehicle seeker includes a conical motor shaft mounting component located at the center and a hub ring coaxially disposed with the conical motor shaft mounting component. The hub ring and the conical motor shaft mounting component are connected by a number of blades, which together form a conical structure. The conical structure is oriented in the opposite direction to the cone of the conical motor shaft mounting component, and the lowest point of the conical motor shaft mounting component is lower than the lowest point of the hub ring.
[0005] Preferably, the angle between the line connecting the upper and lower connection points of the blade and the motor shaft mounting component and the plane of rotation is 30-60 degrees, and the upper and lower connection points are connected by an arc.
[0006] The beneficial effects of this utility model are as follows: This utility model provides a hypersonic aircraft seeker that can create a local low-pressure or near-vacuum state. Creating a local low-pressure or near-vacuum state can reduce wind resistance, allowing the aircraft to increase its speed to another level under extreme speed conditions, while also reducing energy consumption at the same speed. Attached Figure Description
[0007] Figure 1 This is a schematic diagram of the structure of this utility model.
[0008] Figure 2 This is a front view schematic diagram of the present invention.
[0009] Explanation of reference numerals in the attached figures:
[0010] The diagram labels are: 1. Conical motor shaft mounting part; 2. Hub ring; 3. Blade. Detailed Implementation
[0011] The following describes a specific embodiment of the present invention in detail with reference to the accompanying drawings. However, it should be understood that the scope of protection of the present invention is not limited to the specific embodiment.
[0012] Example 1:
[0013] like Figure 1-2 As shown, a hypersonic vehicle seeker includes a conical motor shaft mounting component 1 located at the center and a hub ring 2 coaxially arranged with the conical motor shaft mounting component 1. The hub ring 2 and the conical motor shaft mounting component 1 are connected by several blades 3, which together with the hub ring 2 form a conical structure. The conical structure is opposite in direction to the cone of the conical motor shaft mounting component 1. The lowest point of the conical motor shaft mounting component 1 is lower than the lowest point of the hub ring 2. This design is formed by combining two "conical bodies" in opposite directions to create a fixed intake volume and centrifugal exhaust. The angle formed by the intake port and the centrifugal exhaust port covers the contact surface between the front end of the vehicle and the air, and a local low-pressure or near-vacuum region is formed at the lowest point of the conical motor shaft mounting component 1, which can reduce wind resistance and enable the vehicle to increase its speed to another level under extreme speed conditions.
[0014] Specifically, the angle between the line connecting the upper and lower connection points of the blade 3 and the motor shaft mounting part 1 and the plane of rotation is 30-60 degrees, and the upper and lower connection points are connected by an arc.
[0015] The above-disclosed embodiments are only a few specific examples of the present utility model. However, the embodiments of the present utility model are not limited thereto. Any changes that can be conceived by those skilled in the art should fall within the protection scope of the present utility model.
Claims
1. A seeker for a hypersonic aircraft, characterized in that: It includes a conical motor shaft mounting component (1) located at the center and a hub ring (2) coaxially arranged with the conical motor shaft mounting component (1). The hub ring (2) and the conical motor shaft mounting component (1) are connected by a plurality of blades (3). The plurality of blades (3) and the hub ring (2) form a conical structure. The conical structure is opposite to the cone direction of the conical motor shaft mounting component (1). The lowest point of the conical motor shaft mounting component (1) is set lower than the lowest point of the hub ring (2).
2. The hypersonic vehicle seeker according to claim 1, characterized in that: The angle between the line connecting the upper and lower connection points of the blade (3) and the motor shaft mounting part (1) and the plane of rotation is 30-60 degrees, and the upper and lower connection points are connected by an arc.