Main rotor blade construction

Claim 2

An aircraft propulsion blade which comprises: a. a leading edge spar having upper and lower trailing edges, b. upper and lower after body skins secured at their leading edges to said upper and lower trailing edged, respectively, of said spar and coupled together along the trailing edges thereof, and c. two honeycomb body halves extending rearwardly from said spar between said skins, one secured to and substantially coextensive with each said skin with the cells thereof of length to extend to planes beyond the blade chord plane and oriented substantially perpendicular to said blade chord plane and with confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 3

The combination set forth in claim 1 wherein a root fitting is adhesively secured within said spar at the root of said blade.

Claim 4

The combination set forth in claim 1 wherein the rear face of said spar is adhesively secured to the Front face of said honeycomb body halves.

Claim 5

An aircraft propulsion blade which comprises: a. an elongated laterally curved abrasion strip forming an unbroken front-top-bottom surface of a leading edge spar having upper and lower trailing edges, b. upper and lower after body skins secured in abutting relation at their leading edges to said upper and lower trailing edges, respectively, of said spar and coupled together along the trailing edges thereof, and c. two honeycomb body halves extending rearwardly from said spar between said skins, one secured to and substantially coextensive with each said skin with the cells thereof of length to extend to planes beyond the blade chord plane and oriented substantially perpendicular to said blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 6

An aircraft propulsion blade which comprises: a. an elongated laterally curved abrasion strip forming an unbroken front-top-bottom surface of a leading edge spar having upper and lower trailing edges, b. upper and lower after body skins secured in abutting relation at their leading edges to said upper and lower trailing edges, respectively, of said spar and coupled together along the trailing edges thereof, and c. two honeycomb body halves extending rearwardly from said spar between said skins, one secured to and substantially coextensive with each said skin with the cells thereof of length to extend to planes beyond the blade chord plane and oriented substantially perpendicular to said blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 7

An aircraft propulsion blade which comprises: a. an elongated laterally curved abrasion strip forming an unbroken front-top-bottom surface of a leading edge spar having upper and lower trailing edges, b. an upper spar channel inside said strip, c. a lower spar channel inside said strip with the front edges of said spar channels adherently overlapping, d. a spar web panel of bounded metallic honeycomb forming a rear closure for said spar with the honeycomb cells extending front to rear, e. upper and lower after body skins secured at their leading edges to said upper and lower trailing edges, respectively, of said spar and coupled together along the trailing edges thereof, and f. two honeycomb bodies, one secured to and substantially coextensive with each said skin with the cells thereof oriented substantially perpendicular to the blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 8

An aircraft propulsion blade which comprises: a. an elongated laterally curved abrasion strip forming an unbroken front-top-bottom surface of a leading edge spar having upper and lower trailing edges, b. an upper spar channel inside said strip, c. a lower spar channel inside said strip with the front edges of said spar channels adherently overlapping, d. a spar web panel of bounded metallic honeycomb forming a rear closure for said spar with the honeycomb cells extending front to rear, e. upper and lower after body skins secured at their leading edges to said upper and lower trailing edges, respectively, of said spar and coupled together along the trailing edges thereof, and f. two honeycomb bodies, one secured to and substantially coextensive with each said skin with the cells thereof oriented substantially perpendicular to the blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 9

In an aircraft propulsion blade, the combination which comprises: a. upper and lower body skins forming outer blade surfaces, and b. two honeycomb body halves, one adhesively secured to and substantially coextensive with each said skin with the cells thereof of length to extend beyond the blade chord plane and oriented substantially perpendicular to said blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.

Claim 10

In an aircraft propulsion blade, the combination which comprises: a. upper and lower body skins forming outer blade surfaces, and b. two honeycomb body halves, one adhesively secured to and substantially coextensive with each said skin with the cells thereof of length to extend beyond the blade chord plane and oriented substantially perpendicular to said blade chord plane and with the confronting ends of said cells intercised and adhesively bonded at the blade chord plane.